CN104002981A - Carrier plane landing aid system for small aircraft carriers - Google Patents
Carrier plane landing aid system for small aircraft carriers Download PDFInfo
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- CN104002981A CN104002981A CN201310056192.3A CN201310056192A CN104002981A CN 104002981 A CN104002981 A CN 104002981A CN 201310056192 A CN201310056192 A CN 201310056192A CN 104002981 A CN104002981 A CN 104002981A
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- arrester
- hydraulic brake
- arresting
- brake mechanism
- landing
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Abstract
The invention discloses a carrier plane landing aid system for small aircraft carriers. The carrier plane landing aid system for small aircraft carriers comprises three sets of arresting gears arranged side by side along the direction of an airstrip, respectively being a first set of arresting gear, a second set of arresting gear and a third set of arresting gear; each set of arresting gear includes an arresting wire, a plane rear wheel position detection device, a left hydraulic brake mechanism and a right hydraulic brake mechanism, wherein the left and right hydraulic brake mechanisms are respectively arranged on two sides of the airstrip, two ends of the arresting wire are respectively connected with the left and right hydraulic brake mechanisms, an arresting wire hiding slot is arranged on the upper edge of the airstrip in the direction perpendicular to the airstrip, the arresting wire is arranged in the arresting wire hiding slot which comprises a front side surface and a rear side surface, the front side surface is a slope, and the rear side surface is a vertical plane. According to the carrier plane landing aid system for small aircraft carriers, through adding active detection at the landing positions of planes and hiding the arresting wires in the deck, space required for landing of the planes is greatly reduced, and meanwhile safety in landing of the carrier planes are further improved.
Description
Technical field
The invention belongs to aircraft landing technical field, be specifically related to a kind of small-sized aircraft carrier ship-board aircraft landing ancillary system.
Background technology
Aircraft carrier barrier cable is to fix above deck now, judge whether the sensor that the device of being caught by arrester wires only has aircraft arrestment to hook, caught by arrester wires if sensor detects aircraft, just can slow down, if now arrester wires fracture, aircraft will fall lower runway so.Present design produces in order to prevent such situation, is provided with three redundancies to four arrester wires, and such redundancy is mainly for aircraft provides between more dropping zone, can not ensure that aircraft can hook whole arrester wires.
In addition, for small-sized aircraft carrier, because space is restricted, above-mentioned setting occupies larger space, is extremely unfavorable for the operation on warship face.
Summary of the invention
The object of the invention is to improve the arrester wires structure of existing aircraft carrier, a kind of ship-board aircraft landing auxiliary device is provided, solve above-mentioned problems of the prior art.
Technical scheme of the present invention is as follows:
A kind of small-sized aircraft carrier landing ancillary system, it is characterized in that, described small-sized aircraft carrier landing ancillary system comprises the arrester that three covers are arranged side by side along airstrip direction, be respectively first set arrester, the second cover arrester and the 3rd cover arrester, every cover arrester comprises arrester wires, aircraft trailing wheel position detecting device, left hydraulic brake mechanism and right hydraulic brake mechanism, left hydraulic brake mechanism and right hydraulic brake mechanism are located at respectively runway both sides, arrester wires two ends are connected with left hydraulic brake mechanism and right hydraulic brake mechanism respectively, on runway, hide groove along being provided with arrester wires with runway vertical direction, arrester wires is located in this hiding groove, described hiding groove has leading flank and two sides of trailing flank, leading flank is inclined-plane, trailing flank is vertical plane.
Principle of the present invention is: when aircraft warship, if trailing wheel is not yet by first set arrester, aircraft slides forward, the aircraft trailing wheel position detecting device of first set arrester detects aircraft trailing wheel, the left hydraulic brake mechanism of PLC system control on naval vessel and right hydraulic brake mechanism tension arrester wires, arrester wires slides into runway top along the inclined-plane that hides groove, to be combined with aircraft pintle, Bian You tri-road arrester wires stop like this, can stop rapidly aircraft, also can prevent the danger causing of rupturing of certain root arrester wires; Even trailing wheel is by first set arrester when aircraft warship, also have twice arrester, can ensure that equally aircraft the safety of warship; If trailing wheel is by the second cover arrester when aircraft warship, PLC system control the 3rd cover arrester does not start, and directly sends the instruction of going around to aircraft.
The present invention is mainly towards small-sized ships, certainly also can be used for large-scale by having increased the active detecting of aircraft landing position and arrester wires being hidden in deck, greatly dwindle the needed space of aircraft landing, further improved the safety of carrier-borne aircraft landing simultaneously.
Brief description of the drawings
The structural representation of the small-sized aircraft carrier ship-board aircraft landing of Fig. 1 the present invention ancillary system.
Fig. 2 is the structural representation of hiding groove.
Detailed description of the invention
Embodiment:
As Fig. 1, of the present invention small-sized aircraft carrier landing ancillary system shown in Fig. 2, small-sized aircraft carrier landing ancillary system comprises the arrester that three covers are arranged side by side along airstrip direction, be respectively first set arrester 100, the second cover arrester 200 and the 3rd cover arrester 300, first set arrester comprises arrester wires 110, aircraft trailing wheel position detecting device 120, left hydraulic brake mechanism 130 and right hydraulic brake mechanism 140, aircraft trailing wheel position detecting device 120 is located at arrester wires front side on left hydraulic brake mechanism 130 and is electrically connected with the left hydraulic brake mechanism 130 of control on warship and the PLC system of right hydraulic brake mechanism 140, left hydraulic brake mechanism 130 and right hydraulic brake mechanism 140 are located at respectively runway 400 both sides, arrester wires 110 two ends are connected with left hydraulic brake mechanism 130 and right hydraulic brake mechanism 140 respectively, on runway, hide groove 150 along being provided with arrester wires with runway vertical direction, arrester wires 110 is located in this hiding groove 150, hide groove 150 and there are leading flank 151 and 152 two sides of trailing flank, leading flank 151 is inclined-plane, trailing flank 152 is vertical plane, the second cover arrester 200 has with first set and stops the structure that system is identical with the 3rd cover arrester 300, repeat no more.
Direction when arrow indication is aircraft landing in figure, above-mentioned " front " and in " afterwards ", " afterwards " is arrow direction, " front " otherwise.
Be more than preferred embodiment of the present invention, but the present invention should not be confined to the disclosed content of this embodiment.Do not depart from the equivalence or the amendment that under spirit disclosed in this invention, complete so every, all fall into the scope of protection of the invention.
Claims (1)
1. a small-sized aircraft carrier landing ancillary system, it is characterized in that, described small-sized aircraft carrier landing ancillary system comprises the arrester that three covers are arranged side by side along airstrip direction, be respectively first set arrester, the second cover arrester and the 3rd cover arrester, every cover arrester comprises arrester wires, aircraft trailing wheel position detecting device, left hydraulic brake mechanism and right hydraulic brake mechanism, left hydraulic brake mechanism and right hydraulic brake mechanism are located at respectively runway both sides, arrester wires two ends are connected with left hydraulic brake mechanism and right hydraulic brake mechanism respectively, on runway, hide groove along being provided with arrester wires with runway vertical direction, arrester wires is located in this hiding groove, described hiding groove has leading flank and two sides of trailing flank, leading flank is inclined-plane, trailing flank is vertical plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310056192.3A CN104002981A (en) | 2013-02-22 | 2013-02-22 | Carrier plane landing aid system for small aircraft carriers |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310056192.3A CN104002981A (en) | 2013-02-22 | 2013-02-22 | Carrier plane landing aid system for small aircraft carriers |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104002981A true CN104002981A (en) | 2014-08-27 |
Family
ID=51363944
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310056192.3A Pending CN104002981A (en) | 2013-02-22 | 2013-02-22 | Carrier plane landing aid system for small aircraft carriers |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104002981A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104803005A (en) * | 2015-05-13 | 2015-07-29 | 南京航空航天大学 | Automatic carrier landing composite control method of carrier airflow compensation-containing carrier-borne aircraft |
| CN105065563A (en) * | 2015-09-07 | 2015-11-18 | 成都特戎新材料有限公司 | Kinetic energy buffering absorption device, kinetic energy absorption device and manufacturing technology thereof |
| CN105518488A (en) * | 2014-11-19 | 2016-04-20 | 深圳市大疆创新科技有限公司 | Positioning mechanism, uav base station using the positioning mechanism, and uav replenishment method |
| CN106553763A (en) * | 2015-09-30 | 2017-04-05 | 张承普 | Telescopic arrester wires |
| CN109050960A (en) * | 2018-07-20 | 2018-12-21 | 朱建华 | A kind of arresting gear to land for aircraft safety |
-
2013
- 2013-02-22 CN CN201310056192.3A patent/CN104002981A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105518488A (en) * | 2014-11-19 | 2016-04-20 | 深圳市大疆创新科技有限公司 | Positioning mechanism, uav base station using the positioning mechanism, and uav replenishment method |
| CN105518488B (en) * | 2014-11-19 | 2017-03-15 | 深圳市大疆创新科技有限公司 | Detent mechanism and the UAV base stations using the detent mechanism, UAV replenishing methods |
| US10414517B2 (en) | 2014-11-19 | 2019-09-17 | SZ DJI Technology Co., Ltd. | Positioning mechanism, UAV dock using same, and UAV replenishment method |
| US11524796B2 (en) | 2014-11-19 | 2022-12-13 | SZ DJI Technology Co., Ltd. | Positioning mechanism, UAV dock using same, and UAV replenishment method |
| CN104803005A (en) * | 2015-05-13 | 2015-07-29 | 南京航空航天大学 | Automatic carrier landing composite control method of carrier airflow compensation-containing carrier-borne aircraft |
| CN105065563A (en) * | 2015-09-07 | 2015-11-18 | 成都特戎新材料有限公司 | Kinetic energy buffering absorption device, kinetic energy absorption device and manufacturing technology thereof |
| CN105065563B (en) * | 2015-09-07 | 2018-04-17 | 成都特戎新材料有限公司 | Kinetic energy snubber device, dynamic energy absorber and its manufacture craft |
| CN106553763A (en) * | 2015-09-30 | 2017-04-05 | 张承普 | Telescopic arrester wires |
| CN109050960A (en) * | 2018-07-20 | 2018-12-21 | 朱建华 | A kind of arresting gear to land for aircraft safety |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140827 |