CN102530261A - Launching return linkage type high-power aircraft carrier catapult - Google Patents
Launching return linkage type high-power aircraft carrier catapult Download PDFInfo
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- CN102530261A CN102530261A CN2011104072838A CN201110407283A CN102530261A CN 102530261 A CN102530261 A CN 102530261A CN 2011104072838 A CN2011104072838 A CN 2011104072838A CN 201110407283 A CN201110407283 A CN 201110407283A CN 102530261 A CN102530261 A CN 102530261A
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Abstract
The invention provides a launching return linkage type high-power aircraft carrier catapult. A piston is driven to move vertically in a cylinder by respectively charging air to two ends of the bidirectional cylinder and exhausting, movable pulleys at the ends of piton pull rods at two ends of the piston are further driven to match with fixed pulleys on an upper and lower fixed pulley fixing rack to straighten and bend a traction rope and a return rope, and the traction rope and the return rope synchronously drive accelerating slippage or origin return of a sliding shuttle on a take-off runway, and launching flying of an aircraft carrier can be realized by accelerating motion of the sliding shuttle on a launching runway. The catapult has the characteristics of simple structure, standard modularized production, convenience in assembly and maintenance, safety in use, high automation degree, long service life and the like, and is easy to machine, install and use; and automatic control of launching of the aircraft carrier and automatic return of the sliding shuttle can be realized through an electric control four-way valve and a sensor which is arranged on the end point of the take-off runway.
Description
Technical field
The present invention relates to a kind of military equipment, specifically a kind of launching returned the high-power aircraft carrier ejector of coordinated type.
Background technology
Aircraft carrier is a kind of large-scale naval warfare platform, or a kind of sea moves the airport, no matter is which kind of carrier-borne aircraft; Such as attack plane, antisubmarine plane, early warning plane, transport plane, electronic fighter or the like; All must could on aircraft carrier, take off from aircraft carrier by the short range full and down, have only the fully loaded fighting capacity that could form to cruise, at present with long distance through ejector; More than ten aircraft carrier that the U.S. is on active service all equipped steam catapult; The also unequipped warship of going up of the electromagnetic launch device of new successful development, why the neat ejector of warship will use the electromagnetism ejector to substitute in the U.S., and reason is:
1) high, high, the complex operation of fault rate of steam catapult manufacturing cost height, complex manufacturing technology, service expenditure on average launches the 400-500 sortie and will ground and repair 1-2 days, will return the port overhaul 1000 times.
2) also have power consumption high, steam energy changes into and launches power and have only 4% to 6%, whenever launches the steam that an airplane need consume a fresh water;
3) complicated operation, an ejector needs operating personal and about 120 people of maintainer.
The applicant discloses a kind of name and is called the pneumatic aircraft carrier ejector of high thrust multiplication accelerating type in number of patent application is 201010616996.0 application, it is that unidirectional cylinder launches that this technical scheme adopts, and traction winch returns; The deficiency that exists is that the outer pushing-type of unidirectional cylinder piston rod is in order to prevent firmly bending of piston rod; The diameter that needs the oversize piston bar; So just increase the weight of the weight of cylinder, increased manufacturing cost, used cylinder traction and winch to return playback in addition respectively; Influence the whole synchronous coordination property of ejector, made operability and safety reduce.
Summary of the invention
The objective of the invention is to prevent that for strong China my naval provides a kind of launching to return the high-power aircraft carrier ejector of coordinated type by force.
The objective of the invention is to realize by following mode; Move up and down in cylinder through inflating respectively with the exhaust gas drive piston to two-way cylinder two ends; And then the movable pulley of the pitch brace end at driven plunger two ends cooperate with fixed pulley on the fixed pulley fixed mount up and down with trailing cable with return Suo Lazhi and stretch bending; Realize trailing cable and return rope and drive synchronously that the acceleration of shuttle on takeoff runway slided or initial point returns that shuttle can be realized the catapult-assisted take-off of carrier-borne aircraft launching acceleration operation on the runway;
The structure of ejector comprise the fixed pulley fixed mount, down fixed pulley fixed mount, cylinder fixed mount, cylinder assembly, up and down movable pulley, up and down fixed pulley, about reverse tension pulley block, trailing cable, return rope, shuttle and takeoff runway; Wherein, About reverse tension pulley block be separately positioned on the right ends below of takeoff runway; Be provided with in the middle of the takeoff runway and crack, the shuttle and the sliding block joint that cracks, the shuttle two ends are connected with an end of returning rope with trailing cable; Last fixed pulley fixed mount is provided with fixed pulley up and down with following fixed pulley fixed mount; Last fixed pulley fixed mount is arranged on the below of takeoff runway, and cylinder assembly is decided the below that frame is fixed on the fixed pulley fixed mount through cylinder, and following fixed pulley fixed mount is arranged on the below of cylinder assembly;
Cylinder assembly comprises several two-way cylinders; Be provided with piston in the two-way cylinder, the piston upper end is connected with the upper piston pull bar, and the end of upper piston pull bar is provided with movable pulley; Last movable pulley is on the last fixed pulley fixed mount between the fixed pulley; The piston lower end is connected with the lower piston pull bar, and the end of lower piston pull bar is provided with down movable pulley, and following movable pulley is between the following fixed pulley on the following fixed pulley fixed mount;
The right reverse tension pulley block on takeoff runway the right is walked around in the other end of trailing cable, oppositely passes between the last movable pulley on last fixed pulley and upper piston pull bar top on the fixed pulley fixed mount again, fixes with the left end of last fixed pulley fixed mount;
It is downward with the leading sheave that is arranged on fixed pulley fixed mount left end that the reverse tension pulley block in a left side of takeoff runway left end is walked around in the other end of returning rope, and following fixed pulley and the following movable pulley and the following fixed pulley fixed mount right-hand member of lower piston pull bar bottom walked around down respectively on the movable pulley fixed mount are fixed again;
Reverse tension pulley block is fixing through chest expander and the airstrip bottom be made up of extension spring respectively about the takeoff runway both sides;
The two ends of the two-way cylinder of each in the cylinder assembly are respectively arranged with at least one porting; Two air inlet-outlet pipes of parallel connection are connected with two portings of electric four-way valve respectively; An admission port of electric four-way valve connects high pressure tank through total inlet pipe, and another one is an evacuation port;
Two ends are respectively arranged with recoil spring in the two-way cylinder;
The extension elongation of the quantity=landing airdrome length of two-way cylinder/2/ pitch brace;
The shuttle speed that ejection speed=pitch brace all stretches out on takeoff runway;
The quantity * gas pressure intensity * piston end area of the gross horsepower of ejector=two-way cylinder;
It is following that carrier-borne aircraft launches step:
1) shuttle adjustment in place: high pressure gas holder is through commutate two-way cylinder lower end inflation of four-way cock; Two-way cylinder upper end is communicated with evacuation port, and piston stroking upward will return the rope stretch bending and tighten up; Trailing cable is stretching to be stretched out; Shuttle is fixed a point in taking off the runway starting point, and the aircraft nose-gear is taken off and awaited orders through hook and shuttle hook;
2) carrier-borne aircraft launches: rotate four-way cock, let the porting of two-way cylinder upper end be communicated with high pressure tank, two-way cylinder lower end porting is communicated with the evacuation port of four-way cock; Piston upper end cylinder charging, descent of piston, the last movable pulley of the upper piston tie rod end of piston upper end cooperate with last fixed pulley takes in the trailing cable stretch bending; Shuttle has the right slip of left-hand on takeoff runway; The lower piston pull bar of piston lower end stretches out downwards, returns rope and is drawn isometric output by shuttle, wait the whole stretch bendings of trailing cable take in and return rope by following movable pulley with following fixed pulley when stretching; Shuttle draws carrier-borne aircraft to the takeoff runway terminal point, and carrier-borne aircraft takes off; Shuttle stops automatically.
3) repeat first step, the stretching trailing cable that is about to of trailing cable is emitted, return the rope bending and take in, it is subsequent use that shuttle returns the takeoff runway starting point.
Excellent effect of the present invention adopts many cylinders bivector traction, can make full use of that the compressed-air controlled energy transformation ratio is high, speed of response is fast, power is big, manageable characteristics; The takeoff speed of carrier-borne aircraft depends on coasting speed and the intensity of shuttle on takeoff runway; Adopt a plurality of two-way cylinder combination to use, be equivalent to many people and people's tug-of-war, many humans be reasonable; There is strength in numbers, and ejector partial parameters computing formula of the present invention is following:
The extension elongation of the quantity=landing airdrome length of two-way cylinder/2/ pitch brace;
The shuttle speed that ejection speed=pitch brace all stretches out on takeoff runway;
The quantity * gas pressure intensity * piston end area of the gross horsepower of ejector=two-way cylinder;
More priorly be, piston stroke is short, and inertia is little, and many power that cylinder is used are just big more.
Also have simple in structure, be easy to processing, be easy to install and use; Standard modular is produced, and assembles easy to maintenance, safe in utilization; Degree of automation is high; Characteristics such as long service life, through an electrically controlled 4-way valve be arranged on the sensor on the takeoff runway terminal point, can realize carrier-borne the launching and the returning automatically of shuttle of automatic guidance.
If charge into pressure and speed through computer controlled electrically controlled 4-way valve control high pressure gas, also the coasting speed of may command shuttle is realized launching heavy carrier-borne aircraft and unmanned carrier-borne aircraft.
Description of drawings
Fig. 1 is the integral structure scheme drawing of aircraft carrier ejector;
Fig. 2 is the structural representation of two-way cylinder;
Description of reference numerals: takeoff runway 1; Shuttle 2; Right reverse tension pulley block 3; Trailing cable 4; Upper piston pull bar 5; Two-way cylinder 6; Electrically controlled 4-way valve 7; Air inlet pipe 8; Evacuation port 9; Air inlet-outlet pipe 10; Movable pulley 11; Fixed pulley 12; Following fixed pulley fixed mount 13; Return rope 14; Cylinder fixed mount 15; Leading sheave 16; Last fixed pulley fixed mount 17; Piston 18; Recoil spring 19; Porting 20; Tensioning spring 21; Lower piston pull bar 22; Last movable pulley 23; Last fixed pulley 24; The reverse tension pulley block 25 in a left side.
The specific embodiment
Explanation at length below with reference to Figure of description aircraft carrier ejector of the present invention being done.
Aircraft carrier ejector of the present invention; Shown in accompanying drawing; Basic functional principle is to move up and down in cylinder through inflating respectively with the exhaust gas drive piston to two-way cylinder two ends; And then the movable pulley of the pitch brace end at driven plunger two ends cooperate with fixed pulley on the fixed pulley fixed mount up and down with trailing cable with return Suo Lazhi and stretch bending; Realize trailing cable and return rope and drive synchronously that the acceleration of shuttle on takeoff runway slided or initial point returns that shuttle can be realized the catapult-assisted take-off of carrier-borne aircraft launching acceleration operation on the runway;
The structure of ejector comprise fixed pulley fixed mount 17, down fixed pulley fixed mount 13, cylinder fixed mount 15, cylinder assembly, go up movable pulley 23, down movable pulley 11, go up fixed pulley 24, down fixed pulley 12, the reverse tension pulley block 25 in a left side, right reverse tension pulley block 3, trailing cable 4, return rope 14, shuttle 2 and takeoff runway 1; Wherein, About reverse tension pulley block 25,3 be separately positioned on the right ends below of takeoff runway 1; Be provided with in the middle of the takeoff runway 1 and crack; The shuttle 2 and the sliding block joint that cracks; Shuttle 2 two ends are connected with an end of returning rope 14 with trailing cable 4, and last fixed pulley fixed mount 17 is provided with fixed pulley 12 with following fixed pulley fixed mount 13, and last fixed pulley fixed mount 17 is arranged on the below of takeoff runway 1; Cylinder assembly is decided the below that frame 15 is fixed on fixed pulley fixed mount 17 through cylinder, and following fixed pulley fixed mount 13 is arranged on the below of cylinder assembly;
Cylinder assembly comprises several two-way cylinders 6; Be provided with piston 18 in the two-way cylinder 6, piston 18 upper ends are connected with upper piston pull bar 5, and the end of upper piston pull bar 5 is provided with movable pulley 23; Last movable pulley 23 is on the last fixed pulley fixed mount 17 between the fixed pulley 24; Piston 18 lower ends are connected with lower piston pull bar 22, and the end of lower piston pull bar 22 is provided with down movable pulley 11, and following movable pulley 11 is between the following fixed pulley 12 on the following fixed pulley fixed mount 13;
The right reverse tension pulley block 3 on takeoff runway the right is walked around in the other end of trailing cable 4, oppositely passes between the last movable pulley 23 on last fixed pulley 24 and upper piston pull bar 5 tops on the fixed pulley fixed mount 17 again, fixes with the left end of last fixed pulley fixed mount 17;
It is downward with the leading sheave 16 that is arranged on fixed pulley fixed mount 17 left ends that the reverse tension pulley block 25 in a left side of takeoff runway 1 left end is walked around in the other end of returning rope 14, and following fixed pulley 12 and the following movable pulley 11 and following fixed pulley fixed mount 13 right-hand members of lower piston pull bar 22 bottoms walked around down respectively on the movable pulley fixed mount 13 are fixed again;
Reverse tension pulley block 25,3 is fixed with airstrip 1 bottom through the chest expander of being made up of extension spring 21 respectively about takeoff runway 1 both sides;
The two ends of the two-way cylinder 6 of each in the cylinder assembly are respectively arranged with at least one porting 20; Two air inlet-outlet pipes 10 of parallel connection are connected with two portings of electric four-way valve 7 respectively; An admission port 8 of electric four-way valve 7 connects high pressure tank through total inlet pipe, and another one is an evacuation port 9;
Two ends are respectively arranged with recoil spring 19 in the two-way cylinder 6, prevent the piston slap cylinder end cap.
The extension elongation of the quantity=landing airdrome length of two-way cylinder 9/2/ pitch brace;
The shuttle speed that ejection speed=pitch brace all stretches out on takeoff runway;
The quantity * gas pressure intensity * piston end area of the gross horsepower of ejector=two-way cylinder;
It is following that carrier-borne aircraft launches step:
1) shuttle adjustment in place: high pressure gas holder is through commutate two-way cylinder lower end inflation of four-way cock; Two-way cylinder upper end is communicated with evacuation port, and piston stroking upward will return the rope stretch bending and tighten up; Trailing cable is stretching to be stretched out; Shuttle is fixed a point in taking off the runway starting point, and the aircraft nose-gear is taken off and awaited orders through hook and shuttle hook;
2) carrier-borne aircraft launches: rotate four-way cock, let the porting of two-way cylinder upper end be communicated with high pressure tank, two-way cylinder lower end porting is communicated with the evacuation port of four-way cock; Piston upper end cylinder charging, descent of piston, the last movable pulley of the upper piston tie rod end of piston upper end cooperate with last fixed pulley takes in the trailing cable stretch bending; Shuttle has the right slip of left-hand on takeoff runway; The lower piston pull bar of piston lower end stretches out downwards, returns rope and is drawn isometric output by shuttle, wait the whole stretch bendings of trailing cable take in and return rope by following movable pulley with following fixed pulley when stretching; Shuttle draws carrier-borne aircraft to the takeoff runway terminal point, and carrier-borne aircraft takes off; Shuttle stops automatically.
3) repeat first step, the stretching trailing cable that is about to of trailing cable is emitted, return the rope bending and take in, it is subsequent use that shuttle returns the takeoff runway starting point.
High pressure gas in the high pressure gas holder are pressurized air or high-temperature steam, and four-way cock is the standard pipe fitting, also can use two triple valve interlocks to replace.
Be provided with if two-way cylinder is vertical, the movable pulley guide piece need be set, the last movable pulley that drives trailing cable partly is arranged on the top of two-way cylinder, the part gravity of borrowing apparatus also can improve and launches efficient.
Embodiment
Carrier-based aircraft ejector is with reference to the parameter designing of the U.S.; Takeoff runway is by 98 meters Design of length; Adopt 10 6 meters long two-way cylinders, diameter is selected 400mm for use, and the quiet extension elongation of pitch brace is 5 meters; Pitch brace stretches out can the stretching and drawing rope 10 meters, and 10 5 meters long-term job plug pull bars just can stretch 100 meters; 30 kilograms/cm of air pressure
2
Theoretically, if aircraft 100 meters departure times less than 3 seconds, the pitch brace of 10 cylinders stretch out simultaneously the pulling shuttle run through 100 meters, the consumption time should be 3/10 second.
If gas pressure intensity is identical, cylinder diameter is identical, and power ratio is 10/2=5; Because what the U.S. adopted is open cylinder, air pressure has strict restriction, and what the present invention adopted is the sealing cylinder; So the pressure of working gas can launch power and can also improve greater than the pressure of open cylinder.
Except that the described technical characterictic of specification sheets, be the known technology of those skilled in the art.
Claims (1)
1. launch and return the high-power aircraft carrier ejector of coordinated type; It is characterized in that in cylinder, moving up and down through inflating respectively with the exhaust gas drive piston to two-way cylinder two ends; And then the movable pulley of the pitch brace end at driven plunger two ends cooperate with fixed pulley on the fixed pulley fixed mount up and down with trailing cable with return Suo Lazhi and stretch bending; Realize trailing cable and return rope and drive synchronously that the acceleration of shuttle on takeoff runway slided or initial point returns that shuttle can be realized the catapult-assisted take-off of carrier-borne aircraft launching acceleration operation on the runway;
The structure of ejector comprise the fixed pulley fixed mount, down fixed pulley fixed mount, cylinder fixed mount, cylinder assembly, up and down movable pulley, up and down fixed pulley, about reverse tension pulley block, trailing cable, return rope, shuttle and takeoff runway; Wherein, About reverse tension pulley block be separately positioned on the right ends below of takeoff runway; Be provided with in the middle of the takeoff runway and crack, the shuttle and the sliding block joint that cracks, the shuttle two ends are connected with an end of returning rope with trailing cable; Last fixed pulley fixed mount is provided with fixed pulley up and down with following fixed pulley fixed mount; Last fixed pulley fixed mount is arranged on the below of takeoff runway, and cylinder assembly is decided the below that frame is fixed on the fixed pulley fixed mount through cylinder, and following fixed pulley fixed mount is arranged on the below of cylinder assembly;
Cylinder assembly comprises several two-way cylinders; Be provided with piston in the two-way cylinder, the piston upper end is connected with the upper piston pull bar, and the end of upper piston pull bar is provided with movable pulley; Last movable pulley is on the last fixed pulley fixed mount between the fixed pulley; The piston lower end is connected with the lower piston pull bar, and the end of lower piston pull bar is provided with down movable pulley, and following movable pulley is between the following fixed pulley on the following fixed pulley fixed mount;
The right reverse tension pulley block on takeoff runway the right is walked around in the other end of trailing cable, oppositely passes between the last movable pulley on last fixed pulley and upper piston pull bar top on the fixed pulley fixed mount again, fixes with the left end of last fixed pulley fixed mount;
It is downward with the leading sheave that is arranged on fixed pulley fixed mount left end that the reverse tension pulley block in a left side of takeoff runway left end is walked around in the other end of returning rope, and following fixed pulley and the following movable pulley and the following fixed pulley fixed mount right-hand member of lower piston pull bar bottom walked around down respectively on the movable pulley fixed mount are fixed again;
Reverse tension pulley block is fixing through chest expander and the airstrip bottom be made up of extension spring respectively about the takeoff runway both sides;
The two ends of the two-way cylinder of each in the cylinder assembly are respectively arranged with at least one porting; Two air inlet-outlet pipes of parallel connection are connected with two portings of electric four-way valve respectively; An admission port of electric four-way valve connects high pressure tank through total inlet pipe, and another one is an evacuation port;
Two ends are respectively arranged with recoil spring in the two-way cylinder;
The extension elongation of the quantity=landing airdrome length of two-way cylinder/2/ pitch brace;
The shuttle speed that ejection speed=pitch brace all stretches out on takeoff runway;
The quantity * gas pressure intensity * piston end area of the gross horsepower of ejector=two-way cylinder;
It is following that carrier-borne aircraft launches step:
1) shuttle adjustment in place: high pressure gas holder is through commutate two-way cylinder lower end inflation of four-way cock; Two-way cylinder upper end is communicated with evacuation port, and piston stroking upward will return the rope stretch bending and tighten up; Trailing cable is stretching to be stretched out; Shuttle is fixed a point in taking off the runway starting point, and the aircraft nose-gear is taken off and awaited orders through hook and shuttle hook;
2) carrier-borne aircraft launches: rotate four-way cock, let the porting of two-way cylinder upper end be communicated with high pressure tank, two-way cylinder lower end porting is communicated with the evacuation port of four-way cock; Piston upper end cylinder charging, descent of piston, the last movable pulley of the upper piston tie rod end of piston upper end cooperate with last fixed pulley takes in the trailing cable stretch bending; Shuttle has the right slip of left-hand on takeoff runway; The lower piston pull bar of piston lower end stretches out downwards, returns rope and is drawn isometric output by shuttle, wait the whole stretch bendings of trailing cable take in and return rope by following movable pulley with following fixed pulley when stretching; Shuttle draws carrier-borne aircraft to the takeoff runway terminal point, and carrier-borne aircraft takes off; Shuttle stops automatically.
3) repeat first step, the stretching trailing cable that is about to of trailing cable is emitted, return the rope bending and take in, it is subsequent use that shuttle returns the takeoff runway starting point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110407283.8A CN102530261B (en) | 2011-12-09 | 2011-12-09 | Launching return linkage type high-power aircraft carrier catapult |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110407283.8A CN102530261B (en) | 2011-12-09 | 2011-12-09 | Launching return linkage type high-power aircraft carrier catapult |
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| CN102530261A true CN102530261A (en) | 2012-07-04 |
| CN102530261B CN102530261B (en) | 2014-03-19 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104648687A (en) * | 2013-11-19 | 2015-05-27 | 张文星 | Elastic force source of aircraft carrier air pressure electromagnetic catapult |
| CN105438496A (en) * | 2015-12-01 | 2016-03-30 | 裘尧云 | Ejection arresting gear |
| CN105667820A (en) * | 2016-01-04 | 2016-06-15 | 济南环太机电技术有限公司 | Tunnel type shipboard aircraft catapult capable of using multiple types of energy |
| CN106169264A (en) * | 2016-08-23 | 2016-11-30 | 济南环太机电技术有限公司 | Aircraft carrier launches and blocks simulated training system |
| CN106228863A (en) * | 2016-08-23 | 2016-12-14 | 济南环太机电技术有限公司 | Aircraft carrier launches and blocks simulation training car |
| CN106404333A (en) * | 2016-12-05 | 2017-02-15 | 中国航天空气动力技术研究院 | Gas ejection traction device |
| CN106986044A (en) * | 2017-02-26 | 2017-07-28 | 刘国良 | Carrier-borne aircraft fires vapour ejector |
| CN108820240A (en) * | 2018-07-27 | 2018-11-16 | 新乡市豫新起重机械有限公司 | A kind of aircraft carrier arresting gear |
| CN109033569A (en) * | 2018-07-09 | 2018-12-18 | 哈尔滨理工大学 | A method of optimize for carrier-borne aircraft sensing system prophylactic repair threshold intensity and number |
| CN110293155A (en) * | 2019-07-30 | 2019-10-01 | 易思博 | A kind of reciprocating sheet metal bent shaping equipment |
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| US20050230533A1 (en) * | 2002-09-16 | 2005-10-20 | Robonic Ltd Oy | Arrangement in catapult |
| CN102120497A (en) * | 2010-10-07 | 2011-07-13 | 朱炎炎 | Enclosed cylinder carrier aircraft steam catapult |
| CN102152856A (en) * | 2010-12-31 | 2011-08-17 | 朱惠芬 | Large-thrust multiple acceleration type pneumatic ejector for carrier-based airplanes of airplane carrier |
| CN102198865A (en) * | 2010-09-17 | 2011-09-28 | 朱惠芬 | Steam catapult for carrier-borne aircraft and catapulting method thereof |
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| GB322861A (en) * | 1928-11-09 | 1929-12-19 | William Archibald Davidson For | Improvements in or relating to apparatus for launching aircraft |
| US20050230533A1 (en) * | 2002-09-16 | 2005-10-20 | Robonic Ltd Oy | Arrangement in catapult |
| CN102198865A (en) * | 2010-09-17 | 2011-09-28 | 朱惠芬 | Steam catapult for carrier-borne aircraft and catapulting method thereof |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104648687A (en) * | 2013-11-19 | 2015-05-27 | 张文星 | Elastic force source of aircraft carrier air pressure electromagnetic catapult |
| CN105438496A (en) * | 2015-12-01 | 2016-03-30 | 裘尧云 | Ejection arresting gear |
| CN105667820A (en) * | 2016-01-04 | 2016-06-15 | 济南环太机电技术有限公司 | Tunnel type shipboard aircraft catapult capable of using multiple types of energy |
| CN106228863B (en) * | 2016-08-23 | 2018-08-17 | 济南环太机电技术有限公司 | Simulated training vehicle is blocked in aircraft carrier ejection |
| CN106169264A (en) * | 2016-08-23 | 2016-11-30 | 济南环太机电技术有限公司 | Aircraft carrier launches and blocks simulated training system |
| CN106228863A (en) * | 2016-08-23 | 2016-12-14 | 济南环太机电技术有限公司 | Aircraft carrier launches and blocks simulation training car |
| CN106404333A (en) * | 2016-12-05 | 2017-02-15 | 中国航天空气动力技术研究院 | Gas ejection traction device |
| CN106986044A (en) * | 2017-02-26 | 2017-07-28 | 刘国良 | Carrier-borne aircraft fires vapour ejector |
| CN106986044B (en) * | 2017-02-26 | 2023-04-07 | 刘国良 | Shipboard aircraft gas catapult |
| CN109033569A (en) * | 2018-07-09 | 2018-12-18 | 哈尔滨理工大学 | A method of optimize for carrier-borne aircraft sensing system prophylactic repair threshold intensity and number |
| CN109033569B (en) * | 2018-07-09 | 2021-09-17 | 哈尔滨理工大学 | Method for optimizing strength and times of preventive maintenance threshold of shipboard aircraft sensor system |
| CN108820240A (en) * | 2018-07-27 | 2018-11-16 | 新乡市豫新起重机械有限公司 | A kind of aircraft carrier arresting gear |
| CN108820240B (en) * | 2018-07-27 | 2023-11-10 | 新乡市豫新起重机械有限公司 | Blocking device for carrier-based aircraft of aircraft carrier |
| CN110293155A (en) * | 2019-07-30 | 2019-10-01 | 易思博 | A kind of reciprocating sheet metal bent shaping equipment |
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| CN102530261B (en) | 2014-03-19 |
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