CN111348213A

CN111348213A - Method for taxiing aircraft without landing gear or tires and facility or device therefor

Info

Publication number: CN111348213A
Application number: CN202010090257.6A
Authority: CN
Inventors: 何韧
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-02-04
Filing date: 2020-02-04
Publication date: 2020-06-30

Abstract

The invention relates to a method for taking off and landing an aircraft without landing gear or tires in a sliding mode and a facility or a device thereof, namely, a facility or a device which can replace the functions of the landing gear or the tires or braking members on the aircraft is arranged on a runway, or a facility or a device which can help the aircraft to take off and land is arranged. The facilities or the devices at least comprise a runway groove or a track groove or a raft vehicle or a stop aid or a booster or a power accumulator or a controller or a detector or a fork or a guiding device, the runway or the stop aid or the booster or the raft vehicle is provided with the power accumulator or a steam type catapult or an electromagnetic type catapult or the controller or the detector or a lifter, and the stop aid or the booster or the raft vehicle or the lifter or the runway surface is provided with a hooking device or a guiding device or a lifting device or a fire fighting device or an emergency rescue device or a medical care device or a flight assisting slope or a ladder or a slide or a manned escalator or a cargo elevator. The guiding means can alternatively act as a hooking means.

Description

Method for taxiing aircraft without landing gear or tires and facility or device therefor

Technical Field

The invention relates to a method for landing gear or tire or brake of an aircraft and a facility or device thereof, in particular to a method for safely taking off and landing the aircraft on a runway by a taxiing mode without the landing gear or tire or brake on the aircraft and the facility or device thereof.

Background

Aircraft are known to be provided with landing gear or tires or brakes for safe taxiing take-off and landing. Before the airplane lands, the landing gear is put down to spread the tires, then the tires are damped on the runway by means of the landing gear and the tires, meanwhile, the tires are enabled to slide on the runway and decelerate until the tires are stable, or the tires of the airplane are enabled to stop rotating after sliding for a short distance on the runway through a stopping cable or other various braking modes. The catapult takeoff or the taxi takeoff of the airplane requires that the tire can take off after moving on a runway at high speed through thrust generated by rotation of a steam catapult, an electromagnetic catapult, a fuel injection device or a propeller; vertical take-off and landing of an aircraft also requires landing gear or tires to be supported on the ground.

The shapes and weights of the landing gear, the tires and the braking part are different according to the weight of the airplane. The landing gear and tires of large passenger aircraft, heavy fighters, bombers are large and weigh one or several tons, which undoubtedly wastes the limited space and load capacity of the aircraft. In order to ensure that the aircraft tire is wear-resistant, impact-resistant and high-pressure-resistant during high-speed rotation, the manufacturing cost and the process of the tire and the braking part thereof are high.

The recoverable missile or rocket is not provided with a landing gear and tires, and almost adopts a vertical launching mode and a vertical landing mode. But vertical launch and vertical descent, consume fuel.

I have disclosed different methods and devices for landing, taking off and storing power of aircraft in the inventions of application numbers 201711326472.6, 201910889501.2, 201910873265.5, 201910757015.5, 201911265226.3, etc., but have not disclosed a method and technology for taking off and landing in a sliding manner without landing gear or tires or brakes on the aircraft.

Disclosure of Invention

The invention aims to provide a method for taking off and landing an aircraft without a landing gear or tires in a sliding mode and a facility or a device thereof. The main technical problems to be solved are as follows: 1. no landing gear or tires or brakes are provided on the aircraft. 2. Corresponding facilities or devices are arranged on the runway. 3. The function of landing gear or tires or braking members on the aircraft is transferred to the facilities or devices on the runway, so that the aircraft can be safely taxied and lifted without the landing gear or the tires or the braking members. 4. Is suitable for intelligent control.

The invention solves the problems by adopting the following methods: facilities or devices capable of replacing the functions of landing gears, tires or braking members on the aircraft or facilities or devices capable of assisting the taking-off and landing of the aircraft are arranged on the runway, so that the aircraft without the landing gears, the tires or the braking members can safely take off or land on the runway in a sliding mode.

Preferably, said facilities or devices comprise at least a runway slot or a track slot or a raft vehicle or a stop aid or a booster or an accumulator or a controller or a probe or a fork or a guiding device; the forks include orbital forks or rotating forks or unmanned forks that can move the aircraft into position like a forklift, such as to fork the aircraft from an elevator for placement on a runway in a takeoff position.

The stopping aid, the booster or the raft vehicle compresses or stretches elastic substances, or compresses or stretches gas or liquid in pneumatic or hydraulic parts or the pneumatic or hydraulic parts, or assists the aircraft to land or take off through a steam driving device or an electric driving device.

The guide device comprises a rotating part or a wear-resistant part or a track groove or a track groove or a tubular object or a magnet or a magnetic suspension device or a buffer device or a positioning device or a clamping device or a steam driving device or an electric driving device; the magnet comprises a permanent magnet or an electromagnet.

The main components or parts of the buffer device comprise a wheel or a flywheel or a tire or a gear or a rack or a chain or a track or a liquid filling piece or an inflating piece or an air pressing piece or a hydraulic piece or an air pressing piece or an anti-collision piece or a blocking piece or a braking piece or an elastic shock absorption device. The elastic damping device can be composed of two or more layers, such as two layers of steel plates or springs.

The rotating part comprises a wheel or a flywheel or a ratchet wheel or a gear or a tire or a bearing or a roller or a conveyor belt or a crawler belt; the rotation of the rotating member is controlled by a steam driving device, an electric driving device, a speed changer or a braking member.

The arresting member comprises an arresting cable or an arresting rod or an arresting column or an arresting block or an arresting plate or an arresting wall or an arresting net or an arresting sleeve.

The controller comprises a manual controller, a remote controller, an intelligent controller or an intelligent integrated controller.

The main working mode or main components of the positioning device comprise a magnet or a suction disc or a plug or a buckle or a spiral or an expansion or a binding or a hook or a loop or a sleeve or a clip.

On or in the runway groove, or a liquid or guide device or an accumulator or a steam ejector or an electromagnetic ejector is provided.

The carrier of the runway is the deck of a ground or liquid or surface ship. The facility or apparatus may be located directly or indirectly on the ground or on the deck.

Preferably, the runway or the parking aid or the booster or the raft vehicle is provided with an accumulator or a steam type ejector or an electromagnetic type ejector or a controller or a detector or a lifter. The stop aid or the booster or the raft vehicle is parallel to or connected with or combined with the elevator into a whole. The parking aid or the booster or the raft vehicle or the elevator or the runway is provided with a hooking device or a guiding device or a lifting device or a fire fighting device or an emergency device or a medical care device or a flying assisting slope or a ladder or a slide or a manned staircase or a freight elevator. The guiding means can alternatively act as a hooking means. A boosting part is arranged on the booster, and a rotating part is arranged at the upper end of the boosting part; the booster or the raft vehicle or the runway or the deck is provided with a flame baffle plate, and the flame baffle plate is provided with a rotating part; the flying assisting slope is provided with a guiding device. The accumulator can store the inertia impulse force of the aircraft during landing by compressing or stretching the elastic substance, or store the atmospheric pressure by pumping out the gas or liquid in the pneumatic or hydraulic part or the pneumatic or hydraulic part to make the interior of the pneumatic or hydraulic part or pneumatic or hydraulic part tend to vacuum or become vacuum so as to generate the atmospheric pressure. The upper end face of the stop aid or the booster or the raft vehicle is equal to or almost equal to the height of the runway surface. Or when the raft vehicle stays on the stopping aid or the booster, the upper end surface of the raft vehicle is equal to or almost equal to the road surface of the runway. The stop aid is combined with the booster into a whole.

Preferably, a booster or a stopping aid or an accumulator or a chemical energy pusher or a steam ejector or an electromagnetic ejector is arranged on the raft vehicle.

Preferably, the parking aid or the booster is of a double-layer or three-layer structure or is in a step shape, the parking aid or the booster in the step shape is at least provided with a first step and a second step, the upper end surface of the second step is equal to or almost equal to the road surface of the runway in height, and the upper end surface of the second step is provided with a guide device. When the raft vehicle stays on the first-stage step of the parking aid or the booster, the upper end face of the raft vehicle is equal to or almost equal to the upper end face of the second-stage step.

Preferably, the aircraft is provided with a tail hook or a telescopic piece or a detector or a controller or is provided with a power switch which allows or does not allow the ground command center to remotely control the take-off and landing of the aircraft. The tail hook or the telescopic piece is provided with a rotating piece. The telescopic piece is in a plate shape, a block shape, a tubular shape, a strip shape or a column shape, a groove, a convex object or a corner is arranged on the telescopic piece, and the rotating piece or the corner can be used as a tail hook. The number of the tail hooks or the telescopic pieces is two or more, the tail hooks can be straightened or folded, and the straightened state, the folded state or the hooked state of the tail hooks is controlled by a pneumatic or hydraulic piece, a pulley or a pulley block, a spring or a gear or a chain or a spiral device; the aircraft is connected with the tail hook through a rod-shaped object, a strip-shaped object or a block-shaped object, and the connection position of the rod-shaped object, the strip-shaped object or the block-shaped object and the tail hook can be rotated or is provided with a joint or is provided with a spring, a hydraulic piece, a pneumatic piece or a spiral device; the cross section of the rod-shaped object or the strip-shaped object or the block-shaped object can be in any geometric shape; the strip comprises a rope; the number of the rods, the strips or the blocks is two or more; the shaft or block may be bifurcated or may be flexible or resilient.

Preferably, the side of the aircraft facing the runway for landing is provided with a projection or a groove or a rotating shaft or a transmission or a guiding device. The convex part or the groove or the rotating shaft or the transmission part or the guide device is magnetic or provided with a stealth coating. The cross section of the rotating shaft is a regular or irregular semicircle or trapezoid; the rotating shafts can be arranged together by two or more than two. The shape of the rotating shaft can also be square or diamond or crescent or any other geometrical shape.

Preferably, the guide means may be a clip-type lead-in and lead-out means or an arch-or frame-shaped support means. The leading-in and leading-out device is in a lying type, one end of the leading-in and leading-out device can lead in a landing aircraft or lead out an aircraft needing to take off, two sides of the leading-in and leading-out device or the position of the leading-in and leading-out device can be moved, and the space between the two sides can be narrowed or widened; the controller can move the position of the lead-in and lead-out device or adjust the width of the space according to the real-time position of landing or takeoff of the aircraft. The supporting device is in a vertical or inclined type, two sides of the supporting device are erected on a runway or a stop aid or a booster or a raft vehicle, the two sides can be bent, rotated or stretched, the two sides can keep a vertical or inclined state or an arc shape through elastic force, the two sides are formed by combining superposed elastic sheets, and the two sides are connected into an arch or frame shape through a rotating part or a blocking rod; the barrier rod is provided with a buffer device; the support means may be arranged or combined from two or more pieces. The top surface of the supporting device is provided with a plate-shaped object or a strip-shaped object or a block, and the plate-shaped object or the strip-shaped object or the block is provided with a buffer device.

Preferably, the aircraft is not provided with a landing gear or a tire or a braking member, and the taking-off and landing modes are as follows:

the aircraft is assisted to land safely through a tail hook or a telescopic piece on the aircraft or a hooking device or a guiding device or a lifting device or an accumulator or a detector or a controller on the runway or the stop aid or the raft vehicle; the aircraft can take off safely by the aid of the hooking device or the guiding device or the lifting device or the flying assisting slope or the power accumulator or the steam type catapult or the electromagnetic type catapult or the detector or the controller on the runway or the booster or the raft vehicle. The power for boosting the aircraft to take off in a taxiing mode is from the following steps: a propeller or chemical energy impeller disposed on the aircraft; the chemical energy propeller or the steam type ejector or the electromagnetic type ejector or the accumulator or the magnetic suspension device or the guiding device are arranged on the runway or the booster or the raft vehicle. The chemical energy impeller comprises a jet engine or a fuel injection device.

Preferably, the landing mode of the aircraft is as follows: the aircraft lands on the runway, and safe landing of the aircraft is assisted by a guiding device or a hooking device or an accumulator or a detector or a controller on the runway. The landing mode of the aircraft is as follows: the aircraft lands on the stop-aid device or the raft vehicle, and the aircraft is helped to land safely through the action of a tail hook or a telescopic piece arranged on the aircraft or a guide device or a hooking device or a power accumulator arranged on the stop-aid device or the raft vehicle. The landing mode of the aircraft is as follows: the aircraft lands in the runway, guide device guide helps and descends on the runway, extremely in the time of help stopping ware top, through set up tail hook or extensible member on the aircraft or set up the guide device or the effect of hooking device or power accumulator on the help stopping ware, let the aircraft drive the help stopping ware and slide on the runway or runway groove or track groove, when the help stopping ware removes runway or runway groove or track groove end, the controller can the instruction the tail hook or extensible member or guide device or the device that hooks removes the block to the aircraft, let the aircraft utilize the residual force of inertial impulse to slide to the raft car or conveyer belt or lift or deck on from the help stopping ware. The landing mode of the aircraft is as follows: the aircraft lands along the direction shown by the runway, the landing angle or height is adjusted under the assistance of the detector, and then the aircraft stays on the raft vehicle through the action of a tail hook or a telescopic piece arranged on the aircraft or a guide device or a hooking device or a force accumulator arranged on the raft vehicle, so that the raft vehicle and the stop-aid device are driven to slide on the runway or in a runway groove. The landing mode of the aircraft is as follows: the aircraft lands along the direction shown by the runway, flies or slides to the upper end surface of the second step of the stepped stopping aid, and stops on the upper end surface of the second step through the tail hook or the telescopic piece or the accumulator or the guide device or the hooking device arranged on the upper end surface of the second step to drive the stopping aid and the raft vehicle to slide for a certain distance on the runway or in the runway groove, the controller commands the tail hook or the telescopic piece or the hooking device or the guide device to remove the blocking of the aircraft, so that the aircraft slides to the raft vehicle by means of inertia impulse, and the aircraft is controlled or managed and protected by the guide device on the raft vehicle. The takeoff mode of the aircraft is as follows: the aircraft stops on the raft vehicle or the booster, the raft vehicle or the booster stops on the guiding device of the runway or the runway groove or the track groove, the aircraft can take off in a sliding mode only after the raft vehicle or the booster slides for a certain distance along the aircraft by the thrust of the steam type ejector or the electromagnetic type ejector or the elastic force or the atmospheric pressure accumulated by the accumulator or the power provided for the rotating piece by the steam driving device or the electric driving device in the guiding device or the acting force of a propeller or a chemical energy pusher arranged on the aircraft, and the aircraft takes off in a sliding mode.

The elastic substance comprises a metal elastic substance and a nonmetal elastic substance, wherein the metal elastic substance comprises a spring, a metal strip, a metal sheet and a metal plate, and the nonmetal elastic substance comprises rubber, silica gel, plastics, plastic, resin and gas. The conveyor belt is also called as a conveyor belt. The convex piece comprises a convex strip, a convex block, a convex plate and a convex sheet. The sliding mode comprises a rolling sliding mode, a sliding mode and a magnetic suspension sliding mode. The taking off and landing comprises taking off or landing, landing and stopping stably. The manned escalator comprises a manned elevator; the aircraft includes aircrafts and spacecrafts, such as civil or military aircrafts, space shuttles, missiles and rockets. The landing gear or the tire is not provided with the landing gear or the tire or the braking member, and the landing gear or the tire can completely support the aircraft to be separated from the ground, and the braking member can brake the tire.

The beneficial effect of the invention is that after the method and the device are adopted: (1) because related facilities or devices are arranged on the runway to replace the functions of the landing gear, the tire or the braking part on the aircraft, the landing gear, the tire or the braking part can not be arranged on the aircraft, the saved space and weight can enable the aircraft to carry more people or objects, and if the method and the technology are applied to civil aircrafts, the manufacturing cost can be saved, and the economic benefit can be improved. If the oil is applied to military aircraft, the range can be enlarged by adding oil, and the fighting capacity can be enhanced by increasing the loading capacity. If the device is applied to missiles and rockets and assisted by corresponding facilities or devices, the missiles and the rockets can take off like an unmanned aerial vehicle and cruise on the sky, fuel is exhausted, and for safety, the detonating fuse can be closed firstly to return to a take-off and landing field for replenishing fuel, and then cruise on the day again. The missile and rocket have the advantages of low cost, ultrahigh speed and long-time cruising, can be used as a killer of a stealth airplane, can also be used as a substitute of a bomber and a reconnaissance plane, and can also be used as a recoverable low-cost low-orbit attack type satellite. If the method is applied to the aircraft carrier, under the condition that the original area of a deck is not required to be increased, the carrying capacity of the carrier-based aircraft can be improved, the take-off and landing efficiency of the carrier-based aircraft can be improved, and theoretically, the carrier-based aircraft can take off and land for one rack time in five to twenty seconds on average. The speed is not lower than the take-off and landing speed of the existing vertical take-off and landing aircraft, and the deck can be pushed to work to realize mechanization, intellectualization and unmanned operation. (2) By arranging facilities or devices such as a parking aid, a booster, an accumulator, a guide device and the like, the take-off and landing runway is greatly shortened, which is beneficial to the construction of airports in islands or places with limited conditions. (3) The aircraft is lifted and landed on the raft vehicle, and the aircraft is carried by the raft vehicle in the whole process of getting on or off passengers, loading and unloading goods and the like in an airport, so that the mechanical, fuel or electric power loss of the aircraft can be reduced, and after all, compared with the aircraft, the manufacturing process and material of the raft vehicle and the manufacturing, using and maintaining costs of the raft vehicle are greatly different. (4) The energy accumulator or the steel plate or the arresting rod is used for replacing the arresting cable, so that the manufacturing, using and maintaining costs are reduced, and the safety is higher.

Drawings

The embodiments of the present invention will be further explained with reference to the drawings, but the scope of the present invention is not limited to the drawings and the examples thereof.

Fig. 1 is a schematic side view of a first embodiment of the invention in relation to an aircraft landing on a runway and then taxiing above a stop-aid.

Fig. 2 is a schematic top view of the embodiment shown in fig. 1.

Fig. 3 is a schematic side view of a second embodiment of the invention in relation to a raft vehicle parked on a first step of a parking aid and an aircraft parked on a second step of the parking aid.

Fig. 4 is a schematic side view of the approach shown in fig. 3 with the docking aid moved from the head end to the tail end of the runway and the aircraft also moved onto the raft vehicle.

Fig. 5 is a schematic side view of a third embodiment of the present invention in relation to an accumulator, thrusters, raft vehicles, guidance devices, and an assisted flight ramp to assist in takeoff of an aircraft.

Fig. 6 is a schematic plan view of a fourth embodiment of the present invention, showing the arrangement of thrusters, stops and guides on the deck of an aircraft carrier.

FIG. 7 is a schematic top view of the version of FIG. 6 with the booster and the docking assist deployed.

FIG. 8 is a schematic side view of a fifth embodiment of the invention in relation to a missile landing on a stop aid.

FIG. 9 is a schematic top view of the docking aid, accumulator, assisting in landing a missile in the manner shown in FIG. 8.

Wherein, the first embodiment: the device comprises a runway 1, supporting devices 2 and 3, an elastic damping device 4, a stop aid 5, supporting devices 6 and 7, a track 8, a raft vehicle 9, a supporting device 10, a positioning device 11, an aircraft 12, a telescopic piece 13, a rotating piece 14, a chain 15, a gear 16, a piston 17, a cylinder 18, an intelligent controller 19, an electric pump 20, an air inlet 21, a positioning device 22 and rotating shafts 23 and 24. The second embodiment: runway 201, docking aid 202, raft vehicle 203,

steel plates

204, 205, 206, arresting rod 207, aircraft 208, telescopic part 209, arresting rod 210, intelligent controller 211, motor 212, exhaust hole 213, air cylinder 214, piston 215, spring 216, bolt 217, hole 218, arresting

parts

219, 220 and bolt 221. Third embodiment: the device comprises a runway groove 301, an air pressure member 302, a spring 303, a booster 304,

bolts

305 and 306, a raft vehicle 307, an intelligent controller 308, an air pump 309, an aircraft 310, a flight assisting slope 311, a driving wheel 312, a conveyor belt 313, an air pressure member 314, an air pump 315, a booster 316, a clamping piece 317, a buffer device 318, a switch 319, a flame baffle 320, a clamping piece 321 and a flywheel 322. Fourth embodiment:

elevators

401, 402, 403, 404, guides 405, 406, 407, 408,

positioning devices

409, 410, 411, 412, docking aids 413, guides 415, clamping devices 416, rail ways 417,

rotors

418, 419, transition decks 420,

boosters

421, 422, flame shields 423, guides 424, rotors 425, guides 426, 427, 428, 429, warship islands 430, landing ramps 431, 432, fire suppression devices 433, rescue decks 434, barriers 435, clamping devices 436, rescue devices 437. Fifth embodiment: the parking aid comprises a parking aid 501, a steel plate 502, a rolling shaft 503, a steel plate 504, a steel plate 505, a blocking rod 506, a missile 507, a tail hook 508, a blocking rod 509, an accumulator 510, a folding wing 511, a tail rudder 512, a runway groove 513, a protective cover 514,

fuel tanks

515 and 516 and a crawler 517.

Detailed Description

Referring to fig. 1 and 2, the head runway surface of the runway 1 is provided with arched support devices 2 and 3 and an elastic damping device 4, the support devices 2 and 3 can rotate leftward and can be reset by the elastic force of the spring, and the elastic damping device 4 can move downward and can be reset by the elastic force of the spring. The upper end surface of the stopping aid 5 is as high as the head end track surface of the runway 1, the upper end surface of the stopping aid 5 is also provided with supporting devices 6 and 7, and the stopping aid 5 can move along a track 8. The tail end of the runway 1 is stopped with the raft vehicle 9, the upper end face of the raft vehicle 9 is also provided with a supporting device 10, and a positioning device 11 arranged at the tail end of the runway 1 is upwards bounced to fix the raft vehicle 9 in position. When the aircraft 12 lands on the supporting devices 2 and 3, the impact force of the aircraft can enable the supporting devices 2 and 3 to rotate towards the left lower side and press the elastic damping device 4, and at the moment, the aircraft 12 can bounce up and down; when the aircraft 12 moves to the position above the parking aid 5, the sliding tends to be stable, at this time, the telescopic piece 13 arranged on the aircraft 12 can be made to pop out downwards, meanwhile, the rotating piece 14 below the telescopic piece 13 and the lower part of the telescopic piece 13 are made to be in a tail hook shape through a hydraulic device so as to be convenient to hook the supporting device 6, the aircraft 12 drives the parking aid 5 and pulls the piston 17 to move through the chain 15 and the gear 16, the intelligent controller 19 arranged on the cylinder 18 can control the air inflow of the air inlet 21 through the electric pump 20, even completely close the air inlet 21, ensure that the piston 17 moves at a proper moving speed and obtains enough force to force the parking aid 5 to stop moving at the moment close to the raft vehicle 9, and meanwhile, the intelligent controller 19 instructs the positioning device 22 to pop out upwards to clamp the piston 17 to stop at the position. At this time, the aircraft 12 also changes the tail hook below the telescopic piece 13 into a straight state through a hydraulic device and enables the whole telescopic piece 13 to retract rapidly so that the aircraft 12 is separated from the hooking and blocking, the aircraft 12 after being separated from the hook can automatically slide onto the raft vehicle 9 from the parking aid 5 under the pushing of the residual force of inertia impulse, and the raft vehicle 9 can carry the aircraft 12 to drive away from the runway 1 to a place where the aircraft should go. The side, facing the runway, of the aircraft 12 is provided with rotating shafts 23 and 24 in a transverse arrangement mode, the rotating shafts 23 and 24 are strip-shaped, the cross sections of the rotating shafts 23 and 24 are isosceles trapezoids, and the waist of each rotating shaft is arc-shaped, so that the shape of each rotating shaft belongs to an irregular trapezoid; the upper bottom surface of the rotary shaft is provided with a wear-resistant layer capable of coping with landing sliding friction, the lower bottom surface of the rotary shaft is provided with a stealth coating layer capable of realizing high-altitude stealth, and different selections can be completed as required by rotating the rotary shaft.

Referring to fig. 3 and 4, the runway 201, the second step of the stepped docking aid 202, and the upper end surface of the raft vehicle 203 are at the same height and are provided with elastic shock-absorbing devices, the elastic shock-absorbing devices are formed by arranging a plurality of

steel plates

204, 205, 206 at intervals, the upper end of the steel plate 204 is coiled with a barrier rod 207, and the lower end is connected with the runway surface of the runway 201 in an inclined manner. The aircraft 208 can land on the steel plate 204, and after the aircraft 208 slides stably, the aircraft enters the position above the second step of the parking aid 202, the aircraft 208 pushes the telescopic piece 209 downwards, so that the rotatable corner below the telescopic piece 209 hooks the arresting bar 210, the inertial impulse of the aircraft 208 drives the parking aid 202 and the raft vehicle 203 staying on the first step of the parking aid 202 to move towards the left side, at the moment, the intelligent controller 211 can automatically control the air outlet amount of the air outlet hole 213 through the motor 212, and the inertial impulse of the aircraft 208 is counteracted by the air pressure in the air cylinder 214 and the elastic force of the spring 216 arranged on the piston 215. When the docking aid 202 moves to the end of the left direction, the latch 217 arranged on the docking aid 202 is automatically inserted into the hole 218 arranged at the tail end of the runway 201, and at the same time, the hydraulic device on the aircraft 208 immediately bends the rotatable corner arranged below the telescopic member 209 to retract the telescopic member 209 quickly, so that the aircraft 208 after unhooking automatically slides from the upper end surface of the second step to the upper end surface of the raft 203 by the residual force of inertia impulse and is clamped by the blocking

members

219 and 220 in front and behind, and then the intelligent controller 211 continues to instruct the latch 221 arranged on the first step to fall down, so as to release the positioning control of the raft 203, and enable the raft 203 to drive away from the runway 201 with the aircraft 208.

As shown in fig. 5, an accumulator is arranged in the runway groove 301, the accumulator is composed of a pneumatic component 302 and a spring 303, one end of the pneumatic component 302 is connected with a booster 304, the booster 304 is provided with

bolts

305 and 306, the bolt 305 is responsible for positioning a raft vehicle 307, and the bolt 306 is responsible for positioning the booster 304. An intelligent controller 308 and an air pump 309 are arranged on the side surface of the tail end of the air pressure part 302, and after the booster 304 is positioned through the bolt 306, the air pump 309 can vacuumize the inside of the air pressure part 302. The tail end of the pneumatic component 302 is provided with a flying assisting slope 311, and the flying assisting slope 311 is provided with a rotating component which consists of a driving wheel 312, a flywheel 322 and a conveying belt 313. The raft vehicle 307 is provided with a flame baffle 320 and an accumulator, the accumulator is composed of an air pressure part 314, the air pressure part 314 is provided with an air pump 315, and one end of the air pressure part 314 is connected with a boosting part 316. When the pneumatic member 314 is fully expanded by the force of the internal spring, the boosting member 316 is locked and positioned by the locking member 317, and at this time, the air pump 315 can completely pump out the air in the pneumatic member 314 to form a vacuum in the pneumatic member 314, so that the boosting member 316 stores a strong atmospheric pressure capable of moving in the left direction. When the aircraft 310 needs to be ejected for takeoff, firstly, the raft vehicle 307 is stopped above the booster 304 with the aircraft 310, the position of the raft vehicle is fixed by the bolt 305, then an engine of the aircraft 310 is started, then an electric driving device arranged on the flying-assisting slope 311 is started, the driving wheel 312 and the flywheel 322 drive the conveyor belt 313 to rotate at a high speed, when the rotating speed reaches a preset value, the intelligent controller 308 instructs the bolt 306 to release the control of the booster 304, so that the booster 304 ejects the aircraft 310 for the first time through the raft vehicle 307 under the action of the atmospheric pressure accumulated by the air pressure piece 302, before the raft vehicle 307 collides with the buffer device 318, the switch 319 is touched to release the positioning control of the aircraft 310 by the clamping piece 321 on the raft 307, and simultaneously the positioning control of the booster 316 by the clamping piece 317 is also released, so that the booster 316 can be under the action of the atmospheric pressure accumulated by the air pressure piece 314, the aircraft 310 is ejected for the second time, and the aircraft 310 also obtains the auxiliary thrust of the conveyor belt 313 during the process of the ski-jump takeoff. That is, this takeoff process of the aircraft 310, results in four successive thrust assisted flights: atmospheric pressure stored in the pneumatic element 302, atmospheric pressure stored in the pneumatic element 314, engine thrust of the aircraft 310, and auxiliary thrust of the conveyor belt 313.

As shown in fig. 6 and 7, four

elevators

401, 402, 403, 404 are provided on the aircraft carrier deck, and each elevator is provided with a guiding

device

405, 406, 407, 408 and a

positioning device

409, 410, 411, 412, respectively, wherein the elevator 403 has two layers, the next layer is used for carrying and transporting carrier aircraft, the upper layer is the top layer of the elevator, and the top layer is also provided with a guiding device, so that the carrier aircraft landed from the parking aid 413 can slide on the top layer to reach the elevator 404. The docking aid 413 is provided with a guide 415 and a clamp 416. When the landing of the aircraft carrier needs to be met, the intelligent integrated controller 414 instructs the docking aid 413 to extend backwards along the track groove 417, if the length of the docking aid 413 is 120 meters, according to a common practice, the aircraft carrier will land at the middle section of the docking aid 413 and extend out of the tail hook to hook the guiding device arranged at the middle section, then the inertial impulsive force of the aircraft carrier will drive the whole docking aid 413 to move towards the elevator 403, and at the same time, the docking aid 413 automatically expands two tasks: firstly, the accumulator arranged below the deck stores power, and the inertia impulsive force of the carrier-based aircraft is quickly digested. Secondly, the clamping devices 416 are close to the middle of the two side edges of the docking assistant 413, and the positions of the carrier-based aircraft are corrected, so that each carrier-based aircraft can accurately slide to the elevator 403 or the elevator 404 every time. When the ship-based aircraft is not lifted and landed but needs to be fully loaded, the intelligent integrated controller 414 also instructs the parking aid 413 to extend backwards, then the

rotating pieces

418 and 419 near the track groove 417 are lifted up through the lifting device to be equal to other guiding devices in height, and as the rotating

pieces

418 and 419 can respectively enable the ship-based aircraft staying on the rotating pieces to move towards the transverse direction or the longitudinal direction, the ship-based aircraft can be uniformly distributed at each appropriate position, including the ship-based aircraft after being popped up, and then the ship-based aircraft is positioned through a positioning device such as a sucker device to deal with high wind and high waves. If the pilot can not safely control the aircraft due to the injury, a power switch which requests the remote control of the ship-based aircraft can be turned on, and the landing work is handed over to the ship-based island staff to be completed. If the carrier-based aircraft is on fire, the tail hook hooks the guiding device on the parking aid 413 instantly when the carrier-based aircraft lands, the intelligent integrated controller 414 instructs the fire extinguishing device 433 to be unfolded and operated at the first time, and when the parking aid 413 is to be stopped stably, the carrier-based aircraft is instructed to stretch, straighten and retract the tail hook, so that the carrier-based aircraft rapidly slides over the

elevators

403 and 404 from the parking aid 413 to the rescue deck 434 by using the residual force of inertial impulsive force, and is positioned by the stopping piece 435 and the clamping device 436, so that the rescue device 437 can continuously complete emergency tasks such as fire extinguishing, rescue, medical care and the like. The damaged carrier-based aircraft is quickly moved to the rescue deck 434 to receive emergency rescue, and the normal take-off and landing of other carrier-based aircraft cannot be influenced.

The elevator 401 is able to transport the carrier aircraft to the

thrusters

421, 422 through the transition deck 420. Since the flat flame deflector 423 is provided with the guide 424 and the top end of the booster is provided with the rotating member 425, the carrier-based aircraft can also reach the catapult position of the booster 422 from the lift 402 through the rolling guide of the

guide

406, 426, 424, 425 and can also reach the catapult position of the booster 421 if transmitted through the steering of the guide 427. In the same way, the carrier aircraft staying behind the island 430 can also be transported to the launch position of the thrusters 422 by the guiding

devices

429, 428, 426, 424, 425. The tips of the

thrusters

421 and 422 are provided with flight assist

slopes

431 and 432, respectively. The

boosters

421 and 422 can launch one carrier at a time or two carriers at the same time to take off the carrier-based aircraft as required. Through the control of the intelligent integrated controller 414, all guiding devices on the deck can be lowered to be as high as the deck surface, the work of a fire truck or the take-off and landing of a helicopter are not influenced, the configuration and the use of a tractor can be reduced and avoided, even, tires can be omitted for the fire truck by matching the use of the guiding devices and the accurate and rapid control of the controller, and the complicated work of the deck surface can be spanned towards mechanization, intellectualization and unmanned one step.

Referring to fig. 8 and 9, the upper end surface of the stopping aid 501 is connected with a steel plate 502, the upper end of the steel plate 502 is connected with a rolling shaft 503, the upper surface of the rolling shaft 503 is covered with a steel plate 504, the upper surface of the steel plate 504 is connected with a steel plate 505, the upper end of the steel plate 505 is connected with a stopping rod 506, the stopping rod 506 is wrapped with a high-temperature-resistant and friction-resistant protective layer, and the stopping aid 501 is provided with a guide device with a double-layer elastic shock absorption structure. When the missile 507 is closed, the chemical energy impeller and the initiation fuse fall to the position above the stopping aid 501, the tail hook 508 laid down can hook the arresting rod 509, and the missile 507 can gradually lose inertia power through the actions of the stopping aid 501 and the accumulator 510 arranged in the runway groove 513, so that the missile can land safely and stop stably. The missile 507 is provided with folding wings 511, and when landing, the missile can land in a folding and folding manner as shown in fig. 8, and can land in an unfolding and gliding manner as shown in fig. 9. The tail rudder 512 of the missile 507 can also be rotated to fold as shown in fig. 8 or erected to work as shown in fig. 9. The front end of the missile 507 is provided with a protective cover 514 to protect the missile nose from being impacted by common external force and not exploding.

Reserve fuel tanks

515, 516 are provided on both sides of missile 507 to increase its cruise radius or extend cruise time. Missile 507 performs its mission on the fly, opens protective shield 514, and after launching a bullet or projectile of somewhat smaller size, it can either return to the ground with

fuel tanks

515, 516 or directly attack the target in a self-destructive manner. One surface of the missile 507 used for landing is provided with a crawler belt device 517, and the crawler belt is rotated to enable the surface provided with the wear-resistant layer to face downwards so as to cope with landing sliding friction; and when the rotating part is rotated to the other side provided with the stealth coating downwards, the stealth is realized.

Claims

1. A method for taking off and landing an aircraft without a landing gear or tires in a sliding mode and a facility or a device thereof are characterized in that:

facilities or devices capable of replacing the functions of landing gears, tires or braking members on the aircraft or facilities or devices capable of assisting the taking-off and landing of the aircraft are arranged on the runway, so that the aircraft without the landing gears, the tires or the braking members can safely take off or land on the runway in a sliding mode.

2. A method, apparatus or device according to claim 1, wherein:

the facilities or devices at least comprise a runway groove or a track groove or a raft vehicle or a stop aid or a booster or an accumulator or a controller or a detector or a fork or a guiding device;

the stopping aid, the booster or the raft vehicle adopts a mode of compressing or stretching elastic substances, or a mode of compressing or stretching gas or liquid in gas-pressure parts or hydraulic parts or gas-pressure parts, or a steam driving device or an electric driving device to help the aircraft to land or take off;

the guide device comprises a rotating part or a wear-resistant part or a track groove or a track groove or a tubular object or a magnet or a magnetic suspension device or a buffer device or a positioning device or a clamping device or a steam driving device or an electric driving device;

the main components of the buffer device comprise a wheel, a flywheel, a tire, a gear, a rack, a chain, a track, a liquid filling piece, an inflating piece, an air pressing piece, a hydraulic piece, an air pressing piece, an anti-collision piece, a blocking piece, a braking piece or an elastic damping device; the elastic damping device is composed of two or more layers of structures;

the rotating part comprises a wheel or a flywheel or a ratchet wheel or a gear or a tire or a bearing or a roller or a conveyor belt or a crawler belt; the rotation of the rotating piece is controlled by a steam driving device, an electric driving device, a speed changer or a braking piece;

the arresting piece comprises an arresting cable, an arresting rod, an arresting column, an arresting block, an arresting plate, an arresting wall, an arresting net or an arresting sleeve;

the controller comprises a manual controller, a remote controller, an intelligent controller or an intelligent integrated controller;

the main working mode or main components in the positioning device comprise a magnet, a sucker, a plug, a buckle, a spiral, an expansion, a binding, a hooking, a hanging, a sleeve, a clip or a surrounding;

on the runway or in the runway groove or the track groove, or a liquid or guiding device or an accumulator or a steam ejector or an electromagnetic ejector is arranged;

the carrier of the runway is the deck of a ground or liquid or surface ship.

3. A method, apparatus or device according to claim 2, wherein:

the runway or the parking aid, the booster or the raft vehicle is provided with a power accumulator or a steam type catapult or an electromagnetic type catapult or a controller or a detector or a lifter;

the parking aid, the booster or the raft vehicle is parallel to or connected with or combined with the elevator into a whole;

a hooking device or a guiding device or a lifting device or a fire fighting device or an emergency device or a medical device or a flying assisting slope or a ladder or a slide or a manned escalator or a freight elevator is arranged on the parking aid or the booster or the raft vehicle or the lifter or on the road surface of the runway; the guiding device can be used as a hooking device;

a boosting part is arranged on the booster, and a rotating part is arranged at the upper end of the boosting part; the booster or the raft vehicle or the runway or the deck is provided with a flame baffle plate, and the flame baffle plate is provided with a rotating part; a guide device is arranged on or on the flying assisting slope;

the accumulator can store the inertia impulse force of the aircraft during landing by compressing or stretching an elastic substance, or store the atmospheric pressure by pumping out the gas or liquid in the pneumatic or hydraulic part or the pneumatic or hydraulic part to make the interior of the pneumatic or hydraulic part or pneumatic or hydraulic part tend to vacuum or become vacuum so as to generate the atmospheric pressure;

the upper end face of the stop aid or the booster or the raft vehicle is as high as or almost as high as the road surface of the runway;

or when the raft vehicle stays on the stopping aid or the booster, the upper end surface of the raft vehicle is equal to or almost equal to the road surface of the runway;

the stop aid is combined with the booster into a whole.

4. A method, apparatus or device according to claim 2, wherein:

and a booster or a stopping aid or an accumulator or a chemical energy pusher or a steam type ejector or an electromagnetic type ejector is arranged on the raft vehicle.

5. A method, apparatus or device according to claim 2, wherein:

the stopping aid or the booster is of a double-layer or three-layer structure or is in a step shape, the stopping aid or the booster in the step shape is at least provided with a first step and a second step, the upper end surface of the second step is equal to or almost equal to the road surface of the runway in height, and the upper end surface of the second step is provided with a guide device;

when the raft vehicle stays on the first-stage step of the parking aid or the booster, the upper end face of the raft vehicle is equal to or almost equal to the upper end face of the second-stage step.

6. A method, apparatus or device according to claim 2, wherein:

the aircraft is provided with a tail hook or a telescopic piece or a detector or a controller or is provided with a power switch which allows or does not allow the ground command center to remotely control the aircraft to take off and land;

the tail hook or the telescopic piece is provided with a rotating piece;

the telescopic piece is in a plate shape, a block shape, a tubular shape, a strip shape or a column shape, a groove, a convex object or a corner is arranged on the telescopic piece, and the rotating piece or the corner can be used as a tail hook;

the number of the tail hooks or the telescopic pieces is two or more, the tail hooks can be straightened or folded, and the straightened state, the folded state or the hooked state of the tail hooks is controlled by a pneumatic or hydraulic piece, a pulley or a pulley block, a spring or a gear or a chain or a spiral device; the aircraft is connected with the tail hook through a rod-shaped object, a strip-shaped object or a block-shaped object, and the connection position of the rod-shaped object, the strip-shaped object or the block-shaped object and the tail hook can be rotated or is provided with a joint or is provided with a spring, a hydraulic piece, a pneumatic piece or a spiral device; the cross section of the rod-shaped object or the strip-shaped object or the block-shaped object can be in any geometric shape; the strip comprises a rope; the number of the rods, the strips or the blocks is two or more; the shaft or block may be bifurcated or may be flexible or resilient.

7. A method, apparatus or device according to claim 2, wherein:

a convex part or a groove or a rotating shaft or a transmission part or a guiding device is arranged on one surface of the aircraft, which faces the runway and is used for landing;

the convex part or the groove or the rotating shaft or the transmission part or the guide device is magnetic or provided with a stealth coating;

the cross section of the rotating shaft is a regular or irregular semicircle or trapezoid; the rotating shafts can be arranged together by two or more than two.

8. A method, apparatus or device according to claim 2, wherein:

the guiding device can be a clamping type leading-in and leading-out device or an arched or frame-shaped supporting device;

the leading-in and leading-out device is in a lying type, one end of the leading-in and leading-out device can lead in a landing aircraft or lead out an aircraft needing to take off, two sides of the leading-in and leading-out device or the position of the leading-in and leading-out device can be moved, and the space between the two sides can be narrowed or widened; the controller can move the position of the lead-in and lead-out device or adjust the width of the space according to the real-time position of landing or takeoff of the aircraft;

the supporting device is in a vertical or inclined type, two sides of the supporting device are erected on a runway or a stop aid or a booster or a raft vehicle, the two sides can be bent, rotated or stretched, the two sides can keep a vertical or inclined state or an arc shape through elastic force, the two sides are formed by combining superposed elastic sheets, and the two sides are connected into an arch or frame shape through a rotating part or a blocking rod; the barrier rod is provided with a buffer device; the supporting device can be arranged or combined by two or more pieces;

the top surface of the supporting device is provided with a plate-shaped object or a strip-shaped object or a block, and the plate-shaped object or the strip-shaped object or the block is provided with a buffer device.

9. A method, apparatus or device according to claim 1 or 2 or 3 or 4 or 5 or 6 or 7 or 8, wherein:

the aircraft is not provided with a landing gear or a tire or a braking part, and the taking-off and landing modes are as follows:

the aircraft is assisted to land safely through a tail hook or a telescopic piece on the aircraft or a hooking device or a guiding device or a lifting device or an accumulator or a detector or a controller on the runway or the stop aid or the raft vehicle;

the aircraft can safely take off by the aid of a hooking device or a guiding device or a lifting device or a flying assisting slope or a power accumulator or a steam type catapult or an electromagnetic type catapult or a detector or a controller on the runway or the booster or the raft vehicle;

the power for boosting the aircraft to take off in a taxiing mode is from the following steps: a propeller or chemical energy impeller disposed on the aircraft; the chemical energy propeller or the steam type ejector or the electromagnetic type ejector or the accumulator or the magnetic suspension device or the guiding device are arranged on the runway or the booster or the raft vehicle.

10. A method, apparatus or device according to claim 9, wherein:

the landing mode of the aircraft is as follows: the aircraft lands on the runway, and the safe landing of the aircraft is assisted by a guiding device or a hooking device or an accumulator or a detector or a controller on the runway;

the landing mode of the aircraft is as follows: the aircraft lands on the stop-aid device or the raft vehicle, and the aircraft is helped to land safely under the action of a tail hook or a telescopic piece arranged on the aircraft or a guide device or a hooking device or a power accumulator arranged on the stop-aid device or the raft vehicle;

the landing mode of the aircraft is as follows: the aircraft lands on the runway, the landing is assisted by the guidance of a guidance device on the runway, when the aircraft is above the stopping aid, the aircraft drives the stopping aid to slide on the runway or a runway groove or a track groove under the action of a tail hook or an extensible part arranged on the aircraft or the guidance device or a hooking device or an accumulator arranged on the stopping aid, and when the stopping aid moves to the tail end of the runway or the runway groove or the track groove, the controller can instruct the tail hook or the extensible part or the guidance device or the hooking device to release the blocking of the aircraft, so that the aircraft slides to a raft vehicle or a conveyor belt or a lifter or a deck from the stopping aid by using the residual force of inertial impulse;

the landing mode of the aircraft is as follows: the aircraft lands along the direction shown by the runway, the landing angle or height is adjusted under the assistance of the detector, and then the aircraft stays on the raft vehicle under the action of a tail hook or a telescopic piece arranged on the aircraft or a guide device or a hooking device or a force accumulator arranged on the raft vehicle to drive the raft vehicle and the stop-aid device to slide on the runway or in the runway groove;

the landing mode of the aircraft is as follows: the aircraft lands along the direction shown by the runway, flies or slides to the upper end surface of a second step of the stepped stopping aid, stops on the upper end surface of the second step through the action of the tail hook, the telescopic piece, the accumulator or the guiding device or the hooking device arranged on the upper end surface of the second step, drives the stopping aid and the raft vehicle to slide for a certain distance on the runway or in the runway groove, and the controller commands the tail hook, the telescopic piece, the hooking device or the guiding device to release the blocking of the aircraft, so that the aircraft slides to the raft vehicle by means of inertia impulse force, and the guiding device on the raft vehicle controls or manages and protects the aircraft;

the takeoff mode of the aircraft is as follows: the aircraft stops on the raft vehicle or the booster, the raft vehicle or the booster stops on the guiding device of the runway or the runway groove or the track groove, and the aircraft can take off in a sliding way only after sliding for a certain distance along the aircraft by the thrust of the steam type ejector or the electromagnetic type ejector, the elastic force or the atmospheric pressure accumulated by the accumulator, the power provided for the rotating piece by the steam driving device or the electric driving device in the guiding device, or the acting force of the propeller or the chemical energy propeller arranged on the aircraft.