GB1473749A - Monopropellant thruster with superheater - Google Patents

Monopropellant thruster with superheater

Info

Publication number
GB1473749A
GB1473749A GB1990075A GB1990075A GB1473749A GB 1473749 A GB1473749 A GB 1473749A GB 1990075 A GB1990075 A GB 1990075A GB 1990075 A GB1990075 A GB 1990075A GB 1473749 A GB1473749 A GB 1473749A
Authority
GB
United Kingdom
Prior art keywords
chamber
super
heater
disposed
hydrazine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB1990075A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northrop Grumman Space and Mission Systems Corp
Original Assignee
TRW Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by TRW Inc filed Critical TRW Inc
Publication of GB1473749A publication Critical patent/GB1473749A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/68—Decomposition chambers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/411—Electric propulsion
    • B64G1/415—Arcjets or resistojets
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
    • C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
    • C06D5/04—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by auto-decomposition of single substances

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Organic Chemistry (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Abstract

1473749 Monopropellant thrust units TRW Inc 12 May 1975 [22 Jan 1975] 19900/75 Heading F1J The invention relates to a monopropellant thruster which comprises a decomposition chamber 11 to which monopropellant such as hydrazine is supplied through line 15, a super-heater 20 having means for heating the decomposed hydrazine, and a discharge nozzle 21 for discharge of the superheated decomposition products of hydrazine. The decomposition chamber 11 is heated by means of a spirally-wound electric element 12 disposed around the chamber. The super-heater 20 is in the form of a coiled tube which is electrically heated and is disposed within a chamber 17. A thermal barrier tube 16 of perforated form is disposed between the hydrazine control valve 14 and the decomposition chamber. In a second embodiment Fig. 2, the decomposition chamber 11 is connected tangentially to the super-heater chamber 23 so that the products enter the chamber with a vortex motion; the super-heater chamber is heated by means of a spirally-wound electric element 24 disposed centrally therein, the gases discharging from the super-heater through nozzle 26. The whole assembly is disposed within a casing 27. The thrusters are suitable for mounting on an earth satellite for control thereof.
GB1990075A 1975-01-22 1975-05-12 Monopropellant thruster with superheater Expired GB1473749A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US54319575A 1975-01-22 1975-01-22

Publications (1)

Publication Number Publication Date
GB1473749A true GB1473749A (en) 1977-05-18

Family

ID=24166979

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1990075A Expired GB1473749A (en) 1975-01-22 1975-05-12 Monopropellant thruster with superheater

Country Status (7)

Country Link
JP (1) JPS5950865B2 (en)
CA (1) CA999749A (en)
DE (1) DE2535520C3 (en)
FR (1) FR2298699A1 (en)
GB (1) GB1473749A (en)
IT (1) IT1045168B (en)
NL (1) NL174815C (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3209470A1 (en) * 1981-03-19 1982-09-30 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland, London ELECTROTHERMAL REACTION ENGINE
DE3128735A1 (en) * 1981-07-21 1983-02-10 Erno-Raumfahrttechnik Gmbh, 2800 Bremen ENGINE, ESPECIALLY FOR SPACING BODIES
DE3141354A1 (en) * 1981-10-17 1983-04-28 Erno-Raumfahrttechnik Gmbh, 2800 Bremen Engine, especially vernier engine for space missile

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1534601A (en) * 1976-07-23 1978-12-06 Secr Defence Electrothermal gas thrusters
GB1557590A (en) * 1976-10-25 1979-12-12 Secr Defence Gas thrusters
FR2411972A1 (en) * 1977-12-14 1979-07-13 Hawker Siddeley Dynamics Ltd Device producing hot fluid stream e.g. hydrazine thruster - has heat shunt upstream of combustion chamber coupled between fuel pipe and heat sink containing fuel valves
US4305247A (en) * 1979-06-18 1981-12-15 Hughes Aircraft Company Electrothermally augmented hydrazine thruster

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3016693A (en) * 1960-09-23 1962-01-16 John R Jack Electro-thermal rocket
US3210927A (en) * 1963-10-01 1965-10-12 Paul F Brinich Electro-thermal rockets having improved heat exchangers
US3603093A (en) * 1970-03-06 1971-09-07 Nasa Heated porous plug microthrustor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3209470A1 (en) * 1981-03-19 1982-09-30 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland, London ELECTROTHERMAL REACTION ENGINE
DE3128735A1 (en) * 1981-07-21 1983-02-10 Erno-Raumfahrttechnik Gmbh, 2800 Bremen ENGINE, ESPECIALLY FOR SPACING BODIES
US4470258A (en) * 1981-07-21 1984-09-11 Erno Raumfahrttechnik Gmbh Thruster for space vehicles
DE3141354A1 (en) * 1981-10-17 1983-04-28 Erno-Raumfahrttechnik Gmbh, 2800 Bremen Engine, especially vernier engine for space missile

Also Published As

Publication number Publication date
NL174815C (en) 1984-08-16
DE2535520A1 (en) 1976-07-29
FR2298699A1 (en) 1976-08-20
DE2535520B2 (en) 1978-04-13
NL174815B (en) 1984-03-16
CA999749A (en) 1976-11-16
IT1045168B (en) 1980-05-10
JPS5187610A (en) 1976-07-31
DE2535520C3 (en) 1978-12-07
FR2298699B1 (en) 1978-02-24
JPS5950865B2 (en) 1984-12-11
NL7505797A (en) 1976-07-26

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee

Effective date: 19920512