CN104670515B - The electromagnetism carrier landing system of aircraft carrier - Google Patents
The electromagnetism carrier landing system of aircraft carrier Download PDFInfo
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- CN104670515B CN104670515B CN201410581315.XA CN201410581315A CN104670515B CN 104670515 B CN104670515 B CN 104670515B CN 201410581315 A CN201410581315 A CN 201410581315A CN 104670515 B CN104670515 B CN 104670515B
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Abstract
The present invention discloses a kind of electromagnetism carrier landing system of aircraft carrier, has the stator track of straight line motor in alighting deck, stopping device is housed on the rotor of linear electric motors；The stopping device is arrester hook and check cable, or is the stopping device with same polarity magnet；Control device receives flight status data and the position data of stopping device, transmits a signal to linear electric motors.It is an advantage of the invention that it is safest check cable is carried out constant speed connection when position is identical, speed is equal with pintle；Eliminate aircraft landing and accident caused by check cable is used at deck；Two wedge pieces enable them to play cushioning effect close to without contacting, enable aircraft safe landing under magnetic repulsion effect.
Description
Technical field
The present invention relates to a kind of aircraft carrier landing system, the electromagnetism carrier landing system of more particularly to a kind of aircraft carrier.
Background technology
The aircraft of high speed will land on short narrow aircraft carrier Yue plates, and difficulty is very big, check cable can only be taken to make aircraft at present
In very short distance speed be kept to zero and warship.But the speed of aircraft is that check cable blocks by several hundred kilometers/hour, and aircraft exists
Velocity variations in short time are very big, and caused impulsive force is also very big.This check cable systematic difference problem is a lot, it has also become
The main reason for aircraft landing accident occurs：Aircraft flies too high, and hook will incessantly be gone around；Fly too low to be flushed to deck
On, it is bigger that loss occurs；Hook is inclined to make one side wing land, and steel wire rope, pulley system and the oil cylinder on check cable both sides etc. are each
The action of part is slightly uncoordinated will to draw aircraft askew, seriously understand fatal crass.
Since having a century of aircraft carrier, the casualty accident up to more than 12,000 on aircraft carrier rises, wherein
Dead more than 8,000 people, these accidents are using caused by check cable mostly when aircraft landing is on deck.
Publication No. CN101439761A patent document discloses soft carrier landing system, and pining down rope with warship by body forms
Aircraft landing place is the water surface, body by warship pin down rope pulling realize soft the warship on the water surface.
Publication No. CN101837838A patent document discloses security landing-assistant rescuing system for breakdown plane, works as aircraft takeoffs and landings
When frame can not be opened, aircraft can only be force-landed by aircraft belly and ground friction, and this is danger close, and breakdown plane is safe
After landing-assistant rescuing system can dock breakdown plane, aircraft is set to be fixed in motorcycle so as to complete the safe falling of aircraft.
Publication No. CN10250982A patent document, which discloses landing system of flight vehicle, to be included being arranged on the indoor shooting in hole
Visual angle can continuously adjustabe camera device, communication and computer installation, be provided with the midline position of predetermined glidepath imaging
The video processing unit that computer used in the hole room of device is calculated with synthesising frame analog video and offset, can obtain pilot
The situation of real-time flight route and ideal glidepath is taken, aircraft is corrected in time and the posture before warship, implements the steady safety of aircraft
Land.
The content of the invention
The technical problems to be solved by the invention are to provide for a kind of electromagnetism carrier landing system of safe and reliable aircraft carrier.
In order to solve the technical problem of the above, the invention provides a kind of electromagnetism carrier landing system of aircraft carrier, landing
Deck has the stator track of straight line motor, is provided with the rotor of linear electric motors equipped with landing dolly, landing dolly
Landing platform, a wedge type open slot is additionally provided with landing platform, the wedge type open slot and the wedge type in undercarriage column forward position
Tenon matches, and the plate of wedge type open slot both sides is to have between electromagnetism pole plate, with the wedge type tenon in undercarriage column forward position
Magnetic repulsion, vector aircraft enter landing passage；Landing platform is additionally provided with micromatic setting and receives flight status data, straight
The control device of line rotor data and landing platform data, the control device transmit a signal to landing dolly.
The micromatic setting is hydraulic jack micromatic setting, be installed on the horizontal hydraulic jack micromatic setting of landing dolly with
Landing platform connects, and controls the horizontal fine setting displacement of landing platform.
The control device is microprocessor.
The brake apparatus for blocking aero tyre is additionally provided with the landing platform.
Invention further provides a kind of electromagnetism carrier landing system of aircraft carrier, straight line is had in alighting deck
The stator track of motor, device is connect equipped with blocking on the rotor of linear electric motors；Described block connects device and connects rope to block to connect hook and block, or for
Blocking for same polarity magnet connects device；Control device receives flight status data and blocks the position data for connecing device, and signal is transmitted
To linear electric motors；Described block connects hook and check cable and is connected with the afterbody of aircraft.
Aircraft is under landing signal official LSO commander, and when safe falling is to from a certain distance from mother ship carrier, it is straight just to start the present invention
Blocking on line motor connects device, according to the result of calculation of control device, blocks within a certain period of time and connects device and run with uniform acceleration, aircraft
After then being slided with uniform velocity, aircraft coincides with socketing the position of device, and speed is equal, and the constant speed for reaching both is converged, and now flies
Machine and block that to connect device connection effect be best.Aircraft and block that to connect device and be attached when relative velocity is close to zero be not have punching
Hit, be safe, aircraft landing can be eliminated accident caused by check cable is used at deck.Then again by linear electric motors with etc.
Deceleration makes aircraft and blocked to connect device and stop on predetermined position together, so pilot and aircraft can be made to bear in this section of stroke
Deceleration forces are caused to minimize by by deceleration.It is presently used with the aircraft of 360 kilometers of speed per hour and static stopping device phase
The caused lot of accident of connection can avoid.
Superior effect of the present invention is：
1）Two wedge pieces of the invention enable them to make close to without contacting to play to buffer under magnetic repulsion effect
With enabling aircraft safe landing；
2）Both numerous elite pilots not reason aircraft landing and injures and deaths can have been protected, flying for many costlinesses can be protected again
Therefore machine will not be damaged；
3）It can avoid because excessive negative acceleration makes to damage aircraft and driver impulsive force is excessive；
4）Using electromagnetism carrier landing system same runway can be made both to can serve as the ejection runway to take off, and can is used as blocking for warship
Runway is hindered, can be by four original catapult-assisted take-off runways so for large-scale aircraft carrier, a barrier runway, becoming five can
To take off or landing runway simultaneously, so as to accelerate to take off or sinking speed, improve its combat capabilities.
Brief description of the drawings
Fig. 1 is the overall structure diagram of the present invention；
Fig. 2 is Fig. 1 sectional view；
Fig. 3 is the schematic block circuit diagram of the present invention；
Fig. 4 is the structural representation of wedge type open slot；
Label declaration in figure
1-stator track；2-rotor；
3-landing dolly；4-landing platform；
5-wedge-like opening groove；6-wedge-shaped tenon.
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, divided into alighting deck
There is the stator track 1 of a plurality of linear electric motors, landing dolly 3 is housed on the output shaft of rotor 2 of linear electric motors, set on the dolly 3 that lands
There are landing platform 4, the wedge type open slot 5 of 4 projection of landing platform one, the wedge type open slot 5 and the wedge in undercarriage column forward position
Type tenon 6 matches, and landing platform 4 is additionally provided with micromatic setting and control device, control device receive flight status data,
Linear motor rotor data and landing platform data, the speed of service of instruction control landing dolly is sent, makes aircraft in electromagnetic force
In the presence of warship.
The plate of the both sides of wedge type open slot 5 is to have between electromagnetism pole plate, with the wedge type tenon 6 in undercarriage column forward position
There is magnetic repulsion.
High wide about 1 meter of square of wedge type open slot 5.Correspondingly install in the forward position of undercarriage column and opened with dolly wedge type
The wedge-shaped tenon 6 that mouth is engaged, the vertical buffering and the buffering of rubber front-wheel that this wedge-shaped tenon 6 is brought with undercarriage；Two
Individual wedge piece is close at a high speed, is the magnetic buoyancy repelled each other from several meters to 0. more than zero meter of process of zero point, this magnetic buoyancy pushes away all the time
Aircraft（Buffering is without being in contact）；Speed is down to zero by landing dolly 3 in tens meters of stroke, and aircraft also just stops
.
The micromatic setting is hydraulic jack micromatic setting, be installed on the horizontal hydraulic jack micromatic setting of landing dolly with
Landing platform 4 connects, the fine setting of control platform transverse direction both direction.
The control device is microprocessor, and it is flat to receive flight status data, linear motor rotor data and landing
After the data of platform, data reduction is carried out, so as to control linear motor stator electric operation, hydraulic jack micromatic setting and the height of aircraft
Degree, speed.Microprocessor MDV-STM32-407 including CPU and some peripheral assemblies can complete control work, also possess with
Host computer carries out the ability of network connection.
The brake apparatus for blocking aero tyre is additionally provided with the landing platform 4.
Before aircraft landing to dolly, control device is effectively controlled the present invention to aircraft and dolly, makes aircraft
And dolly is flown all along the center line of runway or benz, and make the position of aircraft directly over dolly, now aircraft and dolly
Speed answer geometry equal, i.e. aircraft and dolly should be geo-stationary, and so the aircraft highly in certain scope is just very
Easily drop on the correct position of dolly.Brake apparatus on platform can block aero tyre if necessary, and aircraft is fixed on
On platform, and platform is finely adjusted with the micromatic setting on dolly, aircraft is on most suitable position.It is loaded with aircraft
Dolly makes their speed be down to zero under the control of linear electric motors with even deceleration, so as to complete warship task.
When aircraft is after living warship and preparing flight, electromagnetism carrier landing system receives aircraft and has dropped down to certain altitude, and has
There is certain speed, and have certain distance with aircraft carrier upper rail terminal, the center line that the center line of aircraft gets on the right track with aircraft carrier coincide
After information, control device just sends instruction to linear electric motors, makes linear motor rotor together with landing dolly with appropriate acceleration
Degree advances, and the speed of aircraft is slightly faster than speed of the rotor together with landing dolly, the position of rotor is slightly ahead of the position of aircraft.
This timed unit sends instruction aircraft landing in type aircraft carrier deck, because the speed of aircraft and the dolly that lands is to connect
Near, their connection is easy to perform.Aircraft is captured by the wedge-like opening groove of landing dolly, makes aircraft and landing dolly
Be connected, make them that speed is down into zero in certain stroke, aircraft also just safety warship.If land dolly and interplane
It is in larger distance, then using electromagnetic system regulation it is fast the characteristics of dolly is slowed down, to shorten the distance for connecting walking, then carry out
Accelerate, make impact when their speed is sufficiently close to and mitigates connection in connection.
Wedge-like opening on the wedge-shaped tenon alignment dolly of the nose undercarriage of aircraft（Horn mouth）, before undercarriage column
Edge is connected with the wedge-shaped tenon that dolly wedge-like opening is engaged.This wedge-shaped tenon have the vertical buffering that undercarriage brings and
The buffering of rubber front-wheel；Two wedge pieces enable them to play cushioning effect close to without contacting under magnetic repulsion effect.
This magnetic repulsion pushes aircraft all the time（Buffering is without being in contact）；Make the rotor of linear electric motors under the control of the two control device,
Landing dolly and aircraft can bear caused by acceleration even retardation in the range of acceleration force, make dolly and aircraft certain
Speed is down to zero in stroke, aircraft also just safety warship.
The present invention is not when aircraft is dropped to also on landing dolly, it is necessary to controls the height of aircraft, speed, makes aircraft center
Line overlaps with runway centerline, and control dolly speed enable aircraft in the best condition warship on dolly.Aircraft with
The dolly secure bond of landing together after, so that it may be controlled with linear electric motors, make they etc. deceleration operation, make deceleration
Impact caused by aircraft and pilot is minimized.Impetus should be improved when being stopped with front-wheel, aircraft is overturn；
Or by wedge-shaped tenon on pintle.
Present invention also offers another specific embodiment, connect rope using blocking to connect hook or block and land a plane safely.Specifically
Technical scheme it is as follows：The stator track of straight line motor is had in alighting deck, is equipped with and blocks on the rotor of linear electric motors
Device is connect, control device receives flight status data and blocks the position data for connecing device, sends instruction control linear electric motors motion,
Make to block and connect device and aircraft is seamless converges.
The control device is according to blocking the initial position for connecing device, the average speed of the position of point and aircraft and most final speed
Degree, the acceleration of linear electric motors is calculated and to the time needed for point, initial bit when stopping device starts where aircraft
Put；The initial position reached according to aircraft, closed-loop control is carried out to the acceleration of linear electric motors, make to block and connect device and converged with aircraft constant speed
Close.
Block and connect device and be mounted in linear motor rotor, it can obtain required data from linear electric motors, i.e., cycle with
Displacement is directly proportional, and frequency is directly proportional to speed, and the rate of change of frequency is directly proportional to acceleration.Other measurements required for of the invention
Data belong to ranging and range rate mostly, using the high speed measured sensor of the high sample frequency of the big precision of range, such as survey
Spacing is measured in 0.5~3000m, measurement accuracy is in ± 20mm, sample frequency highest 2000Hz.Speed measured sensor is surveyed
The data obtained are sent to control device.
During warship, the extraneous factor such as stormy waves has a great influence aircraft against warship, warship can be disturbed to work, so should
Constantly aircraft is measured and calculated with each data for connecing device are blocked, more to be met actual point.Specifically chat
State as follows：
First, device initial position P is met providing to blockBlock end=0, and final position PBlock end=70, calculate
VMachine is whole=100 、VMachine is equal =102。
It can try to achieve：Acceleration A1With required time T.
Because aircraft calculates with blocking that to connect device equal in the common terminal velocity of constant speed point:
Block and meet device stroke SBlock= (1/2)A1T1 2；
VBlock end= A1T 1；
SBlock= (1/2) VBlock endT1 ；
VBlock end= VMachine is whole；
T1= SBlock/(1/2) VMachine is whole=70/(1/2) 100=1.4 second；
A1= VMachine is whole/T 1= 100/1.4=71.43
SMachine=VMachine is equal*T1=102*1.4=142.8；
It is P to block and connect the initial position (coordinate) of deviceBlock end=0；
The initial position (coordinate) of aircraft is PMachine begins=70-142.8=-72.8；
A is obtained1=71.43；
Then connect device and stopped in predetermined stroke S=100 meter together with blocking providing aircraft, it is timely to obtain required acceleration A
Between T.
0-V2=-2AS；
A= V2/2S=1002/2*100 =50；
V=AT；
Time is T=V/A=- 100/-50=2 second；
2nd, before warship, stormy waves has a great influence aircraft to state between aircraft and mother ship carrier, and in aircraft landing in mother
After on warship, aircraft has been integrally formed with mother ship carrier, and stormy waves is smaller to the influence between aircraft and mother ship carrier state, so existing to aircraft
And connect the situation of device after warship to aircraft and blocking and measure and estimate again, be necessary.The aircraft such as after 0.8 second, blocks and connects device
The data such as position, speed are modified, then calculate new point, enable aircraft and block to connect device and carry out in the case of more accurately
Connection.
Accept the first situation data:VMachine 2 is eventually=100； VMachine 2 is equal=102；A2=71.43；PMachine 2 begins=-72.8；
The data that should be obtained are calculated when the time is by T=0.8：
VBlock 2 eventually= A2T 2=71.43*0.8=57.144；
SMachine 2 is eventually=VMachine 2 is equal*T2=102*0.8=81.6；
PMachine 2 is eventually= SMachine 2 is eventually+ PMachine is whole=-72.8+81.6=8.8；
PBlock 2 eventually=（1/2）A2T2 2=(1/2）71.43*0.82=22.86；
3rd, after startup is blocked and connects device 0.8 second, through measuring and calculating needs to repair aircraft average speed, final speed
Just, the various data that aircraft and blocking can also be connect to device are modified, and are obtained aircraft according to this this data and connect device with blocking and converge
Position, acceleration and required time can so make point more tally with the actual situation.
Aircraft average speed is modified to VMachine 3 is equal=98M/S；
Aircraft most final speed is modified to VMachine 3 is eventually=96M/S；
Speed is equal：
VBlock 3 eventually= VBlocked for 3 beginnings+A3T3=57.14+ A3T3= VMachine 2 is eventually=96；
A3T3=96-57.14= 38.86 ；
Position overlaps：
PMachine 3 is eventually= PMachine 2 begins+ VMachine 3 is equal* T3=8.8+98* T3；
PBlock 3 eventually = PBlocked for 3 beginnings+ VBlocked for 3 beginnings*T 3+（1/2）A3T3 2 =22.86+57.14 *T 3+（1/2）A3T3 2；
PMachine 3 is eventually= PBlock 3 eventually；
8.8+98* T3 =22.86+57.14 *T 3+（1/2）A3T3 2；
8.8+98* T3 =22.86+57.14 *T3+（1/2）38.86 T3；
（8.8-22.86）=（-98+57.14+（1/2）38.86） T3；
T 3=0.657；
PMachine 3 is eventually= PBlock 3 eventually=8.8+98* T3=8.8+98*0.657=73.19；
A3=38.86/0.657=59.14,
Block connect device acceleration correction be 59.14,
Connect device with blocking at 73.19 meters from mother ship carrier afterbody of aircraft and converge and be connected,
Aeroplane nose from mother ship carrier afterbody 73.19+22.28=95.47 meter,
Still there is 4.5 meters or so of surplus compared with leaving 100 meters for.
4th, aircraft connects device and linked together with blocking, from VMachine 2 is eventually=96 are slowed down with A, in S distances, are decelerated to zero.
V2=2AS；
If aircraft connects device S=100 that to walk and stopped with blocking；
A=962/200=46.08；
S=1/2AT2
T=√(2S/A)=√(2*100/46.08)=2.08；
It is 100+69.58=169.58 meter that airplane tail group, which stops position away from mother ship carrier afterbody,；
It is 169.58+22.28=191.86 meter that aeroplane nose, which stops position away from mother ship carrier afterbody,.
In summary, control device carries out closed-loop control to acceleration, makes aircraft and block to connect device constant speed and converge, safely
Land.
In electromagnetic ejection system, linear electric motors are primarily as motor running, it is necessary to from the electric power system on warship
Powered to linear electric motors.And the linear electric motors in the present invention are then as generator operation, it will power to electric power system,
The method of operation for being exactly them is different.
Electromagnetism carrier landing system and electromagnetic ejection system, in addition to the control system of use is different, other parts are essentially identical.Electricity
Magnetic carrier landing system is by aircraft, enables aircraft safe falling, and electromagnetic ejection system is conversely aircraft is accelerated so as to aircraft
Take off.The two systems can integrate, and such as be changed electromagnetic force to opposite direction using control circuit, you can share same
The equipment such as linear electric motors, dolly.Same runway is set both to can serve as the ejection runway to take off, and can is used as the barrier runway of landing,
Can be by four original catapult-assisted take-off runways so for large-scale aircraft carrier, a barrier runway, become five can be simultaneously
Take off or landing runway, so as to accelerate to take off or sinking speed, improve its combat capabilities.
Claims (1)
- A kind of 1. electromagnetism carrier landing system of aircraft carrier, it is characterised in that：Determining for straight line motor is had in alighting deck Sub-track, stopping device is housed on the rotor of linear electric motors；The stopping device is arrester hook and check cable, the wing afterbody with aircraft It is connected；The stopping device is the stopping device with same polarity magnet；Control device receives flight status data and blocked The position data of device is hindered, transmits a signal to linear electric motors, the control device is according to the initial position of stopping device, point Position and the average speed and final speed of aircraft, the acceleration of linear electric motors is calculated and to the time needed for point, Initial position when stopping device starts where aircraft；The initial position reached according to aircraft, the acceleration of linear electric motors is carried out Closed-loop control, stopping device is set to converge with aircraft constant speed.
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| CN201410581315.XA CN104670515B (en) | 2013-11-29 | 2014-10-28 | The electromagnetism carrier landing system of aircraft carrier |
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| CN201310620135.3A CN103587712A (en) | 2013-11-29 | 2013-11-29 | Electromagnetic landing system of aircraft carrier |
| CN2013106201353 | 2013-11-29 | ||
| CN201410581315.XA CN104670515B (en) | 2013-11-29 | 2014-10-28 | The electromagnetism carrier landing system of aircraft carrier |
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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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| 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 |
| CN107209521A (en) | 2015-04-30 | 2017-09-26 | 深圳市大疆创新科技有限公司 | Pass through the system and method for magnetic field landing mobile platform |
| 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 |
| 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 |
| CN112340057B (en) * | 2020-11-05 | 2022-06-28 | 燕山大学 | Reliability increasing platform for carrier-based helicopter landing auxiliary equipment |
| 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 |
| 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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| 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 |
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