CN103963988A - Aircraft short-range takeoff air catapult system - Google Patents
Aircraft short-range takeoff air catapult system Download PDFInfo
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- CN103963988A CN103963988A CN201310045934.2A CN201310045934A CN103963988A CN 103963988 A CN103963988 A CN 103963988A CN 201310045934 A CN201310045934 A CN 201310045934A CN 103963988 A CN103963988 A CN 103963988A
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- ejection
- ejection system
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Abstract
Disclosed is an airplane short-range takeoff air catapult system. Taking off of an aircraft by the aid of a catapult from places under severe limitations of take-off runway length, such as aircraft carriers and miniature airports is of great significance. According to the airplane short-range takeoff air catapult system, compressed air is used as energy medium to catapult the aircraft; catapulting energy is obtained by thermal expansion of the compressed air. The airplane short-range takeoff air catapult system has the advantages of simple structure and light weight.
Description
One, technical field
The aircraft short distance the present invention relates to air ejection system (hereinafter to be referred as air ejection system) that takes off belongs to military, aviation field, and it is applicable to the taking off of the serious limited occasion of Take-Off Field Length such as aircraft carrier, miniature airport and launches.
Two, background technology
In the serious limited occasion of the landing airdrome lengths such as aircraft carrier, miniature airport, aircraft takes off significant by ejector.The ejector adopting on aircraft carrier at present has steam ejection and the large class of electromagnetic launch two.The air ejection system the present invention relates to utilizes pressurized air as the energy medium of cataplane, and it has the advantages that structure is simple, weight is lighter.
Three, summary of the invention
1, the air ejection system the present invention relates to belongs to military, aviation field, and it is applicable to taking off under the limited occasions of Take-Off Field Length such as aircraft carrier, miniature airport and launches.
2, this air ejection system is usingd pressurized air as energy medium, utilizes pressurized air heat absorption to expand to obtain and launches energy.
3, the pressurized air of this air ejection system is obtained by turbocompressor and piston compressor collaborative work, and turbocompressor is born one-level compression duty, and piston compressor is born two-stage compression task; After air compressing, be stored in gas storage equipment.
4, the required power of this air ejection system pressurized air is provided by automotive gas turbine.
5, between the ejection mechanism of this air ejection system and aircraft, adopt unidirectional power transmission; During cataplane, combustion fuel makes the pressurized air in gas storage equipment absorb heat and flow into launch cylinder and expand, and high pressure air promotes to launch the piston in cylinder, and piston driving ejection mechanism makes aircraft accelerate to take off; Ejection mechanism during near ejection travel end, brakes ejection mechanism by brake equipment, and aircraft ejects.
When 6, this air ejection system is worked, pressurized air is insufficient expansion in launching cylinder, after having launched at every turn, launches waste gas streams and carries out reexpansion to automotive gas turbine.
7, this air ejection system can adopt two-way launching or unidirectional form of launching.
Four, accompanying drawing explanation
Fig. 1, Figure 2 shows that and the principle of work of this air ejection system Figure 1 shows that unidirectional ejection system, Figure 2 shows that two-way ejection system.In figure, respectively number corresponding component Name as follows:
11---turbocompressor
12---gas-turbine combustion chamber
13---automotive gas turbine
21---flywheel (optional)
22---power-transfer clutch (optional)
23---reductor (change speed gear box)
30---piston compressor
41,42---cooling vessel
50---gas storage equipment (gas tank)
60,61A, 61B, 62A, 62B, 63---air valve
70A, 70B---ejector combustion chamber
80---launch cylinder
90---ejection piston
91---heat-resistant flexible drag-line
92---track adjusting wheel
93---launching cradle
94A, 94B---ejection mechanism drg
95---back haul system (being applicable to unidirectional launching)
96---takeoff runway
Five, the specific embodiment
1, the composition of air ejection system
This air ejection system is mainly partly comprised of following functions:
(1) power and driving system---automotive gas turbine outputting power, through the system (automotive gas turbine 13, flywheel 21, power-transfer clutch 22, reductor 23 etc. belong to power and drive train assemblies) of the process rear drive compressors such as transmission, inertia energy storage, speed change.
(2) air compression system---consume the compressed-air actuated system of mechanical energy (turbocompressor 11, piston compressor 30 etc. belong to air compression system assembly).
(3) launch pneumatic system---by compressed-air actuated Conversion of Energy be the mechanical energy that needs of ejection Pneumatic assembly (launch cylinder 80, piston 90 and launch various air valves in gas circuit etc. belong to launch pneumatic system assembly).
(4) launch force transmission mechanism---the power of ejection piston is passed to mechanism's (heat-resistant flexible drag-line 91, track adjusting wheel 92, launching cradle 93 etc. belong to launch force transmission mechanism assembly) of launched aircraft.
(5) brake system---after having launched, allow the system of ejection mechanism stop motion.
(6) fuel feeding combustion systems---contain automotive gas turbine and launch the fuel feeding combustion systems (gas-turbine combustion chamber 12, ejector combustion chamber 70A, 70B etc. belong to fuel feeding combustion systems assembly) in gas circuit.
(7) cooling system---contain compression process cooling vessel and optionally to launching cylinder, carry out cooling system.
2, principle of work and specifically implement approach
The pneumatic process that launches of this air ejection system can be described as " one-level compression → cooling → two-stage compression → cooling → gas storage → pressurized air is absorbed heat and expanded (launching) → launch waste gas throttling (flowing back to automotive gas turbine) → air heat absorption expansion driven turbine (outputting power) ".
The mechanics principle of this air ejection system work is: automotive gas turbine outputting power drives turbocompressor and piston compressor (turbocompressor and piston compressor are born respectively one-level, two-stage compression task); Compressor produces high pressure air and deposits in gas storage equipment; While needing cataplane, the high pressure air in gas storage equipment absorbs heat and enters and launches cylinder 80 expansion driven pistons 90, and piston 90 drives launching cradle 93 by drag-line 91, and launching cradle 93 is passed to energy in the aircraft that need to take off.
(1) gas compression processes
The starting point of air compressing process is turbocompressor inlet end, after compression finishes, deposits gas storage equipment in, and in this process, concrete link is as follows:
(1) inlet end of intake process---turbocompressor 11 is from realm of nature air amount.
(2) one-level compression process---turbocompressor 11 is carried out one-level compression duty.
(3) compression intercooling process---after one-level compression, air stream carries out cooling through cooling vessel 41.
(4) two-stage compression process---cooled air enters piston compressor 30 and again compresses.
(5) cooling, gas storage---air is after piston compressor compression, and the cooling vessel 42 of flowing through carries out cooling, the gas storage equipment 50 of restoring (gas tank).
(2) ejection process
When needs cataplane, gas storage equipment discharges pressurized air, combustion chamber 7A (or 7B) is for oil firing, air heat absorption heats up and flows into and launches cylinder 80 (expansion), the both sides of piston 90 produce pressure reduction, piston accelerated movement under the differential pressure action of both sides drives launching cradle through drag-line, thereby aircraft is ejected.
(1) ejection process of unidirectional ejection system
In unidirectional ejection system shown in Fig. 1, launch when initial, piston 90 is positioned at the right-hand member of cylinder 80, close gas check valve 62A, open air valve 61A, combustion chamber 70A makes air heat absorption for oil firing, air after heat absorption flows into and launches cylinder 80 and expand, and promotes piston 90 to left movement; The air in cylinder left side " is extruded " cylinder and is flowed to automotive gas turbine when piston is done sling movement; Piston is during near cylinder left end, and aircraft is ejected, and closes gas check valve 61A, and drg 94A implements braking to launching cradle, opens air valve 62A and control its aperture to make to launch waste gas and by certain flow, enter automotive gas turbine 13 and carry out reexpansion.
After unidirectional ejection system shown in Fig. 1 often completes and once launches, ejection mechanism needs " backhaul ", could carry out and launch task next time." backhaul " task of ejection structure completes (winch that back haul system can adopt " towed ") by back haul system 95.Launch waste gas streams and strile-back after gas-turbine eliminates piston 90 both sides pressure reduction, take-off the brake system 94A, opens air valve 62A completely, and back haul system 95 is withdrawn into launching cradle 93 and piston 90 to launch start position.
(2) ejection process of two-way ejection system
In two-way ejection system shown in Fig. 2, aircraft A launches when initial, piston 90 is positioned at the right-hand member of cylinder 80, close gas check valve 62A, 61B, open air valve 61A, 62B, release the brake 94B, combustion chamber 70A makes air heat absorption (combustion chamber 70B does not work) for oil firing, high pressure air flows into cylinder 80 and expands from right side, promote piston 90 to left movement, piston is during near cylinder left end, close gas check valve 61A, aircraft A is ejected, drg 94A implements braking to launching cradle, open air valve 62A and control its aperture and make to launch waste gas and by certain flow, get back to automotive gas turbine 13 and carry out reexpansion.Launching the strile-back process of gas-turbine of waste gas streams should finish before the upper once task of launching starts.
Cataplane B is identical with the principle of cataplane A, and difference is only that the switching mode of air valve 61A, 61B and 62A, 62B is exchanged, the fuel feeding igniting exchange of combustion chamber 70A, 70B, and the use of drg 94A, 94B exchange.
The ejection mechanism of two-way ejector adopts annular drag-line power transmission, and piston is positioned at the two ends of launching cylinder all can carry out the task of launching, so it need not back haul system.
(3) launch the reexpansion of waste gas
For making ejection force maintain a comparatively desirable level, ejection process should be avoided air expansion, and too fully (if air expands fully, the front and back air pressure range of decrease that expands is large, will cause ejection force decay serious, to launching effect, has adverse effect; Meanwhile, air fully expands, and gas storage pressure fluctuation is large, may affect compression system working stability).Therefore, launching expands finish after, the air pressure in cylinder can maintain higher level, when launching waste gas pressure higher than the normal air inlet pressure of automotive gas turbine, by air valve 62A, 62B reducing pressure by regulating flow, make it by certain pressure intensity and flow, get back to automotive gas turbine and carry out reexpansion.
(4) heat energy utilization and interchange of heat
The energy of this air ejection system cataplane is to come from " heat energy " after all, in ejection system, there are two nodes to need heat supply, one place is gas-turbine combustion chamber 12, and heat supply improves rear drive turbine by air energy level herein, thereby obtains the required power of pressurized air; Another place provides heat energy to air when launching expansion, and the heat energy part providing while launching is converted into the kinetic energy of sling movement system, and a part is launched waste gas absorption.
Combustion turbine exhaustion temperature is generally higher, if have between the relative gas storage temperature of exhaust heat (or gas turbine inlet air temperature), be enough to the temperature difference of be worth utilizing, can utilize by H Exch is set the waste gas residual heat (do not illustrate in accompanying drawing waste gas heat utilization) of automotive gas turbine.
In this air ejection system working process, in compression process, air themperature raises, and from reducing compression energy consumption, mitigation system thermal load is considered, can take cooling between compression stage, gas storage cooling provision to reduce compressed-air actuated temperature.In addition, in practical application, can optionally to launching cylinder, take cooling provision.
(5) mechanical drive and braking
This air ejection system ejection force originates from the draught head that launches piston both sides, and the piston launching in cylinder is the starting point of ejection force, and the power of piston can pass to the target (aircraft) that need to launch by various possible approach.For shortening the length of arranging ejection mechanism, in Fig. 1, Fig. 2, adopted flexible cable power transmission, and arranged that guiding wheels turn to drag-line.(when the situation of ejection mechanism length without strict restriction, can cancel steering hardware, launching cradle and cylinder are disposed in order, now can adopt rigid rod to transmit ejection force between piston and launching cradle).
After the task of launching finishes, ejection mechanism, in high-speed motion state, need take brake measure to make ejection mechanism braking, in the schematic diagram shown in Fig. 1, Fig. 2, by the braking that drg is realized ejection mechanism is set near sling movement terminal." arrester wires " mechanism when drg can adopt similar aircraft to land on aircraft carrier, also can adopt friction braking or other actv. brake mode.In two-way ejection system, need establish two cover drgs (94A, 94B), two cover drgs take turns to operate.
(6) other
(1) use of flywheel is selected
During this air ejection system work, piston 90 is very fast at the kinematic velocity of ejection travel middle and later periods, the rapid movement of piston 90 make the air that launches cylinder 80 mesolow sides " be extruded " and flow to automotive gas turbine 13 with very fast speed, now, if charge flow rate and the pressure of automotive gas turbine 13 are too high, will produce the adverse effect of two aspects: the one, may affect the normal work of automotive gas turbine 13; The 2nd, can reduce and launch effect (the too high ejection force that causes of ejection piston back pressure declines).In practical application, the air inlet pressure of automotive gas turbine when initial can be launched by reduction, to avoid this two unfavorable factors.
Due to also corresponding reduction of its outputting power after the air inlet pressure reduction of automotive gas turbine, if the automotive gas turbine outputting power range of decrease is excessive when having influence on air compressor and normally working, flywheel 21 can be set, utilize inertia energy storage the supplementing as automotive gas turbine short time under power of flywheel.
(2) automotive gas turbine and launch the flow regulating problem between gas circuit
During this air ejection system work, depending on different technologies level and user demand, the charge air that driving automotive gas turbine is necessary and the relation of launching between gas circuit flow have three kinds of possibilities (implication of " flow " is herein " average discharge "):
1., automotive gas turbine flow=launch gas circuit flow
2., automotive gas turbine flow > launches gas circuit flow
3., automotive gas turbine flow < launches gas circuit flow
Situation to " automotive gas turbine flow=launch gas circuit flow ", in accompanying drawing air valve 63 when system is normally moved in closed condition.
The essence of " automotive gas turbine flow > launches gas circuit flow " is: only depend on the charge air that launches gas circuit to be not enough to provide and to launch the required mechanical energy of pressurized air in gas circuit through the automotive gas turbine acting of expanding, need the extra airshed that increases automotive gas turbine obtain more power.Now can there is following solution: the one, the exhaust side of turbocompressor is communicated with gas turbine inlet air end, allow the direct supply automotive gas turbine of pressurized air of turbocompressor generation (while adopting this scheme, if launch the gas turbine inlet air pressure of initial point requirement lower than the drain pressure of turbocompressor, can block the supply gas circuit between turbocompressor and automotive gas turbine by air valve 63) temporarily; The 2nd, can outside ejection system shown in the drawings, set up turbo-power unit (containing air compressor and gas turbine), to strengthen compressed-air actuated power.
If " automotive gas turbine flow < launches gas circuit flow " can vent Partial shrinkage air before automotive gas turbine.(also can avoid this situation to occur as adjust turbine inlet temperature by adjusting Specifications in each link, make system get back to the situation of " automotive gas turbine flow=launch gas circuit flow ").
(3) startup of ejection system and shutdown
The operation of this air ejection system is by gas turbine drives, and the startup of ejection system is from starting automotive gas turbine.After automotive gas turbine starts, as long as gas storage pressure arrives the air pressure that launches requirement, ejector can be devoted oneself to work.
The startup of automotive gas turbine can be driven by external force (as starter motor is set).While driving automotive gas turbine startup by external force, air valve 63 is opened, combustion chamber 12 is for oil firing, and automotive gas turbine drives turbocompressor 11 running pressurized airs, and pressurized air enters automotive gas turbine expansion acting and gets final product entry into service after combustion chamber 12 heat absorptions.When system has just started, for alleviating running resistance, can disconnect the power-transfer clutch 22 between automotive gas turbine 13 and piston compressor 30, air valve 60 is placed in closed condition; After gas turbine rotary speed is promoted to normal level, the power-transfer clutch 22 that closes, opens air valve 60, makes piston compressor enter mode of operation.
While having pressurized air in gas storage equipment, ejection system can be disobeyed outer power and be driven, and directly utilizes comperssed air starting automotive gas turbine; In Fig. 1, air valve 61A, 62A to be opened simultaneously, the pressurized air in gas storage equipment can flow to its running of gas turbine drives (when gas storage pressure is during higher than automotive gas turbine operating pressure, 61A need be placed in to throttle).
When ejection system need be shut down, close air valve 61A, 61B, stop control lever allows, and gas turbine inlet air pressure reduces gradually and slows down, and when rotating speed is reduced to certain level, closes gas check valve 60 and cuts off compression gas circuit, and avoid gas leakage.
(4) safety measure
This air ejection system be high-pressure pneumatic equipment, in order to avoid, air pressure is too high causes danger, and should limiting valve (as can be limiting valve be set in air valve 60 front and back, not shown in the figures) be set at appropriate position.
(5) other purposes
Suitable in the situation that, the source of the gas that the gas storage equipment of this air ejection system can be used as other equipment is used; In addition,, if having ready conditions, the power of automotive gas turbine output also can be used for driving miscellaneous equipment.
Claims (7)
1. the aircraft short distance the present invention relates to air ejection system (hereinafter to be referred as air ejection system) that takes off belongs to military, aviation field, and it is applicable to taking off under the limited occasions of Take-Off Field Length such as aircraft carrier, miniature airport and launches.
2. this air ejection system is usingd pressurized air as energy medium, utilizes pressurized air heat absorption to expand to obtain and launches energy.
3. the pressurized air of this air ejection system is obtained by turbocompressor and piston compressor collaborative work, and turbocompressor is born one-level compression duty, and piston compressor is born two-stage compression task; After air compressing, be stored in gas storage equipment.
4. the required power of this air ejection system pressurized air is provided by automotive gas turbine.
5. between the ejection mechanism of this air ejection system and aircraft, adopt unidirectional power transmission; During cataplane, combustion fuel makes the pressurized air in gas storage equipment absorb heat and flow into launch cylinder and expand, and high pressure air promotes to launch the piston in cylinder, and piston driving ejection mechanism makes aircraft accelerate to take off; Ejection mechanism during near ejection travel end, brakes ejection mechanism by brake equipment, and aircraft ejects.
6., when this air ejection system is worked, pressurized air is insufficient expansion in launching cylinder, after having launched at every turn, launches waste gas streams and carries out reexpansion to automotive gas turbine.
7. this air ejection system can adopt two-way launching or unidirectional form of launching.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310045934.2A CN103963988A (en) | 2013-02-05 | 2013-02-05 | Aircraft short-range takeoff air catapult system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310045934.2A CN103963988A (en) | 2013-02-05 | 2013-02-05 | Aircraft short-range takeoff air catapult system |
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| CN103963988A true CN103963988A (en) | 2014-08-06 |
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| CN201310045934.2A Pending CN103963988A (en) | 2013-02-05 | 2013-02-05 | Aircraft short-range takeoff air catapult system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106555782A (en) * | 2015-09-29 | 2017-04-05 | 南京理工大学 | Pressure-air rodless cylinder ejector working stage piston trajectory method |
| CN106864765A (en) * | 2015-12-11 | 2017-06-20 | 章华正 | flywheel ejector |
| CN109178335A (en) * | 2018-08-16 | 2019-01-11 | 刘贵文 | A kind of fan gas operated boosting aircraft catapult |
| WO2020010611A1 (en) * | 2018-07-13 | 2020-01-16 | 彭子航 | Forward-thrust-type launch process method for aerospace vehicle, and apparatus therefor |
-
2013
- 2013-02-05 CN CN201310045934.2A patent/CN103963988A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106555782A (en) * | 2015-09-29 | 2017-04-05 | 南京理工大学 | Pressure-air rodless cylinder ejector working stage piston trajectory method |
| CN106555782B (en) * | 2015-09-29 | 2018-09-25 | 南京理工大学 | Pressure-air rodless cylinder ejector working stage piston trajectory method |
| CN106864765A (en) * | 2015-12-11 | 2017-06-20 | 章华正 | flywheel ejector |
| WO2020010611A1 (en) * | 2018-07-13 | 2020-01-16 | 彭子航 | Forward-thrust-type launch process method for aerospace vehicle, and apparatus therefor |
| CN109178335A (en) * | 2018-08-16 | 2019-01-11 | 刘贵文 | A kind of fan gas operated boosting aircraft catapult |
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Addressee: Zeng Li Document name: Notification that Application Deemed to be Withdrawn |
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Application publication date: 20140806 |