CN102530210B - Aircraft carrier landing interceptor - Google Patents
Aircraft carrier landing interceptor Download PDFInfo
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- CN102530210B CN102530210B CN201110407296.5A CN201110407296A CN102530210B CN 102530210 B CN102530210 B CN 102530210B CN 201110407296 A CN201110407296 A CN 201110407296A CN 102530210 B CN102530210 B CN 102530210B
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- fixed
- damping cylinder
- fixed frame
- check cable
- piston
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- 238000013016 damping Methods 0.000 claims abstract description 51
- 230000000712 assembly Effects 0.000 claims abstract description 4
- 238000000429 assembly Methods 0.000 claims abstract description 4
- 230000029058 respiratory gaseous exchange Effects 0.000 claims description 9
- 230000000694 effects Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000035939 shock Effects 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000013589 supplement Substances 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
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- Fluid-Damping Devices (AREA)
Abstract
The invention provides an aircraft carrier landing interceptor, which comprises at least three interceptor assemblies, wherein each interceptor assembly comprises two groups of dampers which are symmetrically arranged on two sides of an aircraft landing runway; each damper comprises a fixed framework, a damping cylinder, pistons, piston pull rods, a movable pulley and a fixed pulley block; two ends of an intercepting rope are connected with the dampers, and the middle of the intercepting rope is transversely arranged in the middle of the landing runway; each damper comprises the fixed framework, an air pipe, a high-pressure gas tank and a plurality of damping cylinders; a piston is arranged in each damping cylinder, the piston is connected with a piston pull rod, and the extending end of the piston pull rod is connected with the movable pulley; the fixed pulley block is connected with the fixed framework; one end of the intercepting rope is fixed with the fixed framework, the other end of the intercepting rope is fixed with the fixed framework of the opposite damper, and the middle of the intercepting rope is wound between the movable pulley and a fixed pulley.
Description
Technical field
The present invention relates to a kind of military equipment, specifically a kind of aircraft carrier landing interceptor.
background technology
Aircraft carrier is a kind of large-scale naval warfare platform, or a kind of marine mobile airport, no matter carrier-borne aircraft takes off in which way, the recovery of finally all will landing on aircraft carrier, for strong China prevents, Qiang Wo naval, must develop the aircraft carrier landing interceptor of the domestic aircraft carrier needs of adaptation of oneself.
summary of the invention
The object of this invention is to provide a kind of aircraft carrier landing interceptor.
The object of the invention is to realize in the following manner, comprise at least three stopping device assemblies, each stopping device assembly comprises two groups of dampers that are symmetricly set on aircraft landing runway both sides, wherein, the two ends of check cable are connected with damper, check cable intermediate lateral is arranged in the middle of landing runway, damper comprises fixed frame, tracheae, high pressure gas holder, several damping cylinders, in each damping cylinder, be provided with piston, piston is connected with pitch brace, the external part of pitch brace is connected with movable pulley, one group of fixed pulley is connected with fixed frame, one end and the fixed frame of check cable are fixed, the other end of check cable and opposed damper fixed frame are fixed, wear around between movable pulley and fixed pulley the centre of check cable,
Damping cylinder and fixed frame are fixed, fixed frame and aircraft carrier hull are fixed, the tail end of damping cylinder is provided with automatically controlled breathing valve, the head of damping cylinder is that the external part side of pitch brace is provided with admission port, admission port is connected with tracheae, tracheae be arranged on high pressure gas holder on electric T-shaped valve be connected, on electric T-shaped valve, be provided with evacuation port, on evacuation port, be provided with electronic control pressure reducing valve, on the pitch brace of the head of damping cylinder, be also provided with recoil spring;
Damping step is as follows:
1) high pressure gas holder is inflated in damping cylinder by tracheae, and piston moves to damping cylinder afterbody, by connect pitch brace by stretching check cable for subsequent use; Open the Electrocontrolled tee valve that connects high pressure gas holder, allow tracheae communicate with evacuation port, electronic control pressure reducing valve is set on evacuation port;
2) carrier-borne aircraft landing, afterbody drag hook slips over landing runway, with a check cable hook at least three road check cables, check cable is stretched along aircraft landing direction, check cable pulls movable pulley, movable pulley pulls piston by pitch brace, piston moves the air in compression cylinder to damping cylinder head, produce shock damping action, compressed air spreads in the damping cylinder in other dampers by tracheae, a part discharges to atmosphere by the electronic control pressure reducing valve on triple valve evacuation port, reduce the pressure in compressed damping cylinder, play pressure buffer effect, because check cable detours between some movable pulleys and fixed pulley, it is exactly the stretched length of check cable that the miles of relative movement sum of each movable pulley is taken advantage of in 2, the quantity that increases or reduce damping cylinder is the damping distance of adjustable aircraft landing, the automatically controlled breathing valve aperture of damping adjusting tail cylinder, the suction quantity of control damping cylinder tail end, the moving velocity of same adjusting piston, through above-mentioned shock damping action, the landing inertia of aircraft is consumed in the drawing process of check cable, and aircraft reclaims for subsequent use,
3) open the Electrocontrolled tee valve of high pressure gas holder, allow the pressurized air in high pressure gas holder enter damping cylinder by tracheae, piston playback, check cable is again stretching for subsequent use, and it is for subsequent use that Air compressor thinks to supplement in high pressure gas holder high pressure air.
Excellent effect of the present invention, simple in structure, be easy to processing be easy to install use, standard modular is produced, and assembles easy to maintenance, reasonable in design, use safety, degree of automation is high, and long service life, by controlling the throughput of automatically controlled breathing valve and electronic control pressure reducing valve, automatic damping adjusting intensity, falls for the resistance of different tonnage kind aircrafts.
Brief description of the drawings
Fig. 1 is the integral structure schematic diagram of aircraft carrier landing interceptor;
Fig. 2 is the structural representation of damping cylinder;
Description of reference numerals: damping cylinder 1, tracheae 2, pitch brace 3, movable pulley 4, fixed pulley group 5, check cable 6, landing runway 7, fixed frame 8, Electrocontrolled tee valve 9, high pressure gas holder 10, automatically controlled breathing valve 11, recoil spring 12, admission port 13, piston 14, electronic control pressure reducing valve 15.
Detailed description of the invention
Be described in detail below of the present invention with reference to Figure of description.
Aircraft carrier landing interceptor of the present invention, as shown in drawings, its structure comprises at least three stopping device assemblies, each stopping device assembly comprises two groups of dampers that are symmetricly set on aircraft landing runway both sides, wherein, the two ends of check cable 6 are connected with damper, check cable 6 intermediate lateral are arranged in the middle of landing runway 7, damper comprises fixed frame 8, tracheae 2, high pressure gas holder 10, several damping cylinders 1, in each damping cylinder 1, be provided with piston 14, piston 14 is connected with pitch brace 3, the external part of pitch brace 3 is connected with movable pulley 4, fixed pulley group 5 is connected with fixed frame 8, one end of check cable 6 and fixed frame 8 are fixing, the other end of check cable 6 and opposed damper fixed frame 8 are fixing, wear around between movable pulley 4 and fixed pulley group 5 centre of check cable 6,
Damping cylinder 1 is fixing with fixed frame 8, fixed frame 8 is fixed with aircraft carrier hull, the tail end of damping cylinder 1 is provided with automatically controlled breathing valve 11, the head of damping cylinder 1 is that the external part side of pitch brace 3 is provided with admission port 13, admission port 13 is connected with tracheae 2, tracheae 2 be arranged on high pressure gas holder 10 on electric T-shaped valve 9 be connected, on electric T-shaped valve 9, be provided with evacuation port, on evacuation port, be provided with electronic control pressure reducing valve 15, on the pitch brace 3 of the head of damping cylinder 1, be also provided with buffering elastic 12;
Damping step is as follows:
1) high pressure gas holder is inflated in damping cylinder by tracheae, and piston moves to damping cylinder afterbody, by connect pitch brace by stretching check cable for subsequent use; Open the Electrocontrolled tee valve that connects high pressure gas holder, allow tracheae communicate with evacuation port, electronic control pressure reducing valve is set on evacuation port;
2) carrier-borne aircraft landing, afterbody drag hook slips over landing runway, with a check cable hook at least three road check cables, check cable is stretched along aircraft landing direction, check cable pulls movable pulley, movable pulley pulls piston by pitch brace, piston moves the air in compression cylinder to damping cylinder head, produce shock damping action, compressed air spreads in the damping cylinder in other dampers by tracheae, a part discharges to atmosphere by the electronic control pressure reducing valve on triple valve evacuation port, reduce the pressure in compressed damping cylinder, play pressure buffer effect, because check cable detours between some movable pulleys and fixed pulley, it is exactly the stretched length of check cable that the miles of relative movement sum of each movable pulley is taken advantage of in 2, the quantity that increases or reduce damping cylinder is the damping distance of adjustable aircraft landing, the automatically controlled breathing valve aperture of damping adjusting tail cylinder, the suction quantity of control damping cylinder tail end, the moving velocity of same adjusting piston, through above-mentioned shock damping action, the landing inertia of aircraft is consumed in the drawing process of check cable, and aircraft reclaims for subsequent use,
3) open the Electrocontrolled tee valve of high pressure gas holder, allow the pressurized air in high pressure gas holder enter damping cylinder by tracheae, piston playback, check cable is again stretching for subsequent use, and it is for subsequent use that Air compressor thinks to supplement in high pressure gas holder high pressure air.
Embodiment:
Its processing and fabricating of aircraft carrier landing interceptor of the present invention is very simple and convenient, processing and fabricating shown in by specification accompanying drawing, the processing of damping cylinder, movable pulley and fixed pulley is known technology, reducing valve and breathing valve are also known technology, add that electrical motor or magnetic controller can control the aperture of hold-off pressure or the breathing valve of reducing valve.The effect of recoil spring is to prevent the impact of piston to cylinder head cylinder cap.
Radical, diameter and the length of cylinder are carried out specific design according to the length of landing runway and weight.
Except the technical characterictic described in specification sheets, be the known technology of those skilled in the art.
Claims (1)
1. aircraft carrier landing interceptor, it is characterized in that comprising at least three stopping device assemblies, each stopping device assembly comprises two groups of dampers that are symmetricly set on aircraft landing runway both sides, wherein, the two ends of check cable are connected with damper, check cable intermediate lateral is arranged in the middle of landing runway, damper comprises fixed frame, tracheae, high pressure gas holder, several damping cylinders, in each damping cylinder, be provided with piston, piston is connected with pitch brace, the external part of pitch brace is connected with movable pulley, one group of fixed pulley is connected with fixed frame, one end and the fixed frame of check cable are fixed, the other end of check cable and opposed damper fixed frame are fixed, wear around between movable pulley and fixed pulley the centre of check cable,
Damping cylinder and fixed frame are fixed, fixed frame and aircraft carrier hull are fixed, the tail end of damping cylinder is provided with automatically controlled breathing valve, the head of damping cylinder is that the external part side of pitch brace is provided with admission port, admission port is connected with tracheae, tracheae be arranged on high pressure gas holder on electric T-shaped valve be connected, on electric T-shaped valve, be provided with evacuation port, on evacuation port, be provided with electronic control pressure reducing valve, on the pitch brace of the head of damping cylinder, be also provided with recoil spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110407296.5A CN102530210B (en) | 2011-12-09 | 2011-12-09 | Aircraft carrier landing interceptor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110407296.5A CN102530210B (en) | 2011-12-09 | 2011-12-09 | Aircraft carrier landing interceptor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102530210A CN102530210A (en) | 2012-07-04 |
| CN102530210B true CN102530210B (en) | 2014-07-23 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110407296.5A Active CN102530210B (en) | 2011-12-09 | 2011-12-09 | Aircraft carrier landing interceptor |
Country Status (1)
| Country | Link |
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| CN (1) | CN102530210B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107472550A (en) * | 2017-09-19 | 2017-12-15 | 方立波 | Arresting gear and its system energetically |
| CN108860657B (en) * | 2018-05-18 | 2021-10-29 | 西北工业大学 | Aircraft arresting test device and aircraft arresting load transfer simulation equipment |
| CN110450972A (en) * | 2019-08-09 | 2019-11-15 | 何韧 | It is a kind of to facilitate aircraft lands deceleration or slide steady or the reinforcement that takes off method and device |
| CN112810829A (en) * | 2019-11-15 | 2021-05-18 | 李启飞 | Pulley variable speed type nonlinear magnetic coupling blocking cable |
| CN113665832B (en) * | 2021-08-13 | 2024-03-15 | 航天时代飞鹏有限公司 | Unmanned aerial vehicle intelligent airport ground system |
| CN118163955B (en) * | 2024-05-14 | 2024-07-26 | 中国人民解放军海军航空大学 | Runway interception device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3191890A (en) * | 1962-04-12 | 1965-06-29 | Monsanto Co | Arresting systems |
| US3713609A (en) * | 1971-03-02 | 1973-01-30 | Mactaggart Scott & Co Ltd | Aircraft arresting gear |
| GB1422961A (en) * | 1972-01-31 | 1976-01-28 | Secr Defence | Arrester gear |
-
2011
- 2011-12-09 CN CN201110407296.5A patent/CN102530210B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3191890A (en) * | 1962-04-12 | 1965-06-29 | Monsanto Co | Arresting systems |
| US3713609A (en) * | 1971-03-02 | 1973-01-30 | Mactaggart Scott & Co Ltd | Aircraft arresting gear |
| GB1422961A (en) * | 1972-01-31 | 1976-01-28 | Secr Defence | Arrester gear |
Non-Patent Citations (4)
| Title |
|---|
| MK723型拦阻装置滑轮运动特性分析;王海东等;《舰船科学技术》;20110228;第33卷(第2期);75-77 * |
| 李杰等.航空母舰的舰载机着舰装备.《现代军事》.2006,56-58. |
| 王海东等.MK723型拦阻装置滑轮运动特性分析.《舰船科学技术》.2011,第33卷(第2期),75-77. |
| 航空母舰的舰载机着舰装备;李杰等;《现代军事》;20061031;56-58 * |
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| Publication number | Publication date |
|---|---|
| CN102530210A (en) | 2012-07-04 |
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Effective date of registration: 20141104 Address after: 226100, 999, Guangzhou Road, Haimen, Jiangsu, Nantong Patentee after: HAIMEN JIANGHAI CONSTRUCTION INVESTMENT CO., LTD. Address before: 250014 Shandong Province, Lixia District of Ji'nan city by ten Road No. 12588 District No. 5 celebrities heights Public Building Room 202 Patentee before: Zhu Huifen |