[go: up one dir, main page]

GB1248216A - Gaseous thrust engines - Google Patents

Gaseous thrust engines

Info

Publication number
GB1248216A
GB1248216A GB55299/68A GB5529968A GB1248216A GB 1248216 A GB1248216 A GB 1248216A GB 55299/68 A GB55299/68 A GB 55299/68A GB 5529968 A GB5529968 A GB 5529968A GB 1248216 A GB1248216 A GB 1248216A
Authority
GB
United Kingdom
Prior art keywords
nozzle
main nozzle
devices
flow
auxiliary nozzles
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
GB55299/68A
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.)
Nord Aviation Societe Nationale de Constructions Aeronautiques
Original Assignee
Nord Aviation Societe Nationale de Constructions Aeronautiques
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 Nord Aviation Societe Nationale de Constructions Aeronautiques filed Critical Nord Aviation Societe Nationale de Constructions Aeronautiques
Publication of GB1248216A publication Critical patent/GB1248216A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/663—Steering by varying intensity or direction of thrust using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves
    • 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
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
    • 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
    • B64G1/403—Solid propellant rocket engines
    • 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
    • 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
    • B64G1/401—Liquid propellant rocket engines

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Nozzles (AREA)
  • Sampling And Sample Adjustment (AREA)

Abstract

1,248,216. Gaseous thrust engines. NORD-AVIATION SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES. 21 Nov., 1968 [24 Nov., 1967], No. 55299/68. Heading B7G. [Also in Divisions F1 and F2] In an engine wherein hot gas is expelled from a chamber 1a (Fig. 1, not shown), via a main nozzle (1b) gas is also passed to auxiliary nozzles arranged to provide thrust pulses having a radial component away from the main nozzle, the auxiliary nozzles having displaceable obstructing devices 4a to regulate the flow of gas therethrough, and the auxiliary nozzles and devices 4a are cooled by the injection of a laminar flow of liquid on to their respective surface portions. There may be eight such nozzles arranged in pairs symmetrically about the main nozzle, their mouths lying in a plane passing through the throat of the main nozzle and transverse to the longitudinal axis of that nozzle. The obstructing device 4a comprises a bulb movable through an hydraulic or pneumatic arrangement between a fully closed position A and a fully open position B. The bulb and the nozzle have helical cooling coils 5d 1 , 5j 1 , 5f 1 connected to a source of water at flow rate q 1 and 5k 1 , 5l 1 , 5g 1 connected to a source of water at flow rate q 2 . The coils, have respective outlets 5f-5l. The engine includes circuitry to vary the position of devices 4a in dependence upon the cooling water pressure and the flow rates q 1 , q 2 .
GB55299/68A 1967-11-24 1968-11-21 Gaseous thrust engines Expired GB1248216A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR129695 1967-11-24

Publications (1)

Publication Number Publication Date
GB1248216A true GB1248216A (en) 1971-09-29

Family

ID=8642266

Family Applications (1)

Application Number Title Priority Date Filing Date
GB55299/68A Expired GB1248216A (en) 1967-11-24 1968-11-21 Gaseous thrust engines

Country Status (4)

Country Link
US (1) US3554448A (en)
DE (1) DE1810839A1 (en)
FR (1) FR1555741A (en)
GB (1) GB1248216A (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8975565B2 (en) * 2012-07-17 2015-03-10 Raytheon Company Integrated propulsion and attitude control system from a common pressure vessel for an interceptor
CN112780449A (en) * 2021-03-15 2021-05-11 西华大学 Omnibearing vector engine and aircraft

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1036540A (en) * 1951-05-07 1953-09-08 Soc Et Propulsion Par Reaction Combustion chamber of a rocket motor with adjustable thrust and a rocket motor provided with such a combustion chamber
US2865169A (en) * 1956-02-15 1958-12-23 United Aircraft Corp Jet exhaust nozzle
US3245620A (en) * 1961-12-13 1966-04-12 Gen Motors Corp Missile steering control
US3127740A (en) * 1962-10-17 1964-04-07 United Aircraft Corp Clustered rocket nozzles

Also Published As

Publication number Publication date
US3554448A (en) 1971-01-12
FR1555741A (en) 1969-01-31
DE1810839A1 (en) 1969-07-17

Similar Documents

Publication Publication Date Title
US3135291A (en) Bistable fluid valve
GB745630A (en) Fluid flow control device for jet propulsion nozzles
GB1248216A (en) Gaseous thrust engines
GB1059791A (en) Pneumatic or hydraulic adding circuit
GB973401A (en) Gas turbine engine
GB1067123A (en) Pressure recovery from bistable element
GB1230667A (en)
GB1116999A (en) Improvements in supersonic convergent-divergent jet exhaust nozzles
GB1196755A (en) Improvements in and relating to a Slide Valve for Opening and Closing at Least One Passage for a Fluid and Apparatus Comprising at Least One such Slide Valve.
GB1104531A (en) Variable spread fluid dispersal systems
GB1183893A (en) Nozzles having Silencing Means
GB997974A (en) Device for dispersing contaminant in a fluid flow
GB1151016A (en) Improvements in or relating to Temperature Control of Superheated Steam.
GB1043110A (en) Improvements in or relating to anaesthetic administering apparatus
ES469502A1 (en) Method of and apparatus for ascertaining the state of aggregation of a medium
GB1068769A (en) Device for starting gas turbine engines by means of compressed air
GB1042924A (en) Fluid valve device for reducing the pressure and temperature of a gaseous or vaporised working medium
VINOGRADOV Definition of boundary of nucleus of flow and coefficient of pressure recovery in short round channels(Definition of fluid nucleus boundary and coefficient of pressure recovery for gas flow in nozzles and inlets)
GB1162867A (en) Improvement in or relating to a Liquid Flow Control Arrangement
GB606909A (en) Fluid flow control device
GB1079403A (en) Gas flow control and cooling apparatus
SHANDOR Sonic gas jet lateral injection into supersonic duct flow
LAZNIUK et al. Study of a semibounded turbulent jet flow injected tangentially into an isobaric slipstream(Tangentially injected plane jet spreading in slipstream at various Reynolds numbers at jet inlet slot studied in wind tunnel for dynamic behavior)
GOLDAEV et al. Investigation of the operation of jet-engine type combustion chambers under unsteady conditions(Pressure fluctuation onset conditions in jet engine combustion chambers with supersonic nozzles, discussing design factors effect on combustion process stability)
CHENG et al. Freezing of dissociation in supersonic nozzle flows(Inviscid supersonic nozzle flow of ideal dissociating gas, sudden freezing, equilibrium- recombination mechanism and velocity distribution)