GB579968A - Improvements in or relating to the launching and landing of aeroplanes or seaplanes - Google Patents

Improvements in or relating to the launching and landing of aeroplanes or seaplanes

Info

Publication number
GB579968A
GB579968A GB756/41A GB75641A GB579968A GB 579968 A GB579968 A GB 579968A GB 756/41 A GB756/41 A GB 756/41A GB 75641 A GB75641 A GB 75641A GB 579968 A GB579968 A GB 579968A
Authority
GB
United Kingdom
Prior art keywords
chamber
inclination
rocket
tube
landing
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
GB756/41A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB756/41A priority Critical patent/GB579968A/en
Publication of GB579968A publication Critical patent/GB579968A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/023—Aircraft characterised by the type or position of power plants of rocket type, e.g. for assisting taking-off or braking
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/26—Burning control
    • 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
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
    • 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
    • F02K9/97—Rocket nozzles
    • F02K9/972—Fluid cooling arrangements for nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

579,968. Starting and stopping aircraft. BURNEY, SIR C. D. Jan. 20, 1941, No. 756. [Classes 4 and 114] A rocket reaction device for attachment to aircraft to assist in taking off and landing, comprises one or more reaction units each consisting of a chamber containing a combustible charge and carrying a tubular member for connection to an igniting chamber at one end and having a discharge chamber at the other end fitted with one or more expansion nozzles for the gases developed by combustion of the charge. The rockets may be mounted in symmetrical pairs on an aircraft and may be adjustable in inclination and direction. A tube 1, of considerable length, has grids 2 supporting a cylinder 3 of cordite or other rocket composition. One end is closed by a screw cover 4 having a spigot 5 for connection to the igniting device, and the opposite end is screwed into a nozzle chamber 6. A throated conical nozzle 7 is mounted axially within the chamber and is surrounded by a water jacket. An automatic valve is mounted within the nozzle and comprises a head 14 on a tubular member 13 sliding within a fixed sleeve 12 carried by a spider 9. A spring 15 urges the valve to closed position, but it yields under pressure of the combustion gases. A passage 18 from the combustion chamber has holes 19 leading to the space above the water, the passage being normally closed by a diaphragm 21 held in position by a screwed sleeve 20. When the pressure rises, the diaphragm is fractured and water is forced to the valve through passages 23, 24 and the tube 13 so as to issue radially through holes 17 in the valve. Several such devices may be mounted around a central core and the spigots 5 connected to radiating tubes from a central igniting chamber. The rockets discharge backwards to assist take-off in confined spaces and to reduce the run on landing they discharge forwardly. They may be given an inclination so as to have a component of lift and the inclination may be adjustable with the wing control. They may be arranged to be retracted and extended with the landing carriage. Fig. 7 shows a rocket 1 suspended by a rod 36 which can be rotated to reverse the direction of discharge by the gearing 37, 38. A tube 40 surrounds the rod 36 and a cam at its lower end adjusts the inclination of the rocket when the tube is rotated by the gearing 41, 42.
GB756/41A 1941-01-20 1941-01-20 Improvements in or relating to the launching and landing of aeroplanes or seaplanes Expired GB579968A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB756/41A GB579968A (en) 1941-01-20 1941-01-20 Improvements in or relating to the launching and landing of aeroplanes or seaplanes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB756/41A GB579968A (en) 1941-01-20 1941-01-20 Improvements in or relating to the launching and landing of aeroplanes or seaplanes

Publications (1)

Publication Number Publication Date
GB579968A true GB579968A (en) 1946-08-22

Family

ID=9709971

Family Applications (1)

Application Number Title Priority Date Filing Date
GB756/41A Expired GB579968A (en) 1941-01-20 1941-01-20 Improvements in or relating to the launching and landing of aeroplanes or seaplanes

Country Status (1)

Country Link
GB (1) GB579968A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2621871A (en) * 1947-07-30 1952-12-16 Robert Roger Aime Steering control device for jetpropelled flying machines
CN107218156A (en) * 2017-07-26 2017-09-29 北京航空航天大学 Hybrid rocket engine pintle formula becomes larynx footpath Effuser device
CN112211752A (en) * 2020-12-08 2021-01-12 北京星际荣耀空间科技有限公司 Adjustable venturi tube
CN112550752A (en) * 2020-12-30 2021-03-26 阿坝师范学院 Multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude supervision
WO2023211512A3 (en) * 2021-09-03 2024-01-25 Raytheon Company Propulsion system with single initiator for multiple rocket motors

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2621871A (en) * 1947-07-30 1952-12-16 Robert Roger Aime Steering control device for jetpropelled flying machines
CN107218156A (en) * 2017-07-26 2017-09-29 北京航空航天大学 Hybrid rocket engine pintle formula becomes larynx footpath Effuser device
CN107218156B (en) * 2017-07-26 2019-03-22 北京航空航天大学 Hybrid rocket engine pintle formula becomes larynx diameter Effuser device
CN112211752A (en) * 2020-12-08 2021-01-12 北京星际荣耀空间科技有限公司 Adjustable venturi tube
CN112211752B (en) * 2020-12-08 2021-03-16 北京星际荣耀空间科技股份有限公司 Adjustable venturi tube
CN112550752A (en) * 2020-12-30 2021-03-26 阿坝师范学院 Multimode take-off and landing unmanned aerial vehicle for plateau middle and low altitude supervision
WO2023211512A3 (en) * 2021-09-03 2024-01-25 Raytheon Company Propulsion system with single initiator for multiple rocket motors

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