CN103587712A - Electromagnetic landing system of aircraft carrier - Google Patents
Electromagnetic landing system of aircraft carrier Download PDFInfo
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- CN103587712A CN103587712A CN201310620135.3A CN201310620135A CN103587712A CN 103587712 A CN103587712 A CN 103587712A CN 201310620135 A CN201310620135 A CN 201310620135A CN 103587712 A CN103587712 A CN 103587712A
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Abstract
The invention discloses an electromagnetic landing system of an aircraft carrier. A stator rail for a linear motor is arranged under a landing deck, a landing trolley is arranged on a rotor of the linear motor, a landing platform is arranged on the landing trolley, and the height of the landing platform can be adjusted to improve the capture rate of the landing platform. A wedge-shape opening groove is further formed in the landing platform, the wedge-shaped opening groove is matched with a wedge-shape tenon in the front edge of an air craft landing gear, and the landing platform is further provided with a fine adjusting device and a controlling device. The electromagnetic landing system has the advantages that the two wedge-shaped parts can approach to each other but cannot be in contact under the action of magnetic repulsive force to achieve a buffer function, so that aircrafts can land safely. In addition, the electromagnetic landing system is quick in response speed, safe and reliable.
Description
Technical field
The present invention relates to a kind of aircraft carrier landing system, particularly a kind of electromagnetism carrier landing system of aircraft carrier.
Background technology
Aircraft at a high speed will land on short narrow aircraft carrier Yue plate, and difficulty is very large, can only take at present check cable make aircraft speed in short range be kept to very much zero and warship.But the speed of aircraft is several hundred kilometers/hour blocked by check cable, and aircraft velocity variations is at short notice very large, and the impact joint power causing is also very large.The application problem of this check cable system is a lot, has become the major cause that aircraft landing accident occurs: aircraft flies too highly, and hook incessantly will go around; Fly to such an extent that too low meeting is flushed on deck, loss occurs larger; Hook is inclined to one side can make wing on one side land, and the action of each parts such as the steel rope on check cable both sides, pulley system and oil cylinder is slightly inharmonious will draw aircraft askewly, seriously understands fatal crass.
Since having had a century of aircraft carrier, the casualty accident on aircraft carrier nearly more than 12,000 rises, dead more than 8,000 people wherein, and these accidents adopt check cable to cause at aircraft landing during on deck mostly.
Publication number is that the patent documentation of CN101439761A discloses soft carrier landing system, by body and warship pin down rope to form aircraft landing place be the water surface, body pull soft the warship of realizing on the water surface of restricting for warship pins down.
Publication number is the open security landing-assistant rescuing system for breakdown plane of the patent documentation of CN101837838A, when undercarriage cannot be opened, aircraft can only force-land by aircraft belly and ground friction, this is danger close, security landing-assistant rescuing system for breakdown plane can make after breakdown plane docking, thereby makes aircraft be fixed on the safe falling that completes aircraft in motorcycle.
Publication number be the open landing system of flight vehicle of the patent documentation of CN10250982A comprise be arranged on indoor shooting visual angle, hole can continuously controllable camera head, communication and computer installation, midline position in predetermined glidepath is provided with the video processing unit calculating with synthesising frame analog video and side-play amount in order to the chamber, hole of camera head computing machine used, can make aviator obtain the situation of real-time flight route and desirable glide path, revise in time aircraft and the attitude before warship, implement the steadily land of safety of aircraft.
Summary of the invention
Technical matters to be solved by this invention is that a kind of fast response time will be provided
, the electromagnetism carrier landing system of safe and reliable aircraft carrier.
In order to solve above technical matters, the invention provides a kind of electromagnetism carrier landing system of aircraft carrier, at landing deck, have the stator track of straight line motor, landing dolly is housed on the rotor of linear electric motors, landing dolly is provided with landing platform, the height of landing platform can be adjusted, to increase the capture rate of landing platform.On landing platform, be also provided with a wedge type open slot, the wedge type tenon in this wedge type open slot and undercarriage column forward position matches, landing platform is also provided with micromatic setting and control setup, control setup receives flight status data, linear motor rotor data and landing platform data, send the running velocity that landing dolly is controlled in instruction, make aircraft can utilize calutron warship.
The plate of described wedge type open slot both sides is electromagnetism pole plate, and has magnetic repulsion between the wedge type tenon in undercarriage column forward position, and vector aircraft enters landing passage.
Described micromatic setting is hydraulic ram micromatic setting, is installed on the horizontal hydraulic ram micromatic setting of landing dolly and is connected with landing platform, controls the horizontal fine setting displacement of landing platform.
Described control setup is microprocessor, receives after the data of flight status data, linear motor rotor data and landing platform, carries out data operation, thereby controls height, the speed of linear motor stator electric operation, hydraulic ram micromatic setting and aircraft.
On described landing platform, be also provided with the brake equipment that blocks aircraft tyre.
The height of wedge type open slot is wide is about 1 meter of square, correspondingly to match with dolly wedge type opening in the installing of the forward position of alighting gear column wedge shape tenon, and this wedge shape tenon has vertical buffering that alighting gear brings and the buffering of rubber front-wheel; Two wedge pieces approach at a high speed, from several meters of zero points to zero point zero process of several meters be the magnetic force repelling each other, this magnetic repulsion does not contact); Landing dolly is down to speed zero in the stroke of hundred meters of left and right, and aircraft has also just stopped.
When aircraft is being prepared after flight through living warship, electromagnetism carrier landing system receives aircraft and has dropped to certain altitude, and there is certain speed, and there is certain distance with the aircraft carrier terminal that gets on the right track, after the information such as the line of centers that the line of centers of aircraft and aircraft carrier get on the right track coincide, control setup just sends instruction to linear electric motors, and linear motor rotor is advanced with suitable acceleration/accel together with landing dolly, make the speed of aircraft omit the speed together with landing dolly faster than rotor, the position of rotor is slightly ahead of the position of aircraft.
This timed unit sends instruction aircraft landing on aircraft carrier deck, and because aircraft and the speed of landing dolly approach, their connection is easily carried out.Aircraft is caught by the wedge-like opening groove in the little coming year of landing, and aircraft is connected with landing dolly, makes them in certain stroke, speed is being down to zero, aircraft also just safety warship.If the distance of landing dolly and interplane is larger, can utilize electromagnetic system to regulate fast feature to slow down to dolly, to shorten the distance that connects walking, then accelerate, make when connecting the very approaching and impact while alleviating connection of their speed.
The wedge shape tenon of the nose undercarriage of aircraft is aimed at the wedge-like opening (exit skirt) on dolly, and the wedge shape tenon matching with dolly wedge-like opening in the forward position of alighting gear column is connected.This wedge shape tenon has vertical buffering that alighting gear brings and the buffering of rubber front-wheel; Two wedge pieces, under magnetic repulsion effect, can approach them and do not contact to play buffer action.This magnetic repulsion is pushing away aircraft (buffering and do not contact) all the time; Under the two control setup is controlled, make the rotor of linear electric motors, landing dolly and aircraft cause within the scope of acceleration force and evenly slow down can bear acceleration/accel, make dolly and aircraft, in certain stroke, speed is being down to zero, aircraft also just safely warship.
The present invention, when aircraft does not also drop on landing dolly, must control the height of aircraft, and speed, makes aircraft line of centers overlap with runway centerline, and the speed of controlling dolly make aircraft can be in the best condition warship on dolly.After aircraft is together with landing dolly secure bond, with regard to available linear electric motors, control, what make them waits deceleration/decel operation, and the impact that deceleration/decel is caused aircraft and aviator reduces to minimum.
Superior effect of the present invention is:
1) two wedge pieces of the present invention, under magnetic repulsion effect, can approach them and do not contact to play buffer action, make the safe landing of aircraft energy;
2) both can protect numerous elite aviators not reason aircraft landing and injures and deaths, can protect again the aircraft of many costlinesses unlikely so and damage;
3) can avoid crossing and damaging greatly aircraft and chaufeur because of negative acceleration power, impulsive force;
4) adopt electromagnetism carrier landing system can make same runway can be used as the runway that launches taking off, can be used as the barrier runway of warship again, like this can be by four original catapult-assisted take-off runways for large-scale aircraft carrier,, a barrier runway, becoming five to six can take off or landing runway simultaneously, thereby accelerate to take off or sinking speed, improve its combat capabilities.
Accompanying drawing explanation
Fig. 1 is integral structure schematic diagram of the present invention;
Fig. 2 is the section drawing of Fig. 1;
Fig. 3 is schematic block circuit diagram of the present invention;
Fig. 4 is the structural representation of wedge type open slot;
Number in the figure explanation
1-stator track; 2-rotor;
3-landing dolly; 4-landing platform;
5-wedge-like opening groove; 6-wedge shape tenon.
The specific embodiment
Refer to shown in accompanying drawing, the present invention is described in further detail.
As depicted in figs. 1 and 2, the invention provides a kind of electromagnetism carrier landing system of aircraft carrier, at landing deck, have the stator track 1 of many linear electric motors, landing dolly 3 is housed on rotor 2 output shafts of linear electric motors, landing dolly 3 is provided with landing platform 4, landing platform 4 is convexly equipped with a wedge type open slot 5, this wedge type open slot 5 matches with the wedge type tenon 6 in undercarriage column forward position, landing platform 4 is also provided with micromatic setting and control setup, control setup receives flight status data, linear motor rotor data and landing platform data, send the running velocity that landing dolly is controlled in instruction, make aircraft electromagnetism warship.
The plate of described wedge type open slot 5 both sides is electromagnetism pole plate, and 6 of the wedge type tenons in undercarriage column forward position have magnetic repulsion.
The height of wedge type open slot 5 is wide be about 1 meter square.The wedge shape tenon 6 correspondingly matching with dolly wedge type opening in the forward position installing of alighting gear column, this wedge shape tenon 6 has vertical buffering that alighting gear brings and the buffering of rubber front-wheel; Two wedge pieces approach at a high speed, from several meters of zero points to zero point zero process of several meters be the magnetic buoyancy of repelling each other, this magnetic buoyancy is pushing away aircraft (buffering and do not contact) all the time; Landing dolly 3 is down to speed zero in the stroke of tens meters, and aircraft has also just stopped.
Described micromatic setting is hydraulic ram micromatic setting, is installed on the horizontal hydraulic ram micromatic setting of landing dolly and is connected with landing platform 4, controls the fine setting of the horizontal both direction of platform.
Described control setup is microprocessor, receives after the data of flight status data, linear motor rotor data and landing platform, carries out data reduction, thereby controls height, the speed of linear motor stator electric operation, hydraulic ram micromatic setting and aircraft.
On described landing platform 4, be also provided with the brake equipment that blocks aircraft tyre.
The present invention at aircraft landing to before dolly, control setup carries out actv. control to aircraft and dolly, aircraft and dolly are all flown or benz along the line of centers of runway, and make the position of aircraft directly over dolly, now aircraft should equate for how much with the speed of dolly, be that aircraft should be relative static with dolly, the aircraft of height in certain scope is just easy to drop on the correct position of dolly like this.Brake equipment on platform can block aircraft tyre if desired, will fly to be fixed on platform, and with the micromatic setting on dolly, platform be finely tuned, and aircraft is on most suitable position.The dolly that is loaded with aircraft makes their speed be down to zero with even deceleration/decel under the control of linear electric motors, thereby completes warship task.
Electromagnetism carrier landing system and electromagnetic ejection system, except the control system difference adopting, other parts are basic identical.Electromagnetism carrier landing system is that aircraft is slowed down, and makes aircraft energy safe falling, and electromagnetic ejection system is that aircraft is accelerated to take off on the contrary.These two systems can integrate, as utilize control circuit that electromagnetic force is changed to opposite sense, can share the equipment such as same linear electric motors, dolly.Make same runway can be used as the runway that launches taking off, again can be as the barrier runway of landing, like this can be by four original catapult-assisted take-off runways for large-scale aircraft carrier,, a barrier runway, becoming five to six can take off or landing runway simultaneously, thereby accelerate to take off or sinking speed, improve its combat capabilities.
Claims (5)
1. the electromagnetism carrier landing system of an aircraft carrier, it is characterized in that: the stator track that has straight line motor at landing deck, landing dolly is housed on the rotor of linear electric motors, landing dolly is provided with landing platform, on landing platform, be also provided with a wedge type open slot, the wedge type tenon in this wedge type open slot and undercarriage column forward position matches, landing platform is also provided with micromatic setting and control setup, control setup receives flight status data, linear motor rotor data and landing platform data, send the running velocity that landing dolly is controlled in instruction, make aircraft can utilize calutron warship.
2. the electromagnetism carrier landing system of aircraft carrier according to claim 1, is characterized in that: the plate of described wedge type open slot both sides is electromagnetism pole plate, and has magnetic repulsion between the wedge type tenon in undercarriage column forward position, and vector aircraft enters landing passage.
3. the electromagnetism carrier landing system of aircraft carrier according to claim 1, it is characterized in that: described micromatic setting is hydraulic ram micromatic setting, be installed on the horizontal hydraulic ram micromatic setting of landing dolly and be connected with landing platform, control the horizontal fine setting displacement of landing platform.
4. the electromagnetism carrier landing system of aircraft carrier according to claim 1, it is characterized in that: described control setup is microprocessor, receive after the data of flight status data, linear motor rotor data and landing platform, carry out data operation, thereby control height, the speed of linear motor stator electric operation, hydraulic ram micromatic setting and aircraft.
5. the electromagnetism carrier landing system of aircraft carrier according to claim 1, is characterized in that: on described landing platform, be also provided with the brake equipment that blocks aircraft tyre.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310620135.3A CN103587712A (en) | 2013-11-29 | 2013-11-29 | Electromagnetic landing system of aircraft carrier |
| CN201410581315.XA CN104670515B (en) | 2013-11-29 | 2014-10-28 | The electromagnetism carrier landing system of aircraft carrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310620135.3A CN103587712A (en) | 2013-11-29 | 2013-11-29 | Electromagnetic landing system of aircraft carrier |
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| Publication Number | Publication Date |
|---|---|
| CN103587712A true CN103587712A (en) | 2014-02-19 |
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| CN201310620135.3A Pending CN103587712A (en) | 2013-11-29 | 2013-11-29 | Electromagnetic landing system of aircraft carrier |
| CN201410581315.XA Active CN104670515B (en) | 2013-11-29 | 2014-10-28 | The electromagnetism carrier landing system of aircraft carrier |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410581315.XA Active CN104670515B (en) | 2013-11-29 | 2014-10-28 | The electromagnetism carrier landing system of aircraft carrier |
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| CN (2) | CN103587712A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103995465A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Transverse lateral guidance law design method |
| CN105046835A (en) * | 2015-08-26 | 2015-11-11 | 广州极飞电子科技有限公司 | Goods receiving method and device and goods delivery method and system |
| US10509416B2 (en) * | 2015-04-30 | 2019-12-17 | SZ DJI Technology Co., Ltd. | System and method for landing a mobile platform via a magnetic field |
| CN112340057A (en) * | 2020-11-05 | 2021-02-09 | 燕山大学 | Reliability increasing platform for carrier-based helicopter landing auxiliary equipment |
| CN113879695A (en) * | 2021-10-21 | 2022-01-04 | 河北汉光重工有限责任公司 | Adjustable stopping device |
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| CN108038258A (en) * | 2017-11-02 | 2018-05-15 | 成都飞机工业（集团）有限责任公司 | A kind of ejection impact dynamic response analysis method based on Coupled Rigid-flexible |
| CN108082521A (en) * | 2017-12-12 | 2018-05-29 | 佛山市神风航空科技有限公司 | A kind of electromagnet track systems |
| CN113643325B (en) * | 2021-06-02 | 2022-08-16 | 范加利 | Method and system for warning collision of carrier-based aircraft on aircraft carrier surface |
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| RU2005670C1 (en) * | 1992-06-30 | 1994-01-15 | Институт высоких температур научного объединения "Ивтан" | Device for decelerating aircraft (alternatives) |
| US6092763A (en) * | 1998-12-01 | 2000-07-25 | David John Hemes | Aircraft crash damage limitation system |
| US20060131462A1 (en) * | 2004-12-20 | 2006-06-22 | Holland Leo D | Turboelectric arresting gear |
| CN102398680A (en) * | 2010-09-09 | 2012-04-04 | 上海市南洋模范中学 | Airplane emergency landing urn entering device |
| CN202213719U (en) * | 2011-05-26 | 2012-05-09 | 李贺清 | Novel pressure dropping device of carrier aircraft |
| CN103224031B (en) * | 2013-02-19 | 2016-04-20 | 郭新民 | Fixed Wing AirVehicle landing gear |
| CN204184579U (en) * | 2013-11-29 | 2015-03-04 | 陈永年 | The electromagnetism carrier landing system of aircraft carrier |
-
2013
- 2013-11-29 CN CN201310620135.3A patent/CN103587712A/en active Pending
-
2014
- 2014-10-28 CN CN201410581315.XA patent/CN104670515B/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103995465A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Transverse lateral guidance law design method |
| CN103995465B (en) * | 2014-04-17 | 2017-04-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Transverse lateral guidance law design method |
| US10509416B2 (en) * | 2015-04-30 | 2019-12-17 | SZ DJI Technology Co., Ltd. | System and method for landing a mobile platform via a magnetic field |
| US11378982B2 (en) | 2015-04-30 | 2022-07-05 | SZ DJI Technology Co., Ltd. | System and method for landing a mobile platform via a magnetic field |
| US20220348316A1 (en) * | 2015-04-30 | 2022-11-03 | SZ DJI Technology Co., Ltd. | System and method for landing a mobile platform via a magnetic field |
| CN105046835A (en) * | 2015-08-26 | 2015-11-11 | 广州极飞电子科技有限公司 | Goods receiving method and device and goods delivery method and system |
| CN112340057A (en) * | 2020-11-05 | 2021-02-09 | 燕山大学 | Reliability increasing platform for carrier-based helicopter landing auxiliary equipment |
| CN113879695A (en) * | 2021-10-21 | 2022-01-04 | 河北汉光重工有限责任公司 | Adjustable stopping device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104670515A (en) | 2015-06-03 |
| CN104670515B (en) | 2017-11-14 |
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Application publication date: 20140219 |