GB953260A - Air-breathing solid propellant ducted rocket - Google Patents

Air-breathing solid propellant ducted rocket

Info

Publication number
GB953260A
GB953260A GB43261A GB43261A GB953260A GB 953260 A GB953260 A GB 953260A GB 43261 A GB43261 A GB 43261A GB 43261 A GB43261 A GB 43261A GB 953260 A GB953260 A GB 953260A
Authority
GB
United Kingdom
Prior art keywords
propellant
rocket
combustion
air
nozzle
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
GB43261A
Inventor
Joseph Wade Wiggins
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.)
ATK Launch Systems LLC
Original Assignee
Thiokol Corp
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 Thiokol Corp filed Critical Thiokol Corp
Priority to GB43261A priority Critical patent/GB953260A/en
Publication of GB953260A publication Critical patent/GB953260A/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
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/18—Composite ram-jet/rocket engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/105—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines using a solid fuel

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Solid-Fuel Combustion (AREA)

Abstract

953,260. Self-propelled missiles. THIOKOL CHEMICAL CORPORATION. Jan. 4, 1961, No. 432/61. Heading F3A. In a solid propellant rocket the casing incorporates an air intake so as to introduce atmospheric air into the combustion space. As shown, Fig. 1, the rocket casing 11 contains the propellant charge 12, the gases from which are directed by nozzle 13 into the combustion chamber 14. The ducts 15 lead air into 14 to complete the combustion of the gases prior to discharge through nozzle 16. In the second embodiment, Fig. 3, the rocket is first accelerated by the high-thrust propellant 37. After a predetermined time, the charge 33 is ignited and the bulkhead 38 is burned. The partially oxidized gases from 33 are mixed with air supplied through duct 36 to produce further combustion in the space occupied by 37 and are then emitted through nozzle 39. In the third embodiment, Fig. 4, the oxidant rich propellant 43 first accelerates the rocket. Then, partial combustion of propellant 49 supplies fuel rich gas to the combustion chamber 47 where further burning occurs, with air supplied through duct 45, before discharge through 48. Organic polymer or copolymer fuels in conjunction with ammonium perchlorate or a nitrate salt as an oxidizer are used.
GB43261A 1961-01-04 1961-01-04 Air-breathing solid propellant ducted rocket Expired GB953260A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB43261A GB953260A (en) 1961-01-04 1961-01-04 Air-breathing solid propellant ducted rocket

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB43261A GB953260A (en) 1961-01-04 1961-01-04 Air-breathing solid propellant ducted rocket

Publications (1)

Publication Number Publication Date
GB953260A true GB953260A (en) 1964-03-25

Family

ID=9704251

Family Applications (1)

Application Number Title Priority Date Filing Date
GB43261A Expired GB953260A (en) 1961-01-04 1961-01-04 Air-breathing solid propellant ducted rocket

Country Status (1)

Country Link
GB (1) GB953260A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2574480A1 (en) * 1984-12-10 1986-06-13 Matra Device comprising a useable charge and a longitudinally displaceable jet propulsion unit
FR2650341A1 (en) * 1989-07-27 1991-02-01 Messerschmitt Boelkow Blohm GAS GENERATOR FOR STATUS-FUSEES
DE3029495C1 (en) * 1979-08-14 1995-09-28 Poudres & Explosifs Ste Nale Self-firing composition for generating thrust in air with an explosive as the oxidant and ramjet engines with the self-combusting composition as the fuel
FR2863665A1 (en) * 1988-10-12 2005-06-17 Aerospatiale Ramjet engine for propelling missile, includes tubular unit made up of composite material, whose lower volume is separated into two spaces by intermediate transversal partition wall
CN111594344A (en) * 2020-05-01 2020-08-28 西北工业大学 Small-scale two-stage rocket combined ramjet engine
CN111734550A (en) * 2020-06-15 2020-10-02 哈尔滨工程大学 Built-in multistage thrust underwater power system and control method thereof
CN112627982A (en) * 2020-12-15 2021-04-09 中国人民解放军国防科技大学 Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3029495C1 (en) * 1979-08-14 1995-09-28 Poudres & Explosifs Ste Nale Self-firing composition for generating thrust in air with an explosive as the oxidant and ramjet engines with the self-combusting composition as the fuel
FR2574480A1 (en) * 1984-12-10 1986-06-13 Matra Device comprising a useable charge and a longitudinally displaceable jet propulsion unit
FR2863665A1 (en) * 1988-10-12 2005-06-17 Aerospatiale Ramjet engine for propelling missile, includes tubular unit made up of composite material, whose lower volume is separated into two spaces by intermediate transversal partition wall
FR2650341A1 (en) * 1989-07-27 1991-02-01 Messerschmitt Boelkow Blohm GAS GENERATOR FOR STATUS-FUSEES
CN111594344A (en) * 2020-05-01 2020-08-28 西北工业大学 Small-scale two-stage rocket combined ramjet engine
CN111734550A (en) * 2020-06-15 2020-10-02 哈尔滨工程大学 Built-in multistage thrust underwater power system and control method thereof
CN112627982A (en) * 2020-12-15 2021-04-09 中国人民解放军国防科技大学 Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine
CN112627982B (en) * 2020-12-15 2021-12-07 中国人民解放军国防科技大学 Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine

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