GB2414782A - Ejector release unit - Google Patents

Ejector release unit Download PDF

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Publication number
GB2414782A
GB2414782A GB0204203A GB0204203A GB2414782A GB 2414782 A GB2414782 A GB 2414782A GB 0204203 A GB0204203 A GB 0204203A GB 0204203 A GB0204203 A GB 0204203A GB 2414782 A GB2414782 A GB 2414782A
Authority
GB
United Kingdom
Prior art keywords
pressure
piston
reservoir
pressure relief
relief valve
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Withdrawn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
GB0204203A
Other versions
GB0204203D0 (en
Inventor
Dennis Griffin
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.)
Flight Refuelling Ltd
Original Assignee
Flight Refuelling 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 Flight Refuelling Ltd filed Critical Flight Refuelling Ltd
Priority to GB0204203A priority Critical patent/GB2414782A/en
Publication of GB0204203D0 publication Critical patent/GB0204203D0/en
Publication of GB2414782A publication Critical patent/GB2414782A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16KVALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K17/00Safety valves; Equalising valves, e.g. pressure relief valves
    • F16K17/02Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side
    • F16K17/04Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded
    • F16K17/0446Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded with an obturating member having at least a component of their opening and closing motion not perpendicular to the closing faces
    • F16K17/046Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded with an obturating member having at least a component of their opening and closing motion not perpendicular to the closing faces the valve being of the gate valve type or the sliding valve type
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02Dropping, ejecting, or releasing articles
    • B64D1/04Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
    • B64D1/06Bomb releasing; Bombs doors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16KVALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K31/00Actuating devices; Operating means; Releasing devices
    • F16K31/003Actuating devices; Operating means; Releasing devices operated without a stable intermediate position, e.g. with snap action
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16KVALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K31/00Actuating devices; Operating means; Releasing devices
    • F16K31/44Mechanical actuating means
    • F16K31/56Mechanical actuating means without stable intermediate position, e.g. with snap action

Abstract

An ejector release system for an aircraft-mounted store comprises a reservoir 11 for containing a pre-charged gaseous ejection medium, an actuation cylinder 14,15 connected to the reservoir for effecting ejection of the store and a control valve 12 between the reservoir and actuation cylinder, in which a snap-action pressure relief valve 20 is mounted between the control valve and cylinder to allow excess pressure in the system downstream of the reservoir to be vented or diverted when the pressure exceeds a predetermined threshold pressure. The pressure relief valve 20 may include a piston 23 which is stepped to define an annular shoulder between larger and smaller diameter parts 27,26, the shoulder constituting a marginal surface area which causes the piston to be urged towards the forwards position under gas input pressure, a vent passage 32 which is out of registration with the inlet and outlet passages 33,34 at the rearwards position of the piston but is in registration in the forwards position being provided in the piston. One or more resiliently-loaded balls 30 urged into engagement with a corresponding detent 29 formed in the piston in the rearwards or pressure-retaining position provide the snap action.

Description

24 1 4782 Ejector Release Unit This invention relates to ejector release

units of the type for deploying stores from aircraft in flight and, in particular, is intended to provide an ejector release unit which utilises cold gas operation without a requirement for an on-board pump.

Conventionally and until recently, ejector release units have been operated by hot gas systems comprising deflagration of nitro-cellulose compounds in a pyrotechnic cartridge.

Inevitably, however, such cartridges generate corrosive residues and the combination of pressure, temperature and velocity of gases generated in an ejector release unit operated by such a system leads to erosion and corrosion of the containment and carbonaceous obstruction of sliding components. In an attempt to avoid the disadvantages of hot gas systems, it has previously been proposed to use compressed air or compressed nitrogen stored at pressures up to 35 MFa butt having pressurized the medium at ambient ground temperatures the release unit may be exposed to either low or high temperatures in use, which may result either in damage being caused to the ejectable store or in pressurised downstream components at high pressures (at higher temperatures) or insufficient pressure being available successfully to eject the store (at lower temperatures). In an attempt to avoid these problems, electically-driven air pumps have been proposed which, in combination with pressure switches and relief valves, can charge and maintain a workable consistent pressure for operation of the release unit but, although excellent power and consistency can be achieved over a wide environtnental temperature range, nevertheless such systems have attendant disadvantages of high pump costs, additional mass and volume uptake the host aircraft and intermittent high electrical power consumption.

It is an object of the present invention to provide a pressurized gas ejection system of the type described which does not require the use of an attached pump and which is not subject to the operating pressure being dependent upon temperature variations from the charging conditions.

It is also an object of the invention to avoid the use of electronic control systems, malfunction of which could result in an unsafe operation of the ejector release unit, for example, excessive pressure or force at higher temperatures or inadequate ejection velocity at lower temperatures. In any event, such systems, like attached pumps, require additional electrical supplies and bulky equipment which is undesirable, especially in installation locations which are already cramped, such as in legacy aircraft.

In one aspect, the present invention provides an ejector release system for an aircraft-mounted store arid comprising a reservoir for containing a pre-charged gaseous ejection medium, an actuation cylinder connected to the reservoir for effecting ejection of the store and a control valve between the reservoir and actuation cylinder, in which a snap-action pressure relief valve is mounted between the control valve and cylinder to allow excess pressure in the system downstream of the reservoir to be vented or diverted when the pressure exceeds a predetermined threshold pressure.

In anodes aspect, the invention provides a pressure relief valve for incorporation in an ejector release system as herein described, the valve comprising a piston movable in a cylinder between a rearvards or pressureretaining position and a forwards or pressure-release position, the piston and cylinder including snap action means to retain the piston in the rearwards position until a predetermined threshold pressure is exerted on the piston.

Preferably, the piston includes resilient reset means to urge the piston towards the rearwards position for re-use as the excess pressure reduces and forces acting on the piston towards Me forwards position reduce.

The piston in pressure relief valves according to the invention preferably comprises means to attenuate the effect of high input pressure Mom the reservoir to provide a relatively modest actuation force tending to urge the piston towards the forwards position, in order to avoid the use of piston diameters which would be disproportionately small (relative to other components of Me system) and intrinsically delicate. The piston may, for this purpose, comprise double-acting surfaces of respectively different diameters, thus producing a net positive force on the largerdiameter surface proportional to the difference in diameters. In a preferred embodiment of such an arrangement, the piston is stepped to define an annular shoulder between the larger and smaller diameter parts, the shoulder constituting the marginal surface area which causes the piston to be urged towards the forwards position under gas input pressure.

Pressure relief valves according to the invention include gas inlet and outlet passages or ports and the excess pressure may be vented through the outlet passage either to atmosphere or diverted to a secondary reservoir or expansion chamber. Where excess pressure is vented to a secondary reservoir or expansion chamber, the pressure in the secondary reservoir may optionally be used to maintain forwards pressure on the piston, especially against the pressure of the reset means, as excess pressure in the system becomes reduced. Ibis would enable the diverted gas to bolster the pressure in the ejector system when the expanded volume is approaching maximum towards the end of the ejector piston stroke.

In ejector release systems according to the invention, preferably two or more pressure relief valves are incorporated to maintain a more even attenuated ejection pressure over a broader range of operating temperatures, and two or more actuation cylinders are used for ejection purposes.

The piston in pressure relief valves according to the invention preferably includes a vent passage which is out of registration with the inlet and outlet passages at the rearvards position of the piston but is in registration in Me forwards position, thus allowing excess system pressure to be vented.

The piston and cylinder snap action retaining means may comprise any suitable resiliently-acting catch means but preferably comprise a resiliently-loaded ball or a plurality of such balls carried in one of the piston and cylinder and urged into engagement with a corresponding detent formed in the other of the piston and cylinder in the reaIwards or pressure-retaining position whereby, when the predetermined pressure is attained or exceeded, release of the piston towards the forwards or pressure-release position is positive and fast, thus eliminating hunting. Similarly, reset of the piston to the latched rearwards position is positive under the influence of the reset means as the excess pressure is vented and the opening force on the piston reduces. Preferably, the resilient force on the or each ball is adjustable to enable the predetermined threshold pressure to be adjusted during manufacture.

In use, pressure relief valves according to the invention are mounted with the inlet passages in cornTnunication with the main pressure channel between the control valve and actuation cylinder or cylinders, whereby the valve is subject to the same pressure as the main channel, and hence as all downstream pressure-vulnerable components, and snaps open to allow pressure relief when the predetermined threshold pressure is attained or exceeded.

The use of resiliently-loaded detent balls with adjustment provision enables pressure release to be consistently attained at predetermined threshold pressures. Furthermore, such balls have only two equilibrium states, namely retained and released and therefore cause the release to be sudden and rapid once the activation input pressure is attained, thereby eliminating hunting.

Embodiments of the invention will now be described by way of example with reference to the accompanying drawings, of which Figure I is a diagram showing tibe components of an Rector release unit according to the invention, showing only the pneumatic energy source components for the sake of clarity; Figure 2 shows one embodiment ota snap-action vent valve according to the invention in the closed condition; Figure 3 shows the valve of Figure 2 in the vent position; and Figure 4 is a graph showing the effect Event valves according to the invention on the ejection velocity at different temperatures.

Referring first to Figure 1, the ejector release unit consists of a reservoir I I connected through a mam gas valve 12 to a gas supply manifold 13 which in turn is connected to respective cylinders 14, 15 each containing a respective piston 16, 17 for ejection of the store (not shown). Lee manifold includes variable Wattles 18, 1 g for enabling differential forces to be applied to the respective ejection cylinders to apply a pitch moment to the store on release thereof.

A snap-action vent valve 20 is connected in the manifold 13, the outlet of the vent valve being connected to a secondary reservoir or expansion chamber 21. Alternatively, the outlet from the valve 20 may be vented direct to atrnasphere.

In use, the reservoir 11 is pre-charged mth compressed air or nitrogen at ambient ground temperatures and Me main control valve 12 is actuated when it is desired to eject the store from the aircraft. IN order to provide sufficient ejection energy at low temperatures (relative to the charging temperature), the reservoir 11 must be able to provide sufficient gas to the cylinders 14, 15 to overcome the adverse effect of lower pressures but, at higher temperatures and consequently higher pressures, the vent valve 20 will be automatically actuated at a pre-deterrnined threshold pressure in the manifold to prevent overload in dowre components of the system With reference to Figures 2 and 3, the valve consists of a cylinder casing 22 containing a piston 23 equipped with annular seals 24, 25. The piston is stepped and has a smaller- diameter part 26 and a larger diameter part 27 which accommodates a compression spring 28. The part 27 is formed with an annular detent groove 29 which, in the position shown in Figure 2, receives one or more balls 30 each loaded with a spring 31 provided path adjustment means at We remote or distal end. We end region 26 of the piston has a through- passage 32 formed therein. With the piston shown in the position of Figure 2, the throuhpassage 32 is effectively closed by the cylinder wall 22. The cylinder wall has diametrically-opposed passages 33, 34 extending therefrom, passage 33 constituting a gas entry port and passage 34 constituting a gas exit port. The end port is of larger diameter than the exit port and We ports are partially axially offset, whereby the entry port 33 extends either side of the step and exit port 34 is closed off by the lar$er-diameter part of the piston.

As shown particularly in Figure 3, the piston 23 has been subject to system pressures in excess of the predetermined threshold and acting on differential area between the smaller and larger diameter parts of the piston, whereby the piston has been urged to the right as shown, the ball 30 having been urged out of its detent position, against pressure of the spring 31, and also against the pressure of coil spring 28. As shown, excess gas pressure Is then vented through the passage 32, which is in registration with the entry and exit ports 33, 34. When the system pressure has reduced sufficiently, the force exerted by coil spring 28 overcomes any residual pressure left in the system and moves the piston to the left, thereby re-engaging Me ball 30 in the detent groove 29 and re-setting the valve.

Turning now to Figure 4, there is shown in graphical form the effect of increasing ambient ejection temperature on the ejection velocity. The sold line indicates that, without a pressure relief valve according to the invention, the velocity steadily increases with increasing temperature; the dotted line indicates how one pressure relief valve can reduce the pressure at temperatures in excess of say 30 C and the dashed line indicates how the use of two pressure relief valves can maintain the ejection velocity at a reasonably constant level between temperatures say of minus 20 C and plus 40 C.

It has been found that, mine ejector release units according to the invention, acceptable performance can be achieved at temperatures between, say, minus 54 C if charging takes place at a temperature of 15 C, the system still being protected from excess pressures at temperatures as high as say 90 C. Such temperatures are not necessarily encountered in use but, according to the local conditions, may be typical of the temperatures encountered in military applications.

Claims (6)

  1. Claims 1. An ejector release system for an aircraft-mounted store and
    comprising a reserve* for containing a pre-charged gaseous ejection medium, an actuation cylinder connected to the reservoir for effecting ejection of the store and a control valve between the reservoir and actuation cylinder, in which a snap-action pressure relief valve is mounted between the control valve and cylinder to allow excess pressure in the system downstream of the reservoir to be vented or diverted when the pressure exceeds a predetermined threshold pressure.
  2. 2. An ejector release system according to Claire 1, including a secondary reservoir or expansion chamber in communication with the downstream side of the pressure relief valve.
  3. 3. Pin ejector release system according to claim I or claim 2, including two or more pressure relief valves to maintain a more even attenuated ejection pressure over a broad range of operating temperatures.
  4. 4 An ejector release system according to any preceding claim, including two or more actuation cylinders for ejection purposes.
  5. 5. An ejector release system according to claim 4, in which each actuation cylinder is operatively associated with a variable throttle.
  6. 6. An ejector release system substantially as herein described with reference to and as illustrated in Figure I of the accompanying drawings.
    6. pressure relief valve for incorporation in an ejector release system according to any preceding claim, the valve comprising a piston movable in a cylinder between a rearwards or pressure-retaining position and a forwards or pressure-release position, the piston and cylinder including snap action means to retain the piston in the rearwards position until a predetermined threshold pressure is exerted on die piston.
    7. A pressure relief valve according to claim 6, including resilient reset means acting on the piston.
    S. A pressure relief valve according to claim G or claim 7, the piston comprises means lo attenuate the effect of high input pressure Tom tile reservoir.
    9. A pressure relief valve according to claim 8, in which Me piston comprises double-acting surfaces of respective!,, different diameters. a
    10. A pressure relief valve according to claim 8 or claim 9, in which the piston is stepped to define an annular shoulder between the larger and smaller diameter parts, the shoulder constituting a marginal surface area which causes the piston to be urged towards the forwards position under gas input pressure.
    11. A pressure relief valve accordir2 to any of claims 6 to 10, including a vent passage which is Out of registration with the inlet and outlet passages at the rearwards position ofthe piston but is in registration in the forwards position.
    12. A pressure relief valve according to any of claims 6 to 11, in which the piston and cylinder snap action retying means comprises one or more resiliently-loaded balls carried in one of the piston and cylinder and urged into engagement with a corresponding detent Conned in the other of the piston and cylinder in the rearwards or pressure-reining position.
    13. A pressure relief valve according to claim 12, in which the resilient force on the or each
    ball is adjustable.
    14. An ejector release system substantially as herein described win reference to and as illustrated in Figure I of the accompanying drawings.
    15. A pressure relief valve substantially as herein described with reference to and as illustrated in Figures 2 and 3 of Me accompanying dravvings.
    Amendments to the claims have been filed as follows 1. An ejector release system for an aircraft-mounted store and comprising a reservoir for containing a pre-charged gaseous ejection medium, an actuation cylinder connected to the reservoir for effecting ejection of the store and a control valve between the reservoir and actuation cylinder, in which a snap-action pressure relief valve is mounted between the control valve and cylinder to allow excess pressure in the system downstream of the reservoir to be vented or diverted when the pressure exceeds a predetermined threshold pressure.
    2. An ejector release system according to claim 1, including a secondary reservoir or expansion chamber in communication with the downstream side of the pressure relief valve.
    3. An ejector release system according to claim I or claim 2, including two or more pressure relief valves to maintain a more even attenuated ejection pressure over a broad range of operating temperatures.
    4. An ejector release system according to any preceding claim, including two or more I actuation cylinders for ejection purposes.
    5. An ejector release system according to claim 4, in which e,ach actuation cylinder is operatively associated with a variable throttle.
GB0204203A 2002-02-22 2002-02-22 Ejector release unit Withdrawn GB2414782A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0204203A GB2414782A (en) 2002-02-22 2002-02-22 Ejector release unit

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0204203A GB2414782A (en) 2002-02-22 2002-02-22 Ejector release unit

Publications (2)

Publication Number Publication Date
GB0204203D0 GB0204203D0 (en) 2004-11-24
GB2414782A true GB2414782A (en) 2005-12-07

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011028346A1 (en) * 2009-08-24 2011-03-10 Norgren Gt Development Corporation Pneumatic valve
WO2013009747A1 (en) * 2011-07-11 2013-01-17 Crowder Kenneth Lee Fluid pressure actuating mechanism with mechanical lock
FR3013098A1 (en) * 2013-11-08 2015-05-15 Snecma Device for limiting the pressure
WO2019106015A1 (en) * 2017-11-28 2019-06-06 Hachadorian Design & Calculation Gmbh Differential-free, pressure-controlled valve with non-linear control
EP3517880A2 (en) 2018-01-28 2019-07-31 Israel Aerospace Industries Ltd. Ejector rack

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2332630A (en) * 1941-08-07 1943-10-26 Crane Co Snap action relief valve
GB983031A (en) * 1962-06-29 1965-02-10 Caterpillar Tractor Co Hydraulic charging valve
GB1449143A (en) * 1973-05-31 1976-09-15 Cam Gears Ltd Pluralservice hydraulic system
GB1573903A (en) * 1977-05-24 1980-08-28 Auto Research Corp Resettable pressure responsive valve
GB2230076A (en) * 1989-03-04 1990-10-10 Heatrae Sadia Heating Ltd Pressure relief valve
GB2266579A (en) * 1992-04-16 1993-11-03 Meggitt Uk Ltd Gas operated injection system
US5341838A (en) * 1993-08-23 1994-08-30 Powell Walter W Direct spring pressure operated valve
GB2280736A (en) * 1989-07-06 1995-02-08 Ml Aviat Ltd Store ejector
US5583312A (en) * 1995-03-01 1996-12-10 Mcdonnell Douglas Helicopter Company Cold gas ejector rack
GB2377267A (en) * 2000-04-03 2003-01-08 Larry Rayner Russell Dual snap action for valves

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2332630A (en) * 1941-08-07 1943-10-26 Crane Co Snap action relief valve
GB983031A (en) * 1962-06-29 1965-02-10 Caterpillar Tractor Co Hydraulic charging valve
GB1449143A (en) * 1973-05-31 1976-09-15 Cam Gears Ltd Pluralservice hydraulic system
GB1573903A (en) * 1977-05-24 1980-08-28 Auto Research Corp Resettable pressure responsive valve
GB2230076A (en) * 1989-03-04 1990-10-10 Heatrae Sadia Heating Ltd Pressure relief valve
GB2280736A (en) * 1989-07-06 1995-02-08 Ml Aviat Ltd Store ejector
GB2266579A (en) * 1992-04-16 1993-11-03 Meggitt Uk Ltd Gas operated injection system
US5341838A (en) * 1993-08-23 1994-08-30 Powell Walter W Direct spring pressure operated valve
US5583312A (en) * 1995-03-01 1996-12-10 Mcdonnell Douglas Helicopter Company Cold gas ejector rack
GB2377267A (en) * 2000-04-03 2003-01-08 Larry Rayner Russell Dual snap action for valves

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011028346A1 (en) * 2009-08-24 2011-03-10 Norgren Gt Development Corporation Pneumatic valve
WO2013009747A1 (en) * 2011-07-11 2013-01-17 Crowder Kenneth Lee Fluid pressure actuating mechanism with mechanical lock
CN103717486A (en) * 2011-07-11 2014-04-09 肯尼思·李·克劳德 Fluid pressure actuating mechanism with mechanical lock
FR3013098A1 (en) * 2013-11-08 2015-05-15 Snecma Device for limiting the pressure
WO2019106015A1 (en) * 2017-11-28 2019-06-06 Hachadorian Design & Calculation Gmbh Differential-free, pressure-controlled valve with non-linear control
EP3517880A2 (en) 2018-01-28 2019-07-31 Israel Aerospace Industries Ltd. Ejector rack
US10640213B2 (en) 2018-01-28 2020-05-05 Israel Aerospace Industries Ltd. Ejector rack

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Publication number Publication date
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