CN102485595A - Aircraft landing damper for aircraft carrier - Google Patents
Aircraft landing damper for aircraft carrier Download PDFInfo
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- CN102485595A CN102485595A CN2009102182361A CN200910218236A CN102485595A CN 102485595 A CN102485595 A CN 102485595A CN 2009102182361 A CN2009102182361 A CN 2009102182361A CN 200910218236 A CN200910218236 A CN 200910218236A CN 102485595 A CN102485595 A CN 102485595A
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- fixed pulleys
- oil
- hydraulic
- steel cable
- oil cylinder
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Abstract
The invention relates to an aircraft landing damper for an aircraft carrier. The aircraft landing damper comprises two hydraulic cylinders, hydraulic oil tanks, high-pressure oil pumps, work motors, high-pressure pipelines, a steel rope and fixed pulleys, wherein the high-pressure pipelines are used for interconnecting the two hydraulic cylinders, the hydraulic oil tanks, the high-pressure oil pumps and the work motors, the steel rope is connected with pistons in the hydraulic cylinders, and the fixed pulleys are used for mounting the steel rope; the two hydraulic cylinders are parallel side by side; two ends of the steel rope are respectively and fixedly connected with the pistons in the two hydraulic cylinders; two parallel fixed pulleys are mounted in front of each hydraulic cylinder respectively, the edge of one of the two parallel fixed pulleys is correspondingly located on the same straight line as the steel rope in each hydraulic cylinder, and the edge of the other one of the two parallel fixed pulleys is located at an outer side of the end cover of each hydraulic cylinder and is not in contact with the end cover of each hydraulic cylinder; and two fixed pulleys are amounted in front of the other end of each hydraulic cylinder and are located between extension lines of the two hydraulic cylinders, the two fixed pulleys are located on the same straight line, and the distance between the two fixed pulleys ensures a space needed for the landing of an aircraft.
Description
Technical field
The present invention relates to a kind of carrier-based aircraft landing damper.
Background technology
Aircraft carrier is boarded a plane, and landing is used for slowing down and resistance trolley that aircraft is stopped rapidly is by a kind of mechanism that is called damper resistance to be provided, and adapts to the technology that aircraft landing slows down gradually.Be carrier-borne aircraft can aircraft carrier normally take off the landing indispensable equipment.
Summary of the invention
The present invention provides a kind of aircraft safe falling damper on aircraft carrier with hydraulic technique.
The technical scheme that realizes above-mentioned purpose is:
Carrier-based aircraft landing damper; Comprise hydraulic ram, hydraulic reservoir, high-pressure oil pump and work drive motor and be connected they pressure duct and with hydraulic ram in piston bonded assembly steel cable and the fixed pulley of steel cable is installed; Two parallel hydraulic rams arranged side by side are wherein arranged; The two ends of steel cable respectively with two hydraulic rams in piston captive joint, in the place ahead of two hydraulic rams two fixed pulleys arranged side by side are installed respectively, the edge of one of them fixed pulley is corresponding in a straight line with steel cable in the oil cylinder; The edge of another fixed pulley will be in the outside of cylinder cover, does not contact with the end cap edge.In the place ahead of the other end of two hydraulic rams and be in two fixed pulleys are installed between two hydraulic ram extended lines, two fixed pulleys in a straight line and spacing guarantee the required space of aircraft landing.
The steel cable that connects two oil cylinder pistons is walked around two fixed pulleys outside the oil cylinder outlet, turn to 90 degree to walk around again and be in oil cylinder two fixed pulleys of end in addition, and promptly steel cable contacts with each fixed pulley cliding friction.At the toe lateral wall opening of oil cylinder the high pressure oil pipeline is installed, is communicated with oil pump and hydraulic reservoir respectively, and oil pump be switched in the oil cylinder again after high pressure oil pipeline between fuel tank is communicated with.Between oil pump and fuel tank, there is the high pressure oil pipeline to be communicated with.A by-pass valve control is installed in the high pressure oil pipeline between fuel tank to oil cylinder.Gap is between the two blocked by oil sealing in the end cap exit of steel cable and two oil cylinders.
Promptly can be made into a kind of carrier-based aircraft landing damper that constitutes by hydraulic ram and corresponding oil pump, fuel tank and steel cable according to aforesaid way.It is simple in structure, uses hydraulic ram and high pressure oil pipeline and resistance mechanism that the steel cable controlled forms, make from the aircraft that drops in the air on the aircraft carrier deck and obtain flexible resistance, between the distance of the fixed pulley at oil cylinder two ends by the shutdown of slowing down.
Description of drawings
Fig. 1 is the structural representation of aircraft landing damper.
The specific embodiment
Below in conjunction with accompanying drawing, technical scheme is further specified as embodiment.
With reference to 1, damper comprises two being made up of oil cylinder 11 and corresponding high-pressure oil pump 6 and work drive motor 5, fuel tank 9 and pipeline 7 of symmetry fully.The oil cylinder 11 of damper is processed cylindrical shape; The Resistance Value that the size of the resistance of the speed required generation of length during according to aircraft 16 safe fallings and oil cylinder mesohigh oil produce piston 12; Can guarantee that aircraft safety lands designs, i.e. the active distance of 12 operations of the piston in the oil cylinder will be that aircraft landing slides into and shuts down needed length; Midway location at oil cylinder is installed an oil pressure indicator 10, so that observe oil pressure value.Oil cylinder is processed with high strength steel, is manufactured with annular groove on piston 12 cylinders in the cylinder, and flexible seal ring 13 is installed in the groove; Can slide between assurance and casing wall; The effective high pressure oil in the oil cylinder chamber, packed-piston front again, piston 12 operations are carried out high pressure oil fully forward, to produce enough resistances.The requirements for quality of the impulsive force that speed produced when steel cable 14 structures should guarantee to bear aircraft landing, and can combine closely oily no leak in the oil cylinder with the oil sealing 3 in cylinder cover 4 exits.
With reference to 1; Two oil cylinder front ends respectively have two fixed pulleys arranged side by side; Steel cable 14 in-lines that come out in fixed pulley 2 and the oil cylinder, with steel cable break-in an angle of 90 degrees, another fixed pulley 1 is with steel cable break-in an angle of 90 degrees again; Through the effect of these two fixed pulleys, make the steel cable service direction realize that turning to of 180 degree angles is socketed in 11 of two oil cylinders again and on two fixed pulleys 15 of the other end.Like this, make the aircraft that settles out, when touching the deck, the tail under dragging behind the machine colludes 17, catches on steel cable, and piston 12 advances in the pulling oil cylinder 11, has just produced resistance, and air speed is slowed down rapidly, to directly stopping.
Before above-mentioned operational process, high-pressure oil pump 6 is squeezed into high pressure oil in the oil cylinder 11, and at this moment, and the valve in the pipeline between fuel tank 8 closes, and to oil pump 6 fuel feeding, what guarantee to inject oil cylinder 11 is high pressure oil from fuel tank 9 along pipeline.Aircraft 16 landing, pulling piston 12 ahead runnings, high pressure oil gives piston with big resistance; Pass to steel cable 14, simultaneously the oil pressure in the oil cylinder is gone out, the valve 8 in the pipeline is opened; The oil of having done merit in the oil cylinder 11 is along this pipeline backflow oil-feed tank 9, and in order to oil pump fuel feeding once more, oil pump re-injects high pressure oil in oil cylinder; Piston 12 is back into the rearmost end of oil cylinder 11 again, arrange the landing of next aircraft fully.
Claims (5)
1. carrier-based aircraft landing damper; Comprise hydraulic ram (11), hydraulic reservoir (9), high-pressure oil pump (6) and work drive motor (5) and be connected they pressure duct (7), with hydraulic ram in piston (12) bonded assembly steel cable (14) and the fixed pulley (2,1,15) of steel cable is installed; It is characterized in that having two parallel hydraulic rams arranged side by side (11); The two ends of steel cable (14) respectively with two hydraulic rams in piston (12) captive joint; Two fixed pulleys arranged side by side (1,2) respectively are installed in the place ahead of two hydraulic rams (11); The edge of one of them fixed pulley (2) is corresponding in a straight line with steel cable (14) in the oil cylinder, and the edge of another fixed pulley (1) will be in the outside of cylinder cover (4), does not contact with the end cap edge; In the place ahead of the other end of two hydraulic rams and be in two fixed pulleys are installed between two hydraulic ram extended lines, two fixed pulleys in a straight line and spacing guarantee the required space of aircraft landing.
2. carrier-based aircraft landing damper according to claim 1; The steel cable (14) that it is characterized in that connecting two oil cylinder pistons (12) is walked around two fixed pulleys (2,1) outside the oil cylinder outlet; Turn to 90 degree to walk around again and be in oil cylinder two fixed pulleys (15) of end in addition, steel cable (14) contacts with each fixed pulley cliding friction.
3. carrier-based aircraft landing damper according to claim 1; Toe lateral wall opening at oil cylinder (11) is installed high pressure oil pipeline (7); Be communicated with oil pump (6) and hydraulic reservoir (9) respectively, and oil pump (6) be switched to again in the oil cylinder (11) after high pressure oil pipeline (7) between fuel tank (9) is communicated with.
4. carrier-based aircraft according to claim 1 landing damper has high pressure oil pipeline (7) to be communicated with between oil pump (6) and fuel tank (9), an installation by-pass valve control (8) in the high pressure oil pipeline between fuel tank (9) to oil cylinder (11).
5. carrier-based aircraft landing damper according to claim 1, steel cable (14) is blocked gap between the two with end cap (4) exit of two oil cylinders (11) by oil sealing (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102182361A CN102485595A (en) | 2009-11-24 | 2009-11-24 | Aircraft landing damper for aircraft carrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102182361A CN102485595A (en) | 2009-11-24 | 2009-11-24 | Aircraft landing damper for aircraft carrier |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102485595A true CN102485595A (en) | 2012-06-06 |
Family
ID=46151173
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009102182361A Pending CN102485595A (en) | 2009-11-24 | 2009-11-24 | Aircraft landing damper for aircraft carrier |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102485595A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102923311A (en) * | 2012-11-10 | 2013-02-13 | 明峰 | Arrester wire system for aircraft to take off and land on aircraft carrier |
| CN103640694A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Hook arm of buffer load-shedding arresting hook |
| CN105691631A (en) * | 2014-11-28 | 2016-06-22 | 四川航空工业川西机器有限责任公司 | Hydraulic ejection high-speed damping buffer system |
| CN107472550A (en) * | 2017-09-19 | 2017-12-15 | 方立波 | Arresting gear and its system energetically |
| CN108058844A (en) * | 2017-12-15 | 2018-05-22 | 陈穗 | A kind of aircraft landing brake apparatus peculiar to vessel |
| CN110282146A (en) * | 2019-06-19 | 2019-09-27 | 西安电子科技大学 | A kind of fixed-wing unmanned plane recovery system |
| CN115432199A (en) * | 2022-11-09 | 2022-12-06 | 南京航空航天大学 | Unmanned aerial vehicle arresting system and working method thereof |
Citations (5)
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| GB886274A (en) * | 1957-05-23 | 1962-01-03 | Acme Prec Products Inc | Vehicle decelerating apparatus |
| CN1032645A (en) * | 1988-10-18 | 1989-05-03 | 黄泽荣 | Stol device for ultralight aircraft |
| US5042750A (en) * | 1989-11-16 | 1991-08-27 | Datron, Inc. | Aircraft arresting system |
| CN1146414A (en) * | 1994-09-05 | 1997-04-02 | 朱炎 | Airplane catapult and recovery system |
| CN101054115A (en) * | 2007-04-25 | 2007-10-17 | 张�杰 | High-pressure steam dynamic sealing ejection machine for aircraft carrier |
-
2009
- 2009-11-24 CN CN2009102182361A patent/CN102485595A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB886274A (en) * | 1957-05-23 | 1962-01-03 | Acme Prec Products Inc | Vehicle decelerating apparatus |
| CN1032645A (en) * | 1988-10-18 | 1989-05-03 | 黄泽荣 | Stol device for ultralight aircraft |
| US5042750A (en) * | 1989-11-16 | 1991-08-27 | Datron, Inc. | Aircraft arresting system |
| CN1146414A (en) * | 1994-09-05 | 1997-04-02 | 朱炎 | Airplane catapult and recovery system |
| CN101054115A (en) * | 2007-04-25 | 2007-10-17 | 张�杰 | High-pressure steam dynamic sealing ejection machine for aircraft carrier |
Non-Patent Citations (2)
| Title |
|---|
| 于浩: "舰载飞机着舰动态性能仿真研究", 《中国优秀硕士学位论文全文数据库》 * |
| 李杰: "航空母舰的舰载机着舰装备", 《现代军事》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102923311A (en) * | 2012-11-10 | 2013-02-13 | 明峰 | Arrester wire system for aircraft to take off and land on aircraft carrier |
| CN103640694A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Hook arm of buffer load-shedding arresting hook |
| CN105691631A (en) * | 2014-11-28 | 2016-06-22 | 四川航空工业川西机器有限责任公司 | Hydraulic ejection high-speed damping buffer system |
| CN107472550A (en) * | 2017-09-19 | 2017-12-15 | 方立波 | Arresting gear and its system energetically |
| CN108058844A (en) * | 2017-12-15 | 2018-05-22 | 陈穗 | A kind of aircraft landing brake apparatus peculiar to vessel |
| CN108058844B (en) * | 2017-12-15 | 2019-09-10 | 陈穗 | A kind of aircraft landing brake apparatus peculiar to vessel |
| CN110282146A (en) * | 2019-06-19 | 2019-09-27 | 西安电子科技大学 | A kind of fixed-wing unmanned plane recovery system |
| CN115432199A (en) * | 2022-11-09 | 2022-12-06 | 南京航空航天大学 | Unmanned aerial vehicle arresting system and working method thereof |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
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Application publication date: 20120606 |