CN204184579U - The electromagnetism carrier landing system of aircraft carrier - Google Patents
The electromagnetism carrier landing system of aircraft carrier Download PDFInfo
- Publication number
- CN204184579U CN204184579U CN201420625258.6U CN201420625258U CN204184579U CN 204184579 U CN204184579 U CN 204184579U CN 201420625258 U CN201420625258 U CN 201420625258U CN 204184579 U CN204184579 U CN 204184579U
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- landing
- aircraft
- carrier
- block
- dolly
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Abstract
The utility model discloses a kind of electromagnetism carrier landing system of aircraft carrier, has the stator track of straight line motor at landing deck, the rotor of linear electric motors is equipped with to block connect device; Described blocking connects device and connects rope for blocking to connect hook and block, or for connect device with blocking of same polarity magnet; Control setup receives flight status data and blocks the position data connecing device, by Signal transmissions to linear electric motors.The utility model has the advantages that the accident eliminated aircraft landing and adopt when deck check cable to cause; Two wedge pieces under magnetic repulsion effect, make their can close to and do not contact and play buffer action, make the safe landing of aircraft energy.
Description
Technical field
The utility model 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 very short range be kept to zero and warship.But the speed of aircraft is several hundred kilometers/hour to be blocked by check cable, and aircraft velocity variations is at short notice very large, and the impulsive force caused is also very large.This check cable systematic difference problem is a lot, has become the major cause that aircraft landing accident occurs: aircraft flies too high, and hook incessantly will go around; Fly too low meeting is flushed on deck, loss occurs larger; Hook is inclined 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 askew by aircraft, seriously understand fatal crass.
Since a century having aircraft carrier, the casualty accident on aircraft carrier reaches more than 12,000 and rises, wherein dead more than 8,000 people, these accidents mostly aircraft landing on deck time adopt check cable cause.
Publication number be CN101439761A patent document discloses soft carrier landing system, by body and warship pin down rope form aircraft landing place be the water surface, body restrict for warship pins down pull and realize soft the warship on the water surface.
Publication number is the open security landing-assistant rescuing system for breakdown plane of patent documentation of CN101837838A, when undercarriage cannot be opened, aircraft can only be force-landed by aircraft belly and ground friction, this is danger close, after security landing-assistant rescuing system for breakdown plane can make breakdown plane dock, aircraft is fixed in motorcycle thus completes the safe falling of aircraft.
Publication number be the open landing system of flight vehicle of patent documentation of CN10250982A comprise be arranged on indoor shooting visual angle, hole can continuously controllable camera head, communication and computer installation, the video processing unit calculated with synthesising frame analog video and side-play amount in order to the computing machine that the room, hole of camera head is used is provided with at the midline position of predetermined glidepath, aviator can be made to obtain the situation of real-time flight route and ideal glidepath, the attitude before warship by timely correction aircraft, implements the land that aircraft is steadily safe.
Utility model content
Technical problem to be solved in the utility model is the electromagnetism carrier landing system that will provide a kind of aircraft carrier, and based on magnetic repulsion principle, making aircraft and landing, dolly is seamless converges.
In order to solve above technical matters, the utility model provides a kind of electromagnetism carrier landing system of aircraft carrier, the stator track of straight line motor is had at landing deck, landing dolly the rotor of linear electric motors is equipped with, landing dolly is provided with landing platform, landing platform is also provided with a wedge type open slot, the wedge type tenon in this wedge type open slot and undercarriage column forward position matches, the plate of wedge type open slot both sides is electromagnetism pole plate, and have magnetic repulsion between the wedge type tenon in undercarriage column forward position, vector aircraft enters landing passage; Landing platform is also provided with micromatic setting and receives the control setup of flight status data, linear motor rotor data and landing platform data, and described control setup sends signal to landing dolly.
Described micromatic setting is hydraulic ram micromatic setting, and the hydraulic ram micromatic setting being installed on landing dolly transverse direction is connected with landing platform, controls the transverse direction fine setting displacement of landing platform.
Described control setup is microprocessor.
Described landing platform is also provided with the brake equipment blocking aircraft tyre.
The utility model further provides a kind of electromagnetism carrier landing system of aircraft carrier, has the stator track of straight line motor at landing deck, the rotor of linear electric motors is equipped with to block connect device; Described blocking connects device and connects rope for blocking to connect hook and block, or for connect device with blocking of same polarity magnet; Control setup receives flight status data and blocks the position data connecing device, by Signal transmissions to linear electric motors; Described block to connect hook and block connect rope and be connected with the afterbody of aircraft.
Aircraft is under the commander of landing signal official LSO, safe falling is to during with a certain distance from mother ship carrier, just start blocking on linear electric motors of the present invention and connect device, according to the result of calculation of control setup, block within a certain period of time and connect device and run with constant acceleration, after aircraft then slides with constant velocity, aircraft coincides with the position socketing device, speed is equal, and the constant speed reaching both is converged, and now aircraft connects device to be connected effect be best with blocking.Aircraft with block connect device relative velocity close to zero time to carry out being connected be do not have impact, be safe, the accident that aircraft landing adopts when deck check cable to cause can be eliminated.And then by linear electric motors with etc. deceleration/decel aircraft is stopped with blocking to connect together with device on preposition, aviator and aircraft can be made like this to stand in this section of stroke and to cause deceleration forces to reduce to minimum by deceleration/decel.Usedly at present all can to avoid with the aircraft of the speed per hour 360 kilometers caused lot of accident that to be connected with static stopping device.
Superior effect of the present utility model is:
1) the utility model two wedge pieces are under magnetic repulsion effect, make their can close to and do not contact and play buffer action, slow down the impulsive force of aircraft;
2) based on this landing modes of the utility model, both can protect numerous elite aviator not reason aircraft landing and injures and deaths, and many expensive aircrafts can have been protected again therefore unlikely and damage;
3) based on this landing modes of the utility model, can avoid because excessive negative acceleration makes impulsive force excessive and damage aircraft and chaufeur;
4) adopt electromagnetism carrier landing system that same runway can be made can to launch runway as what take off, the barrier runway of warship can be used as again, like this for can by original four catapult-assisted take-off runways large-scale aircraft carrier,, a barrier runway, become five can take off or landing runway simultaneously, thus accelerate to take off or sinking speed, improve its combat capabilities.
Accompanying drawing explanation
Fig. 1 is integral structure schematic diagram of the present utility model;
Fig. 2 is the section drawing of Fig. 1;
Fig. 3 is schematic block circuit diagram of the present utility model;
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.
Detailed description of the invention
Refer to shown in accompanying drawing, the utility model is described in further detail.
As depicted in figs. 1 and 2, the utility model provides a kind of electromagnetism carrier landing system of aircraft carrier, the stator track 1 of many linear electric motors is had at landing deck, landing dolly 3 rotor 2 output shaft of linear electric motors is equipped with, landing dolly 3 is provided with landing platform 4, landing platform 4 projection one 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 instruction controls landing dolly, aircraft electromagnetism is made warship.
The plate of described wedge type open slot 5 both sides is electromagnetism pole plate, and has magnetic repulsion between the wedge type tenon 6 in undercarriage column forward position.
The height of wedge type open slot 5 is wide be about 1 meter square.Correspondingly install the wedge shape tenon 6 matched with dolly wedge type opening in the forward position of alighting gear column, this wedge shape tenon 6 has the buffering of vertical buffering that alighting gear brings and rubber front-wheel; Two wedge piece high speeds are close, and the process from zero point several meters to 0. more than zero meter is the magnetic buoyancy of repelling each other, and this magnetic buoyancy pushes aircraft (cushion and do not contact) all the time; Speed is down to zero by landing dolly 3 in the stroke of tens meters, and aircraft has also just stopped.
Described micromatic setting is hydraulic ram micromatic setting, and the hydraulic ram micromatic setting being installed on landing dolly transverse direction is connected with landing platform 4, the fine setting of the horizontal both direction of parametric controller.
Described control setup is microprocessor, after receiving the data of flight status data, linear motor rotor data and landing platform, carries out data reduction, thus control that linear motor stator electric runs, height, the speed of hydraulic ram micromatic setting and aircraft.The microprocessor MDV-STM32-407 comprising CPU and some peripheral assemblies can complete control work, also possesses the ability of to carry out network with host computer and being connected.
Described landing platform 4 is also provided with the brake equipment blocking aircraft tyre.
Principle of the present utility model is before aircraft landing to dolly, control setup carries out actv. monitoring to aircraft and dolly, make aircraft and dolly all along line of centers flight or the benz of runway, and make the position of aircraft directly over dolly, now aircraft answers geometry equal with the speed of dolly, namely aircraft and dolly should be geo-stationary, and 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, is fixed on platform by aircraft, and finely tunes platform with the micromatic setting on dolly, and aircraft is on most suitable position.The dolly being loaded with aircraft makes their speed be down to zero with even deceleration/decel under the control of linear electric motors, thus completes warship task.
When aircraft is after living warship preparation flight, electromagnetism carrier landing system receives aircraft and drops to certain altitude, and there is certain speed, and have 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 slightly faster than the speed of 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, and because aircraft and the speed of landing dolly are close, their connection is easily carried out.Aircraft catch by the wedge-like opening groove of the dolly that lands, aircraft is connected with landing dolly, makes them be down to close to zero by speed in certain stroke, aircraft also just safety warship.If the distance of landing dolly and interplane is comparatively large, then electromagnetic system can be utilized to regulate fast feature to slow down to dolly, to shorten the distance connecting walking, then accelerate, impact when making their speed when connection very close and alleviate connection.
The wedge shape tenon of the nose undercarriage of aircraft aims at the wedge-like opening (exit skirt) on dolly, and the wedge shape tenon that forward position and the dolly wedge-like opening of alighting gear column match is connected.This wedge shape tenon has the buffering of vertical buffering that alighting gear brings and rubber front-wheel; Two wedge pieces under magnetic repulsion effect, make their can close to and do not contact and play buffer action.This magnetic repulsion pushes aircraft (cushion and do not contact) all the time; Under the two control setup controls, make the rotor of linear electric motors, landing dolly and aircraft can bear even retardation within the scope of acceleration force caused by acceleration/accel, make dolly and aircraft be down to close to zero by speed in certain stroke, aircraft also just safety warship.
The utility model aircraft also do not drop to landing dolly on time, the height of aircraft must be controlled, speed, aircraft line of centers is overlapped with runway centerline, and the speed controlling dolly make aircraft can in the best condition warship on dolly.After aircraft is together with landing dolly secure bond, control with regard to available linear electric motors, their deceleration/decel that waits is run, makes deceleration/decel reduce to minimum to the impact that aircraft and aviator cause.Should acting point be improved when stopping with front-wheel, making the unlikely upset of aircraft; Or wedge shape tenon is contained on pintle.
The utility model additionally provides another kind of specific embodiment, adopts to block to connect hook or block to connect rope and land a plane safely.Concrete technical scheme is as follows: the stator track having straight line motor at landing deck, the rotor of linear electric motors is equipped with to block and connects device, control setup receives flight status data and blocks the position data connecing device, send instruction and control linear electric motors motion, make to block and connect device and aircraft constant speed is converged.
Described control setup connects the initial position of device, the average velociity of the position of point and aircraft and final velocity according to blocking, calculate linear electric motors acceleration/accel and to the time needed for point, block the initial position connecing aircraft place when device starts; According to the initial position that aircraft arrives, closed loop control is carried out to the acceleration/accel of linear electric motors, make to block and connect device and aircraft constant speed is converged.
Block and connect device and be mounted in linear motor rotor, it can obtain desired data from linear electric motors, and namely cycle is directly proportional to displacement, and frequency is directly proportional to speed, and the rate of change of frequency is directly proportional to acceleration/accel.The required data that other are measured of the utility model belong to ranging and range rate mostly, adopt the speed measured sensor that range large precision high sampling frequency is high, as measured spacing at 0.5 ~ 3000m, survey precision ± 20mm, the highest 2000Hz of sampling frequency.The data that speed measured sensor records are sent to control setup.
Aircraft is in warship process, and the external factors such as stormy waves are comparatively large facing to warship impact, can disturb warship work, so should constantly to aircraft with block each data connecing device and carry out measurements and calculations, to obtain more realistic point.Be specifically described as follows:
One, device initial position P is met providing to block
block end=0, and final position P
block end=70, calculate
V
machine eventually=100, V
machine is equal=102.
Obtain: acceleration A
1with required time T.
Because aircraft with block that to connect device equal in the common terminal velocity of constant speed point, calculate:
Block and meet device stroke S
block=(1/2) A
1t
1 2;
V
block end=A
1t
1;
S
block=(1/2) V
block endt
1;
V
block end=V
machine eventually;
T
1=S
block/ (1/2) V
machine eventually=70/(1/2) 100=1.4 seconds;
A
1=V
machine eventually/ T
1=100/1.4=71.43
S
machine=V
machine is equal* T
1=102*1.4=142.8;
Blocking the initial position (coordinate) connecing device is P
block end=0;
The initial position (coordinate) of aircraft is P
machine begins=70-142.8=-72.8;
Obtain A
1=71.43;
And then provide aircraft and connect device stop required stroke S=100 rice together with blocking, then obtain required acceleration A and time T.
0-V
2=-2AS；
A= V
2/2S=100
2/2*100 =50；
V=AT；
Time is T=V/A=-100/-50=2 second;
Two, aircraft is before warship, stormy waves is larger on the impact of state between aircraft and mother ship carrier, and after aircraft landing is on mother ship carrier, it is less on the impact between aircraft and mother ship carrier state that aircraft and mother ship carrier have become to be integrated stormy waves, thus can to aircraft after warship to aircraft and block the situation connecing device and measure each estimation again, as aircraft after 0.8 second, block the position connecing device, data are revised between speed etc., then calculate point, and aircraft can be connected in situation more accurately.
Accept the first situation data: V
machine 2 eventually=100; V
machine 2 is equal=102; A
2=71.43; P
machine 2 begins=-72.8;
Data when the time obtains through T=0.8:
V
block 2 eventually=A
2t
2=71.43*0.8=57.144;
S
machine 2 eventually=V
machine 2 is equal* T
2=102*0.8=81.6;
P
machine 2 eventually=S
machine 2 eventually+ P
machine eventually=-72.8+81.6=8.8;
P
block 2 eventually=(1/2) A
2t
22=(1/2) 71.43*0.8
2=22.86;
Three, block in startup and connect device after 0.8 second, need to revise aircraft average velociity final velocity through measuring and calculating, also and the various data connecing device can be blocked revise aircraft, and obtain aircraft according to these these data and block the position connecing device and converge, acceleration/accel and required time, can make point more tally with the actual situation like this.
Aircraft average velociity is modified to V
machine 3 is equal=98M/S;
The most final speed of aircraft is modified to V
machine 3 eventually=96M/S;
Speed is equal:
V
block 3 eventually=V
blocked for 3 beginnings+ A
3t
3=57.14+ A
3t
3=V
machine 2 eventually=96;
A
3T
3=96-57.14= 38.86 ；
Position overlaps:
P
machine 3 eventually=P
machine 2 begins+ V
machine 3 is equal* T
3=9.8+98* T
3;
P
block 3 eventually=P
blocked for 3 beginnings+ V
blocked for 3 beginnings* T
3+ (1/2) A
3t
3 2=22.86+57.14 * T
3+ (1/2) A
3t
3 2;
P
machine 3 eventually=P
block 3 eventually;
9.8+98* T
3 =22.86+57.14 *T
3+（1/2）A
3T
3 2；
9.8+98* T
3=22.86+57.14 *T
3+（1/2）38.86 T
3；
（9.8-22.88）=（-98+57.14+（1/2）38.86 T
3；
T
3=0.61；
P
machine 3 eventually=P
block 3 eventually=9.8+98* T
3=9.8+98*0.61=69.58;
A
3=38.86/0.61=63.6；
Blocking the acceleration correction connecing device is 63.6;
Aircraft stops at aircraft from mother ship carrier afterbody 69.58 meters of;
Aircraft is from mother ship carrier afterbody 69.58+22.28=91.86 rice;
With leave the surplus still having about 8 meters compared with in the of 100 meters for.
Four, aircraft and block and connect device and link together, from V
machine 2 eventually=96 slow down with A, in S distance, are decelerated to zero.
V
2=2AS；
If aircraft meets the device S=100 that will walk and stops with blocking;
A=96
2/200=46.08；
S=1/2AT
2
T=√(2S/A)=√(2*100/46.08)=2.08；
It is 100+69.58=169.58 rice that airplane tail group stops position apart from mother ship carrier afterbody;
It is 169.58+22.28=191.86 rice that aeroplane nose stops position apart from mother ship carrier afterbody.
In sum, control setup carries out closed loop control to acceleration/accel, makes aircraft connect device constant speed and converge, safe landing with blocking.
In electromagnetic ejection system, linear electric motors mainly as motor running, need to power from the electric power system warship to linear electric motors.Linear electric motors in the utility model are then as generator operation, and it will be powered to electric power system, and namely their operation scheme is different.
Electromagnetism carrier landing system and electromagnetic ejection system, except the control system difference adopted, other parts are substantially identical.Electromagnetism carrier landing system is by aircraft, 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, and as utilized 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 launch runway as what take off, the barrier runway of landing can be used as again, like this for can by original four catapult-assisted take-off runways large-scale aircraft carrier,, a barrier runway, become five can take off or landing runway simultaneously, thus 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 having straight line motor at landing deck, landing dolly the rotor of linear electric motors is equipped with, landing dolly is provided with landing platform, landing platform is also provided with a wedge type open slot, the wedge type tenon in this wedge type open slot and undercarriage column forward position matches, the plate of wedge type open slot both sides is electromagnetism pole plate, and have magnetic repulsion between the wedge type tenon in undercarriage column forward position, vector aircraft enters landing passage; Landing platform is also provided with micromatic setting and receives the control setup of flight status data, linear motor rotor data and landing platform data, and described control setup sends signal to landing dolly.
2. 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, the hydraulic ram micromatic setting being installed on landing dolly transverse direction is connected with landing platform, controls the transverse direction fine setting displacement of landing platform.
3. the electromagnetism carrier landing system of aircraft carrier according to claim 1, is characterized in that: described control setup is microprocessor.
4. the electromagnetism carrier landing system of aircraft carrier according to claim 1, is characterized in that: described landing platform is also provided with the brake equipment blocking aircraft tyre.
5. an electromagnetism carrier landing system for aircraft carrier, is characterized in that: the stator track having straight line motor at landing deck, the rotor of linear electric motors is equipped with to block connect device; Described blocking connects device and connects rope for blocking to connect hook and block, or for connect device with blocking of same polarity magnet; Control setup receives flight status data and blocks the position data connecing device, by Signal transmissions to linear electric motors; Described block to connect hook and block connect rope and be connected with the afterbody of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420625258.6U CN204184579U (en) | 2013-11-29 | 2014-10-28 | The electromagnetism carrier landing system of aircraft carrier |
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|---|---|---|---|
| CN201320767435 | 2013-11-29 | ||
| CN201320767435X | 2013-11-29 | ||
| CN201420625258.6U CN204184579U (en) | 2013-11-29 | 2014-10-28 | The electromagnetism carrier landing system of aircraft carrier |
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| Publication Number | Publication Date |
|---|---|
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ID=52616596
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104670515A (en) * | 2013-11-29 | 2015-06-03 | 陈永年 | Electromagnetic carrier landing system of aircraft carrier |
| CN104960671A (en) * | 2015-06-15 | 2015-10-07 | 南京航空航天大学 | Landing electromagnetic damping system for shipboard aircraft |
| 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 |
-
2014
- 2014-10-28 CN CN201420625258.6U patent/CN204184579U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104670515A (en) * | 2013-11-29 | 2015-06-03 | 陈永年 | Electromagnetic carrier landing system of aircraft carrier |
| 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 |
| CN104960671A (en) * | 2015-06-15 | 2015-10-07 | 南京航空航天大学 | Landing electromagnetic damping system for shipboard aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150304 Termination date: 20161028 |