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Automatic Engine Data

MAKS_Enjoyer
Nov 13th, 2022
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  1. Engine Designation: RO-720 "Moskva"
  2. Fuel Flow Cycle: Gridded Ion Thruster
  3. Propellant(Remass): Cs (Caesium)
  4. Exhaust Nozzle Geometry: Electrostatic Ion Nozzle
  5. Engine Use Case: Space Tug (Main Propulsion)
  6. Altitude Of Operation: 80 km+ (Vacuum)
  7. Engine Power Source: Nuclear Fission Reactor
  8. Rated Power Level: 690 kW
  9.  
  10.  
  11. Engine Designation: TYS-161K "Gayamun"
  12. Fuel Flow Cycle: Electric Pump Fed
  13. Engine Oxidizer: O3 (Ozone)
  14. Engine Fuel: CH3OH (Methanol)
  15. Average Mixture Ratio: -1.0
  16. Propellant properties: Hypergolic and cryogenic
  17. Altitude Of Operation: 0-20 km (Sea Level)
  18. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  19. Exhaust Nozzle Area Ratio: 15:1
  20. Characteristic Exhaust Velocity: -1 m/s
  21. Adiabatic Combustion Temperature: -1°K
  22. Engine Gimbal Range: ±7°
  23. Engine Injector Design: Liquid Pintle Injector
  24. Engine chamber configuration: Single Chamber
  25. Engine Use Case: Payload (Main Propulsion)
  26. Tank repressurisation Method: Autogenous
  27. Nozzle Cooling Mechanism: Film Cooling
  28. Engine Throttle Range: Not Throttleable
  29.  
  30.  
  31. Engine Designation: JD-455m "Destiny"
  32. Fuel Flow Cycle: Liquid Core
  33. Propellant(Remass): Uranium impregnated Tantalum and Carbon Monoxide (CO)
  34. Propellant State: Cryogenic Liquid
  35. Reactor Generation: Generation V+
  36. Reactor Fuel Material: 19% Uranium-235
  37. Engine Exhaust velocity: 7,211 m/s
  38. Reactor Core Temperature: 4,457 °K
  39. Reactor Coolant: Carbon Monoxide (CO)
  40. Engine Bimodality: Engine is bimodal
  41. Engine Electrical Output: 802 MW
  42. Altitude Of Operation: 80 km+ (Vacuum)
  43. Exhaust Nozzle Geometry: Contour Bell Nozzle
  44. Exhaust Nozzle Area Ratio: 127:1
  45. Exhaust Nozzle Cooling Mechanism: Film Cooling
  46. Engine Use Case: Space Tug (Main Propulsion)
  47. Tank repressurisation Method: Inert Gas
  48.  
  49.  
  50. Engine Designation: MV-396l "Hornet"
  51. Fuel Flow Cycle: Monopropellant (Decomposition)
  52. Propellant(Remass): 65% NH4N(NO2)2 (Ammonium Dinitramide) + 35% CH3OH(Methanol)
  53. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  54. Engine Use Case: Space Tug (Vernier)
  55. Altitude Of Operation: 80 km+ (Vacuum)
  56. Nozzle Cooling Mechanism: Ablative Cooling
  57. Engine catalyst: Iridium coated Alumina Pellets
  58.  
  59.  
  60. Engine Designation: MV-98J "Insider"
  61. Fuel Flow Cycle: Monopropellant (Cold Gas)
  62. Propellant(Remass): Helium (He)
  63. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  64. Engine Use Case: Payload (Vernier)
  65. Altitude Of Operation: 80 km+ (Vacuum)
  66. Nozzle Cooling Mechanism: Ablative Cooling
  67.  
  68.  
  69. Engine Designation: TYS-145B "Federation"
  70. Fuel Flow Cycle: Liquid Core
  71. Propellant(Remass): Uranium impregnated Tungsten and Carbon Dioxide (CO2)
  72. Propellant State: Cryogenic Liquid
  73. Reactor Generation: Generation IV
  74. Reactor Fuel Material: 38% Uranium-235
  75. Engine Exhaust velocity: 3,344 m/s
  76. Reactor Core Temperature: 3,773 °K
  77. Reactor Coolant: Carbon Dioxide (CO2)
  78. Engine Bimodality: Engine is bimodal
  79. Engine Electrical Output: 679 MW
  80. Altitude Of Operation: 80 km+ (Vacuum)
  81. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  82. Exhaust Nozzle Area Ratio: 157:1
  83. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  84. Engine Use Case: Payload (Main Propulsion)
  85. Tank repressurisation Method: Autogenous
  86.  
  87.  
  88. Engine Designation: RSA-567Y "Pulsar"
  89. Fuel Flow Cycle: Nuclear SaltWater
  90. Propellant(Remass): Uranium(IV) TetraBromide (UBr4) + Water (H2O)
  91. Propellant State: Aqueous
  92. Reactor Generation: Engine has no reactor
  93. Reactor Fuel Material: 90% Uranium
  94. Engine Exhaust velocity: 4,725,902 m/s
  95. Reactor Core Temperature: 127,708 °K
  96. Reactor Coolant: Water (H2O)
  97. Engine Bimodality: Engine isn't bimodal
  98. Engine Electrical Output: None
  99. Altitude Of Operation: 80 km+ (Vacuum)
  100. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  101. Exhaust Nozzle Area Ratio: 134:1
  102. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  103. Engine Use Case: Payload (Main Propulsion)
  104. Tank repressurisation Method: Inert Gas
  105.  
  106.  
  107. Engine Designation: MV-671V "Dunay"
  108. Fuel Flow Cycle: Variable Specific Impulse Magnetoplasma Rocket (VASIMR)
  109. Propellant(Remass): Ar (Argon)
  110. Exhaust Nozzle Geometry: VASIMR Magnetic Confinement Nozzle
  111. Engine Use Case: Space Tug (Main Propulsion)
  112. Altitude Of Operation: 80 km+ (Vacuum)
  113. Engine Power Source: Nuclear Fusion Reactor
  114. Rated Power Level: 390 kW
  115.  
  116.  
  117. Engine Designation: DST-595C "Philae"
  118. Fuel Flow Cycle: Solid Core
  119. Propellant(Remass):
  120. Propellant State: Cryogenic Liquid
  121. Reactor Generation: Generation V+
  122. Reactor Fuel Material: 5% Uranium-235
  123. Engine Exhaust velocity: 12,950 m/s
  124. Reactor Core Temperature: 2,050 °K
  125. Reactor Coolant: Hydrogen (H2)
  126. Engine Bimodality: Engine is bimodal
  127. Engine Electrical Output: 369 MW
  128. Altitude Of Operation: 80 km+ (Vacuum)
  129. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  130. Exhaust Nozzle Area Ratio: 168:1
  131. Exhaust Nozzle Cooling Mechanism: Radiative Cooling
  132. Engine Use Case: Payload (Main Propulsion)
  133. Tank repressurisation Method: Inert Gas
  134.  
  135.  
  136. Engine Designation: LE-960 "Proton"
  137. Fuel Flow Cycle: Variable Specific Impulse Magnetoplasma Rocket (VASIMR)
  138. Propellant(Remass): Ar (Argon)
  139. Exhaust Nozzle Geometry: VASIMR Magnetic Confinement Nozzle
  140. Engine Use Case: Payload (Main Propulsion)
  141. Altitude Of Operation: 80 km+ (Vacuum)
  142. Engine Power Source: Nuclear Fusion Reactor
  143. Rated Power Level: 430 kW
  144.  
  145.  
  146. Engine Designation: HS-705S "Lotos"
  147. Fuel Flow Cycle: Staged Combustion (Oxidizer Rich)
  148. Engine Oxidizer: O2 (Oxygen)
  149. Engine Fuel: C2H5OH(Ethanol) 95%
  150. Average Mixture Ratio: 1.49
  151. Propellant properties: Not Hypergolic but cryogenic
  152. Altitude Of Operation: Any Altitude (0-80 km+)
  153. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  154. Exhaust Nozzle Area Ratio: 16:1
  155. Characteristic Exhaust Velocity: 2,713 m/s
  156. Adiabatic Combustion Temperature: 3,314°K
  157. Engine Gimbal Range: ±5°
  158. Engine Injector Design: Liquid Swirl Injector
  159. Engine chamber configuration: Single Chamber
  160. Engine Use Case: Payload (Main Propulsion)
  161. Tank repressurisation Method: Autogenous
  162. Nozzle Cooling Mechanism: Film Cooling
  163. Engine Throttle Range: Not Throttleable
  164.  
  165.  
  166. Engine Designation: F-471W "Sentinel"
  167. Fuel Flow Cycle: Liquid Core
  168. Propellant(Remass): Uranium impregnated Osmium and Carbon Dioxide (CO2)
  169. Propellant State: Cryogenic Liquid
  170. Reactor Generation: Generation III+
  171. Reactor Fuel Material: 94% Uranium-235
  172. Engine Exhaust velocity: 9,100 m/s
  173. Reactor Core Temperature: 4,613 °K
  174. Reactor Coolant: Carbon Dioxide (CO2)
  175. Engine Bimodality: Engine is bimodal
  176. Engine Electrical Output: 830 MW
  177. Altitude Of Operation: 80 km+ (Vacuum)
  178. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  179. Exhaust Nozzle Area Ratio: 93:1
  180. Exhaust Nozzle Cooling Mechanism: Film Cooling
  181. Engine Use Case: Upper Stage(Main Propulsion)
  182. Tank repressurisation Method: Autogenous
  183.  
  184.  
  185. Engine Designation: DOK-391H "Orlets"
  186. Fuel Flow Cycle: Dual Expander (Closed)
  187. Engine Oxidizer: F2 (Fluorine)
  188. Engine Fuel: H2 (Hydrogen)
  189. Average Mixture Ratio: 6.0
  190. Propellant properties: Hypergolic and cryogenic
  191. Altitude Of Operation: Any Altitude (0-80 km+)
  192. Exhaust Nozzle Geometry: Toroidal Aerospike Nozzle
  193. Exhaust Nozzle Area Ratio: None
  194. Characteristic Exhaust Velocity: 3,925 m/s
  195. Adiabatic Combustion Temperature: 3,689°K
  196. Engine Gimbal Range: ±2°
  197. Engine Injector Design: Gas Pintle Injector
  198. Engine chamber configuration: Single Chamber
  199. Engine Use Case: Lower Stage (Main Propulsion)
  200. Tank repressurisation Method: Inert Gas
  201. Nozzle Cooling Mechanism: Film Cooling
  202. Engine Throttle Range: 56-107%
  203.  
  204.  
  205. Engine Designation: RD-485y "Voyager"
  206. Fuel Flow Cycle: Liquid Core
  207. Propellant(Remass): Uranium impregnated Osmium and Oxygen (O2)
  208. Propellant State: Cryogenic Liquid
  209. Reactor Generation: Generation III+
  210. Reactor Fuel Material: 69% Uranium-235
  211. Engine Exhaust velocity: 3,344 m/s
  212. Reactor Core Temperature: 4,357 °K
  213. Reactor Coolant: Oxygen (O2)
  214. Engine Bimodality: Engine is bimodal
  215. Engine Electrical Output: 784 MW
  216. Altitude Of Operation: 80 km+ (Vacuum)
  217. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  218. Exhaust Nozzle Area Ratio: 135:1
  219. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  220. Engine Use Case: Space Tug (Main Propulsion)
  221. Tank repressurisation Method: Inert Gas
  222.  
  223.  
  224. Engine Designation: RM02-217B "Ariane"
  225. Fuel Flow Cycle: Liquid Core
  226. Propellant(Remass): Uranium impregnated Rhenium and Oxygen (O2)
  227. Propellant State: Cryogenic Liquid
  228. Reactor Generation: Generation III+
  229. Reactor Fuel Material: 50% Uranium-235
  230. Engine Exhaust velocity: 14,437 m/s
  231. Reactor Core Temperature: 4,413 °K
  232. Reactor Coolant: Oxygen (O2)
  233. Engine Bimodality: Engine is bimodal
  234. Engine Electrical Output: 794 MW
  235. Altitude Of Operation: 80 km+ (Vacuum)
  236. Exhaust Nozzle Geometry: Contour Bell Nozzle
  237. Exhaust Nozzle Area Ratio: 112:1
  238. Exhaust Nozzle Cooling Mechanism: Film Cooling
  239. Engine Use Case: Payload (Main Propulsion)
  240. Tank repressurisation Method: Inert Gas
  241.  
  242.  
  243. Engine Designation: MA-140r "Bryozoa"
  244. Fuel Flow Cycle: Monopropellant (Decomposition)
  245. Propellant(Remass): NH2OH+NO3 (Hydroxylammonium nitrate)
  246. Exhaust Nozzle Geometry: Conical Nozzle
  247. Engine Use Case: Payload (Main Propulsion)
  248. Altitude Of Operation: 80 km+ (Vacuum)
  249. Nozzle Cooling Mechanism: Ablative Cooling
  250. Engine catalyst: Iridium coated Copper Pellets
  251.  
  252.  
  253. Engine Designation: RS-189M "Oberon"
  254. Fuel Flow Cycle: Hall Effect Thruster
  255. Propellant(Remass): Mg (Magnesium)
  256. Exhaust Nozzle Geometry: Hall Effect Thruster Nozzle
  257. Engine Use Case: Space Tug (Main Propulsion)
  258. Altitude Of Operation: 80 km+ (Vacuum)
  259. Engine Power Source: Nuclear Fusion Reactor
  260. Rated Power Level: 890 kW
  261.  
  262.  
  263. Engine Designation: F-186y "Chronos"
  264. Fuel Flow Cycle: Gridded Ion Thruster
  265. Propellant(Remass): Xe (Xenon)
  266. Exhaust Nozzle Geometry: Electrostatic Ion Nozzle
  267. Engine Use Case: Space Tug (Main Propulsion)
  268. Altitude Of Operation: 80 km+ (Vacuum)
  269. Engine Power Source: Hydrogen Fuel cell
  270. Rated Power Level: 70 kW
  271.  
  272.  
  273. Engine Designation: KMV-126P "Kometa"
  274. Fuel Flow Cycle:  Vapor Core
  275. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Ammonia (NH3)
  276. Propellant State: Cryogenic Liquid
  277. Reactor Generation: Generation II
  278. Reactor Fuel Material: 93% Uranium-235
  279. Engine Exhaust velocity: 8,683 m/s
  280. Reactor Core Temperature: 6,076 °K
  281. Reactor Coolant: Ammonia (NH3)
  282. Engine Bimodality: Engine is bimodal
  283. Engine Electrical Output: 1,094 MW
  284. Altitude Of Operation: 80 km+ (Vacuum)
  285. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  286. Exhaust Nozzle Area Ratio: 108:1
  287. Exhaust Nozzle Cooling Mechanism: Radiative Cooling
  288. Engine Use Case: Space Tug (Main Propulsion)
  289. Tank repressurisation Method: Inert Gas
  290.  
  291.  
  292. Engine Designation: JDK-876S "Phoenix"
  293. Fuel Flow Cycle: Dual Expander (Closed)
  294. Engine Oxidizer: O2 (Oxygen)
  295. Engine Fuel: CH4 (Methane)
  296. Average Mixture Ratio: 2.77
  297. Propellant properties: Not Hypergolic but cryogenic
  298. Altitude Of Operation: 0-20 km (Sea Level)
  299. Exhaust Nozzle Geometry: Contour Bell Nozzle
  300. Exhaust Nozzle Area Ratio: 13:1
  301. Characteristic Exhaust Velocity: 2,932 m/s
  302. Adiabatic Combustion Temperature: 3,379°K
  303. Engine Gimbal Range: ±2°
  304. Engine Injector Design: Gas Pintle Injector
  305. Engine chamber configuration: Dual Chamber
  306. Engine Use Case: Upper Stage(Main Propulsion)
  307. Tank repressurisation Method: Autogenous
  308. Nozzle Cooling Mechanism: Film Cooling
  309. Engine Throttle Range: Not Throttleable
  310.  
  311.  
  312. Engine Designation: BF-248 "Ruby"
  313. Fuel Flow Cycle:  Solid Core
  314. Propellant(Remass):
  315. Propellant State: Cryogenic Liquid
  316. Reactor Generation: Generation IV
  317. Reactor Fuel Material: 10% Uranium-235
  318. Engine Exhaust velocity: 2,649 m/s
  319. Reactor Core Temperature: 2,124 °K
  320. Reactor Coolant: Water (H2O)
  321. Engine Bimodality: Engine is bimodal
  322. Engine Electrical Output: 382 MW
  323. Altitude Of Operation: 80 km+ (Vacuum)
  324. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  325. Exhaust Nozzle Area Ratio: 95:1
  326. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  327. Engine Use Case: Payload (Main Propulsion)
  328. Tank repressurisation Method: Autogenous
  329.  
  330.  
  331. Engine Designation: DOK-850B "Zemlya"
  332. Fuel Flow Cycle:  Vapor Core
  333. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Water (H2O)
  334. Propellant State: Cryogenic Liquid
  335. Reactor Generation: Generation III+
  336. Reactor Fuel Material: 93% Uranium-235
  337. Engine Exhaust velocity: 2,842 m/s
  338. Reactor Core Temperature: 5,791 °K
  339. Reactor Coolant: Water (H2O)
  340. Engine Bimodality: Engine is bimodal
  341. Engine Electrical Output: 1,042 MW
  342. Altitude Of Operation: 80 km+ (Vacuum)
  343. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  344. Exhaust Nozzle Area Ratio: 156:1
  345. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  346. Engine Use Case: Payload (Main Propulsion)
  347. Tank repressurisation Method: Inert Gas
  348.  
  349.  
  350. Engine Designation: P-237w "Mariner"
  351. Fuel Flow Cycle: Combustion Tap Off
  352. Engine Oxidizer: O2 (Oxygen)
  353. Engine Fuel: C2H5OH(Ethanol) 75%
  354. Average Mixture Ratio: 1.29
  355. Propellant properties: Not Hypergolic but cryogenic
  356. Altitude Of Operation: 30-80 km (High Atmosphere)
  357. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  358. Exhaust Nozzle Area Ratio: 67:1
  359. Characteristic Exhaust Velocity: 2,635 m/s
  360. Adiabatic Combustion Temperature: 3,167°K
  361. Engine Gimbal Range: ±1°
  362. Engine Injector Design: Liquid Cross-impinging Injector
  363. Engine chamber configuration: Dual Chamber
  364. Engine Use Case: Upper Stage (Main Propulsion)
  365. Tank repressurisation Method: Inert Gas
  366. Nozzle Cooling Mechanism: Film Cooling
  367. Engine Throttle Range: Not Throttleable
  368.  
  369.  
  370. Engine Designation: LR-227A "Pirs"
  371. Fuel Flow Cycle:  Vapor Core
  372. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Water (H2O)
  373. Propellant State: Cryogenic Liquid
  374. Reactor Generation: Generation III+
  375. Reactor Fuel Material: 93% Uranium-235
  376. Engine Exhaust velocity: 2,842 m/s
  377. Reactor Core Temperature: 6,016 °K
  378. Reactor Coolant: Water (H2O)
  379. Engine Bimodality: Engine is bimodal
  380. Engine Electrical Output: 1,083 MW
  381. Altitude Of Operation: 80 km+ (Vacuum)
  382. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  383. Exhaust Nozzle Area Ratio: 92:1
  384. Exhaust Nozzle Cooling Mechanism: Dump Cooling
  385. Engine Use Case: Space Tug (Main Propulsion)
  386. Tank repressurisation Method: Inert Gas
  387.  
  388.  
  389. Engine Designation: KMV-318X "Pamir"
  390. Fuel Flow Cycle: Gridded Ion Thruster
  391. Propellant(Remass): Cs (Caesium)
  392. Exhaust Nozzle Geometry: Electrostatic Ion Nozzle
  393. Engine Use Case: Payload (Main Propulsion)
  394. Altitude Of Operation: 80 km+ (Vacuum)
  395. Engine Power Source: Hydrogen Fuel cell
  396. Rated Power Level: 840 kW
  397.  
  398.  
  399. Engine Designation: KDTU-415T "Progress"
  400. Fuel Flow Cycle: Gas Generator
  401. Engine Oxidizer: O3 (Ozone)
  402. Engine Fuel: C12H26 (n-Dodecane)
  403. Average Mixture Ratio: -1.0
  404. Propellant properties: Hypergolic and cryogenic
  405. Altitude Of Operation: 0-20 km (Sea Level)
  406. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  407. Exhaust Nozzle Area Ratio: 18:1
  408. Characteristic Exhaust Velocity: -1 m/s
  409. Adiabatic Combustion Temperature: -1°K
  410. Engine Gimbal Range: ±5°
  411. Engine Injector Design: Liquid Self-impinging Injector
  412. Engine chamber configuration: Dual Chamber
  413. Engine Use Case: Upper Stage(Main Propulsion)
  414. Tank repressurisation Method: Inert Gas
  415. Nozzle Cooling Mechanism: Radiative Cooling
  416. Engine Throttle Range: Not Throttleable
  417.  
  418.  
  419. Engine Designation: UA-629C "Uragan"
  420. Fuel Flow Cycle: Nuclear SaltWater
  421. Propellant(Remass): Plutonium(III) TriBromide (PuBr3) + Water (H2O)
  422. Propellant State: Aqueous
  423. Reactor Generation: Engine has no reactor
  424. Reactor Fuel Material: 2% Plutonium
  425. Engine Exhaust velocity: 66,404 m/s
  426. Reactor Core Temperature: 25,337 °K
  427. Reactor Coolant: Water (H2O)
  428. Engine Bimodality: Engine isn't bimodal
  429. Engine Electrical Output: None
  430. Altitude Of Operation: 80 km+ (Vacuum)
  431. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  432. Exhaust Nozzle Area Ratio: 166:1
  433. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  434. Engine Use Case: Payload (Main Propulsion)
  435. Tank repressurisation Method: Autogenous
  436.  
  437.  
  438. Engine Designation: DF-288 "Hephaestus"
  439. Fuel Flow Cycle: Staged Combustion (Fuel Rich)
  440. Engine Oxidizer: F2 (Fluorine) + O2 (Oxygen)
  441. Engine Fuel: H2 (Hydrogen)
  442. Average Mixture Ratio: -1.0
  443. Propellant properties: Hypergolic and cryogenic
  444. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  445. Exhaust Nozzle Geometry: Contour Bell Nozzle
  446. Exhaust Nozzle Area Ratio: 38:1
  447. Characteristic Exhaust Velocity: -1 m/s
  448. Adiabatic Combustion Temperature: -1°K
  449. Engine Gimbal Range: ±5°
  450. Engine Injector Design: Liquid Swirl Injector
  451. Engine chamber configuration: Single Chamber
  452. Engine Use Case: Lower Stage (Main Propulsion)
  453. Tank repressurisation Method: Autogenous
  454. Nozzle Cooling Mechanism: Film Cooling
  455. Engine Throttle Range: 14-113%
  456.  
  457.  
  458. Engine Designation: JD-64 "Tethys"
  459. Fuel Flow Cycle: Droplet Core
  460. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Oxygen (O2)
  461. Propellant State: Cryogenic Liquid
  462. Reactor Generation: Generation II
  463. Reactor Fuel Material: 71% Uranium-235
  464. Engine Exhaust velocity: 4,496 m/s
  465. Reactor Core Temperature: 6,690 °K
  466. Reactor Coolant: Oxygen (O2)
  467. Engine Bimodality: Engine is bimodal
  468. Engine Electrical Output: 1,204 MW
  469. Altitude Of Operation: 80 km+ (Vacuum)
  470. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  471. Exhaust Nozzle Area Ratio: 170:1
  472. Exhaust Nozzle Cooling Mechanism: Film Cooling
  473. Engine Use Case: Payload (Main Propulsion)
  474. Tank repressurisation Method: Inert Gas
  475.  
  476.  
  477. Engine Designation: XLR-154W "Sirius"
  478. Fuel Flow Cycle: Colloid Thruster
  479. Propellant(Remass): NH2OH+NO3 (Hydroxylammonium nitrate)
  480. Exhaust Nozzle Geometry: Capillary Emitter-Electrode Cone
  481. Engine Use Case: Payload (Main Propulsion)
  482. Altitude Of Operation: 80 km+ (Vacuum)
  483. Engine Power Source: Nuclear Fission Reactor
  484. Rated Power Level: 300 kW
  485.  
  486.  
  487. Engine Designation: SOK-543T "Oktan"
  488. Fuel Flow Cycle: Dual Expander (Open/Bleed)
  489. Engine Oxidizer: O2 (Oxygen)
  490. Engine Fuel: H2 (Hydrogen)
  491. Average Mixture Ratio: 5.0
  492. Propellant properties: Not Hypergolic but cryogenic
  493. Altitude Of Operation: Any Altitude (0-80 km+)
  494. Exhaust Nozzle Geometry: Toroidal Aerospike Nozzle
  495. Exhaust Nozzle Area Ratio: None
  496. Characteristic Exhaust Velocity: 3,738 m/s
  497. Adiabatic Combustion Temperature: 3,304°K
  498. Engine Gimbal Range: ±2°
  499. Engine Injector Design: Gas Showerhead Injector
  500. Engine chamber configuration: Single Chamber
  501. Engine Use Case: Upper Stage(Main Propulsion)
  502. Tank repressurisation Method: Inert Gas
  503. Nozzle Cooling Mechanism: Radiative Cooling
  504. Engine Throttle Range: 97-112%
  505.  
  506.  
  507. Engine Designation: KVD-952 "Molniya"
  508. Fuel Flow Cycle: Monopropellant (Cold Gas)
  509. Propellant(Remass): Ammonia (NH3)
  510. Exhaust Nozzle Geometry: Contour Bell Nozzle
  511. Engine Use Case: Payload (Main Propulsion)
  512. Altitude Of Operation: 80 km+ (Vacuum)
  513. Nozzle Cooling Mechanism: Ablative Cooling
  514.  
  515.  
  516. Engine Designation: SOK-603V "Orlets"
  517. Fuel Flow Cycle: Full Flow Staged
  518. Engine Oxidizer: H2O2 (Hydrogen Peroxide) 85%
  519. Engine Fuel: H2 (Hydrogen)
  520. Average Mixture Ratio: 14.0
  521. Propellant properties: Not Hypergolic but cryogenic
  522. Altitude Of Operation: 30-80 km (High Atmosphere)
  523. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  524. Exhaust Nozzle Area Ratio: 66:1
  525. Characteristic Exhaust Velocity: 2,882 m/s
  526. Adiabatic Combustion Temperature: 2,544°K
  527. Engine Gimbal Range: ±7°
  528. Engine Injector Design: Liquid Cross-impinging Injector
  529. Engine chamber configuration: Single Chamber
  530. Engine Use Case: Upper Stage (Main Propulsion)
  531. Tank repressurisation Method: Inert Gas
  532. Nozzle Cooling Mechanism: Transpiration Cooling
  533. Engine Throttle Range: Not Throttleable
  534.  
  535.  
  536. Engine Designation: LM10-782X "Gamma"
  537. Fuel Flow Cycle: Nuclear SaltWater
  538. Propellant(Remass): Plutonium(III) TriBromide (PuBr3) + Water (H2O)
  539. Propellant State: Aqueous
  540. Reactor Generation: Engine has no reactor
  541. Reactor Fuel Material: 90% Plutonium
  542. Engine Exhaust velocity: 4,725,462 m/s
  543. Reactor Core Temperature: 127,674 °K
  544. Reactor Coolant: Water (H2O)
  545. Engine Bimodality: Engine isn't bimodal
  546. Engine Electrical Output: None
  547. Altitude Of Operation: 80 km+ (Vacuum)
  548. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  549. Exhaust Nozzle Area Ratio: 93:1
  550. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  551. Engine Use Case: Payload (Main Propulsion)
  552. Tank repressurisation Method: Autogenous
  553.  
  554.  
  555. Engine Designation: DC-254F "Atlas"
  556. Fuel Flow Cycle: Colloid Thruster
  557. Propellant(Remass): NH2OH+NO3 (Hydroxylammonium nitrate)
  558. Exhaust Nozzle Geometry: Capillary Emitter-Electrode Cone
  559. Engine Use Case: Payload (Main Propulsion)
  560. Altitude Of Operation: 80 km+ (Vacuum)
  561. Engine Power Source: Radioisotope Thermoelectric Generator (RTG)
  562. Rated Power Level: 660 kW
  563.  
  564.  
  565. Engine Designation: XLR-683B "Amal"
  566. Fuel Flow Cycle: Dual Expander (Open/Bleed)
  567. Engine Oxidizer: O2 (Oxygen)
  568. Engine Fuel: H2 (Hydrogen)
  569. Average Mixture Ratio: 5.0
  570. Propellant properties: Not Hypergolic but cryogenic
  571. Altitude Of Operation: 30-80 km (High Atmosphere)
  572. Exhaust Nozzle Geometry: Contour Bell Nozzle
  573. Exhaust Nozzle Area Ratio: 77:1
  574. Characteristic Exhaust Velocity: 3,738 m/s
  575. Adiabatic Combustion Temperature: 3,304°K
  576. Engine Gimbal Range: 18
  577. Engine Injector Design: Gas Pintle Injector
  578. Engine chamber configuration: Dual Chamber
  579. Engine Use Case: Upper Stage (Vernier)
  580. Tank repressurisation Method: Autogenous
  581. Nozzle Cooling Mechanism: Dump Cooling
  582. Engine Throttle Range: Not Throttleable
  583.  
  584.  
  585. Engine Designation: DC-317D "Rufus"
  586. Fuel Flow Cycle: MagnetoPlasmaDynamic Thruster
  587. Propellant(Remass): Ne (Neon)
  588. Exhaust Nozzle Geometry: Cathode Plug Magnetic Confinement Nozzle
  589. Engine Use Case: Space Tug (Main Propulsion)
  590. Altitude Of Operation: 80 km+ (Vacuum)
  591. Engine Power Source: Hydrogen Fuel cell
  592. Rated Power Level: 440 kW
  593.  
  594.  
  595. Engine Designation: M-898v "Dream"
  596. Fuel Flow Cycle: Solid Core
  597. Propellant(Remass):
  598. Propellant State: Cryogenic Liquid
  599. Reactor Generation: Generation V+
  600. Reactor Fuel Material: 9% Uranium-235
  601. Engine Exhaust velocity: 12,950 m/s
  602. Reactor Core Temperature: 2,934 °K
  603. Reactor Coolant: Water (H2O)
  604. Engine Bimodality: Engine is bimodal
  605. Engine Electrical Output: 528 MW
  606. Altitude Of Operation: 80 km+ (Vacuum)
  607. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  608. Exhaust Nozzle Area Ratio: 195:1
  609. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  610. Engine Use Case: Upper Stage(Main Propulsion)
  611. Tank repressurisation Method: Autogenous
  612.  
  613.  
  614. Engine Designation: CE-648 "Cassini"
  615. Fuel Flow Cycle: Droplet Core
  616. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Carbon Monoxide (CO)
  617. Propellant State: Cryogenic Liquid
  618. Reactor Generation: Generation IV
  619. Reactor Fuel Material: 84% Uranium-235
  620. Engine Exhaust velocity: 3,341 m/s
  621. Reactor Core Temperature: 6,490 °K
  622. Reactor Coolant: Carbon Monoxide (CO)
  623. Engine Bimodality: Engine isn't bimodal
  624. Engine Electrical Output: None
  625. Altitude Of Operation: 80 km+ (Vacuum)
  626. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  627. Exhaust Nozzle Area Ratio: 123:1
  628. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  629. Engine Use Case: Payload (Main Propulsion)
  630. Tank repressurisation Method: Autogenous
  631.  
  632.  
  633. Engine Designation: FWR-548S "Parom"
  634. Fuel Flow Cycle: Dual Expander (Closed)
  635. Engine Oxidizer: O2 (Oxygen)
  636. Engine Fuel: CH4 (Methane)
  637. Average Mixture Ratio: 2.77
  638. Propellant properties: Not Hypergolic but cryogenic
  639. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  640. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  641. Exhaust Nozzle Area Ratio: 36:1
  642. Characteristic Exhaust Velocity: 2,932 m/s
  643. Adiabatic Combustion Temperature: 3,379°K
  644. Engine Gimbal Range: ±6°
  645. Engine Injector Design: Gas Pintle Injector
  646. Engine chamber configuration: Dual Chamber
  647. Engine Use Case: Lower Stage (Course Correction)
  648. Tank repressurisation Method: Inert Gas
  649. Nozzle Cooling Mechanism: Dump Cooling
  650. Engine Throttle Range: Not Throttleable
  651.  
  652.  
  653. Engine Designation: NK-237W "Carrier"
  654. Fuel Flow Cycle: Electric Pump Fed
  655. Engine Oxidizer: AK27I: 73% HNO3 + 27% N2O4 (Nitric Acid)
  656. Engine Fuel: N2H4 (Hydrazine)
  657. Average Mixture Ratio: 1.28
  658. Propellant properties: Hypergolic but not cryogenic
  659. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  660. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  661. Exhaust Nozzle Area Ratio: 34:1
  662. Characteristic Exhaust Velocity: 2,702 m/s
  663. Adiabatic Combustion Temperature: 2,932°K
  664. Engine Gimbal Range: 14
  665. Engine Injector Design: Gas Showerhead Injector
  666. Engine chamber configuration: Single Chamber
  667. Engine Use Case: Lower Stage (Vernier)
  668. Tank repressurisation Method: Inert Gas
  669. Nozzle Cooling Mechanism: Fuel Regenerative Cooling
  670. Engine Throttle Range: Not Throttleable
  671.  
  672.  
  673. Engine Designation: KDU-359Z "Panther"
  674. Fuel Flow Cycle: Expander (Closed)
  675. Engine Oxidizer: O2 (Oxygen)
  676. Engine Fuel: C2H5OH(Ethanol) 95%
  677. Average Mixture Ratio: 1.49
  678. Propellant properties: Not Hypergolic but cryogenic
  679. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  680. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  681. Exhaust Nozzle Area Ratio: 33:1
  682. Characteristic Exhaust Velocity: 2,713 m/s
  683. Adiabatic Combustion Temperature: 3,314°K
  684. Engine Gimbal Range: ±7°
  685. Engine Injector Design: Gas Self-impinging Injector
  686. Engine chamber configuration: Dual Chamber
  687. Engine Use Case: Lower Stage (Course Correction)
  688. Tank repressurisation Method: Inert Gas
  689. Nozzle Cooling Mechanism: Radiative Cooling
  690. Engine Throttle Range: 86-101%
  691.  
  692.  
  693. Engine Designation: LE-128 "Zephyr"
  694. Fuel Flow Cycle: Hall Effect Thruster
  695. Propellant(Remass): Zn (Zinc)
  696. Exhaust Nozzle Geometry: Hall Effect Thruster Nozzle
  697. Engine Use Case: Space Tug (Main Propulsion)
  698. Altitude Of Operation: 80 km+ (Vacuum)
  699. Engine Power Source: Hydrogen Fuel cell
  700. Rated Power Level: 40 kW
  701.  
  702.  
  703. Engine Designation: KDTU-661G "Svir"
  704. Fuel Flow Cycle: Monopropellant (Decomposition)
  705. Propellant(Remass): 65% NH4N(NO2)2 (Ammonium Dinitramide) + 35% CH3OH(Methanol)
  706. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  707. Engine Use Case: Space Tug (Ullage)
  708. Altitude Of Operation: 80 km+ (Vacuum)
  709. Nozzle Cooling Mechanism: Radiative Cooling
  710. Engine catalyst: Iridium coated Alumina Pellets
  711.  
  712.  
  713. Engine Designation: NAA75-712 "Aerolus"
  714. Fuel Flow Cycle: Expander (Open/Bleed)
  715. Engine Oxidizer: F2 (Fluorine) + O2 (Oxygen)
  716. Engine Fuel: CH3OH (Methanol)
  717. Average Mixture Ratio: -1.0
  718. Propellant properties: Hypergolic and cryogenic
  719. Altitude Of Operation: 80 km+ (Vacuum)
  720. Exhaust Nozzle Geometry: Contour Bell Nozzle
  721. Exhaust Nozzle Area Ratio: 175:1
  722. Characteristic Exhaust Velocity: -1 m/s
  723. Adiabatic Combustion Temperature: -1°K
  724. Engine Gimbal Range: None
  725. Engine Injector Design: Gas Swirl Injector
  726. Engine chamber configuration: Single Chamber
  727. Engine Use Case: Upper Stage(Main Propulsion)
  728. Tank repressurisation Method: Inert Gas
  729. Nozzle Cooling Mechanism: Dump Cooling
  730. Engine Throttle Range: Not Throttleable
  731.  
  732.  
  733. Engine Designation: XS-919R "Douglas"
  734. Fuel Flow Cycle: Monopropellant (Decomposition)
  735. Propellant(Remass): 65% NH4N(NO2)2 (Ammonium Dinitramide) + 35% CH3OH(Methanol)
  736. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  737. Engine Use Case: Payload (Main Propulsion)
  738. Altitude Of Operation: 80 km+ (Vacuum)
  739. Nozzle Cooling Mechanism: Radiative Cooling
  740. Engine catalyst: Iridium coated Alumina Pellets
  741.  
  742.  
  743. Engine Designation: LE-460S "Saturn"
  744. Fuel Flow Cycle: Liquid Core
  745. Propellant(Remass): Uranium impregnated Tungsten and Ammonia (NH3)
  746. Propellant State: Cryogenic Liquid
  747. Reactor Generation: Generation IV
  748. Reactor Fuel Material: 69% Uranium-235
  749. Engine Exhaust velocity: 9,100 m/s
  750. Reactor Core Temperature: 4,287 °K
  751. Reactor Coolant: Ammonia (NH3)
  752. Engine Bimodality: Engine is bimodal
  753. Engine Electrical Output: 772 MW
  754. Altitude Of Operation: 80 km+ (Vacuum)
  755. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  756. Exhaust Nozzle Area Ratio: 151:1
  757. Exhaust Nozzle Cooling Mechanism: Film Cooling
  758. Engine Use Case: Upper Stage(Main Propulsion)
  759. Tank repressurisation Method: Autogenous
  760.  
  761.  
  762. Engine Designation: BE-303R "Sarychev"
  763. Fuel Flow Cycle: MagnetoPlasmaDynamic Thruster
  764. Propellant(Remass): Xe (Xenon)
  765. Exhaust Nozzle Geometry: Cathode Plug Magnetic Confinement Nozzle
  766. Engine Use Case: Payload (Main Propulsion)
  767. Altitude Of Operation: 80 km+ (Vacuum)
  768. Engine Power Source: Nuclear Fission Reactor
  769. Rated Power Level: 120 kW
  770.  
  771.  
  772. Engine Designation: P-147P "Thumper"
  773. Fuel Flow Cycle: Hall Effect Thruster
  774. Propellant(Remass): I2 (Iodine)
  775. Exhaust Nozzle Geometry: Hall Effect Thruster Nozzle
  776. Engine Use Case: Space Tug (Main Propulsion)
  777. Altitude Of Operation: 80 km+ (Vacuum)
  778. Engine Power Source: Nuclear Fusion Reactor
  779. Rated Power Level: 600 kW
  780.  
  781.  
  782. Engine Designation: E-587A "Haptophyta"
  783. Fuel Flow Cycle: Gridded Ion Thruster
  784. Propellant(Remass): Cs (Caesium)
  785. Exhaust Nozzle Geometry: Electrostatic Ion Nozzle
  786. Engine Use Case: Space Tug (Main Propulsion)
  787. Altitude Of Operation: 80 km+ (Vacuum)
  788. Engine Power Source: Hydrogen Fuel cell
  789. Rated Power Level: 550 kW
  790.  
  791.  
  792. Engine Designation: RSA-719G "Granit"
  793. Fuel Flow Cycle: Liquid Core
  794. Propellant(Remass): Uranium impregnated Rhenium and Ammonia (NH3)
  795. Propellant State: Cryogenic Liquid
  796. Reactor Generation: Generation III+
  797. Reactor Fuel Material: 30% Uranium-235
  798. Engine Exhaust velocity: 4,725 m/s
  799. Reactor Core Temperature: 4,278 °K
  800. Reactor Coolant: Ammonia (NH3)
  801. Engine Bimodality: Engine is bimodal
  802. Engine Electrical Output: 770 MW
  803. Altitude Of Operation: 80 km+ (Vacuum)
  804. Exhaust Nozzle Geometry: Contour Bell Nozzle
  805. Exhaust Nozzle Area Ratio: 92:1
  806. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  807. Engine Use Case: Payload (Main Propulsion)
  808. Tank repressurisation Method: Inert Gas
  809.  
  810.  
  811. Engine Designation: XS-669D "Krugazor"
  812. Fuel Flow Cycle: Solid Core
  813. Propellant(Remass):
  814. Propellant State: Cryogenic Liquid
  815. Reactor Generation: Generation III+
  816. Reactor Fuel Material: 37% Plutonium-238
  817. Engine Exhaust velocity: 3,000 m/s
  818. Reactor Core Temperature: 2,525 °K
  819. Reactor Coolant: Hydrogen (H2)
  820. Engine Bimodality: Engine is bimodal
  821. Engine Electrical Output: 454 MW
  822. Altitude Of Operation: 80 km+ (Vacuum)
  823. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  824. Exhaust Nozzle Area Ratio: 168:1
  825. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  826. Engine Use Case: Payload (Main Propulsion)
  827. Tank repressurisation Method: Inert Gas
  828.  
  829.  
  830. Engine Designation: BADR-935J "Reflektor"
  831. Fuel Flow Cycle: Staged Combustion (Oxidizer Rich)
  832. Engine Oxidizer: O3 (Ozone)
  833. Engine Fuel: CH6N2 (MonomethylHydrazine)
  834. Average Mixture Ratio: -1.0
  835. Propellant properties: Hypergolic and cryogenic
  836. Altitude Of Operation: 80 km+ (Vacuum)
  837. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  838. Exhaust Nozzle Area Ratio: 183:1
  839. Characteristic Exhaust Velocity: -1 m/s
  840. Adiabatic Combustion Temperature: -1°K
  841. Engine Gimbal Range: None
  842. Engine Injector Design: Liquid Swirl Injector
  843. Engine chamber configuration: Single Chamber
  844. Engine Use Case: Upper Stage (Main Propulsion)
  845. Tank repressurisation Method: Inert Gas
  846. Nozzle Cooling Mechanism: Radiative Cooling
  847. Engine Throttle Range: Not Throttleable
  848.  
  849.  
  850. Engine Designation: NAA75-22x "Minerva"
  851. Fuel Flow Cycle: Variable Specific Impulse Magnetoplasma Rocket (VASIMR)
  852. Propellant(Remass): Ar (Argon)
  853. Exhaust Nozzle Geometry: VASIMR Magnetic Confinement Nozzle
  854. Engine Use Case: Space Tug (Main Propulsion)
  855. Altitude Of Operation: 80 km+ (Vacuum)
  856. Engine Power Source: Nuclear Fusion Reactor
  857. Rated Power Level: 530 kW
  858.  
  859.  
  860. Engine Designation: LMP-167U "Fram"
  861. Fuel Flow Cycle: Dual Expander (Closed)
  862. Engine Oxidizer: F2 (Fluorine)
  863. Engine Fuel: CH4 (Methane)
  864. Average Mixture Ratio: -1.0
  865. Propellant properties: Hypergolic and cryogenic
  866. Altitude Of Operation: 30-80 km (High Atmosphere)
  867. Exhaust Nozzle Geometry: Contour Bell Nozzle
  868. Exhaust Nozzle Area Ratio: 77:1
  869. Characteristic Exhaust Velocity: -1 m/s
  870. Adiabatic Combustion Temperature: -1°K
  871. Engine Gimbal Range: 21
  872. Engine Injector Design: Gas Pintle Injector
  873. Engine chamber configuration: Dual Chamber
  874. Engine Use Case: Upper Stage(Vernier)
  875. Tank repressurisation Method: Inert Gas
  876. Nozzle Cooling Mechanism: Radiative Cooling
  877. Engine Throttle Range: 54-101%
  878.  
  879.  
  880. Engine Designation: KDU-115v "Melibea"
  881. Fuel Flow Cycle: MagnetoPlasmaDynamic Thruster
  882. Propellant(Remass): Ne (Neon)
  883. Exhaust Nozzle Geometry: Cathode Plug Magnetic Confinement Nozzle
  884. Engine Use Case: Payload (Main Propulsion)
  885. Altitude Of Operation: 80 km+ (Vacuum)
  886. Engine Power Source: Hydrogen Fuel cell
  887. Rated Power Level: 840 kW
  888.  
  889.  
  890. Engine Designation: MV-959R "Hermes"
  891. Fuel Flow Cycle: Droplet Core
  892. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Water (H2O)
  893. Propellant State: Cryogenic Liquid
  894. Reactor Generation: Generation V+
  895. Reactor Fuel Material: 69% Uranium-235
  896. Engine Exhaust velocity: 9,090 m/s
  897. Reactor Core Temperature: 5,928 °K
  898. Reactor Coolant: Water (H2O)
  899. Engine Bimodality: Engine is bimodal
  900. Engine Electrical Output: 1,067 MW
  901. Altitude Of Operation: 80 km+ (Vacuum)
  902. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  903. Exhaust Nozzle Area Ratio: 166:1
  904. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  905. Engine Use Case: Upper Stage(Main Propulsion)
  906. Tank repressurisation Method: Autogenous
  907.  
  908.  
  909. Engine Designation: LE-508V "Redstone"
  910. Fuel Flow Cycle: Nuclear SaltWater
  911. Propellant(Remass): Uranium(IV) TetraBromide (UBr4) + Water (H2O)
  912. Propellant State: Aqueous
  913. Reactor Generation: Engine has no reactor
  914. Reactor Fuel Material: 2% Uranium
  915. Engine Exhaust velocity: 65,556 m/s
  916. Reactor Core Temperature: 25,325 °K
  917. Reactor Coolant: Water (H2O)
  918. Engine Bimodality: Engine isn't bimodal
  919. Engine Electrical Output: None
  920. Altitude Of Operation: 80 km+ (Vacuum)
  921. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  922. Exhaust Nozzle Area Ratio: 107:1
  923. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  924. Engine Use Case: Payload (Main Propulsion)
  925. Tank repressurisation Method: Inert Gas
  926.  
  927.  
  928. Engine Designation: GE-318E "Ceres"
  929. Fuel Flow Cycle: Gas Generator
  930. Engine Oxidizer: AK20F: 80% HNO3 + 20% N2O4 (Nitric Acid)
  931. Engine Fuel: CH6N2 (MonomethylHydrazine)
  932. Average Mixture Ratio: 2.13
  933. Propellant properties: Hypergolic but not cryogenic
  934. Altitude Of Operation: Any Altitude (0-80 km+)
  935. Exhaust Nozzle Geometry: Linear Aerospike Nozzle
  936. Exhaust Nozzle Area Ratio: None
  937. Characteristic Exhaust Velocity: 2,635 m/s
  938. Adiabatic Combustion Temperature: 3,033°K
  939. Engine Gimbal Range: None
  940. Engine Injector Design: Liquid Pintle Injector
  941. Engine chamber configuration: Single Chamber
  942. Engine Use Case: Lower Stage (Main Propulsion)
  943. Tank repressurisation Method: Autogenous
  944. Nozzle Cooling Mechanism: Ablative Cooling
  945. Engine Throttle Range: Not Throttleable
  946.  
  947.  
  948. Engine Designation: MBB-864 "Argos"
  949. Fuel Flow Cycle: Solid Core
  950. Propellant(Remass):
  951. Propellant State: Cryogenic Liquid
  952. Reactor Generation: Generation V
  953. Reactor Fuel Material: 61% Uranium-235
  954. Engine Exhaust velocity: (12,950/~3850) m/s
  955. Reactor Core Temperature: 2,307 °K
  956. Reactor Coolant: Hydrogen (H2)
  957. Engine Bimodality: Engine is bimodal
  958. Engine Electrical Output: 415 MW
  959. Altitude Of Operation: 80 km+ (Vacuum)
  960. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  961. Exhaust Nozzle Area Ratio: 192:1
  962. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  963. Engine Use Case: Space Tug (Main Propulsion)
  964. Tank repressurisation Method: Autogenous
  965.  
  966.  
  967. Engine Designation: OBA-549f "Icarus"
  968. Fuel Flow Cycle: Staged Combustion (Oxidizer Rich)
  969. Engine Oxidizer: O2 (Oxygen)
  970. Engine Fuel: N2H4 (Hydrazine)
  971. Average Mixture Ratio: 0.74
  972. Propellant properties: Not Hypergolic but cryogenic
  973. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  974. Exhaust Nozzle Geometry: Contour Bell Nozzle
  975. Exhaust Nozzle Area Ratio: 45:1
  976. Characteristic Exhaust Velocity: 2,973 m/s
  977. Adiabatic Combustion Temperature: 3,275°K
  978. Engine Gimbal Range: ±6°
  979. Engine Injector Design: Gas Pintle Injector
  980. Engine chamber configuration: Dual Chamber
  981. Engine Use Case: Lower Stage (Main Propulsion)
  982. Tank repressurisation Method: Autogenous
  983. Nozzle Cooling Mechanism: Fuel Regenerative Cooling
  984. Engine Throttle Range: 62-108%
  985.  
  986.  
  987. Engine Designation: JDK-874X "Vysota"
  988. Fuel Flow Cycle: Droplet Core
  989. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Hydrogen (H2)
  990. Propellant State: Cryogenic Liquid
  991. Reactor Generation: Generation IV
  992. Reactor Fuel Material: 73% Uranium-235
  993. Engine Exhaust velocity: 14,422 m/s
  994. Reactor Core Temperature: 6,605 °K
  995. Reactor Coolant: Hydrogen (H2)
  996. Engine Bimodality: Engine is bimodal
  997. Engine Electrical Output: 1,189 MW
  998. Altitude Of Operation: 80 km+ (Vacuum)
  999. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1000. Exhaust Nozzle Area Ratio: 97:1
  1001. Exhaust Nozzle Cooling Mechanism: Radiative Cooling
  1002. Engine Use Case: Payload (Main Propulsion)
  1003. Tank repressurisation Method: Autogenous
  1004.  
  1005.  
  1006. Engine Designation: LR-635T "Dizhou"
  1007. Fuel Flow Cycle: Monopropellant (Decomposition)
  1008. Propellant(Remass): NH2OH+NO3 (Hydroxylammonium nitrate)
  1009. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1010. Engine Use Case: Payload (Vernier)
  1011. Altitude Of Operation: 80 km+ (Vacuum)
  1012. Nozzle Cooling Mechanism: Ablative Cooling
  1013. Engine catalyst: Iridium coated Copper Pellets
  1014.  
  1015.  
  1016. Engine Designation: CE-235R "Resurs"
  1017. Fuel Flow Cycle: Monopropellant (Decomposition)
  1018. Propellant(Remass): NH2OH+NO3 (Hydroxylammonium nitrate)
  1019. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1020. Engine Use Case: Upper Stage(Ullage)
  1021. Altitude Of Operation: 80 km+ (Vacuum)
  1022. Nozzle Cooling Mechanism: Ablative Cooling
  1023. Engine catalyst: Iridium coated Copper Pellets
  1024.  
  1025.  
  1026. Engine Designation: RM02-301y "Neutron"
  1027. Fuel Flow Cycle: Gridded Ion Thruster
  1028. Propellant(Remass): Xe (Xenon)
  1029. Exhaust Nozzle Geometry: Electrostatic Ion Nozzle
  1030. Engine Use Case: Space Tug (Main Propulsion)
  1031. Altitude Of Operation: 80 km+ (Vacuum)
  1032. Engine Power Source: Nuclear Fission Reactor
  1033. Rated Power Level: 270 kW
  1034.  
  1035.  
  1036. Engine Designation: XLR-759G "Voyager"
  1037. Fuel Flow Cycle: Electric Pump Fed
  1038. Engine Oxidizer: N2O4 (Nitrogen Tetroxide)
  1039. Engine Fuel: C6H5NH2 (Aniline)
  1040. Average Mixture Ratio: 2.64
  1041. Propellant properties: Hypergolic but not cryogenic
  1042. Altitude Of Operation: 0-20 km (Sea Level)
  1043. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  1044. Exhaust Nozzle Area Ratio: 19:1
  1045. Characteristic Exhaust Velocity: 2,538 m/s
  1046. Adiabatic Combustion Temperature: 3,468°K
  1047. Engine Gimbal Range: ±1°
  1048. Engine Injector Design: Liquid Pintle Injector
  1049. Engine chamber configuration: Single Chamber
  1050. Engine Use Case: Payload (Main Propulsion)
  1051. Tank repressurisation Method: Autogenous
  1052. Nozzle Cooling Mechanism: Dump Cooling
  1053. Engine Throttle Range: Not Throttleable
  1054.  
  1055.  
  1056. Engine Designation: LM10-348z "Federation"
  1057. Fuel Flow Cycle: Monopropellant (Cold Gas)
  1058. Propellant(Remass): Helium (He)
  1059. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1060. Engine Use Case: Payload (Vernier)
  1061. Altitude Of Operation: 80 km+ (Vacuum)
  1062. Nozzle Cooling Mechanism: Ablative Cooling
  1063.  
  1064.  
  1065. Engine Designation: CE-304 "Sokol"
  1066. Fuel Flow Cycle: Electric Pump Fed
  1067. Engine Oxidizer: AK20F: 80% HNO3 + 20% N2O4 (Nitric Acid)
  1068. Engine Fuel: N2H4 (Hydrazine)
  1069. Average Mixture Ratio: 1.28
  1070. Propellant properties: Hypergolic but not cryogenic
  1071. Altitude Of Operation: 30-80 km (High Atmosphere)
  1072. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1073. Exhaust Nozzle Area Ratio: 49:1
  1074. Characteristic Exhaust Velocity: 2,702 m/s
  1075. Adiabatic Combustion Temperature: 2,932°K
  1076. Engine Gimbal Range: ±1°
  1077. Engine Injector Design: Liquid Showerhead Injector
  1078. Engine chamber configuration: Single Chamber
  1079. Engine Use Case: Upper Stage(Main Propulsion)
  1080. Tank repressurisation Method: Inert Gas
  1081. Nozzle Cooling Mechanism: Film Cooling
  1082. Engine Throttle Range: Not Throttleable
  1083.  
  1084.  
  1085. Engine Designation: AR-269w "Kvant"
  1086. Fuel Flow Cycle: Gas Generator
  1087. Engine Oxidizer: H2O2 (Hydrogen Peroxide) 85%
  1088. Engine Fuel: 50% CH6N2 + 50% N2H4 (Aerosine-50)
  1089. Average Mixture Ratio: 3.39
  1090. Propellant properties: Neither Hypergolic nor cryogenic
  1091. Altitude Of Operation: 30-80 km (High Atmosphere)
  1092. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1093. Exhaust Nozzle Area Ratio: 48:1
  1094. Characteristic Exhaust Velocity: 2,604 m/s
  1095. Adiabatic Combustion Temperature: 2,668°K
  1096. Engine Gimbal Range: ±8°
  1097. Engine Injector Design: Gas Cross-impinging Injector
  1098. Engine chamber configuration: Single Chamber
  1099. Engine Use Case:
  1100. Tank repressurisation Method: Inert Gas
  1101. Nozzle Cooling Mechanism: Fuel Regenerative Cooling
  1102. Engine Throttle Range: Not Throttleable
  1103.  
  1104.  
  1105. Engine Designation: BADR-888 "Epsilon"
  1106. Fuel Flow Cycle: Expander (Open/Bleed)
  1107. Engine Oxidizer: F2 (Fluorine)
  1108. Engine Fuel: NH3 (Ammonia)
  1109. Average Mixture Ratio: 2.81
  1110. Propellant properties: Hypergolic and cryogenic
  1111. Altitude Of Operation: Any Altitude (0-80 km+)
  1112. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  1113. Exhaust Nozzle Area Ratio: 13:1
  1114. Characteristic Exhaust Velocity: 3,278 m/s
  1115. Adiabatic Combustion Temperature: 4,469°K
  1116. Engine Gimbal Range: ±9°
  1117. Engine Injector Design: Gas Showerhead Injector
  1118. Engine chamber configuration: Single Chamber
  1119. Engine Use Case: Lower Stage (Main Propulsion)
  1120. Tank repressurisation Method: Autogenous
  1121. Nozzle Cooling Mechanism: Ablative Cooling
  1122. Engine Throttle Range: Not Throttleable
  1123.  
  1124.  
  1125. Engine Designation: DC-214Y "Pamir"
  1126. Fuel Flow Cycle: Full Flow Staged
  1127. Engine Oxidizer: AK27I: 73% HNO3 + 27% N2O4 (Nitric Acid)
  1128. Engine Fuel: H2 (Hydrogen)
  1129. Average Mixture Ratio: 8.0
  1130. Propellant properties: Not Hypergolic but cryogenic
  1131. Altitude Of Operation: 30-80 km (High Atmosphere)
  1132. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1133. Exhaust Nozzle Area Ratio: 51:1
  1134. Characteristic Exhaust Velocity: 3,112 m/s
  1135. Adiabatic Combustion Temperature: 2,795°K
  1136. Engine Gimbal Range: ±4°
  1137. Engine Injector Design: Liquid Pintle Injector
  1138. Engine chamber configuration: Dual Chamber
  1139. Engine Use Case: Upper Stage (Main Propulsion)
  1140. Tank repressurisation Method: Inert Gas
  1141. Nozzle Cooling Mechanism: Transpiration Cooling
  1142. Engine Throttle Range: Not Throttleable
  1143.  
  1144.  
  1145. Engine Designation: BADR-61N "Reflektor"
  1146. Fuel Flow Cycle: Full Flow Staged
  1147. Engine Oxidizer: AK27P: 73% HNO3 + 27% N2O4 (Nitric Acid)
  1148. Engine Fuel: C2H5OH(Ethanol) 95%
  1149. Average Mixture Ratio: 2.75
  1150. Propellant properties: Not Hypergolic but cryogenic
  1151. Altitude Of Operation: Any Altitude (0-80 km+)
  1152. Exhaust Nozzle Geometry: Linear Aerospike Nozzle
  1153. Exhaust Nozzle Area Ratio: None
  1154. Characteristic Exhaust Velocity: 2,449 m/s
  1155. Adiabatic Combustion Temperature: 2,905°K
  1156. Engine Gimbal Range: ±8°
  1157. Engine Injector Design: Gas Swirl Injector
  1158. Engine chamber configuration: Single Chamber
  1159. Engine Use Case: Payload (Main Propulsion)
  1160. Tank repressurisation Method: Autogenous
  1161. Nozzle Cooling Mechanism: Fuel Regenerative Cooling
  1162. Engine Throttle Range: 59-105%
  1163.  
  1164.  
  1165. Engine Designation: FWR-145t "Oplot"
  1166. Fuel Flow Cycle: MagnetoPlasmaDynamic Thruster
  1167. Propellant(Remass): H2 (Hydrogen)
  1168. Exhaust Nozzle Geometry: Cathode Plug Magnetic Confinement Nozzle
  1169. Engine Use Case: Payload (Main Propulsion)
  1170. Altitude Of Operation: 80 km+ (Vacuum)
  1171. Engine Power Source: Nuclear Fusion Reactor
  1172. Rated Power Level: 60 kW
  1173.  
  1174.  
  1175. Engine Designation: KDU-957A "Oplot"
  1176. Fuel Flow Cycle: Gas Generator
  1177. Engine Oxidizer: O2 (Oxygen)
  1178. Engine Fuel: CH4 (Methane)
  1179. Average Mixture Ratio: 2.77
  1180. Propellant properties: Not Hypergolic but cryogenic
  1181. Altitude Of Operation: 80 km+ (Vacuum)
  1182. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1183. Exhaust Nozzle Area Ratio: 156:1
  1184. Characteristic Exhaust Velocity: 2,932 m/s
  1185. Adiabatic Combustion Temperature: 3,379°K
  1186. Engine Gimbal Range: None
  1187. Engine Injector Design: Liquid Self-impinging Injector
  1188. Engine chamber configuration: Single Chamber
  1189. Engine Use Case: Upper Stage (Main Propulsion)
  1190. Tank repressurisation Method: Inert Gas
  1191. Nozzle Cooling Mechanism: Film Cooling
  1192. Engine Throttle Range: Not Throttleable
  1193.  
  1194.  
  1195. Engine Designation: X-869B "Sturt"
  1196. Fuel Flow Cycle: Full Flow Staged
  1197. Engine Oxidizer: AK20K: 80% HNO3 + 20% N2O4 (Nitric Acid)
  1198. Engine Fuel: C2H5OH(Ethanol) 95%
  1199. Average Mixture Ratio: 2.75
  1200. Propellant properties: Not Hypergolic but cryogenic
  1201. Altitude Of Operation: 80 km+ (Vacuum)
  1202. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1203. Exhaust Nozzle Area Ratio: 137:1
  1204. Characteristic Exhaust Velocity: 2,449 m/s
  1205. Adiabatic Combustion Temperature: 2,905°K
  1206. Engine Gimbal Range: None
  1207. Engine Injector Design: Liquid Self-impinging Injector
  1208. Engine chamber configuration: Single Chamber
  1209. Engine Use Case: Upper Stage (Main Propulsion)
  1210. Tank repressurisation Method: Autogenous
  1211. Nozzle Cooling Mechanism: Dump Cooling
  1212. Engine Throttle Range: 87-109%
  1213.  
  1214.  
  1215. Engine Designation: FWR-590P "Altair"
  1216. Fuel Flow Cycle: Monopropellant (Decomposition)
  1217. Propellant(Remass): 65% NH4N(NO2)2 (Ammonium Dinitramide) + 35% CH3OH(Methanol)
  1218. Exhaust Nozzle Geometry: Conical Nozzle
  1219. Engine Use Case: Upper Stage(Vernier)
  1220. Altitude Of Operation: 80 km+ (Vacuum)
  1221. Nozzle Cooling Mechanism: Radiative Cooling
  1222. Engine catalyst: Iridium coated Alumina Pellets
  1223.  
  1224.  
  1225. Engine Designation: BADR-713P "Reliant"
  1226. Fuel Flow Cycle: Hall Effect Thruster
  1227. Propellant(Remass): Xe (Xenon)
  1228. Exhaust Nozzle Geometry: Hall Effect Thruster Nozzle
  1229. Engine Use Case: Payload (Main Propulsion)
  1230. Altitude Of Operation: 80 km+ (Vacuum)
  1231. Engine Power Source: Radioisotope Thermoelectric Generator (RTG)
  1232. Rated Power Level: 330 kW
  1233.  
  1234.  
  1235. Engine Designation: RM-17D "Kazbek"
  1236. Fuel Flow Cycle: Staged Combustion (Oxidizer Rich)
  1237. Engine Oxidizer: O3 (Ozone)
  1238. Engine Fuel: C6H5NH2 (Aniline)
  1239. Average Mixture Ratio: -1.0
  1240. Propellant properties: Hypergolic and cryogenic
  1241. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  1242. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1243. Exhaust Nozzle Area Ratio: 37:1
  1244. Characteristic Exhaust Velocity: -1 m/s
  1245. Adiabatic Combustion Temperature: -1°K
  1246. Engine Gimbal Range: ±7°
  1247. Engine Injector Design: Liquid Swirl Injector
  1248. Engine chamber configuration: Dual Chamber
  1249. Engine Use Case: Lower Stage (Main Propulsion)
  1250. Tank repressurisation Method: Autogenous
  1251. Nozzle Cooling Mechanism: Radiative Cooling
  1252. Engine Throttle Range: 18-109%
  1253.  
  1254.  
  1255. Engine Designation: BE-146b "Olympia"
  1256. Fuel Flow Cycle: Pressure-Fed
  1257. Engine Oxidizer: AK27P: 73% HNO3 + 27% N2O4 (Nitric Acid)
  1258. Engine Fuel: CH3OH (Methanol)
  1259. Average Mixture Ratio: 2.13
  1260. Propellant properties: Not Hypergolic but cryogenic
  1261. Altitude Of Operation: 80 km+ (Vacuum)
  1262. Exhaust Nozzle Geometry: Expanding Nozzle
  1263. Exhaust Nozzle Area Ratio: 120:1
  1264. Characteristic Exhaust Velocity: 2,441 m/s
  1265. Adiabatic Combustion Temperature: 2,824°K
  1266. Engine Gimbal Range: None
  1267. Engine Injector Design: Liquid Showerhead Injector
  1268. Engine chamber configuration: Single Chamber
  1269. Engine Use Case: Upper Stage (Main Propulsion)
  1270. Tank repressurisation Method: Autogenous
  1271. Nozzle Cooling Mechanism: Film Cooling
  1272. Engine Throttle Range: Not Throttleable
  1273.  
  1274.  
  1275. Engine Designation: B-379Q "Veter"
  1276. Fuel Flow Cycle: Staged Combustion (Fuel Rich)
  1277. Engine Oxidizer: F2 (Fluorine) + O2 (Oxygen)
  1278. Engine Fuel: H2 (Hydrogen)
  1279. Average Mixture Ratio: -1.0
  1280. Propellant properties: Hypergolic and cryogenic
  1281. Altitude Of Operation: 0-20 km (Sea Level)
  1282. Exhaust Nozzle Geometry: Conical Nozzle
  1283. Exhaust Nozzle Area Ratio: 15:1
  1284. Characteristic Exhaust Velocity: -1 m/s
  1285. Adiabatic Combustion Temperature: -1°K
  1286. Engine Gimbal Range: ±7°
  1287. Engine Injector Design: Liquid Pintle Injector
  1288. Engine chamber configuration: Single Chamber
  1289. Engine Use Case: Payload (Main Propulsion)
  1290. Tank repressurisation Method: Autogenous
  1291. Nozzle Cooling Mechanism: Radiative Cooling
  1292. Engine Throttle Range: Not Throttleable
  1293.  
  1294.  
  1295. Engine Designation: DST-982W "Rotifera
  1296. Fuel Flow Cycle: Variable Specific Impulse Magnetoplasma Rocket (VASIMR)
  1297. Propellant(Remass): Kr (Krypton)
  1298. Exhaust Nozzle Geometry: VASIMR Magnetic Confinement Nozzle
  1299. Engine Use Case: Space Tug (Main Propulsion)
  1300. Altitude Of Operation: 80 km+ (Vacuum)
  1301. Engine Power Source: Hydrogen Fuel cell
  1302. Rated Power Level: 470 kW
  1303.  
  1304.  
  1305. Engine Designation: XLR-704 "Aves"
  1306. Fuel Flow Cycle: Dual Expander (Open/Bleed)
  1307. Engine Oxidizer: F2 (Fluorine) + O2 (Oxygen)
  1308. Engine Fuel: H2 (Hydrogen)
  1309. Average Mixture Ratio: -1.0
  1310. Propellant properties: Hypergolic and cryogenic
  1311. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  1312. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1313. Exhaust Nozzle Area Ratio: 37:1
  1314. Characteristic Exhaust Velocity: -1 m/s
  1315. Adiabatic Combustion Temperature: -1°K
  1316. Engine Gimbal Range: ±9°
  1317. Engine Injector Design: Gas Self-impinging Injector
  1318. Engine chamber configuration: Dual Chamber
  1319. Engine Use Case: Lower Stage (Course Correction)
  1320. Tank repressurisation Method: Inert Gas
  1321. Nozzle Cooling Mechanism: Film Cooling
  1322. Engine Throttle Range: Not Throttleable
  1323.  
  1324.  
  1325. Engine Designation: TYS-396x "Impuls"
  1326. Fuel Flow Cycle: Expander (Open/Bleed)
  1327. Engine Oxidizer: F2 (Fluorine) + O2 (Oxygen)
  1328. Engine Fuel: C12H26 (n-Dodecane)
  1329. Average Mixture Ratio: 3.67
  1330. Propellant properties: Hypergolic and cryogenic
  1331. Altitude Of Operation: Any Altitude (0-80 km+)
  1332. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  1333. Exhaust Nozzle Area Ratio: 12:1
  1334. Characteristic Exhaust Velocity: 3,166 m/s
  1335. Adiabatic Combustion Temperature: 4,571°K
  1336. Engine Gimbal Range: ±9°
  1337. Engine Injector Design: Gas Pintle Injector
  1338. Engine chamber configuration: Single Chamber
  1339. Engine Use Case: Upper Stage(Main Propulsion)
  1340. Tank repressurisation Method: Inert Gas
  1341. Nozzle Cooling Mechanism: Radiative Cooling
  1342. Engine Throttle Range: Not Throttleable
  1343.  
  1344.  
  1345. Engine Designation: RS-750I "Perseus"
  1346. Fuel Flow Cycle: Gridded Ion Thruster
  1347. Propellant(Remass): Xe (Xenon)
  1348. Exhaust Nozzle Geometry: Electrostatic Ion Nozzle
  1349. Engine Use Case: Payload (Main Propulsion)
  1350. Altitude Of Operation: 80 km+ (Vacuum)
  1351. Engine Power Source: Hydrogen Fuel cell
  1352. Rated Power Level: 690 kW
  1353.  
  1354.  
  1355. Engine Designation: GE-777Q "Daedlus"
  1356. Fuel Flow Cycle: Hall Effect Thruster
  1357. Propellant(Remass): Bi (Bismuth)
  1358. Exhaust Nozzle Geometry: Hall Effect Thruster Nozzle
  1359. Engine Use Case: Payload (Main Propulsion)
  1360. Altitude Of Operation: 80 km+ (Vacuum)
  1361. Engine Power Source: Photovoltaic Panel
  1362. Rated Power Level: 60 kW
  1363.  
  1364.  
  1365. Engine Designation: XS-573Z "Rosetta"
  1366. Fuel Flow Cycle: MagnetoPlasmaDynamic Thruster
  1367. Propellant(Remass): Li (Lithium)
  1368. Exhaust Nozzle Geometry: Cathode Plug Magnetic Confinement Nozzle
  1369. Engine Use Case: Space Tug (Main Propulsion)
  1370. Altitude Of Operation: 80 km+ (Vacuum)
  1371. Engine Power Source: Photovoltaic Panel
  1372. Rated Power Level: 150 kW
  1373.  
  1374.  
  1375. Engine Designation: RT-671z "Visionalis"
  1376. Fuel Flow Cycle: Staged Combustion (Fuel Rich)
  1377. Engine Oxidizer: O3 (Ozone)
  1378. Engine Fuel: H2 (Hydrogen)
  1379. Average Mixture Ratio: -1.0
  1380. Propellant properties: Hypergolic and cryogenic
  1381. Altitude Of Operation: 80 km+ (Vacuum)
  1382. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1383. Exhaust Nozzle Area Ratio: 126:1
  1384. Characteristic Exhaust Velocity: -1 m/s
  1385. Adiabatic Combustion Temperature: -1°K
  1386. Engine Gimbal Range: None
  1387. Engine Injector Design: Liquid Pintle Injector
  1388. Engine chamber configuration: Dual Chamber
  1389. Engine Use Case: Upper Stage (Main Propulsion)
  1390. Tank repressurisation Method: Autogenous
  1391. Nozzle Cooling Mechanism: Film Cooling
  1392. Engine Throttle Range: 66-100%
  1393.  
  1394.  
  1395. Engine Designation: HM-183t "Irtysh"
  1396. Fuel Flow Cycle: Colloid Thruster
  1397. Propellant(Remass): NH2OH+NO3 (Hydroxylammonium nitrate)
  1398. Exhaust Nozzle Geometry: Capillary Emitter-Electrode Cone
  1399. Engine Use Case: Payload (Main Propulsion)
  1400. Altitude Of Operation: 80 km+ (Vacuum)
  1401. Engine Power Source: Radioisotope Thermoelectric Generator (RTG)
  1402. Rated Power Level: 480 kW
  1403.  
  1404.  
  1405. Engine Designation: RT-984 "Vector"
  1406. Fuel Flow Cycle: Liquid Core
  1407. Propellant(Remass): Uranium impregnated Tantalum and Nitrogen (N2)
  1408. Propellant State: Cryogenic Liquid
  1409. Reactor Generation: Generation IV
  1410. Reactor Fuel Material: 63% Uranium-235
  1411. Engine Exhaust velocity: 4,725 m/s
  1412. Reactor Core Temperature: 4,515 °K
  1413. Reactor Coolant: Nitrogen (N2)
  1414. Engine Bimodality: Engine is bimodal
  1415. Engine Electrical Output: 813 MW
  1416. Altitude Of Operation: 80 km+ (Vacuum)
  1417. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1418. Exhaust Nozzle Area Ratio: 194:1
  1419. Exhaust Nozzle Cooling Mechanism: Radiative Cooling
  1420. Engine Use Case: Upper Stage(Main Propulsion)
  1421. Tank repressurisation Method: Inert Gas
  1422.  
  1423.  
  1424. Engine Designation: DC-544 "Oko"
  1425. Fuel Flow Cycle: Staged Combustion (Fuel Rich)
  1426. Engine Oxidizer: F2 (Fluorine) + O2 (Oxygen)
  1427. Engine Fuel: H2 (Hydrogen)
  1428. Average Mixture Ratio: -1.0
  1429. Propellant properties: Hypergolic and cryogenic
  1430. Altitude Of Operation: 30-80 km (High Atmosphere)
  1431. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1432. Exhaust Nozzle Area Ratio: 87:1
  1433. Characteristic Exhaust Velocity: -1 m/s
  1434. Adiabatic Combustion Temperature: -1°K
  1435. Engine Gimbal Range: ±9°
  1436. Engine Injector Design: Liquid Pintle Injector
  1437. Engine chamber configuration: Single Chamber
  1438. Engine Use Case: Upper Stage (Main Propulsion)
  1439. Tank repressurisation Method: Inert Gas
  1440. Nozzle Cooling Mechanism: Dump Cooling
  1441. Engine Throttle Range: Not Throttleable
  1442.  
  1443.  
  1444. Engine Designation: A-718H "Fregat"
  1445. Fuel Flow Cycle: Monopropellant (Decomposition)
  1446. Propellant(Remass): N2H4 (Hydrazine)
  1447. Exhaust Nozzle Geometry: Conical Nozzle
  1448. Engine Use Case: Upper Stage(Vernier)
  1449. Altitude Of Operation: 80 km+ (Vacuum)
  1450. Nozzle Cooling Mechanism: Ablative Cooling
  1451. Engine catalyst: Iridium coated Alumina Pellets
  1452.  
  1453.  
  1454. Engine Designation: H-241N "Antares"
  1455. Fuel Flow Cycle: Nuclear SaltWater
  1456. Propellant(Remass): Plutonium(III) TriBromide (PuBr3) + Water (H2O)
  1457. Propellant State: Aqueous
  1458. Reactor Generation: Engine has no reactor
  1459. Reactor Fuel Material: 90% Plutonium
  1460. Engine Exhaust velocity: 4,725,716 m/s
  1461. Reactor Core Temperature: 127,636 °K
  1462. Reactor Coolant: Water (H2O)
  1463. Engine Bimodality: Engine isn't bimodal
  1464. Engine Electrical Output: None
  1465. Altitude Of Operation: 80 km+ (Vacuum)
  1466. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  1467. Exhaust Nozzle Area Ratio: 147:1
  1468. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  1469. Engine Use Case: Upper Stage(Main Propulsion)
  1470. Tank repressurisation Method: Inert Gas
  1471.  
  1472.  
  1473. Engine Designation: S.10-24 "Pamir"
  1474. Fuel Flow Cycle: Gas Core
  1475. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Carbon Monoxide (CO)
  1476. Propellant State: Cryogenic Liquid
  1477. Reactor Generation: Generation III+
  1478. Reactor Fuel Material: 93% Uranium-235
  1479. Engine Exhaust velocity: 3,478 m/s
  1480. Reactor Core Temperature: 14,300 °K
  1481. Reactor Coolant: Carbon Monoxide (CO)
  1482. Engine Bimodality: Engine is bimodal
  1483. Engine Electrical Output: 2,574 MW
  1484. Altitude Of Operation: 80 km+ (Vacuum)
  1485. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  1486. Exhaust Nozzle Area Ratio: 124:1
  1487. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  1488. Engine Use Case: Upper Stage(Main Propulsion)
  1489. Tank repressurisation Method: Inert Gas
  1490.  
  1491.  
  1492. Engine Designation: V-84l "Perseverence"
  1493. Fuel Flow Cycle: Droplet Core
  1494. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Carbon Monoxide (CO)
  1495. Propellant State: Cryogenic Liquid
  1496. Reactor Generation: Generation II
  1497. Reactor Fuel Material: 94% Uranium-235
  1498. Engine Exhaust velocity: 4,720 m/s
  1499. Reactor Core Temperature: 6,825 °K
  1500. Reactor Coolant: Carbon Monoxide (CO)
  1501. Engine Bimodality: Engine is bimodal
  1502. Engine Electrical Output: 1,228 MW
  1503. Altitude Of Operation: 80 km+ (Vacuum)
  1504. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  1505. Exhaust Nozzle Area Ratio: 195:1
  1506. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  1507. Engine Use Case: Upper Stage(Main Propulsion)
  1508. Tank repressurisation Method: Inert Gas
  1509.  
  1510.  
  1511. Engine Designation: LMP-926N "Sputnik"
  1512. Fuel Flow Cycle:  Vapor Core
  1513. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Carbon Dioxide (CO2)
  1514. Propellant State: Cryogenic Liquid
  1515. Reactor Generation: Generation III+
  1516. Reactor Fuel Material: 93% Uranium-235
  1517. Engine Exhaust velocity: 8,683 m/s
  1518. Reactor Core Temperature: 6,209 °K
  1519. Reactor Coolant: Carbon Dioxide (CO2)
  1520. Engine Bimodality: Engine is bimodal
  1521. Engine Electrical Output: 1,118 MW
  1522. Altitude Of Operation: 80 km+ (Vacuum)
  1523. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  1524. Exhaust Nozzle Area Ratio: 107:1
  1525. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  1526. Engine Use Case: Upper Stage(Main Propulsion)
  1527. Tank repressurisation Method: Autogenous
  1528.  
  1529.  
  1530. Engine Designation: P-357K "Polyot"
  1531. Fuel Flow Cycle: Combustion Tap Off
  1532. Engine Oxidizer: O3 (Ozone)
  1533. Engine Fuel: C2H5OH(Ethanol) 95%
  1534. Average Mixture Ratio: -1.0
  1535. Propellant properties: Hypergolic and cryogenic
  1536. Altitude Of Operation: 80 km+ (Vacuum)
  1537. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1538. Exhaust Nozzle Area Ratio: 188:1
  1539. Characteristic Exhaust Velocity: -1 m/s
  1540. Adiabatic Combustion Temperature: -1°K
  1541. Engine Gimbal Range: None
  1542. Engine Injector Design: Liquid Showerhead Injector
  1543. Engine chamber configuration: Dual Chamber
  1544. Engine Use Case: Upper Stage (Main Propulsion)
  1545. Tank repressurisation Method: Autogenous
  1546. Nozzle Cooling Mechanism: Dump Cooling
  1547. Engine Throttle Range: Not Throttleable
  1548.  
  1549.  
  1550. Engine Designation: LRE-865N "Valient"
  1551. Fuel Flow Cycle: Staged Combustion (Fuel Rich)
  1552. Engine Oxidizer: F2 (Fluorine)
  1553. Engine Fuel: N2H4 (Hydrazine)
  1554. Average Mixture Ratio: 1.82
  1555. Propellant properties: Hypergolic and cryogenic
  1556. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  1557. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  1558. Exhaust Nozzle Area Ratio: 45:1
  1559. Characteristic Exhaust Velocity: 3,315 m/s
  1560. Adiabatic Combustion Temperature: 4,544°K
  1561. Engine Gimbal Range: ±8°
  1562. Engine Injector Design: Liquid Cross-impinging Injector
  1563. Engine chamber configuration: Single Chamber
  1564. Engine Use Case: Lower Stage (Main Propulsion)
  1565. Tank repressurisation Method: Autogenous
  1566. Nozzle Cooling Mechanism: Radiative Cooling
  1567. Engine Throttle Range: Not Throttleable
  1568.  
  1569.  
  1570. Engine Designation: MJ-692a "Hera"
  1571. Fuel Flow Cycle: Expander (Open/Bleed)
  1572. Engine Oxidizer: O3 (Ozone)
  1573. Engine Fuel: CH3OH (Methanol)
  1574. Average Mixture Ratio: -1.0
  1575. Propellant properties: Hypergolic and cryogenic
  1576. Altitude Of Operation: 80 km+ (Vacuum)
  1577. Exhaust Nozzle Geometry: Expanding Nozzle
  1578. Exhaust Nozzle Area Ratio: 177:1
  1579. Characteristic Exhaust Velocity: -1 m/s
  1580. Adiabatic Combustion Temperature: -1°K
  1581. Engine Gimbal Range: None
  1582. Engine Injector Design: Gas Swirl Injector
  1583. Engine chamber configuration: Single Chamber
  1584. Engine Use Case: Upper Stage(Course Correction)
  1585. Tank repressurisation Method: Inert Gas
  1586. Nozzle Cooling Mechanism: Radiative Cooling
  1587. Engine Throttle Range: Not Throttleable
  1588.  
  1589.  
  1590. Engine Designation: PS-829U "Tarsier"
  1591. Fuel Flow Cycle: Variable Specific Impulse Magnetoplasma Rocket (VASIMR)
  1592. Propellant(Remass): Kr (Krypton)
  1593. Exhaust Nozzle Geometry: VASIMR Magnetic Confinement Nozzle
  1594. Engine Use Case: Space Tug (Main Propulsion)
  1595. Altitude Of Operation: 80 km+ (Vacuum)
  1596. Engine Power Source: Nuclear Fusion Reactor
  1597. Rated Power Level: 320 kW
  1598.  
  1599.  
  1600. Engine Designation: P-66b "Asimov"
  1601. Fuel Flow Cycle: Pressure-Fed
  1602. Engine Oxidizer: AK20K: 80% HNO3 + 20% N2O4 (Nitric Acid)
  1603. Engine Fuel: C2H5OH(Ethanol) 95%
  1604. Average Mixture Ratio: 2.75
  1605. Propellant properties: Not Hypergolic but cryogenic
  1606. Altitude Of Operation: 30-80 km (High Atmosphere)
  1607. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  1608. Exhaust Nozzle Area Ratio: 88:1
  1609. Characteristic Exhaust Velocity: 2,449 m/s
  1610. Adiabatic Combustion Temperature: 2,905°K
  1611. Engine Gimbal Range: ±3°
  1612. Engine Injector Design: Liquid Self-impinging Injector
  1613. Engine chamber configuration: Single Chamber
  1614. Engine Use Case: Upper Stage (Main Propulsion)
  1615. Tank repressurisation Method: Inert Gas
  1616. Nozzle Cooling Mechanism: Film Cooling
  1617. Engine Throttle Range: Not Throttleable
  1618.  
  1619.  
  1620. Engine Designation: CE-166Z "Luch"
  1621. Fuel Flow Cycle:  Solid Core
  1622. Propellant(Remass):
  1623. Propellant State: Cryogenic Liquid
  1624. Reactor Generation: Generation V
  1625. Reactor Fuel Material: 89% Uranium-235
  1626. Engine Exhaust velocity: 8,094 m/s
  1627. Reactor Core Temperature: 3,338 °K
  1628. Reactor Coolant: Nitrogen (N2)
  1629. Engine Bimodality: Engine is bimodal
  1630. Engine Electrical Output: 601 MW
  1631. Altitude Of Operation: 80 km+ (Vacuum)
  1632. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1633. Exhaust Nozzle Area Ratio: 184:1
  1634. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  1635. Engine Use Case: Space Tug (Main Propulsion)
  1636. Tank repressurisation Method: Autogenous
  1637.  
  1638.  
  1639. Engine Designation: UA-685n "Filosa"
  1640. Fuel Flow Cycle: Gas Core
  1641. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Carbon Dioxide (CO2)
  1642. Propellant State: Cryogenic Liquid
  1643. Reactor Generation: Generation V
  1644. Reactor Fuel Material: 93% Uranium-235
  1645. Engine Exhaust velocity: 4,914 m/s
  1646. Reactor Core Temperature: 14,272 °K
  1647. Reactor Coolant: Carbon Dioxide (CO2)
  1648. Engine Bimodality: Engine is bimodal
  1649. Engine Electrical Output: 2,569 MW
  1650. Altitude Of Operation: 80 km+ (Vacuum)
  1651. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  1652. Exhaust Nozzle Area Ratio: 152:1
  1653. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  1654. Engine Use Case: Upper Stage(Main Propulsion)
  1655. Tank repressurisation Method: Inert Gas
  1656.  
  1657.  
  1658. Engine Designation: A-391T "Oko"
  1659. Fuel Flow Cycle: Combustion Tap Off
  1660. Engine Oxidizer: F2 (Fluorine)
  1661. Engine Fuel: H2 (Hydrogen)
  1662. Average Mixture Ratio: 6.0
  1663. Propellant properties: Hypergolic and cryogenic
  1664. Altitude Of Operation: Any Altitude (0-80 km+)
  1665. Exhaust Nozzle Geometry: Toroidal Aerospike Nozzle
  1666. Exhaust Nozzle Area Ratio: None
  1667. Characteristic Exhaust Velocity: 3,925 m/s
  1668. Adiabatic Combustion Temperature: 3,689°K
  1669. Engine Gimbal Range: ±4°
  1670. Engine Injector Design: Liquid Showerhead Injector
  1671. Engine chamber configuration: Single Chamber
  1672. Engine Use Case: Lower Stage (Main Propulsion)
  1673. Tank repressurisation Method: Inert Gas
  1674. Nozzle Cooling Mechanism: Ablative Cooling
  1675. Engine Throttle Range: Not Throttleable
  1676.  
  1677.  
  1678. Engine Designation: F-237d "Tsyklon"
  1679. Fuel Flow Cycle: Variable Specific Impulse Magnetoplasma Rocket (VASIMR)
  1680. Propellant(Remass): Ar (Argon)
  1681. Exhaust Nozzle Geometry: VASIMR Magnetic Confinement Nozzle
  1682. Engine Use Case: Payload (Main Propulsion)
  1683. Altitude Of Operation: 80 km+ (Vacuum)
  1684. Engine Power Source: Photovoltaic Panel
  1685. Rated Power Level: 770 kW
  1686.  
  1687.  
  1688. Engine Designation: KDTU-263V "Philae"
  1689. Fuel Flow Cycle: Gas Core
  1690. Propellant(Remass): Uranium(VI) Fluoride (UF6) and Oxygen (O2)
  1691. Propellant State: Cryogenic Liquid
  1692. Reactor Generation: Generation IV
  1693. Reactor Fuel Material: 93% Uranium-235
  1694. Engine Exhaust velocity: 3,478 m/s
  1695. Reactor Core Temperature: 14,443 °K
  1696. Reactor Coolant: Oxygen (O2)
  1697. Engine Bimodality: Engine is bimodal
  1698. Engine Electrical Output: 2,600 MW
  1699. Altitude Of Operation: 80 km+ (Vacuum)
  1700. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  1701. Exhaust Nozzle Area Ratio: 181:1
  1702. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  1703. Engine Use Case: Payload (Main Propulsion)
  1704. Tank repressurisation Method: Inert Gas
  1705.  
  1706.  
  1707. Engine Designation: XLR-380F "Siluet"
  1708. Fuel Flow Cycle: Radioisotope Engine
  1709. Propellant(Remass): Water (H2O)
  1710. Propellant State: Cryogenic Liquid
  1711. Reactor Generation: Engine has no reactor
  1712. Reactor Fuel Material: Uranium-233
  1713. Engine Exhaust velocity: 9,124 m/s
  1714. Reactor Core Temperature: 2,165 °K
  1715. Reactor Coolant: Water (H2O)
  1716. Engine Bimodality: Engine is bimodal
  1717. Engine Electrical Output: 390 MW
  1718. Altitude Of Operation: 80 km+ (Vacuum)
  1719. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1720. Exhaust Nozzle Area Ratio: 174:1
  1721. Exhaust Nozzle Cooling Mechanism: Film Cooling
  1722. Engine Use Case: Upper Stage(Main Propulsion)
  1723. Tank repressurisation Method: Autogenous
  1724.  
  1725.  
  1726. Engine Designation: KMV-12l "Electron"
  1727. Fuel Flow Cycle: Radioisotope Engine
  1728. Propellant(Remass): Ammonia (NH3)
  1729. Propellant State: Cryogenic Liquid
  1730. Reactor Generation: Engine has no reactor
  1731. Reactor Fuel Material: Fermium-252
  1732. Engine Exhaust velocity: 5,751 m/s
  1733. Reactor Core Temperature: 2,186 °K
  1734. Reactor Coolant: Ammonia (NH3)
  1735. Engine Bimodality: Engine is bimodal
  1736. Engine Electrical Output: 393 MW
  1737. Altitude Of Operation: 80 km+ (Vacuum)
  1738. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  1739. Exhaust Nozzle Area Ratio: 105:1
  1740. Exhaust Nozzle Cooling Mechanism: Transpiration Cooling
  1741. Engine Use Case: Upper Stage(Main Propulsion)
  1742. Tank repressurisation Method: Inert Gas
  1743.  
  1744.  
  1745. Engine Designation: XS-777H "Stratus"
  1746. Fuel Flow Cycle: Expander (Closed)
  1747. Engine Oxidizer: O3 (Ozone)
  1748. Engine Fuel: C12H26 (n-Dodecane)
  1749. Average Mixture Ratio: -1.0
  1750. Propellant properties: Hypergolic and cryogenic
  1751. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  1752. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1753. Exhaust Nozzle Area Ratio: 32:1
  1754. Characteristic Exhaust Velocity: -1 m/s
  1755. Adiabatic Combustion Temperature: -1°K
  1756. Engine Gimbal Range: ±2°
  1757. Engine Injector Design: Gas Self-impinging Injector
  1758. Engine chamber configuration: Single Chamber
  1759. Engine Use Case: Lower Stage (Course Correction)
  1760. Tank repressurisation Method: Inert Gas
  1761. Nozzle Cooling Mechanism: Film Cooling
  1762. Engine Throttle Range: Not Throttleable
  1763.  
  1764.  
  1765. Engine Designation: PS-823J "Hephaestus"
  1766. Fuel Flow Cycle: Solid Core
  1767. Propellant(Remass):
  1768. Propellant State: Cryogenic Liquid
  1769. Reactor Generation: Generation V
  1770. Reactor Fuel Material: 57% Uranium-235
  1771. Engine Exhaust velocity: (12,950/~3850) m/s
  1772. Reactor Core Temperature: 3,135 °K
  1773. Reactor Coolant: Hydrogen (H2)
  1774. Engine Bimodality: Engine is bimodal
  1775. Engine Electrical Output: 564 MW
  1776. Altitude Of Operation: 80 km+ (Vacuum)
  1777. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1778. Exhaust Nozzle Area Ratio: 173:1
  1779. Exhaust Nozzle Cooling Mechanism: Dump Cooling
  1780. Engine Use Case: Payload (Main Propulsion)
  1781. Tank repressurisation Method: Inert Gas
  1782.  
  1783.  
  1784. Engine Designation: AJ-695Y "Voyager"
  1785. Fuel Flow Cycle: Monopropellant (Cold Gas)
  1786. Propellant(Remass): Carbon Dioxide (CO2)
  1787. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1788. Engine Use Case: Payload (Vernier)
  1789. Altitude Of Operation: 80 km+ (Vacuum)
  1790. Nozzle Cooling Mechanism: Ablative Cooling
  1791.  
  1792.  
  1793. Engine Designation: SOK-689W "Contour"
  1794. Fuel Flow Cycle: Solid Core
  1795. Propellant(Remass):
  1796. Propellant State: Cryogenic Liquid
  1797. Reactor Generation: Generation V+
  1798. Reactor Fuel Material: 66% Plutonium-238
  1799. Engine Exhaust velocity: 12,950 m/s
  1800. Reactor Core Temperature: 2,835 °K
  1801. Reactor Coolant: Nitrogen (N2)
  1802. Engine Bimodality: Engine is bimodal
  1803. Engine Electrical Output: 510 MW
  1804. Altitude Of Operation: 80 km+ (Vacuum)
  1805. Exhaust Nozzle Geometry: Magnetic Virtual Nozzle
  1806. Exhaust Nozzle Area Ratio: 198:1
  1807. Exhaust Nozzle Cooling Mechanism: Dump Cooling
  1808. Engine Use Case: Payload (Main Propulsion)
  1809. Tank repressurisation Method: Inert Gas
  1810.  
  1811.  
  1812. Engine Designation: BF-107u "Anapsida"
  1813. Fuel Flow Cycle: Hall Effect Thruster
  1814. Propellant(Remass): Zn (Zinc)
  1815. Exhaust Nozzle Geometry: Hall Effect Thruster Nozzle
  1816. Engine Use Case: Space Tug (Main Propulsion)
  1817. Altitude Of Operation: 80 km+ (Vacuum)
  1818. Engine Power Source: Photovoltaic Panel
  1819. Rated Power Level: 570 kW
  1820.  
  1821.  
  1822. Engine Designation: E-654U "Ceres"
  1823. Fuel Flow Cycle: Full Flow Staged
  1824. Engine Oxidizer: AK27P: 73% HNO3 + 27% N2O4 (Nitric Acid)
  1825. Engine Fuel: CH6N2 (MonomethylHydrazine)
  1826. Average Mixture Ratio: 2.13
  1827. Propellant properties: Hypergolic but not cryogenic
  1828. Altitude Of Operation: 80 km+ (Vacuum)
  1829. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1830. Exhaust Nozzle Area Ratio: 193:1
  1831. Characteristic Exhaust Velocity: 2,635 m/s
  1832. Adiabatic Combustion Temperature: 3,033°K
  1833. Engine Gimbal Range: None
  1834. Engine Injector Design: Liquid Pintle Injector
  1835. Engine chamber configuration: Single Chamber
  1836. Engine Use Case: Space Tug (Main Propulsion)
  1837. Tank repressurisation Method: Inert Gas
  1838. Nozzle Cooling Mechanism: Transpiration Cooling
  1839. Engine Throttle Range: Not Throttleable
  1840.  
  1841.  
  1842. Engine Designation: X-642W "Star"
  1843. Fuel Flow Cycle: Colloid Thruster
  1844. Propellant(Remass): NH2OH+NO3 (Hydroxylammonium nitrate)
  1845. Exhaust Nozzle Geometry: Capillary Emitter-Electrode Cone
  1846. Engine Use Case: Space Tug (Main Propulsion)
  1847. Altitude Of Operation: 80 km+ (Vacuum)
  1848. Engine Power Source: Radioisotope Thermoelectric Generator (RTG)
  1849. Rated Power Level: 670 kW
  1850.  
  1851.  
  1852. Engine Designation: AJ-698d "Aeonian"
  1853. Fuel Flow Cycle: Electric Pump Fed
  1854. Engine Oxidizer: H2O2 (Hydrogen Peroxide) 85%
  1855. Engine Fuel: CH3OH (Methanol)
  1856. Average Mixture Ratio: 3.55
  1857. Propellant properties: Not Hypergolic but cryogenic
  1858. Altitude Of Operation: 0-20 km (Sea Level)
  1859. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1860. Exhaust Nozzle Area Ratio: 11:1
  1861. Characteristic Exhaust Velocity: 2,464 m/s
  1862. Adiabatic Combustion Temperature: 2,511°K
  1863. Engine Gimbal Range: ±4°
  1864. Engine Injector Design: Liquid Self-impinging Injector
  1865. Engine chamber configuration: Dual Chamber
  1866. Engine Use Case: Lower Stage (Main Propulsion)
  1867. Tank repressurisation Method: Inert Gas
  1868. Nozzle Cooling Mechanism: Film Cooling
  1869. Engine Throttle Range: Not Throttleable
  1870.  
  1871.  
  1872. Engine Designation: DOK-530Z "Liberty"
  1873. Fuel Flow Cycle: Combustion Tap Off
  1874. Engine Oxidizer: O2 (Oxygen)
  1875. Engine Fuel: NH3 (Ammonia)
  1876. Average Mixture Ratio: 1.28
  1877. Propellant properties: Not Hypergolic but cryogenic
  1878. Altitude Of Operation: 80 km+ (Vacuum)
  1879. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1880. Exhaust Nozzle Area Ratio: 174:1
  1881. Characteristic Exhaust Velocity: 2,815 m/s
  1882. Adiabatic Combustion Temperature: 3,020°K
  1883. Engine Gimbal Range: None
  1884. Engine Injector Design: Liquid Pintle Injector
  1885. Engine chamber configuration: Dual Chamber
  1886. Engine Use Case: Upper Stage (Main Propulsion)
  1887. Tank repressurisation Method: Inert Gas
  1888. Nozzle Cooling Mechanism: Radiative Cooling
  1889. Engine Throttle Range: Not Throttleable
  1890.  
  1891.  
  1892. Engine Designation: KRD-192 "Agat"
  1893. Fuel Flow Cycle: Pressure-Fed
  1894. Engine Oxidizer: F2 (Fluorine) + O2 (Oxygen)
  1895. Engine Fuel: C12H26 (n-Dodecane)
  1896. Average Mixture Ratio: 3.67
  1897. Propellant properties: Hypergolic and cryogenic
  1898. Altitude Of Operation: 20-30 km (Medium Atmosphere)
  1899. Exhaust Nozzle Geometry: Stepped Dual Bell Nozzle
  1900. Exhaust Nozzle Area Ratio: 45:1
  1901. Characteristic Exhaust Velocity: 3,166 m/s
  1902. Adiabatic Combustion Temperature: 4,571°K
  1903. Engine Gimbal Range: ±5°
  1904. Engine Injector Design: Liquid Self-impinging Injector
  1905. Engine chamber configuration: Single Chamber
  1906. Engine Use Case: Lower Stage (Course Correction)
  1907. Tank repressurisation Method: Inert Gas
  1908. Nozzle Cooling Mechanism: Dump Cooling
  1909. Engine Throttle Range: Not Throttleable
  1910.  
  1911.  
  1912. Engine Designation: DST-499f "Discoverer"
  1913. Fuel Flow Cycle:  Solid Core
  1914. Propellant(Remass):
  1915. Propellant State: Cryogenic Liquid
  1916. Reactor Generation: Generation IV
  1917. Reactor Fuel Material: 52% Plutonium-238
  1918. Engine Exhaust velocity: 2,524 m/s
  1919. Reactor Core Temperature: 2,736 °K
  1920. Reactor Coolant: Water (H2O)
  1921. Engine Bimodality: Engine isn't bimodal
  1922. Engine Electrical Output: None
  1923. Altitude Of Operation: 80 km+ (Vacuum)
  1924. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1925. Exhaust Nozzle Area Ratio: 176:1
  1926. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  1927. Engine Use Case: Space Tug (Main Propulsion)
  1928. Tank repressurisation Method: Inert Gas
  1929.  
  1930.  
  1931. Engine Designation: DE-666t "Heliozoa"
  1932. Fuel Flow Cycle: Staged Combustion (Oxidizer Rich)
  1933. Engine Oxidizer: N2O4 (Nitrogen Tetroxide)
  1934. Engine Fuel: 75% CH6N2 + 25% N2H4 (UH-25)
  1935. Average Mixture Ratio: 1.85
  1936. Propellant properties: Hypergolic but not cryogenic
  1937. Altitude Of Operation: 80 km+ (Vacuum)
  1938. Exhaust Nozzle Geometry: Contour Bell Nozzle
  1939. Exhaust Nozzle Area Ratio: 175:1
  1940. Characteristic Exhaust Velocity: 2,730 m/s
  1941. Adiabatic Combustion Temperature: 3,268°K
  1942. Engine Gimbal Range: None
  1943. Engine Injector Design: Liquid Pintle Injector
  1944. Engine chamber configuration: Dual Chamber
  1945. Engine Use Case: Upper Stage(Main Propulsion)
  1946. Tank repressurisation Method: Autogenous
  1947. Nozzle Cooling Mechanism: Film Cooling
  1948. Engine Throttle Range: Not Throttleable
  1949.  
  1950.  
  1951. Engine Designation: DST-996F "Kolibr"
  1952. Fuel Flow Cycle: Nuclear SaltWater
  1953. Propellant(Remass): Plutonium(III) TriBromide (PuBr3) + Water (H2O)
  1954. Propellant State: Aqueous
  1955. Reactor Generation: Engine has no reactor
  1956. Reactor Fuel Material: 90% Plutonium
  1957. Engine Exhaust velocity: 4,725,442 m/s
  1958. Reactor Core Temperature: 127,716 °K
  1959. Reactor Coolant: Water (H2O)
  1960. Engine Bimodality: Engine isn't bimodal
  1961. Engine Electrical Output: None
  1962. Altitude Of Operation: 80 km+ (Vacuum)
  1963. Exhaust Nozzle Geometry: Parabolic Bell Nozzle
  1964. Exhaust Nozzle Area Ratio: 170:1
  1965. Exhaust Nozzle Cooling Mechanism: Regenerative Cooling
  1966. Engine Use Case: Upper Stage(Main Propulsion)
  1967. Tank repressurisation Method: Inert Gas
  1968.  
  1969.  
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