CN103507964A - Aircraft catapult-assisted take-off device and aircraft landing stopping device - Google Patents
Aircraft catapult-assisted take-off device and aircraft landing stopping device Download PDFInfo
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- CN103507964A CN103507964A CN201210225282.6A CN201210225282A CN103507964A CN 103507964 A CN103507964 A CN 103507964A CN 201210225282 A CN201210225282 A CN 201210225282A CN 103507964 A CN103507964 A CN 103507964A
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Abstract
Provided is an aircraft catapult-assisted take-off device. According to the aircraft catapult-assisted take-off device, compressed air serves as a power source, an air cylinder works to pull a sliding vehicle to accomplish aircraft catapult, and acting force of the aircraft catapult-assisted take-off device is large, and is adjustable. The aircraft catapult-assisted take-off device is composed of a catapult system, a buffering system and a sliding vehicle return system in an organically combined mode, wherein the components of the aircraft catapult-assisted take-off device are common mechanical devices, and are convenient to machine, reliable in operation and convenient to maintain. Provided is an aircraft landing stopping device. According to the aircraft landing stopping device, air serves as a medium, when the air is compressed, resistance is produced, and effective stopping can be carried out on a sliding aircraft. The aircraft landing stopping device is simple and compact, components of the aircraft landing stopping device cannot be easily damaged, stopping force is adjustable, the resistance is gentle, and the aircraft landing stopping device is applicable to landing stopping of various shipboard aircrafts.
Description
Technical background
The invention belongs to carrier-based aircraft catapult-assisted take-off and aircraft landing and stop equipment
Background technology
At present, aircraft carrier sliding the jumping up of having taken off flies, and steam ejection takes off, and takes off vertically and the electromagnetic launch developed takes off.
Sliding jumping up flies, and take-off weight is affected, fuel load no matter, or the relative catapult-assisted take-off of bullet-loading capacity all will be lacked.Therefore affect combat radius and fight capability.
Steam ejection takes off, and it launches cylinder length should be identical with required catapult-assisted take-off distance, and cylinder body needs the unified processing of sectional, while launching piston move ahead below cylinder body opening will be with the shutoff of envelope band, to guarantee steam pressure, complex structure, rapid wear, steam can not reclaim, and water consumption is large.
Take off vertically, aircraft is relatively little, and load is few, affects combat radius and fighting capacity.
It is to be completed by linear electric motors that electromagnetic launch takes off.Linear electric motors requirement on machining accuracy is high, and dustproof and waterproof facility is indispensable, needs fast charge, rapid discharge.The corresponding increasing of its generator set thus.Large-scale electric energy storage device is also indispensable.The draw gear of high-speed motion should have brake equipment at transmitting end, is also very complicated.
At present, an aircraft carrier housing has been bought from Ukraine by known China, sea examination after repacking, and it belongs to the sliding flight mother that jumps up.
Aircraft landing arrester is to adopt arrester wires substantially, and difference is that its damping mode is different.Some employing liquid gas mixing dampings, have gravity damping in early days, also can hydro retarder dampings, and electromagnetic damping, heavy load damping.But soft with regard to damping, briefly, take air as medium be comparatively ideal method.
Summary of the invention
The present invention aims to provide a kind of airplane catapult launching apparatus and aircraft landing arrester.
The present invention is achieved in that airplane catapult launching apparatus comprises ejection system, buffer system, slide trucks return system.Airplane catapult launching apparatus is put in aircraft carrier flying-off deck Xia cabin.Ejection system is provided with storage tank [13], through pipeline, gate valve [12], flow valve [11], be connected with cylinder [8], pulley combination [7] is equipped with in cylinder [8] piston rod end, is installed with little cable wire [6] by wire cable connector [49] and main tow rope [4] combination on pulley combination [7], and main tow rope [4] is connected with slide trucks [1] through main track adjusting wheel [5].Slide trucks [1] is directed to device [3] and is limited in guide track [2].Open gate valve [12], storage tank [13] compressed air enters cylinder [8] through flow valve [11] and promotes piston rod and stretch out along piston rod end righting track and move ahead, affect little cable wire [6], main tow rope [4], slide trucks [1] motion, make to take off taking off of deck.
Airplane catapult launching apparatus buffer system is provided with secondary cable wire [14], winding number circle is on swift [16], through secondary track adjusting wheel [15] two ends, be connected with slide trucks [1] rear and front end respectively, swift [16] right-hand member has the input end gear engagement of gear and damping drop-gear box [17], after slowing down, its gear of output end and damping cylinder [18] piston rod tooth bar [39] engagement, make being compressed in minor diameter cylinder compared with rarefied air in damping cylinder [18], when the piston of damping cylinder [18] stressed during with cylinder [8] tension balanced, slide trucks [1] stop motion.
The swift [16] of airplane catapult launching apparatus slide trucks return system is connected with the gear on left end swift [16] axle through power-transfer clutch [19].The output shaft gear engagement of this gear and slide trucks return drop-gear box [20].While having a power failure brake adjustable frequency motor [21] energising, power drives swift [16] to rotate in the opposite direction through slide trucks return drop-gear box [20], power-transfer clutch [19], make slide trucks [1] return, during return, slide trucks [1] wedge has contacted bearing pin and has shunk and extend action with the bearing pin of registration device [9], make slide trucks [1] location, the brake variable-frequency motor [21] that simultaneously makes to have a power failure has a power failure brake and quits work.Completing an airplane catapult takes off and slide trucks [1] return.
Cylinder [8] piston and damping cylinder [18] piston are comprised of piston body [22], y-type seal ring [23], wear-resistant guiding ring [24], oil resevoir [25], lubricating oil filler plug [26], lubricating oil through hole [27].
Aircraft landing arrester major equipment is arranged under aircraft landing deck in cabin, establishes stage casing arrester wires [28], horizontal guide sheave [30], waterproof case [31] above aircraft landing deck.Stage casing arrester wires [28] is connected by arrester wires head [29] with steel cable [33], steel cable [33] is on reel [34], reel [34] right-hand member gear [46] and drop-gear box [37] input shaft gear [47] engagement, cylinder [35] piston rod tooth bar [39] engagement in drop-gear box [37] output shaft gear [38] and damping.Cylinder in two dampings [35] rear portion was communicated with by two cylinder communicating pipes [42], and was connected with aie escape valve [41], valve [49], main valve, air outlet valve [43], flow-controlling gate [44], compression gas tank [45].When aircraft landing, pintle drives stage casing arrester wires [28] to move ahead; and then its gas in the jar of cylinder [35] piston compression in band dynamic damping; drive venting control stalk [40] to slide simultaneously; its male and female face makes aie escape valve [41] be interrupted venting and enters compression gas tank [45]; make the gas in cylinder in damping [35] keep suitable pressure; aircraft is slided with suitable resistance; the speed that the apomecometer that tests the speed [48] of reel [34] side measures or distance allow to shut down; brake disc [36] can self-actuating brake, and aircraft stops immediately.After the de-rope of aircraft pintle, shutoff valve [49], open gas in air outlet valve [43], compression gas tank [45] under flow-controlling gate [44] is controlled, with suitable flow, enter damping in cylinder [35] band movable reel [34] rotated backward rope closing.
Accompanying drawing explanation
Fig. 1---airplane catapult front view.Fig. 2---A---A birds-eye view (being that slide trucks birds-eye view and D are to view).Fig. 3---airplane catapult equipment birds-eye view and cylinder E---E cutaway view.Fig. 4---aircraft ejection kit damping system and slide trucks return system C-C birds-eye view.Aircraft landing arrester is arranged lateral plan to Fig. 5---aircraft landing arrester is arranged birds-eye view Fig. 6---.
1, slide trucks 2, guide track 3, guide piece 4, main tow rope 5, main track adjusting wheel 6, little cable wire 7, pulley combination 8, cylinder 9, registration device 10, idler pulley 11, flow valve 12, gate valve 13, storage tank 14, secondary cable wire 15, secondary track adjusting wheel 16, swift 17, damping drop-gear box 18, damping cylinder 19, power-transfer clutch 20, slide trucks return drop-gear box 21, brake variable-frequency motor 22 has a power failure, piston body 23, y-type seal ring 24, wear-resistant guiding ring 25, trapped fuel groove 26, lubricating oil filler plug 27, lubrication hole 28, stage casing arrester wires 29, arrester wires head 30, horizontal guide sheave 31, waterproof case 32, vertical guide sheave 33, steel cable 34, reel 35, in damping, cylinder 36, brake disc 37, drop-gear box 38, drop-gear box gear of output end 39, piston rod tooth bar 40, aie escape valve control stalk 41, aie escape valve 42, two cylinder communicating pipes 43, air outlet valve 44, flow-controlling gate 45, compression gas tank 46, right-hand member gear 47, input shaft gear 48, apomecometer 49 tests the speed, valve is described in further detail the present invention by reference to the accompanying drawings
Airplane catapult launching apparatus as shown in Figure 1, Figure 2, Fig. 3, Fig. 4, shown in, propulsion source is pressurized air, pressurized air in storage tank [13] is through gate valve [12], flow valve [11] enters cylinder [8], promotion piston moves ahead, and four movable pulleys of the pulley combination [7] that install piston rod end travel forward with same speed, and the wire rope handling of pulley combination [7] is as shown in X wire rope handling figure, fast line traction slide trucks [1] moves ahead with the speed of four times, and slide trucks [1] helps taking off on deck.Rod end is provided with slide block and inserts in end righting track, and confined piston end moves along a straight line, and plays and supports own wt and strengthen the anti-unstability ability of piston rod.Piston is provided with trapped fuel groove [25], has lubricating oil in groove, so as lubricating cylinder [8], six, the total pulley of pulley combination [7], two are fixing, and four movable pulley symmetries are contained in piston rod end, every pulley double flute.Slide trucks [1] is to rely on guide piece [7] constraint along guide track [2] operation, and upper and lower spacing by rectangular shaped slider, left and right is spacing by circular slide plate.
While taking off, the speed of slide trucks [1] is very fast, its kinetic energy is huge, in airplane catapult launching apparatus, designed damping system thus, it is to go up a few by being wrapped in swift [16], is connected on respectively the secondary cable wire [14] of slide trucks [1] rear and front end, swift [16] through secondary track adjusting wheel [15] two ends, damping drop-gear box [17], damping cylinder [18] forms.When slide trucks [1] is moved to stem cataplane, by secondary cable wire [14], affect swift [16] to rotate.The gear engagement of swift end gear and damping drop-gear box [17] input end, after slowing down, damping drop-gear box [17] gear of output end makes piston rod tooth bar [39] straight-line motion of damping cylinder [18], what its piston compression damping cylinder [18] was interior enters minor diameter cylinder compared with rarefied air, when launching tractive force and dumping force balance, slide trucks [1] stops, now take off, complete and launch.
Slide trucks [1] is got back to airplane catapult initial position and is realized by a set of slide trucks return system.It is comprised of secondary cable wire [14], swift [16], power-transfer clutch [19], slide trucks return drop-gear box [20], the brake variable-frequency motor [21] that has a power failure.After brake variable-frequency motor [21] energising that has a power failure, brake un-brake, starts to rotarily drive slide trucks return drop-gear box [20] and rotates, and the power-transfer clutch that closes [19], drives swift [16] to rotate in the opposite direction.Simultaneously, pressure gas in minor diameter cylinder promotes the piston rod rack linear motion of damping cylinder [18], through damping drop-gear box [17], make the equidirectional rotation of swift [16], common traction slide trucks [1] return, when arriving airplane catapult initial position, the wedge of slide trucks [1] is stretched bearing pin one contracting one of registration device [9] and is pinned slide trucks [1].The brake variable-frequency motor [21] that simultaneously makes to have a power failure is stopped power supply and checks electrical motor.Now, the piston rod of cylinder [8] is pulled in cylinder [8], and gas in the jar is pushed back storage tank [13], completes slide trucks [1] return process.After the second airplane catapult-assisted take-off work is ready, first make power-transfer clutch [19] separation, then make the bearing pin of registration device [9] separated with slide trucks [1], the second airplane starts by catapult-assisted take-off.
Aircraft landing arrester is as Fig. 5, shown in Fig. 6, during aircraft landing, when its pintle hooks stage casing arrester wires [28], because hauling steel cable [33], the inertia of aircraft rotates through horizontal guide sheave [30], waterproof case [31], vertical guide sheave [32] band movable reel [34], reel [34] right-hand member gear [46] and drop-gear box [37] input shaft gear [47] engagement, after slowing down, drop-gear box [37] gear of output end [38] makes piston rod tooth bar [39] promote gas in the piston compressing cylinder of cylinder [35] in damping and produces damping, produces the Intercepting effects to landing aircraft.Consider the impact of aircraft pintle pulling force on aircaft configuration intensity, need suitable application force and suitable coasting distance, the pressure of cylinder in damping [35] should adapt with the application force that aircraft is allowed, and should be interrupted step-down.Aie escape valve [41] and aie escape valve control stalk [40] have been designed thus, aie escape valve control stalk [40] is fixed on piston rod tooth bar [39] end, and be parallel to piston rod tooth bar [39], aie escape valve control stalk [40] is provided with male and female face enters in compression gas tank [45] venting of aie escape valve [41] interruption.When during because of aircraft landing, pintle hooks stage casing arrester wires, it can not be theoretical mid point.Aircraft is different sliding Shi， both sides rope stretching length like this, will cause the pressure of cylinder in two dampings [35] different, two ropes are different to the pulling force of aircraft, in order to overcome this problem, designed two cylinder communicating pipes [42] between cylinder [35] in damping, keep the equilibrium of pressure of two cylinders.When aircraft landing slide certain distance or coasting speed slowly to a certain extent after, the apomecometer that tests the speed [48] of reel [34] side is controlled brake disc [36] brake automatically, aircraft stops sliding.After the de-rope of aircraft pintle, should first shutoff valve [49], dish [36] gets off the brakes, turn-on flow rate control cock [44], gas in compression gas tank [45], under flow-controlling gate [44] is controlled, with suitable flow, enter damping in cylinder [35], band movable reel [34] has rotated rope closing in the opposite direction.
The specific embodiment
Airplane catapult launching apparatus all devices is all arranged on to be taken off under deck in cabin, minute three layers of layout.Upper strata has steel structure to be connected with hull structure, the guide track 2 of steel structure side installing slide trucks 1, and idler pulley 10 is equipped with in steel structure bottom surface, and registration device 9 is also fixed on steel structure side.Middle level is arranged and is mainly contained storage tank 13, cylinder 8 and piston rod end righting track, and their base is all connected with hull structure.Storage tank 13 air inlet pipe nipples are connected with middle pressure Air compressor.Lower floor arranges swift 16, damping drop-gear box 17, damping cylinder 18, slide trucks return drop-gear box 20, idler pulley 10 and the controller switching equipment that has a power failure brake variable-frequency motor 21 and match.Main track adjusting wheel 5 bases, secondary track adjusting wheel 15 bases, dead line bottom seat are connected with hull structure.Aircraft carrier uppermost deck be in fact one wider than the platform of length of hull than hull.Cabin below it is mainly hangar, shoots district, fueling area, and aircraft maintenance district, stops battery limits, airplane catapult battery limits etc.Divide storehouse to require large, its structural framing requires large, and the airplane catapult equipment of taking off divides three layers of its pedestal of layout and hull structure to be connected with difficulty, just need to establish separately structure and specifically implement.Various device is all conventional common apparatus, single-piece manufacture, unified installation, unified debugging.
Aircraft landing arrester major equipment is arranged in the underdeck cabin of aircraft landing, Jin You stage casing arrester wires 28 above, horizontal guide sheave 30, waterproof case 31, steel cable 33 enters cabin through deck opening, and opening should be avoided strong aggregate, vertical guide sheave 32 should have anti-steel cable to go out race measure, should be provided with damping wheel so that when rope closing, it is tight making the steel cable between vertical guide sheave 32 and reel 34, avoid steel cable 33 on reel 34 disorderly around.Reel 34, in damping, cylinder 35, brake disc 36, drop-gear box 37, compression gas tank 45 all should have base to be connected with hull base plate.Stressed large local cabin base plate should carry out part and strengthen, and during the larger aircraft landing of steel cable length basis, allows coasting distance to determine.The impulsive force that in damping, the air pressure of cylinder 35 be take in the time of effectively cushioning aircraft landing is determined as principle.In damping, the piston stroke of cylinder 35 is with the rotating cycle of reel 34, the reduction ratio of drop-gear box 37, and the modulus of piston rod tooth bar 39 is for according to calculating.And cylinder body two ends leave suitable surplus consider damping in the length of cylinder 35.Aie escape valve control stalk 40 male and female face quantity take in damping the pressure of cylinder 35 basic consistent with initial pressure be principle, the length of male and female face should be greater than the piston effective travel of cylinder 35 in damping.In damping, the ratio of the volume of cylinder 35 and the volume of compression gas tank 45, should all be compressed in compression gas tank 45 with the gas in cylinder in damping 35, and pressure rise is not more than 0.5MPa for well.The apomecometer 48 that tests the speed, testing the speed is exactly the cireular frequency of surveying reel 34, and the rotating speed of reel 34 is with regard to known aircraft taxi speed.Range finding is exactly the number of turns of surveying reel 34, i.e. the length of steel cable 33, the coasting distance of the aircraft that namely lands.No matter test the speed, range finding is when the data with setting are harmonious, and brake disc 36 can brake.During rope closing, shutoff valve 49, open air outlet valve 43, releasing of brake dish 36, under flow-controlling gate 44 is controlled, the pressure gas in compression gas tank 45 enters and in damping, promotes piston in cylinder 35 and make piston rod tooth bar 39 through drop-gear box 37, reel 34 be rotated and rope closing in the opposite direction.Also can control slowly rope closing of brake disc 36 by hydraulic proportion valve.
Principal feature of the present invention is: airplane catapult launching apparatus propulsion source is pressurized air, by cylinder work done, affects slide trucks to carry out cataplane, and its application force is large, application force and speed are adjustable, this device is by ejection system, buffer system, and slide trucks return system in combination forms.Each system major equipment is conventional machinery equipment, easy to process, and reliable operation is easy to maintenance.Aircraft landing arrester is to take air as medium, produces resistance and implement effectively to stop sliding aircraft when air is compressed.This installs mainly by reel, drop-gear box, and cylinder in damping, is interrupted aie escape valve, and compression gas tank forms.Device is compact, and each parts are not fragile, and obstruction power is adjustable, soft, and the landing that is applicable to various aircrafts stops.
China's aircraft carrier has just started to build, and airplane catapult launching apparatus and landing arrester are very necessary.
Claims (10)
1. airplane catapult launching apparatus and aircraft landing arrester, airplane catapult launching apparatus comprises ejection system, buffer system, slide trucks return system, is positioned in aircraft carrier flying-off deck Xia cabin.It is characterized in that: ejection system is provided with storage tank [13], through pipeline, gate valve [12], flow valve [11] is connected with cylinder [8], cylinder [8] piston rod end is equipped with pulley combination [7] and is installed with little cable wire [6], by wire cable connector [49] and main tow rope [4] combination, main tow rope [4] is connected with slide trucks [1] through main track adjusting wheel [5].Open a sluice gate valve [12], storage tank [13] compressed air enters cylinder [8] promotion piston rod through flow valve [11] and stretches out motion, and through little cable wire [6], main tow rope [4] affects slide trucks [1] to move ahead, and drive is taken off;
Airplane catapult launching apparatus buffer system is provided with secondary cable wire [14], winding number circle is on swift [16], through secondary track adjusting wheel [15] two ends, be connected with slide trucks [1] rear and front end respectively, swift [16] right-hand member gear and the engagement of damping drop-gear box [17] input end gear, damping drop-gear box [17] gear of output end and the engagement of damping cylinder [18] piston rod upper rack.Slide trucks [1] moves ahead, and swift [16] rotates, damping cylinder [18] compression compared with rarefied air to minor diameter cylinder, when damping cylinder [18] piston stressed during with cylinder [8] tension balanced, slide trucks [1] stop motion;
Airplane catapult launching apparatus slide trucks return system is provided with swift [16] and is cogged and be connected with left end swift [16] axle by power-transfer clutch [19], this gear and the engagement of slide trucks return drop-gear box [20] output shaft gear, brake adjustable frequency motor [21] energising has a power failure, power is through slide trucks return drop-gear box [20], power-transfer clutch [19] drives swift [16] to rotate round about, drive slide trucks [1] return, slide trucks [1] wedge contacts with registration device [9] bearing pin, bearing pin stretches out after shrinking and inserts slide trucks [1] pin-and-hole, brake adjustable frequency motor [21] the while power interruption braking that has a power failure quits work,
Aircraft landing arrester, is characterized in that: aircraft landing deck is provided with stage casing arrester wires [28], horizontal guide sheave [30], waterproof case [31].Major equipment is fixed under landing deck in cabin, steel cable [33] is on two winding drum [34], reel [34] right-hand member gear [46] and drop-gear box [37] input shaft gear [47] engagement, in drop-gear box [37] gear of output end [38] and damping, cylinder [35] piston rod tooth bar [39] is connected with a joggle.Cylinder in two dampings [35] afterbody be communicated with and with aie escape valve [41], valve [49], main valve, air outlet valve [43] flow-controlling gate [44], compression gas tank [45] is connected.Aircraft pintle hooks stage casing arrester wires [28] and slides; reel [34] is forced to rotate cylinder [35] piston compression gas in the jar in band dynamic damping; venting control stalk is servo-actuated in the same way; its male and female face is controlled the venting of aie escape valve [41] interruption and is entered compression gas tank [45]; keep suitable gaseous tension that aircraft is slided with suitable resistance, reel [34] side is provided with the apomecometer that tests the speed [48], records speed or distance and allows to shut down; brake disc [36] can self-actuating brake, and aircraft stops sliding.The de-rope of aircraft pintle, shutoff valve [49], outputs air valve [43], and the gas of compression gas tank [45] enters cylinder in damping [35] along flow-controlling gate [44] with suitable flow, makes reel [34] rotate backward rope closing.
2. according to described in claims 1, airplane catapult launching apparatus and aircraft landing arrester, it is characterized in that: airplane catapult system is provided with slide trucks [1], storage tank [13], cylinder [8], pulley combination [7], take pressurized air as propulsion source, cylinder [8] work done, affects slide trucks [1] that airplane catapult is taken off.
3. according to described in claims 1, airplane catapult launching apparatus and aircraft landing arrester, it is characterized in that: pulley combination [7] is comprised of four movable pulleys of two fixed pulleys, four movable pulley symmetries are fixed on cylinder [8] piston rod end, with piston rod movement.
4. according to described in claims 1, airplane catapult launching apparatus and aircraft landing arrester, is characterized in that: buffer system is provided with secondary cable wire [14], swift [16], damping drop-gear box [17], damping cylinder [18].During airplane catapult, slide trucks [1] affects secondary cable wire [14] that swift [16] is rotated, and makes in damping cylinder [18] compressor cylinder γ-ray emission dumping force make stop motion after slide trucks [1] cataplane after deceleration.
5. according to described in claims 1, airplane catapult launching apparatus and aircraft landing arrester, is characterized in that: slide trucks return system is provided with secondary cable wire [14], swift [16], power-transfer clutch [19], slide trucks return drop-gear box [20], brake adjustable frequency motor [21], registration device [9] have a power failure.
6. according to described in claims 1, airplane catapult launching apparatus and aircraft landing arrester, it is characterized in that: the bearing pin of registration device [9] contacts with slide trucks [1] wedge, after bearing pin is shunk, stretch out and insert slide trucks [1] pin-and-hole, make its location, the brake adjustable frequency motor [21] that also makes to have a power failure has a power failure to brake and quits work.
7. according to described in claims 1, airplane catapult launching apparatus and aircraft landing arrester, is characterized in that: aircraft landing arrester is provided with two reels [34], and aircraft landing slides drawn steel cable [33] on reel [34].
8. according to described in claims 1, airplane catapult launching apparatus and aircraft landing arrester, it is characterized in that: aircraft landing arrester is provided with cylinder in two dampings [35], on its piston rod, be fixed with tooth bar, reel [34] rotates, after deceleration, drop-gear box gear of output end [38] promotes piston rod tooth bar [39] straight-line motion and makes γ-ray emission resistance in piston compressing cylinder.
9. according to described in claims 1, airplane catapult launching apparatus and aircraft landing arrester, it is characterized in that: aircraft landing arrester is provided with aie escape valve control stalk [40] and aie escape valve [41], aie escape valve control stalk has male and female face on [40], and convex surface and aie escape valve [41] spool is done used time venting and entered compression gas tank [45].Concave surface and aie escape valve [41] spool was closed as the used time.
10. according to described in claims 1, airplane catapult launching apparatus and aircraft landing arrester, is characterized in that: aircraft landing arrester is provided with the apomecometer that tests the speed, and it can automatically be controlled brake disc [36] reel [34] is braked.
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| WO2016019814A1 (en) * | 2014-08-02 | 2016-02-11 | 王振川 | Vacuum energy-storing type take-off ejector for fixed wing aircraft |
| CN105438496A (en) * | 2015-12-01 | 2016-03-30 | 裘尧云 | Ejection arresting gear |
| CN105460230A (en) * | 2015-12-11 | 2016-04-06 | 陕西飞机工业（集团）有限公司 | Pneumatic catapult-assisted take-off device and method used for unmanned plane |
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| CN110539893A (en) * | 2019-09-07 | 2019-12-06 | 何韧 | method and device for helping landing deceleration or takeoff augmentation of aircraft |
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| CN113643325A (en) * | 2021-06-02 | 2021-11-12 | 范加利 | Method and system for warning collision of carrier-based aircraft on aircraft carrier surface |
| CN113815883A (en) * | 2021-08-20 | 2021-12-21 | 中国船舶重工集团公司第七0四研究所 | High-energy-level emission and multi-level braking test system and method |
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