EP0267938A1 - Dispositif regulateur de la vitesse de combustion d'un propergol solide - Google Patents

Dispositif regulateur de la vitesse de combustion d'un propergol solide

Info

Publication number
EP0267938A1
EP0267938A1 EP19870903370 EP87903370A EP0267938A1 EP 0267938 A1 EP0267938 A1 EP 0267938A1 EP 19870903370 EP19870903370 EP 19870903370 EP 87903370 A EP87903370 A EP 87903370A EP 0267938 A1 EP0267938 A1 EP 0267938A1
Authority
EP
European Patent Office
Prior art keywords
valve
control
power unit
vehicle
chamber
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.)
Withdrawn
Application number
EP19870903370
Other languages
German (de)
English (en)
Inventor
Brian Walter Muddle
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.)
Plessey Overseas Ltd
Original Assignee
Plessey Overseas Ltd
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 Plessey Overseas Ltd filed Critical Plessey Overseas Ltd
Publication of EP0267938A1 publication Critical patent/EP0267938A1/fr
Withdrawn legal-status Critical Current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
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/805—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control servo-mechanisms or control devices therefor

Definitions

  • This invention relates to a solid propellant burn rate control device. It relates particularly to a control device that may be used with a solid propellant gas generator for a vehicle and which will give effective control over the rate of burning of the propellant material.
  • the burn rate is influenced by the pressure applied within the gas generation chamber. Between a significant range of pressure levels, the propellant burn rate tends to increase with pressure.
  • One way of controlling the chamber pressure would be to vary the effective area of the exhaust port. An increase in the flow area would cause a reduction in both the chamber pressure and the propellant burn rate.
  • the present invention was devised to overcome some of these problems by providing alternative means of controlling the pressure within the gas generation chamber.
  • a power unit for a vehicle of the kind using a solid propellant fuel material which is burned within a combustion chamber the chamber having an outlet port including an adjustable valve arranged for controlling the rate of gas flow through said port, in which the said valve is a fluid flow valve capable of effecting control of the gas flow in the absence of a mechanically movable valve member.
  • the fluid flow valve may be a fluidic vortex valve.
  • the vortex valve may have a control port coupled through a control valve to a control fluid source.
  • the said combustion chamber includes a gas pressure sensor capable of producing an output signal representative of the gas pressure within the chamber, the vehicle further including means responsive to the said signal and effective to control operation of said control valve.
  • the power unit comprises a gas generation chamber 1 enclosing a mass of solid propellant fuel material 2.
  • the chamber 1 has an outlet port 3 at which is fitted a vortex valve 4 which controls flow of the generated gases to a discharge port 6.
  • the operation of the vortex valve 4 is controlled by a flow of a control fluid which passes through a control valve 7 from a control fluid reservoir 8.
  • the control valve 7 is operated in accordance with an electrical signal from a control unit (not shown) of the rocket vehicle.
  • the control unit is arranged to respond to the output of a gas pressure sensor located in the gas generation chamber 1 and in addition, the control unit has an input responsive to the output power demanded from the propulsion unit in accordance with the operation of the vehicle.
  • control valve 7 When the demanded gas flow rate from the discharge port 6 is required to be increased, the control valve 7 will open and this will allow control fluid from the reservoir 8 to pass into the valve 4. The fluid pressure within the valve 4 will thus increase and this will cause the pressure within the chamber 1 to rise with a consequent acceleration of the rate of burn of the fuel material 2. This will produce the required increase in flow from the discharge port 6.
  • the control valve 7 is operated by a control unit of the vehicle and this unit also has an input connected to a gas pressure sensor (not shown) located in the gas generation chamber 1.
  • a gas pressure sensor not shown located in the gas generation chamber 1.
  • the control unit of the vehicle will also have an input adjustable in response to the power output demanded from the propulsion unit at any time.
  • the burn rate control device of the invention has been found to be useful in practice since the rate of gas flow can be adjusted in response to the demands made on the vehicle propulsion unit and if the demand is low then the burn rate can be reduced to reduce wastage of the propellant material.
  • control fluid it is not essential that the supply of control fluid should be derived from a control fluid reservoir.
  • the control fluid might be derived from a suitable liquid supply, a pressurised cold gas supply or a separate gas generator. It will generally be necessary for the control fluid to be provided at a higher gas pressure than the pressure available in the chamber 1, but in some circumstances it might be possible for the control gas supply to be derived from the gas in the gas generation chamber.
  • the power unit of the- invention should be used only as the main thrust motor of a rocket vehicle.
  • it might be used as a power source for attitude control in a vehicle having no motor, such as a projectile.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Fluid Pressure (AREA)

Abstract

Dans l'unité motrice d'un véhicule utilisant un propergol solide qui est brûlé dans une chambre de combustion (1), la chambre est pourvue d'un orifice de sortie (3) comprenant une vanne réglable (4) permettant de réguler le débit de gaz à travers ledit orifice, cette vanne (4) étant une vanne à écoulement de fluide pouvant effectuer la régulation du débit de gaz en l'absence d'un organe de vanne mobile mécaniquement. La vanne (4) peut être du type à tourbillon fluidique, l'écoulement à travers cette vanne étant modifié en régulant l'écoulement d'un fluide de commande dans la vanne. Cet agencement provoque l'accumulation d'une pression de gaz à l'intérieur de la chambre (1), ce qui permet d'accroître la vitesse de combustion du carburant lorsqu'une puissance élevée est requise.
EP19870903370 1986-05-21 1987-05-21 Dispositif regulateur de la vitesse de combustion d'un propergol solide Withdrawn EP0267938A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB8612368 1986-05-21
GB08612368A GB2190729A (en) 1986-05-21 1986-05-21 Solid propellant burn rate control device

Publications (1)

Publication Number Publication Date
EP0267938A1 true EP0267938A1 (fr) 1988-05-25

Family

ID=10598208

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19870903370 Withdrawn EP0267938A1 (fr) 1986-05-21 1987-05-21 Dispositif regulateur de la vitesse de combustion d'un propergol solide

Country Status (3)

Country Link
EP (1) EP0267938A1 (fr)
GB (1) GB2190729A (fr)
WO (1) WO1987007331A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8920695D0 (en) * 1989-09-13 1989-10-25 Rolls Royce Plc Engine cooling system protection device
DE19813330C2 (de) * 1998-03-26 2000-04-13 Daimler Chrysler Ag Verfahren zur Erzeugung eines Querschubes
RU2167327C1 (ru) * 2000-08-25 2001-05-20 Федеральный центр двойных технологий "Союз" Установка для определения скорости горения твердого ракетного топлива
RU2194874C2 (ru) * 2001-03-01 2002-12-20 Федеральный центр двойных технологий "Союз" Установка для определения скорости горения твердого ракетного топлива
RU2188963C1 (ru) * 2001-07-12 2002-09-10 Федеральный центр двойных технологий "Союз" Установка для определения скорости горения твердого ракетного топлива в напряженно-деформированном состоянии
RU2208694C1 (ru) * 2001-10-22 2003-07-20 Южно-Российский государственный технический университет (Новочеркасский политехнический институт) Способ подавления вибрационного горения высокоэнергетичных конденсированных систем

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO8707331A1 *

Also Published As

Publication number Publication date
GB2190729A (en) 1987-11-25
GB8612368D0 (en) 1986-08-20
WO1987007331A1 (fr) 1987-12-03

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Legal Events

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Effective date: 19880223

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Inventor name: MUDDLE, BRIAN, WALTER