CN102530210A - Aircraft carrier landing interceptor - Google Patents
Aircraft carrier landing interceptor Download PDFInfo
- Publication number
- CN102530210A CN102530210A CN2011104072965A CN201110407296A CN102530210A CN 102530210 A CN102530210 A CN 102530210A CN 2011104072965 A CN2011104072965 A CN 2011104072965A CN 201110407296 A CN201110407296 A CN 201110407296A CN 102530210 A CN102530210 A CN 102530210A
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- damping cylinder
- fixed
- check cable
- damping
- piston
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- 238000013016 damping Methods 0.000 claims abstract description 64
- 230000029058 respiratory gaseous exchange Effects 0.000 claims description 10
- 230000035939 shock Effects 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 5
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
- 230000000712 assembly Effects 0.000 abstract 1
- 238000000429 assembly Methods 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 4
- 230000006978 adaptation Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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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, device is blocked in specifically a kind of aircraft carrier landing.
Background technology
Aircraft carrier is a kind of large-scale naval warfare platform; Or the airport is moved at a kind of sea; No matter carrier-borne aircraft takes off in which way, and the recovery of finally all will on aircraft carrier, landing is for strong China prevents; My naval must develop the aircraft carrier landing of the homemade aircraft carrier needs of adaptation of oneself and block device by force.
Summary of the invention
The purpose of this invention is to provide a kind of aircraft carrier landing and block device.
The objective of the invention is to realize that by following mode comprise that at least three are blocked the device assembly, each blocks the device assembly and comprise 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, and the check cable intermediate lateral is arranged in the middle of the landing runway; Damper comprises fixed frame, tracheae, high pressure gas holder, several damping cylinders; Be provided with piston in each damping cylinder, piston is connected with pitch brace, and 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, and the other end of check cable and opposed damper fixed frame are fixed, and wear around between movable pulley and the fixed pulley centre of check cable;
Damping cylinder and fixed frame are fixed, and fixed frame and aircraft carrier hull are fixed, and 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, electric T-shaped valve is provided with evacuation port; Evacuation port is provided with the electronic control pressure reducing valve, also is provided with recoil spring on the pitch brace of the head of damping cylinder;
The damping step is following:
1) high pressure gas holder is inflated in damping cylinder through tracheae, and piston moves to the damping cylinder afterbody, and is through the bonded assembly pitch brace that check cable is stretching subsequent use; Open the automatically controlled triple valve that connects high pressure gas holder, let tracheae communicate, the electronic control pressure reducing valve is set on the evacuation port with evacuation port;
2) carrier-borne aircraft landing, the afterbody drag hook slips over landing runway, with a check cable hook at least three road check cables check cable is stretched along the aircraft landing direction; Check cable pulling movable pulley, movable pulley is through pitch brace pulling piston, and piston moves the air in the compression cylinder to the damping cylinder head; Produce shock damping action; Compressed air is through spreading in the damping cylinder of tracheae in other dampers, and a part discharges to atmosphere through the electronic control pressure reducing valve on the triple valve evacuation port, reduces the pressure in the compressed damping cylinder; Play the pressure buffer effect; Because check cable detours between some movable pulleys and fixed pulley, the miles of relative movement sum of each movable pulley is taken advantage of in 2 being exactly the stretched length of check cable, and the quantity that increases or reduce damping cylinder is the damping distance of scalable aircraft landing; Regulate the automatically controlled breathing valve aperture of damping cylinder afterbody, 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 subsequent use;
3) open the automatically controlled triple valve of high pressure gas holder, let the pressurized air in the high pressure gas holder get into damping cylinder through tracheae, the piston playback, check cable is stretching again subsequent use, and it is subsequent use that Air compressor thinks to replenish high pressure air in the high pressure gas holder.
Excellent effect of the present invention, simple in structure, be easy to processing and be easy to install and use standard modular production; Assemble easy to maintenance, reasonable in design, safe in utilization; Degree of automation is high, and long service life is through controlling the throughput of automatically controlled breathing valve and electronic control pressure reducing valve; The automatically regulating damping intensity, the resistance that is used for different tonnage kind aircrafts is fallen.
Description of drawings
Fig. 1 is the integral structure scheme drawing that device is blocked in the aircraft carrier landing;
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, automatically controlled triple 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.
The specific embodiment
With reference to Figure of description to explanation at length below the work of the present invention.
Device is blocked in aircraft carrier landing of the present invention, and shown in accompanying drawing, its structure comprises that at least three are blocked the device assembly; Each blocks the device assembly and comprises two groups of dampers that are symmetricly set on aircraft landing runway both sides, and wherein, the two ends of check cable 6 are connected with damper; Check cable 6 intermediate lateral are arranged in the middle of the landing runway 7, and damper comprises fixed frame 8, tracheae 2, high pressure gas holder 10, several damping cylinders 1, is provided with piston 14 in each damping cylinder 1; Piston 14 is connected with pitch brace 3; The external part of pitch brace 3 is connected with movable pulley 4, and fixed pulley group 5 is connected with fixed frame 8, and an 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, and wear around between movable pulley 4 and the fixed pulley group 5 centre of check cable 6;
The damping step is following:
1) high pressure gas holder is inflated in damping cylinder through tracheae, and piston moves to the damping cylinder afterbody, and is through the bonded assembly pitch brace that check cable is stretching subsequent use; Open the automatically controlled triple valve that connects high pressure gas holder, let tracheae communicate, the electronic control pressure reducing valve is set on the evacuation port with evacuation port;
2) carrier-borne aircraft landing, the afterbody drag hook slips over landing runway, with a check cable hook at least three road check cables check cable is stretched along the aircraft landing direction; Check cable pulling movable pulley, movable pulley is through pitch brace pulling piston, and piston moves the air in the compression cylinder to the damping cylinder head; Produce shock damping action; Compressed air is through spreading in the damping cylinder of tracheae in other dampers, and a part discharges to atmosphere through the electronic control pressure reducing valve on the triple valve evacuation port, reduces the pressure in the compressed damping cylinder; Play the pressure buffer effect; Because check cable detours between some movable pulleys and fixed pulley, the miles of relative movement sum of each movable pulley is taken advantage of in 2 being exactly the stretched length of check cable, and the quantity that increases or reduce damping cylinder is the damping distance of scalable aircraft landing; Regulate the automatically controlled breathing valve aperture of damping cylinder afterbody, 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 subsequent use;
3) open the automatically controlled triple valve of high pressure gas holder, let the pressurized air in the high pressure gas holder get into damping cylinder through tracheae, the piston playback, check cable is stretching again subsequent use, and it is subsequent use that Air compressor thinks to replenish high pressure air in the high pressure gas holder.
Embodiment:
It is very simple and convenient that its processing and fabricating of device is blocked in aircraft carrier landing of the present invention; Processing and fabricating gets final product shown in the by specification accompanying drawing; The processing of damping cylinder, movable pulley and fixed pulley is known technology; Reducing valve and breathing valve are known technology also, add that electrical motor or magnetic controller are the aperture of the hold-off pressure or the breathing valve of may command reducing valve.The effect of recoil spring is to prevent the impact of piston to the cylinder head cylinder cap.
The radical of cylinder, diameter and length are come concrete design according to the length and the weight of landing runway.
Except that the described technical characterictic of specification sheets, be the known technology of those skilled in the art.
Claims (1)
1. device is blocked in the aircraft carrier landing, it is characterized in that comprising that at least three are blocked the device assembly, and each blocks the device assembly and 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, and the check cable intermediate lateral is arranged in the middle of the landing runway; Damper comprises fixed frame, tracheae, high pressure gas holder, several damping cylinders; Be provided with piston in each damping cylinder, piston is connected with pitch brace, and 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, and the other end of check cable and opposed damper fixed frame are fixed, and wear around between movable pulley and the fixed pulley centre of check cable;
Damping cylinder and fixed frame are fixed, and fixed frame and aircraft carrier hull are fixed, and 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, electric T-shaped valve is provided with evacuation port; Evacuation port is provided with the electronic control pressure reducing valve, also is provided with recoil spring on the pitch brace of the head of damping cylinder;
The damping step is following:
1) high pressure gas holder is inflated in damping cylinder through tracheae, and piston moves to the damping cylinder afterbody, and is through the bonded assembly pitch brace that check cable is stretching subsequent use; Open the automatically controlled triple valve that connects high pressure gas holder, let tracheae communicate, the electronic control pressure reducing valve is set on the evacuation port with evacuation port;
2) carrier-borne aircraft landing, the afterbody drag hook slips over landing runway, with a check cable hook at least three road check cables check cable is stretched along the aircraft landing direction; Check cable pulling movable pulley, movable pulley is through pitch brace pulling piston, and piston moves the air in the compression cylinder to the damping cylinder head; Produce shock damping action; Compressed air is through spreading in the damping cylinder of tracheae in other dampers, and a part discharges to atmosphere through the electronic control pressure reducing valve on the triple valve evacuation port, reduces the pressure in the compressed damping cylinder; Play the pressure buffer effect; Because check cable detours between some movable pulleys and fixed pulley, the miles of relative movement sum of each movable pulley is taken advantage of in 2 being exactly the stretched length of check cable, and the quantity that increases or reduce damping cylinder is the damping distance of scalable aircraft landing; Regulate the automatically controlled breathing valve aperture of damping cylinder afterbody, 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 subsequent use;
3) open the automatically controlled triple valve of high pressure gas holder, let the pressurized air in the high pressure gas holder get into damping cylinder through tracheae, the piston playback, check cable is stretching again subsequent use, and it is subsequent use that Air compressor thinks to replenish high pressure air in the high pressure gas holder.
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 true CN102530210A (en) | 2012-07-04 |
| CN102530210B CN102530210B (en) | 2014-07-23 |
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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) |
Cited By (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 |
| CN108860657A (en) * | 2018-05-18 | 2018-11-23 | 西北工业大学 | Aircraft blocks experimental rig and aircraft blocks load transmission analog machine |
| 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 |
| CN113665832A (en) * | 2021-08-13 | 2021-11-19 | 航天时代飞鹏有限公司 | Unmanned aerial vehicle intelligent airport ground system |
| CN118163955A (en) * | 2024-05-14 | 2024-06-11 | 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 (2)
| Title |
|---|
| 李杰等: "航空母舰的舰载机着舰装备", 《现代军事》 * |
| 王海东等: "MK723型拦阻装置滑轮运动特性分析", 《舰船科学技术》 * |
Cited By (9)
| 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 |
| CN108860657A (en) * | 2018-05-18 | 2018-11-23 | 西北工业大学 | Aircraft blocks experimental rig and aircraft blocks load transmission analog machine |
| 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 |
| CN113665832A (en) * | 2021-08-13 | 2021-11-19 | 航天时代飞鹏有限公司 | Unmanned aerial vehicle intelligent airport ground system |
| 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 |
| CN118163955A (en) * | 2024-05-14 | 2024-06-11 | 中国人民解放军海军航空大学 | Runway interception device |
| CN118163955B (en) * | 2024-05-14 | 2024-07-26 | 中国人民解放军海军航空大学 | Runway interception device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102530210B (en) | 2014-07-23 |
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Owner name: HAIMEN JIANGHAI CONSTRUCTION INVESTMENT CO., LTD. Free format text: FORMER OWNER: ZHU HUIFEN Effective date: 20141104 |
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| C41 | Transfer of patent application or patent right or utility model | ||
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Free format text: CORRECT: ADDRESS; FROM: 250014 JINAN, SHANDONG PROVINCE TO: 226100 NANTONG, JIANGSU PROVINCE |
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| TR01 | Transfer of patent right |
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 |