11D428
Country of origin | Russia |
---|---|
Date | 1993–1997 |
First flight | 1997-10-05 (Progress M-36) |
Designer | NIIMash |
Application | RCSthruster |
Predecessor | 11D428A |
Successor | 11D428AF-16 |
Status | In Production |
Liquid-fuel engine | |
Propellant | N2O4/UDMH |
Mixture ratio | 1.85±0.15 |
Cycle | pressure fed |
Configuration | |
Chamber | 1 |
Performance | |
Thrust, vacuum | 129.16 N (29.04 lbf) |
Chamberpressure | 0.88 MPa (128 psi) |
Specific impulse,vacuum | 291 s (2.85 km/s) |
Restarts | 500,000 |
Dimensions | |
Dry mass | 1.5 kg (3.3 lb) |
Used in | |
SoyuzsinceSoyuz TM-28andProgresssinceProgress M-36 | |
References | |
References | [1][2][3] |
The11D428A-16(manufacturer's nameRDMT-135M) is aliquidpressure-fedrocket engineburningN2O4/UDMHwith anO/Fof 1.85. It is used for crew-ratedspacecraft propulsionapplications. It is currently used in theKTDU-80spacecraft propulsion module. The previous version, the11D428A(manufacturer's nameRDMT-135) is still used as thereaction control systemthrusters of theZvezdaISSmodule. The 11D428A-16 generates 129.16 N (29.04 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and achieves aspecific impulseof 291 s (2.85 km/s). It is rated for 500,000 starts with a certified ignition time of 0.03 seconds to 2000 seconds. Each unit weights 1.5 kg (3.3 lb).
Versions
[edit]This engine has been used with certain variations in thecrewedRussian space programsince theSalyut 6inSoviettimes. The three main versions are:[4]
- 11D428:Delivered in 1970 for use inSalyut 1.
- 11D428M:Version developed for theYantar-2Kplatform. It reached space on the first launch,Kosmos 697on August 6, 1974.
- 11D428A(AKARDMT-135): Version developed for theSoyuz 7K-S,it flew onKosmos 670,Kosmos 772andKosmos 869.Later used on theKTDU-426.[5]
- 11D428A-10:Thruster used on theZvezda ISS Module.Originally developed for theMir Core Module.
- 11D428A-14:Thruster used on the Zvezda ISS module.
- 11D428A-16(AKARDMT-135M): Improved specific impulse version. Used on theKTDU-80sinceSoyuz TM-28.[6]
- 11D428AF-16:Thruster version developed for theFobos-Gruntplanetary sample mission.
Engine | 11D428A | 11D428A-16 | 11D428AF-16 |
---|---|---|---|
Development | 1968–1974 | 1968–1977 | 1993–1997 |
Engine Type | Liquidpressure-fedrocket engine | ||
Propellant | N2O4/UDMHwith 1.85 O/F ratio | ||
Thrust | 130.5 N (29.3 lbf) | 129.16 N (29.04 lbf) | 123.5 N (27.8 lbf) |
isp | 1:56 Exp. Nozzle:290 s (2.8 km/s) 1:150 Exp. Nozzle:302 s (2.96 km/s) |
291 s (2.85 km/s) | 306.2 s (3.003 km/s) |
Nominal Inlet Pressure | 1.77 MPa (257 psi) | 1.76 MPa (255 psi) | 1.47 MPa (213 psi) |
Nozzle | 1 | 1 | 1 |
Burn time | 570s | 2700s | 50,000s |
Ignitions | 500,000 | ||
Ignition time | 0.03 to 2000s | ||
Mass | 1.2 kg (2.6 lb) | 1.5 kg (3.3 lb) | 1.9 kg (4.2 lb) |
Length | 274 mm (10.8 in) | 289.5 mm (11.40 in) | 372 mm (14.6 in) |
Diameter | 98 mm (3.9 in) | 157.4 mm (6.20 in) | |
Uses | Soyuz 7K-S,Soyuz-TandSoyuz-TM | Soyuz-TMA,Salyut-6,Salyut-7,Mir Core Module,Zvezda | Fobos-Grunt |
References | [1][3][7][8][9] |
See also
[edit]References
[edit]- ^ab"Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные"[Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry](PDF)(in Russian). pp. 75–81.Retrieved2015-07-25.
- ^Pillet, Nicolas."Le système de propulsion du vaisseau Soyouz"[The propulsion system of the Soyuz spacecraft] (in French). Kosmonavtika.com.Retrieved2015-07-14.
- ^ab"Двухкомпонентный ракетный двигатель малой тяги 11Д428А-16"[Bipropellant thruster 11D428A-16] (in Russian).NIIMash.Archived fromthe originalon 2015-11-26.Retrieved2015-07-30.
- ^"История"[History] (in Russian).NIIMash.Retrieved2015-07-30.
- ^"RDMT-135".Encyclopedia Astronautica. Archived fromthe originalon 2015-08-24.Retrieved2015-07-30.
- ^Malikov, A.; Zhuk, E. (June 1999). "3.17. Комбинированная Двигательная Установка (КДУ) (Combined Propulsion System)".Soyuz Crew Operations Manual (SoyCOM) (ROP-19) (Final)(PDF).Yu.A. Gagarin Cosmonautís Training Center.pp. 122–129.Archived(PDF)from the original on 16 August 2023.
- ^"Двухкомпонентный ракетный двигатель малой тяги 11Д428АФ-16"[Bipropellant thruster 11D428AF-16] (in Russian).NIIMash.Archived fromthe originalon 2015-11-26.Retrieved2015-07-30.
- ^"Серийный двухкомпонентный ракетный двигатель малой тяги 11Д428А"[Bipropellant thruster 11D428A](PDF)(in Russian).NIIMash.Retrieved2015-07-25.
- ^"RDMT-100".Encyclopedia Astronautica. Archived fromthe originalon 2015-08-24.Retrieved2015-07-30.
External links
[edit]- KB KhIMMASH Official Page (in Russian)Archived2016-03-20 at theWayback Machine