HM7B - Wikipedia

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• 2 Overview
• 3 See also Toggle See also subsection
  • 3.1 Comparable engines
• 4 References

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Appearance move to sidebar hide From Wikipedia, the free encyclopedia European rocket engine HM7B

Country of origin	France
First flight	24 December 1979
Designer	Snecma
Manufacturer	Snecma
Application	Upper stage engine
Predecessor	HM4
Successor	Vinci
Status	Retired
Liquid-fuel engine
Propellant	LOX / LH2
Mixture ratio	5:1
Cycle	Gas-generator
Configuration
Chamber	1
Nozzle ratio	83.1:1
Performance
Thrust, vacuum	62.2 kN (13,980 lbf)[1]
Chamber pressure	3.7 MPa (37 bar)
Specific impulse, vacuum	444.6 s (4.36 km/s)
Dimensions
Length	2.01 m (6 ft 7 in)
Diameter	0.992 m (3 ft 3.1 in)
Dry mass	165 kg (364 lb)
Used in
HM7B: Ariane 5 ECA Ariane 4 Ariane 3 Ariane 2 HM7(A): Ariane 1
References
References	[1][2][3]

The HM7B was a European cryogenic upper stage rocket engine used on the vehicles in the Ariane rocket family.[3] It was replaced by Vinci, which acts as the new upper stage engine on Ariane 6.[4] Nearly 300 engines have been produced to date.[3]

History

[edit]

The development of HM7 engine begun in 1973 on a base of HM4 rocket engine. It was designed to power a third stage of newly constructed Ariane 1, the first launch system for European Space Agency. Maiden flight took place on 24 December 1979 successfully placing CAT-1 satellite on the orbit. With the later introduction of Ariane 2 and Ariane 3 it became necessary to improve the performance of the upper stage engine. This was achieved by extending the nozzle length and increasing the chamber pressure from 30 to 35 bar, increasing the engine's specific impulse and resulting in a nominal burn time increase from 570 to 735 seconds. Qualification tests were completed in 1983 and this upgraded variant was designated HM7B. It was also used on the Ariane 4 vehicle's upper stage where the burn time was further increased to 780 seconds, and since 12 February 2005 it's also used on the upper stage of Ariane 5 ECA.[2]

Overview

[edit]

The HM7B is a regeneratively cooled gas generator rocket engine fed with liquid oxygen and liquid hydrogen. It has no restart capability: the engine is continuously fired for 950 seconds in its Ariane 5 version (780 s in the Ariane 4). It provides 62.7 kN of thrust with a specific impulse of 444.6 s.[1] The engine's chamber pressure is 3.5 MPa.[2]

See also

[edit]

• Spacecraft propulsion
• Timeline of hydrogen technologies
• Comparison of orbital rocket engines
• HM4

Comparable engines

[edit]

• YF-75
• RL-10
• Vinci
• CE-7.5

References

[edit]

1. ^ a b c B.T.C. Zandbergen. "Simple mass and size estimation relationships of pump fed rocket engines for launch vehicle conceptual design". Retrieved 14 August 2017.
2. ^ a b c Airbus Air and Defence. "HM-7 and HM-7B Rocket Engine - Thrust Chamber". Archived from the original on 8 May 2012. Retrieved 10 August 2014.
3. ^ a b c Snecma S.A. "HM7B - Snecma". Archived from the original on 2013-04-19. Retrieved 10 August 2014.
4. ^ Safran Group (December 2012). "Safran: Shooting for the StarS" (PDF). Archived from the original (PDF) on 12 August 2014. Retrieved 10 August 2014.

v t e Rocket engines and solid motors for orbital launch vehicles
Comparison of orbital rocket engines
Liquid fuel	Cryogenic Hydrolox (LH2 / LOX) China YF-73 YF-75 YF-75D YF-77 YF-79 YF-90 Europe HM7B Vinci Vulcain India CE-7.5 CE-20 Japan LE-5 LE-7 LE-9 Russia KVD-1 (RD-56) RD-0120 RD-0146 United States BE-3U BE-7 J-2 RL10 RS-25 RS-68 Methalox (CH4 / LOX) China BF-20 Lingyun Longyun TQ-11 TQ-12 TQ-15A YF-209 YF-215 United States BE-4 Raptor Archimedes Aeon 1 Aeon R Russia RD-0169 Europe Prometheus M-10 Semi-cryogenic Kerolox (RP-1 / LOX) China TH-11 TH-12 YF-100 YF-102 YF-115 YF-130 Welkin India SCE-200 Russia NK-15 NK-33, 44 RD-58 RD-0105, 0109 RD-0107, 0108, 0110 RD-0110R RD-0124 RD-107, 108, 117, 118 RD-120 RD-170, 171 RD-180 RD-191, 151, 181 RD-193 S1.5400 Spain TEPREL Ukraine RD-8 RD-801 RD-810 United States F-1 H-1 Kestrel LR-79 LR89 LR105 LR70-NA , S-3D Merlin Miranda RS-27 RS-27A RS-56 S-3D Rutherford XLR50 Storable Hypergolic (Aerozine, UH 25, MMH, or UDMH / N2O4, MON, or HNO3) China YF-1, 2, 3 YF-20, 21, 22, 24, 25 YF-23 YF-40 YF-50D Europe Aestus Astris Vexin Viking India PS4 Vikas Israel LK-4 North Korea Paektusan LRE along other LREs Russia 17D61 RD-0202 to 0206, 0208 to 0213 RD-0207, 0214 RD-0216, 0217, 0235 RD-0233, 0234 RD-0236 RD-0237 RD-0243 to 0245 RD-0255 to 0257 RD-215 to 219 RD-250 to 252, 261, 262 RD-253, 275 RD-263, 268, 273 RD-270 S5.92 S5.98M Ukraine RD-843 RD-854, 861 RD-855 RD-856 RD-864, 869 United States AJ10 LR-87 LR-91 RS-88* TR-201 XLR81* Other Russia RD-109, 119 RD-211 to 214 UK Gamma United States Curie RS-88* XLR81*
Solid fuel	China FG-02 FG-36 FG-46 FG-47 SpaB-65 SpaB-140C Europe Mage 1 P-4 P-6 PAP P80 P120C P230 Topaze Waxwing Zefiro 9 Zefiro 23 Zefiro 40 India S7 S9 S12 S139 S200 Iran Salman Rafe Israel LK-1 RSA-3 Japan KM-V1 KM-V2b M-14 M-24 M-34 M-34c SRB-A United States AJ-60A Algol Castor 30 GEM Orbus-6 Orbus-21 Orion Space Shuttle SRB Star 37 Star 48 UA120 SRMU X-248 X-254
* Different versions of the engine use different propellant combinations Engines in italics are/were under development

v t e Ariane rocket family
Rockets	Current Ariane 6 In development Ariane Next Retired Ariane 1 Ariane 2 Ariane 3 Ariane 4 Ariane 5
Launch sites	Guiana Space Centre (Kourou) ELA-1 ELA-2 ELA-3 ELA-4
Engines	Aestus HM7B P120C P160C Viking Vinci Vulcain
Launches	List of launches 1979–1989 1990–1999 2000–2009 2010–2019 2020–2029
Flights	VA240 VA241 VA242 VA244 VA243 VA245 VA246 VA247 VA248 VA253 VA254 VA255 VA256 VA260 VA261 VA262
Organizations	Manufacturing ArianeGroup Airbus Space Aérospatiale (merged) Safran Aircraft Engines Beyond Gravity MT Aerospace SABCA Nammo Launch provider Arianespace Related European Space Agency CNES
Related	Proposals SUSIE Cancelled Adeline Ariane 5 ME DC4EU Hermes Liquid fly-back booster Retired Automated Transfer Vehicle Europa
Category Multimedia

v t e Snecma/Safran aircraft engines
Turbojets	Atar Atar 101 Atar Volant M45
Turbofans	M45G M53 M88 Silvercrest
Spacecraft engines	Viking HM7B PPS-1350 Vinci Vulcain
Experimental	Coléoptère
Joint development	CFM International CFM56 LEAP RISE PowerJet SaM146 Europrop International TP400-D6 Rolls-Royce Olympus 593 M45H Safran Larzac

Retrieved from "https://en.wikipedia.org/w/index.php?title=HM7B&oldid=1246711296" Categories:

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• Rocket engines using hydrogen propellant
• Space program of France
• Rocket engines using the gas-generator cycle

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