CN113335546A

CN113335546A - Method and device for enabling aircraft to take off and land in short distance

Info

Publication number: CN113335546A
Application number: CN202110616818.6A
Authority: CN
Inventors: 何韧
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-05-29
Filing date: 2021-05-29
Publication date: 2021-09-03

Abstract

The invention relates to a method and a device for taking off and landing an aircraft in a short distance, which comprises the following steps: the take-off and landing device is adopted to replace a take-off and landing runway of the aircraft and serve as a take-off device, a landing device, a transmitter or a recovery device of the aircraft. The take-off and landing device can be of a rotary type, and can help the aircraft to take off or land through centrifugal force generated by rotation or acting force of a traction piece or lifting change of an auxiliary frame, so that the take-off and landing track of the aircraft is in an arc shape or a circular form; the rotary lifting device is formed by combining at least four parts, namely a connecting rod or a rotating part, a carrier plate, a rotating shaft or an auxiliary frame and a restraining part. The take-off and landing device assists the take-off and landing of the aircraft in an inclined mode, a bent mode or a vertical mode; the inclined lifting device is formed by combining at least three parts, namely a carrier plate, an inclined plane frame and a restraining part; the bending type lifting device is formed by combining at least three parts, namely a support plate, a bending frame and a restraining piece; the vertical lifting device is formed by combining at least four parts, namely a telescopic part, a carrier plate or a carrier net, an auxiliary frame and a restraining part.

Description

Method and device for enabling aircraft to take off and land in short distance

Technical Field

The invention relates to a method and a device for taking off or landing an aircraft, in particular to a method and a device for taking off and landing the aircraft in a short distance.

Background

Currently, there are four main common ways of rocket landing recovery: sliding recovery, parachute recovery, aerial recovery and reverse thrust recovery. The taxiing recovery needs to be carried out on a three-to-five kilometer long runway by means of a space shuttle, and the occupied area of the long runway is too large. The parachute is recovered, which is only suitable for small and medium-sized rockets and is not easy to control the landing point. The air recovery method is that the parachute is used for helping the rocket to decelerate, and then the rocket is lifted away in the air by the helicopter, so that a driver is required to have a high driving level, and the air recovery method is still not suitable for the landing recovery of large rockets. The reverse thrust recovery technology has the advantages that the occupied area of the falling point is small, and the technology is suitable for directly falling on an external planet. But the disadvantages are many, such as more fuel consumption, rocket load increase; for another example, under the influence of unfavorable weather conditions, the balance and constant control when the rocket is close to the ground are not easy to master, and the safety is unstable.

The patent application with the publication number of CN103029848A discloses a technology for assisting an aircraft to take off by using a centrifugal force generated by circular motion of a disc, the invention patent with the publication number of CN111252263A discloses a technology for assisting a carrier-based aircraft on an aircraft carrier to take off by using a centrifugal force generated by rotation motion of a rotating table, the patent with the publication number of CN203975236U discloses a technology for assisting a carrier-based aircraft on an aircraft carrier to take off by using slope diving gliding, the technologies are all technologies for assisting the aircraft to take off and do not comprise an aircraft landing technology, and the rotation technology is only limited to a plane type and an inclined plane type, even, gravity or a motor is simply used to directly drive the aircraft to rotate, or the power is insufficient, the time consumption is too long, or the energy consumption is too large. The patent publication No. CN206954488U discloses a technology for landing an airplane in the air by installing a first landing frame on the airplane and an air bag in the air, and the patent publication No. CN206590136U discloses a technology for landing an airplane by installing a hanging frame and an air bag in the air, which both have the disadvantages of difficult and unstable operation and low safety.

Disclosure of Invention

The invention aims to provide a method and a device for taking off and landing an aircraft in a short distance. The main technical problems to be solved include: 1. the current common plane runway is changed into a three-dimensional runway, and the aircraft is taken off and landed in the air. 2. The aircraft is assisted to take off by utilizing the strong inertia kinetic energy or potential energy when the aircraft lands. 3. The form is optimized by a rotating mode, an inclined plane mode, a curved plane mode, a spiral plane mode or a vertical telescopic mode so as to assist the takeoff and landing of the aircraft. 4. The towing piece or the auxiliary piece is used for assisting the aircraft to take off or land and providing safety protection.

The invention solves the problems by adopting the following methods: a method and its apparatus that can let the aircraft take off and land in the short distance, take off and land the runway of the aircraft with taking off and land the apparatus to replace completely or partly, take off and land the apparatus can be regarded as the take-off or landing device or launcher or recoverer of the aircraft; the main body part of the lifting device is arranged above or beside a basic plane, wherein the basic plane comprises the ground or the water surface or the deck surface or the platform surface or the building plane.

The take-off and landing mode of the device is a rotary type, and the take-off or landing of the aircraft is assisted by the centrifugal force generated by rotation or the acting force of a traction piece or the lifting change of an auxiliary frame; the take-off or landing track of the aircraft is in a circular arc shape or a circular form, and the take-off and landing sliding distance of the aircraft is relatively prolonged by the circular arc-shaped or circular take-off and landing track; the rotary type or the unidirectional rotation mode.

The rotary type lifting device is formed by combining at least four parts, namely a link rod or a rotating part, a carrier plate, a rotating shaft or an auxiliary frame and a restraining part, wherein the link rod, the rotating part, the rotating shaft and the auxiliary frame can be used as different parts and exist in the same lifting device at the same time; one end of the link rod is connected with the carrier plate, the other end of the link rod is connected with the rotating shaft, and the rotating shaft is directly or indirectly connected with the basic plane.

The rotating piece and the rotating shaft are coaxial or different in axial lead, the rotating piece can rotate around the axial lead of the rotating shaft, and the rotating shaft is connected with the basic plane through an auxiliary frame; the support plate is arranged on the link rod or the rotating piece; the carrier plate can move along the surface or the side surface of the cylindrical or wheel disc-shaped rotating piece, and the carrier plate is connected with the rotating piece or is connected with the rotating piece through a restraining piece. When the link rod and the rotating part exist as two parts at the same time and the link rod is connected with the support plate, the support plate can drive the link rod or the link rod can drive the support plate to rotate on the surface or the side surface of the rotating part.

Alternatively, the rotary member itself does not rotate, and the carrier plate can move along the circular surface of the cylindrical or disk-shaped rotary member or along a predetermined arc-shaped track on the cylindrical or disk-shaped rotary member.

The rotating member is in a ring shape, the ring can rotate around the rotating shaft, and the carrier plate can rotate around the ring of the ring.

The connecting rod is connected with the auxiliary frame; the connecting rod or the support plate is connected with the auxiliary frame or the basic plane directly through a pulling piece; the connecting rod or the support plate is connected with the restraining part through the auxiliary frame through a rope or a chain; the pulling piece is arranged on the connecting rod or the support plate directly; a clutch device is arranged between the link rod or the rotating piece and the restraining piece; the link rod or the support plate can extend and retract; the auxiliary frame can be either telescopic or rotatable or foldable or movable.

Carrying the aircraft by using a carrier plate; the traction piece is used for increasing power for takeoff of the aircraft or controlling the speed for landing of the aircraft; the main body of the traction piece comprises an elastic device, an electromagnetic device, an air pressure device, a hydraulic device, a power driving device, a counterweight device, a wheel disc device, a steam type ejection device, an electromagnetic damper, a gear set, a pulley block, a winch or a linear tension type mechanism, and the power driving of the power driving device comprises electric power driving, fuel oil driving and fuel driving; the counterweight device is used for configuring a heavy object according to the gravity required by the aircraft to be pulled to perform rapid movement; the wheel disc device drives the connecting rod to rotate or drives the support plate to lift through the acting force of the rotating wheel or the rotating disc, and the wheel disc comprises a toothed wheel disc, an energy storage wheel disc, an acceleration wheel disc and a constant-speed wheel disc.

The traction part is a power accumulator which can store inertial impulsive force of aircraft landing, and the inertial impulsive force comprises kinetic energy and potential energy; the power storage mode of the power accumulator comprises the steps of storing power by adopting a spring, a pneumatic power or a hydraulic power or storing kinetic energy or potential energy after converting the kinetic energy or the potential energy into electric energy; the tow may alternatively assist in the takeoff of the aircraft with the stored capacity.

The rotary type lifting device can be regarded as a folding type lifting device, and the number of folding layers can reach two or more than two. The carrier plate and the link rod can be folded towards the direction of the basic plane when the aircraft is helped to land, and then the carrier plate and the link rod are unfolded towards the air when the aircraft is helped to take off.

The rotary type lifting device at least comprises a rotating mode of three-dimensional rotation, horizontal rotation, inclined rotation or spiral rotation.

The rotary type take-off and landing device can enable the carrier plate to bear the aircraft in the air for landing, and then the aircraft is directly conveyed to the basic plane through the gradual downward rotation or movement of the carrier plate; or may require shortening or lowering of the auxiliary frame to enable the aircraft to land on the substantially planar surface.

The three-dimensional rotating lifting device is similar to the rotating mode of a windmill.

The horizontal rotating take-off and landing device is internally or additionally provided with an auxiliary flying frame, a movable platform is arranged in the middle of the upper end surface of the auxiliary flying frame, a flying assisting inclined plane is arranged at the rear end or the upper end of the auxiliary flying frame, the movable platform penetrates through the middle of the auxiliary flying frame and the lower part of the flying assisting inclined plane, and the movable platform can stretch or move under the help of a restraining piece; the aircraft on the carrier plate can be quickly transferred onto the movable table through butt joint or collision of the movable table and the carrier plate, and the aircraft takes off along the flight assisting inclined plane through contraction or movement of the movable table.

The carrier plate can slide along the spiral surface of the spirally rotating lifting device.

By means of the rotation of the link rod or the rotating part or the extension or displacement of the auxiliary frame, the collision of the fuselage of the landing aircraft with the carrier plate can be avoided, or the shock absorption of the landing aircraft with the carrier plate can be assisted.

Preferably, one end of the link or the rotary member is arranged on the stern or the side of the ship, and the landing aircraft can be directly sent to the top deck or the lower deck of the ship from the air through the bearing of the carrier plate and the rotation of the link or the rotary member.

The carrier plate can alternatively be adjusted to be a sail of a vessel.

Preferably, the lifting device is provided with an auxiliary fitting, and the auxiliary fitting comprises: an angle control device or a state constancy device is arranged between the connecting rod and the carrier plate; arranging a barrier or a protective cover on the carrier plate, wherein the barrier can be used as a positioning piece; the barricade is provided with a self-adjusting device or a constant device for keeping the barricade rod in a horizontal state. The protective cover is used for weakening air resistance when the carrier plate moves or blocking the jet of flames at the tail part of the aircraft; the protective cover is in a three-dimensional triangle shape, an arc shape or a rhombus shape; an ejection device is arranged between the protective cover and the aircraft or between the protective cover and the carrier plate; elastic means are provided at the junction of the link and said base plane.

Preferably, the flying assisting process of the rotary take-off and landing device comprises the following steps: firstly, rotating the connecting position of the link rod or the rotating piece and the carrier plate to a low position to ensure that the carrier plate is butted with the receiving and conveying table; secondly, enabling the aircraft to drive into the carrier plate from the receiving and delivering platform; thirdly, the starting barrier piece is propped against the rear end of the belly of the aircraft and protects the two sides of the belly or is propped against the rear part of the front wheels or the rear wheels of the aircraft and protects the left side and the right side of the front wheels or the rear wheels; fourthly, or the carrier plate needs to be rotated to be in an inclined upward bending state; meanwhile, or the pneumatic device or the hydraulic device on the containment part needs to be vacuumized; fifthly, the link rod or the rotating part is rapidly pulled to enable the carrier plate to be lifted from the low position to the high position or to rotate around in a horizontal mode by means of the elasticity of the elastic device in the pulling part or by means of the atmospheric pressure generated by the vacuum or by means of steam type ejecting force or electromagnetic type ejecting force or by means of power driving; and sixthly, the arresting member on the carrier plate selects the airplane to quickly release the control on the belly of the aircraft or the front wheel or the rear wheel, and the aircraft is assisted to take off by the centrifugal force generated by rotation or the acting force of the traction member on the carrier plate.

The landing assisting process of the rotary lifting device comprises the following steps: firstly, or a carrier plate on a link rod or a rotating part needs to be lifted to a high position; secondly, a barrier on the carrier plate blocks a wheel or a wheel carrier of the aircraft in flight or after landing, or a tail hook of the aircraft hooks the barrier, so that the aircraft can drive a connecting rod or a rotating piece to rotate through the carrier plate; thirdly, the towing part is used for consuming the inertial kinetic energy or the potential energy of the aircraft, or the towing part is used for storing the inertial kinetic energy or the potential energy of the aircraft.

The rotation of the link or rotating member may be one half turn or one turn or two or more turns.

Preferably, the take-off and landing device assists the take-off and landing of the aircraft in an inclined mode or a bent mode or a vertical mode;

the inclined lifting device is formed by combining at least three parts, namely a carrier plate, an inclined plane frame or an inclined plane plate and a traction piece, wherein the inclined plane frame is in a three-dimensional type, the upper end surface of the inclined plane frame is a section of inclined plane or a zigzag inclined plane, and a guide piece is arranged at or near the top end of the inclined plane frame; the carrier plate may be connected directly to the hold-down member or to the hold-down member via a guide member by means of a rope or chain.

The flight assisting process of the inclined type take-off and landing device comprises the following steps: firstly, the carrier plate is stopped at the lower end of the inclined plane of the three-dimensional inclined plane frame or in front of the lower end of the inclined plane; secondly, enabling the aircraft to drive into the carrier plate from the receiving and delivering platform; thirdly, the starting barrier piece is propped against the rear end of the belly of the aircraft and protects the two sides of the belly or is propped against the rear part of the front wheels or the rear wheels of the aircraft and protects the left side and the right side of the front wheels or the rear wheels; fourthly, the support plate is rotated to be in an inclined upward bending state; meanwhile, or the pneumatic device or the hydraulic device in the pulling piece needs to be vacuumized; fifthly, the carrier plate and the aircraft are quickly pulled to move from a low position to a high position along the inclined plane of the inclined plane frame by means of the elastic force of an elastic device in the holdback, the atmospheric pressure generated by the vacuum, the steam type ejection force, the electromagnetic type ejection force or power driving.

The landing assisting process of the inclined type lifting device comprises the following steps: firstly, the carrier plate is stopped at the upper end of the inclined plane of the three-dimensional inclined plane frame; secondly, a barrier on the carrier plate blocks a wheel or a wheel carrier of the aircraft, or a tail hook of the aircraft hooks the barrier; thirdly, the aircraft can slide downwards from the upper end of the bevel rack through the carrier plate, and in the process, the carrier plate directly pulls the pulling piece to obtain braking force, or pulls the pulling piece through the rope to obtain braking force, or obtains braking force through the assistance of the motorized device or the electromagnetic damper; or the towing part is used for storing the inertia kinetic energy or potential energy of the aircraft.

The bending type lifting device is formed by combining at least three parts, namely a support plate, a bending frame or a bending plate and a traction piece, wherein the bending frame is in a three-dimensional type, the upper end surface of the bending frame can be a section of arc surface or wave shape, in a vertical section of arc surface, the left side and the right side of the lowest part of the arc surface are represented as two arc-shaped inclined surfaces, and each inclined surface can be regarded as a descending inclined surface or an ascending inclined surface; the carrier plate may be connected directly to the hold-down member or to the hold-down member via a guide member by means of a rope or chain.

The flight assisting process of the bending type take-off and landing device comprises the following steps: firstly, lifting the aircraft to one end of the section of cambered surface by using a lifting platform; secondly, enabling the aircraft to enter the carrier plate from the lifting platform and be positioned on the carrier plate; thirdly, the carrier plate slides along the descending inclined plane of the cambered surface, and the aircraft on the carrier plate obtains initial speed or acceleration through gravity or acting force of the traction piece; fourthly, when the carrier plate reaches the lowest part of the section of the cambered surface, the carrier plate or the aircraft is quickly adjusted to be in an inclined upward pitching state; fifthly, the aircraft takes off along the ascending slope of the cambered surface by means of inertia kinetic energy of the carrier plate, traction force of the traction piece or power of the aircraft.

The landing assisting process of the bending type lifting device comprises the following steps: firstly, a blocking piece on the carrier plate blocks a wheel or a wheel carrier of the aircraft, or a tail hook of the aircraft hooks the blocking piece, so that the aircraft drives the carrier plate to slide along a descending inclined plane of the cambered surface, and then the carrier plate continues to slide along an ascending inclined plane until the carrier plate is stopped stably; the carrier plate is braked or accumulated by the restraining piece in the sliding process; secondly, transferring the aircraft which is stably stopped from the carrier plate to a lifting platform, and then transferring the aircraft to the ground through the lifting platform; the lifting platform can be used as an accumulator to store the gravity of the aircraft during descending.

The inclined plane plate or the bent plate can be folded; the inclined plane plate or the bent plate is provided with a track.

The vertical lifting device can be vertically telescopic, the lower section of the lifting device is arranged below the basic plane, a support plate or a carrying net or a clamp or a buffer is arranged above the middle section of the lifting device, the carrying net comprises a net-shaped object or a cloth-shaped object, and the carrying net can be made of high-temperature resistant materials; the carrier web is either resilient.

The vertical lifting device is formed by combining at least four parts, namely a telescopic part, a carrier plate or a carrier net, an auxiliary frame and a restraining part; the telescopic piece and the auxiliary frame can be combined into a whole.

The working method of the vertical take-off and landing device comprises the following steps:

a method comprises the following steps: when the top end or the upper section of the lifting device is provided with a clamp or a buffer, a carrying plate is arranged below the clamp or the buffer, and the landing assisting step of the vertical lifting device comprises the following steps: firstly, enabling an aircraft to vertically land above the carrier plate; secondly, enabling the tail part of the aircraft to be close to the carrier plate, and enabling the tail part to be close to the carrier plate by a set distance through reverse-thrust flame sprayed by the aircraft; thirdly, the aircraft, the carrier plate and the telescopic piece descend at the same speed at the same time, and the descending speed can be controlled by controlling the contraction speed of the telescopic piece or controlling the reverse thrust of the aircraft; in the descending process, the tail part of the aircraft can be gradually close to the carrier plate, and meanwhile, the clamp or the buffer object arranged at the top end or the upper section of the lifting device can rapidly move towards the position of the aircraft; fourthly, the aircraft is stopped on the carrier plate, and the body of the aircraft is clamped, wrapped or enclosed by the clamp or the buffer; and fifthly, closing the reverse thrust power of the aircraft, and transferring or consuming the inertial kinetic energy or potential energy of the aircraft landing by controlling the traction force of the traction piece or controlling the contraction speed of the telescopic piece.

A method comprises the following steps: when the top end or the upper section of the lifting device is provided with a net or a clamp or a buffer, the landing assisting step of the vertical lifting device comprises the following steps: firstly, enabling an aircraft to vertically land in the carrier net by closing reverse thrust power in advance, and enabling the carrier net to descend along with the aircraft; secondly, the carrier net drives the telescopic piece to contract, and inertial kinetic energy or potential energy of the aircraft landing is transferred or consumed by controlling the contraction speed of the telescopic piece or controlling the traction force of the telescopic piece; thirdly, the clamp or the buffer object arranged on the lifting device moves towards the aircraft rapidly until the clamp or the buffer object clamps or wraps or surrounds the body of the aircraft.

A method comprises the following steps: the flight assisting step of the vertical take-off and landing device comprises the following steps: firstly, the telescopic piece is contracted to accumulate force, or the restraining piece is prepared in advance or kinetic energy is accumulated; secondly, the aircraft is vertically erected above the carrier plate or the carrier net, and a clamp arranged at the top end or the upper section of the take-off and landing device clamps the body of the aircraft; thirdly, the carrier plate or the carrier net is quickly pushed or pulled by means of the elastic force generated after the telescopic piece is contracted or by means of the kinetic energy stored by the traction piece or by means of steam type ejection force or electromagnetic type ejection force or by means of power drive, so that the aircraft is driven to be ejected and lifted off.

Preferably, the rotary type lifting device or the inclined type lifting device or the bending type lifting device or the vertical type lifting device are combined together for use.

In the rotary type lifting device, at least one link rod is arranged; alternatively, two or more link rods may be combined with the same lifting device.

In each lifting device, the holdback is at least one piece; or two or more traction members are combined in the same lifting device for use.

A magnetic suspension device, a power driving device, a steam type ejection device, an electromagnetic type ejection device, a braking device, a gliding device, a damping device, a pressure transmission device, a power driving device, a fire extinguishing and explosion preventing device or a medical aid device is arranged on the carrier plate, the inclined plane frame, the bending frame or the movable table or the flight assisting inclined plane.

The carrier plate is adjusted in its inclination angle either by means of pressure elements.

Preferably, the main body of the angle control device is a pressure piece, and the shape of the pressure piece comprises a straight shape, a square shape, an annular shape, a semi-annular shape or an arc shape.

The angle control device determines or controls the input amount of liquid or gas in the pressure piece B arranged between the carrier plate and the link rod according to the change of the rotation angle of the link rod, or the height change of one end of the link rod, or the telescopic distance of a piston rod in the pressure piece A arranged on the auxiliary frame or the basic plane, thereby adjusting the telescopic distance of the piston rod of the pressure piece B and enabling the carrier plate to be in a horizontal state or an inclined upward-bending state all the time.

When the volumes of the pressure piece A and the pressure piece B are unchanged, and the apertures and the flow rates of the gas or the liquid flowing in and out are unchanged, the in-out flow rate of the gas or the liquid in the pressure piece B is determined or controlled by detecting the in-out flow rate of the gas or the liquid in the pressure piece A, so that the carrier plate is always in a horizontal state or an inclined upward bending state.

Preferably, the state constancy device is formed by at least three major components in combination of a controller in the form of a circuit board and a posture-maintaining instrument in the form of a gyroscope and an actuator in the form of a motor.

Preferably, an air assisted-flight and landing runway or an assisted-flight and landing guide device or a sensor or a detector is arranged beside the link rod or the wheel disc or at the upper end or the side of the inclined plane frame or at the upper end or the side of the bent frame or at the upper end or the side of the auxiliary frame.

Preferably, one end or both ends of the air assisted flight and landing runway can be lifted, so that the runway can be changed from a horizontal state to an inclined upward-bending state, and the lifting mode is as follows: and a telescopic supporting column or a supporting piece is arranged below the runway.

The guiding device comprises a signal transmitting device or a signal receiving device, or comprises a device for setting a virtual runway by using light or waves.

The guide means are either arranged on the carrier plate or on the barrier.

The aircraft comprises aircrafts and spacecrafts, such as civil airliners, military aircrafts, space shuttles, rockets and missiles; the taking-off and landing comprises taking-off and landing, the taking-off comprises launching, and the landing comprises recovery, landing and stable stopping; the half circle comprises a small half circle or a large half circle; the connection comprises a movable connection, a direct connection or an indirect connection; the rotating part comprises a cylinder, a wheel, a disc, a ring, a rod or any other geometrical shape; the auxiliary frame comprises a telescopic piece, a folding piece and a supporting frame; the traction piece at least has a traction function, a limiting function, a braking function or an energy storage and accumulation function, or can be directly expressed as an elastic piece and a pressure piece; the protection comprises clamping and clipping; the vertical standing comprises vertical standing and inclined standing; the rope comprises a rope-shaped object, a chain-shaped object and a cable; the guide comprises a pulley, a roller, a bearing, a shaft-shaped object and a guide object; the barrier piece comprises a hook hanging piece, and the barrier form of the barrier piece at least comprises a rod-shaped barrier, a reticular barrier, a belt-shaped barrier and a rope barrier; the pressure part comprises a pneumatic part, a hydraulic part, a pneumatic and hydraulic part or a telescopic part; the carrier includes a platform.

The beneficial effect of the invention is that after the method and the device are adopted: (1) the runway length may even be less than three hundred meters. Meanwhile, or because the lifting device is in a three-dimensional type, the space utilization rate of the airport is improved. (2) The airplane can land in the air, once the landing is unsuccessful, the airplane head does not need to be pulled up, the re-flying can be completed only by continuing to glide along the horizontal direction, and the influence of crosswind can be weakened. (3) The airplane lands in the air, the ground noise is low, and the airport does not need to be far away from the city by adding some sound insulation measures. (4) The technology provided by the invention is applied to the ship, so that the carrier capacity of the ship can be increased, the manufacturing, using and maintenance cost of the ship can be reduced, the space utilization rate of the ship can be improved, the taking-off and landing efficiency can be improved, the taking-off and landing can be safer, and even a tower can be cancelled. (5) If the rocket or the missile vertically lands on the aerial platform, the inertia kinetic energy or potential energy of the rocket or the missile can be quickly absorbed and transferred until the rocket or the missile is completely consumed due to the protection and the power assistance of the lifting device, so that the safety factor and the success rate of the landing are high. (6) The aircraft is subjected to cold ejection and cold landing by using the take-off and landing device, or cold launching and cold recovery are performed on the rocket and the missile, so that the operation mode can save the fuel oil of the aircraft and the fuel carried by the rocket or the missile.

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 present invention in relation to landing an aircraft using a rotary takeoff and landing gear.

Fig. 2 is a schematic side view of the manner shown in fig. 1 with respect to the landing gear for landing an aircraft to the ground.

Fig. 3 is a schematic top view of the carrier and dam structure shown in fig. 1.

FIG. 4 is a schematic side view of a second embodiment of the present invention in relation to the use of a tilting takeoff and landing gear to assist in the takeoff of an aircraft.

Fig. 5 is a schematic side view of the arrangement shown in fig. 4 with respect to adjusting the aircraft to a pitch-up condition for takeoff.

Fig. 6 is a schematic side view of a third embodiment of the invention in relation to a vertical lifting device provided with a carrier plate, i.e. for lifting an ejection rocket.

Fig. 7 is a schematic side view of a fourth embodiment of the invention relating to the use of a vertical take-off and landing gear with a net to assist in the landing of a rocket.

FIG. 8 is a schematic side view of a rocket in a manner as shown in FIG. 7 for safe landing.

Fig. 9 is a schematic side view of a curved take-off and landing apparatus according to a fifth embodiment of the present invention.

FIG. 10 is a schematic side view of the curved take-off and landing gear of FIG. 9 about to assist the aircraft in achieving initial velocity and acceleration.

Fig. 11 is a schematic side view of the aircraft about to be airborne in the manner shown in fig. 9.

Fig. 12 is a schematic side view of a sixth embodiment of the present invention in relation to a rotary takeoff and landing gear for use on a vessel to assist in the takeoff and landing of an aircraft.

Fig. 13 is a schematic side view of a seventh embodiment of the invention in relation to a rotatable swivel.

Fig. 14 is a schematic side view of an eighth embodiment of the invention in relation to a non-rotatable swivel.

Fig. 15 is a schematic side view of a ninth embodiment of the invention with respect to a carrier plate rotatable around a ring of a ring rotator.

Fig. 16 is a schematic side view of the carrier plate rotated to the outer surface of the rotary member in the manner shown in fig. 15.

FIG. 17 is a schematic side view of the carrier plate in the manner shown in FIG. 15 ready to retract the flight stop and release the magnetic force to allow the aircraft to fly.

Fig. 18 is a schematic plan view of a take-off and landing apparatus for a flat rotation according to a tenth embodiment of the present invention.

Fig. 19 is a schematic side view of the eleventh embodiment of the present invention with respect to a spirally rotating take-off and landing apparatus.

Wherein, the first embodiment: the airplane comprises a receiving platform 1, a base plane 2, a buffer piece 3, a connecting rod 4, an auxiliary frame 5, a hydraulic piece 6, a supporting column 7, a piston rod 8, an air flight assisting and landing assisting runway 9, a supporting plate 10, a hydraulic piece 11, a piston rod 12, an airplane 13, rear wheels 14, a long-rod stopping piece 15, a rotating shaft 16, a piston rod 17, clamping

pieces

18 and 19, a groove 20, a short-rod stopping piece 30, a middle line 31, a clamping piece 32, an expansion rod 33 and a front wheel 34. The second embodiment: the device comprises a delivery table 201, a hydraulic part 202, a bevel frame 203, a rope 204,

pulleys

205 and 206, a bevel 207, a carrier plate 208, a sliding plate 209, a hydraulic part 210, a liquid storage tank 211, an airplane 212, a short rod blocking part 213, a front wheel 214, an electric pump 215, a conduit 216, a piston rod 217, a clamping part 218 and an elastic blocking part 219. Third embodiment: the device comprises a basic plane 301,

hydraulic parts

302 and 303,

elastic parts

304 and 305,

telescopic rods

306 and 307, a carrier plate 308, clamps 309 and 310,

ropes

311 and 312,

auxiliary frames

313 and 314,

pulleys

315 and 316,

piston rods

317 and 318 and a rocket 319. Fourth embodiment:

hydraulic parts

401, 402, net 403, clamps 404, 405,

air cushions

406, 407, rocket 408, and base plane 409. Fifth embodiment: the bending frame 501, the lifting platform 502, the pressure piece 503, the cambered surface 504, the carrier plate 505, the arc-shaped plate 506, the telescopic piece 507, the airplane 508, the receiving and conveying platform 509, the blocking piece 510, the front wheel 511, the bolt 512, the steel cable 513 and the

pulleys

514 and 515. Sixth embodiment: the ship 601, the deck 602, the auxiliary frame 603, the link 604, the carrier plate 605, the circuit board 606, the gyroscope 607, the motor 608, the barrier 609, the pick-up station 610, the wheel disc 611, the auxiliary frame 612, the link 613, the carrier plate 614, the signal emitter 615, the positioning part 616 and the hydraulic transmission part 617. The seventh embodiment: the ship comprises a ship 701, a deck 702, an auxiliary frame 703, a rotating shaft 704, a wheel-shaped rotating member 705,

carrier plates

706 and 707, and a receiving and sending platform 708. The eighth embodiment: deck 801, auxiliary frame 802, annular rotating member 803, arc-shaped rail 804, carrier plate 805 and rotating shaft 806. Ninth embodiment: annular rotating member 901, stem 902, carrier plate 903, shaft 904, drone 905, stopper 906. Tenth embodiment: the airplane landing assisting device comprises a wheel disc 1001, a rotating shaft 1002, a connecting rod 1003, a carrier plate 1004, a ring 1005, an auxiliary landing platform 1006, an auxiliary flying frame 1007, an airplane 1008, an auxiliary landing runway 1009, a stopping piece 1010, a movable platform 1011 and an auxiliary flying sloping plate 1012. Eleventh embodiment: a substantially planar surface 1101, an auxiliary frame 1102, a spiral track 1103, a link 1104, a carrier plate 1105, a spiral surface 1106 sliding, a stopper 1107, and a track 1108.

Detailed Description

As shown in fig. 1, a base plane 2 is arranged on one side of a receiving and sending table 1, a buffer member 3, a link rod 4, an auxiliary frame 5, a hydraulic member 6 and a support column 7 are arranged on the base plane 2, the vertical hydraulic member 6 is respectively connected and positioned with the base plane 2 and the auxiliary frame 5, and one end of a piston rod 17 in the hydraulic member 6 is connected with the middle section of the link rod 4; in this embodiment, the hydraulic unit 6 is a drag unit by which the link 4 is connected to the auxiliary frame 5. The supporting column 7 is provided with a piston rod 8, and the telescopic distance of the piston rod 8 is adjusted, so that the flying-assisting landing-assisting runway 9 in the air can be adjusted to be in a horizontal state or an inclined upward pitching state; the upper end of the link 4 is movably connected to the carrier plate 10, one end of the hydraulic unit 11 is connected to the carrier plate 10, one end of the piston rod 12 is connected to the middle section of the link 4, and the upper section of the link 4 is extendable or retractable by the retractable rod 33.

When the airplane 13 lands on the air landing-aid runway 9 and slides onto the carrier plate 10, as shown in fig. 3, the rear wheel 14 is blocked by the long-rod blocking member 15, and the clamping

members

18 and 19 disposed at the two ends of the long-rod blocking member 15 are immediately closed to the middle section along the groove 20 to clamp the rear wheel 14, so that the inertial kinetic energy of the airplane 13 drives the link rod 4 to rotate around the rotating shaft 16 through the carrier plate 10, and the rotation of the link rod 4 drives the piston rod 17 to extend. Since the extension length of the piston rod 17 is constant each time the link 4 rotates from the vertical state to the horizontal state, the extension length of the piston rod 12 in the hydraulic unit 11 should be constant if the carrier plate 10 is to be kept horizontal throughout the lifting process. Thus, by adjusting the corresponding extension length of the piston rod 12 according to the extension length of the piston rod 17, the carrier plate 10 can be always kept horizontal or close to horizontal when descending from a high position to the ground, thereby ensuring that the aircraft 13 cannot slide off the carrier plate 10.

As shown in fig. 2, the airplane 13 can pull the telescopic rod 33 to extend to a set length during the rotation of the driving link 4. When the link 4 rotates to the horizontal state, the inertia kinetic energy of the airplane 13 is exhausted by the extension of the piston rod 17 in the hydraulic part 6, and the buffer part 3 buffers and protects the link 4, so that the carrier plate 10 can be butted with the receiving and sending table 1 without vibration. The extending process of the piston rod 17 can be a flowing process of oil liquid or a process of forming vacuum or tending to vacuum in the hydraulic part 6 according to different operation modes, so that the hydraulic part 6 becomes a power storage process, and when the connecting rod 4 and the carrier plate 10 are needed to help the airplane 13 take off, the atmospheric pressure stored in the hydraulic part 6 can play a role. Referring to fig. 3, the control of the rear wheels 14 by the clamping

members

18 and 19 is released, so that the long bar block 15 is retracted downwards below the surface of the carrier plate 10, and the airplane 13 can drive into the receiving platform 1 from the carrier plate 10, thereby completing the whole landing process.

As shown in fig. 3, fig. 1 and fig. 2, the hydraulic unit 11 is disposed on a side of the carrier plate 10. Two sets of stoppers, namely a long-rod stopper 15 and a short-rod stopper 30, are provided on the carrier plate 10. To assist in landing the aircraft 13, the short bar barrier 30 is retracted downwardly below the surface of the carrier plate 10 and the long bar barrier 15 is raised upwardly. At the moment when the rear wheel 14 of the airplane 13 is slid in the direction indicated by the middle line 31 and blocked by the long-rod blocker 15, the clamping

members

18 and 19 immediately move towards the position of the rear wheel 14 until the rear wheel 14 is clamped, so that the airplane 13 drives the carrier plate 10 and the connecting rod 4 to move towards the receiving and delivering table 1 through the long-rod blocker 15. At this time, the long bar block 15 and the

clips

18 and 19 not only block but also clamp the rear wheel 14, so that the airplane 13 cannot roll left and right, but also serve as a positioning member. If the airplane 13 needs to be assisted to take off, the airplane 13 drives in from the pick-up table 1 onto the carrier plate 10, at this time, the long-rod blocker 15 has been retracted downwards to below the surface of the carrier plate 10, the short-rod blocker 30 has been raised upwards to block the rear of the front wheel 34 of the airplane 13, then the movable clamping piece 32 protects the left and right sides of the front wheel 34, and the carrier plate 10 is adjusted to be in an inclined upward pitching state, so that the link 4 rapidly rotates from a horizontal state to a vertical state by virtue of the atmospheric pressure stored by the vacuum already generated in the hydraulic piece 6, and the airplane 13 is driven to take off.

As shown in fig. 4, a hydraulic part 202 is arranged right below the receiving and sending table 201, the lower side of the receiving and sending table 201 is connected with the lower end corner of the inclined plane frame 203, and a liquid storage tank 211 is arranged in the inclined plane frame 203; one end of a piston rod 217 in the hydraulic part 202 is connected with one end of a carrier plate 208 at an inclined plane 207 of the inclined plane frame 203 through a rope 204 and

pulleys

205 and 206, the carrier plate 208 is connected with a sliding plate 209 and the hydraulic part 210 end to form a triangular combined body, and the sliding plate 209 and the inclined plane 207 are in a magnetic suspension state. In this embodiment, the carrier plate 208, the slide plate 209 and the hydraulic part 210 are a carrier plate assembly; the hydraulic part 202 is a pulling part; the carrier plate assembly is connected to the pulling means, i.e. the hydraulic means 202, via a cable 204 via a ramp 203 and

pulleys

205, 206.

After the airplane 212 is driven from the pick-up table 201 onto the carrier plate 208, the short bar blocking member 213 is extended upward to block the rear of the front wheel 214 and the clamping members at both ends of the short bar blocking member 213 block both sides of the front wheel 214, and then the electric pump 215 is activated to pump the oil in the hydraulic part 202 to the reservoir 211 through the conduit 216, so as to form a vacuum in the hydraulic part 202.

As shown in fig. 5, hydraulic 210 is retracted, tilting carrier plate 208. After the engine of the airplane 212 is started, the airplane 212 is kept in a brake state, and meanwhile, the clamping piece 218 is contracted upwards, the control of the piston rod 217 by the clamping piece 218 is released, so that the piston rod 217 is rapidly contracted due to the atmospheric pressure generated by the vacuum in the hydraulic part 202, the rope 204 is pulled, and the carrier plate 208 and the airplane 212 are pulled to catapultly slide along the inclined plane 207 by the aid of the

pulleys

205 and 206. When the carrier plate 208 slides to the upper corner of the bevel bracket 203 and hits the elastic stopper 219, the aircraft 212 releases the brake, and the aircraft 212 can take off smoothly by means of inertia impulse and the power of its own engine.

As shown in fig. 6,

hydraulic parts

302 and 303 and

elastic parts

304 and 305 are arranged below a basic plane 301, the

elastic parts

304 and 305 are connected with a carrier plate 308 between

telescopic rods

306 and 307 above the basic plane 301, clamps 309 and 310 are respectively arranged at the upper ends of the

telescopic rods

306 and 307, and the top ends of the

telescopic rods

306 and 307 are respectively connected with the top ends of

piston rods

317 and 318 at the upper ends of the

hydraulic parts

302 and 303 through

ropes

311 and 312 via

pulleys

315 and 316 at the top ends of

auxiliary frames

313 and 314.

When the rocket 319 needs to be launched, the

elastic members

304 and 305 are contracted to store energy, the

hydraulic members

302 and 303 are fully extended and positioned, then the

hydraulic members

302 and 303 are vacuumized, the rocket 319 is erected on the carrier plate 308, the

clamps

309 and 310 are moved to clamp the body of the rocket 319, and then the control of the control members on the

hydraulic members

302 and 303 and the

elastic members

304 and 305 is released, so that the

telescopic rods

306 and 307 in the

elastic members

304 and 305 can be rapidly ejected upwards, the

piston rods

317 and 318 at the upper sections of the

hydraulic members

302 and 303 are immediately contracted downwards, and the

traction ropes

311 and 312 draw the

telescopic rods

306 and 307 to extend upwards. In this embodiment, the

hydraulic members

302, 303 and their

piston rods

317, 318 are a set of hold-downs that are illustrated by the

cords

311, 312 as tension; the

elastic members

304, 305 and the

telescopic rods

306, 307 thereof are a set of drags which exhibit elastic force through the

telescopic rods

306, 307. When the

telescopic rods

306 and 307 extend upwards to drive the carrier plate 308 to launch the rocket 319, the power of the rocket 319 is started, the

clamps

309 and 310 are moved away towards the two sides, and after the

telescopic rods

306 and 307 complete the launching of the rocket 319, the rocket 319 can be continuously lifted off by means of the power of the rocket 319.

As shown in fig. 7 and 8, the upper sections of the

hydraulic parts

401 and 402 are connected with a load net 403, and the load net 403 has a suitable elastic force; the top ends of the

hydraulic parts

401 and 402 are provided with

clamps

404 and 405 capable of moving, one ends of the

clamps

404 and 405 corresponding to each other are respectively provided with a buffer, the buffers are

air cushions

406 and 407, and the

air cushions

406 and 407 are wrapped by air and are made of high-temperature-resistant and elastic materials.

When the rocket 408 is vertically dropped onto the carrier net 403 after the power is turned off, on one hand, the

clamps

404 and 405 can be immediately closed towards the dropping point of the rocket 408 due to the guidance and control of the sensor or the detector until the rocket 408 is clamped; on the other hand, rocket 408 will push carrier net 403 to sink, driving

hydraulic parts

401 and 402 to contract, thereby consuming the inertia kinetic energy and potential energy of rocket 408 until being exhausted, and stably staying on the plane of base plane 409. The magnitude of the braking force generated by the contraction of the

hydraulic parts

401 and 402 can be controlled by adjusting the sizes of the oil flow inlet and outlet passage apertures of the

hydraulic parts

401 and 402.

As shown in fig. 9, a lifting platform 502 is disposed on the left side of the bending frame 501, a pressure member 503 is disposed below the bending frame 501, an arc surface 504 is disposed at the upper end of the bending frame 501, an arc plate 506 is disposed below the carrier plate 505, and a telescopic member 507 is disposed between the carrier plate 505 and the arc plate 506. After the airplane 508 enters the top of the lifting platform 502 from the pick-up table 509, with reference to fig. 10 and 11, the lifting platform 502 is lifted, the airplane 508 enters the carrier 505, the stoppers 510 are lifted from the carrier 505 to block the rear and both sides of the front wheel 511 of the airplane 508, the front wheel 511 is clamped, the pressure member 503 is vacuumized, the airplane 508 is started, the control of the latch 512 on the pressure member 503 is released, the pressure member 503 is rapidly contracted, the steel cable 513 is pulled, the arc-shaped plate 506 is pulled to rapidly slide along the arc-shaped surface 504 under the guidance of the

pulleys

514 and 515, the airplane 508 on the carrier 505 obtains the initial speed and the acceleration, the telescopic member 507 is contracted to enable the carrier 505 and the airplane 508 to tilt upwards, and at the moment before the arc-shaped plate 506 reaches the end point of the arc-shaped surface 504, the control of the stoppers 510 on the front wheel 511 is released, and the airplane 508 which has obtained enough takeoff power can be lifted upwards. After the aircraft 508 takes off, the pressure members 503 may be re-extended by inflation or inflation, and the arcuate plates 506 may be returned to the sides of the lift platform 502 by magnetic levitation and magnetomotive or elastic forces.

As shown in fig. 12, two sets of rotary take-off and landing devices are arranged on a deck 602 of a vessel 601, wherein the take-off and landing device with a short head arranged on a bow is a take-off device of an aircraft. The auxiliary frame 603 can extend and retract, one end of a link 604 is movably connected with the upper end of the auxiliary frame 603, the other end of the link 604 is connected with a carrier plate 605, a state constancy device and a blocking piece 609 are arranged on the carrier plate 605, the state constancy device comprises a circuit board 606, a gyroscope 607 and a motor 608, as shown in the figure, when the link 604 is rotated to a downward vertical state, an aircraft can be conveyed onto the carrier plate 605 through the displacement and the lifting of a receiving and conveying table 610, and then the blocking piece 609 is pressed against the rear side of the aircraft wheel and clamps the wheel, so that the aircraft is positioned on the surface of the carrier plate 605. Then, the wheel disc 611 is started to rotate at a high speed, after the wheel disc 611 reaches a preset rotating speed, the wheel disc 611 rapidly drives the connecting rod 604 to rotate through the help of the clutch, if the light aircraft is carried on the carrier plate 605, the connecting rod 604 only needs to rotate for half a turn, and the blocking piece 609 can release the clamping control of the aircraft wheel, so that the aircraft can be lifted off along with the self power and the throwing force of the connecting rod 604 to the aircraft. If a heavy aircraft is carried on the carrier plate 605, the link 604 can be rotated two or three times until the centrifugal force reaches a set value, and the blocker 609 can not release the clamping control of the aircraft wheels, so that the aircraft can be lifted off. The circuit board 606, the gyroscope 607 and the motor 608 in the state constancy device can keep the carrier board 605 in a horizontal state or a tilting-up state at all times during the rotation process. An aircraft that has just taken off may be given a route to fly in a left turn.

The high take-off and landing device arranged on the stern is a landing device of an aircraft. The auxiliary frame 612 can be extended or shortened, one end of a link 613 is movably connected with the upper end of the auxiliary frame 612 and can only rotate clockwise in a single direction, the other end of the link 613 is connected with a carrier plate 614, and a signal emitter 615 is arranged at the tail of the carrier plate 614. When the aircraft needs to land, the aircraft can land far away from several kilometers, the flying height and the flying angle are adjusted and confirmed in advance according to the laser guidance and the radar wave guidance of the signal emitter 615, the aircraft flies to the carrier plate in a horizontal mode, the tail hook is firstly used for hooking the tail end of the carrier plate 614, the positioning piece 616 immediately clamps front and rear wheels of the aircraft while the aircraft drives the carrier plate 614 and the link 613 to rotate clockwise through the tail hook, the state constancy device can enable the carrier plate 614 to be kept in a horizontal state constantly in the rotating process of the link 613, and when the link 613 rotates to a downward vertical state and is stable, on one hand, the link 613 consumes or stores the inertia impulsive force of the aircraft through the hydraulic transmission piece 617 in the rotating process, and on the other hand, the receiving and conveying platform 610 can timely move towards the stern direction and is close to the carrier plate 614 to transfer the aircraft away.

If the tail hook of the aircraft is not hooked to the tail end of the carrier plate 614, the aircraft can continuously fly forward straightly, then turn right, and then repeatedly perform landing operation. That is, the flying height and angle of the aircraft during landing are guided by the signal emitter 615, during which the aircraft can be corrected in time if deviation occurs, the aircraft approaches the carrier plate 614, and if the wind wave is large and the jolt and sway are serious, height or angle error still occurs, the auxiliary frame 612 can help to correct through rapid contraction and displacement, so that the fuselage of the aircraft cannot collide with the carrier plate 614.

The rotary type take-off and landing device is arranged at the head and the tail of the ship, even if the length of the connecting rod 613 exceeds 50 meters and each aircraft with dozens of tons carries out alternate take-off and landing, the displacement of the aircraft carrier generally exceeds ten thousand tons or even tens of thousands tons, the stability is excellent, and the aircraft only pulls the ship longitudinally when taking off and landing, so the navigation safety of the ship cannot be influenced theoretically.

The

carrier plates

605, 614 can also be used as sails by erecting the

carrier plates

605, 614 by means of a state constancy apparatus and extending the width and length of the additional parts thereof sufficiently, as soon as necessary.

As shown in fig. 13, an auxiliary frame 703 is disposed on a deck 702 of a vessel 701, a rotating shaft 704 is disposed at an upper end of the auxiliary frame 703, an annular rotating member 705 is disposed on the rotating shaft 704, and

carrier plates

706 and 707 are disposed above and below the rotating member 705 through

rotating shafts

709 and 710, respectively. When the aircraft lands on the carrier plate 706 to drive the rotating member 705 to rotate, the carrier plate 706 is stopped and stabilized when moving to the receiving and delivering table 708 by the braking of the drag member arranged inside the auxiliary frame 703, and at this time, the carrier plate 707 is rotated into the air for continuing to receive the aircraft landing.

As shown in fig. 14, a deck 801 of a vessel is provided with a retractable auxiliary frame 802, an upper section of the auxiliary frame 802 is fixedly connected with an annular rotating member 803, therefore, the rotating member 803 cannot rotate, but an arc-shaped rail 804 is arranged on a side surface of the ring of the auxiliary frame 802, when an aircraft falls on a carrier plate 805 to drive a rotating shaft 806 to slide along the rail 804 from top to bottom, a drag member arranged in the rotating member 803 can control the sliding speed of the rotating shaft 806 until the aircraft stops stably.

As shown in fig. 15, a vertical ring-shaped rotating member 901 can rotate clockwise around a shaft 904, a rotating handle 902 is arranged on the ring of the rotating member 901, a carrier plate 903 is arranged on the rotating handle 902, and a control member is arranged below the carrier plate 903, so that the carrier plate 903 can rotate around the rotating handle 902 and can also be stably stopped thereon as required. When the rotating member 901 is rotated to stop the carrier plate 903 at a low position, the aircraft 905 can be placed on the carrier plate 903, and then the stopper 906 is extended to block the front end of the aircraft, and the aircraft 905 is firmly attached to the carrier plate 903 through electromagnetism. As shown in fig. 16 and 17, when the rotating element 901 rotates clockwise, the carrier plate 903 may rotate around the rotating handle 902 according to the rotation angle of the rotating element 901 or the orientation of the carrier plate 903, so that the airplane 905 is located on the outer end surface of the rotating element 901, so as to quickly retract the stopper 906 after reaching a proper orientation, and release the control of the electromagnetic force on the airplane 905, so as to smoothly lift the airplane 905 off.

As shown in fig. 18, a wheel disc 1001 is arranged on a flat ground, a rotating shaft 1002 is arranged at the center of the wheel disc 1001, a clutch is arranged between the rotating shaft 1002 and the wheel disc 1001, the rotating shaft 1002 is connected with a link 1003, one end of the link 1003 is connected with a carrier plate 1004, a wheel is arranged at the bottom of the carrier plate 1004, and when the rotating shaft 1002 rotates, the link 1003 can drive the carrier plate 1004 to rotate in the ring 1005. One end of the carrier plate 1004 is provided with an auxiliary landing platform 1006, and the auxiliary landing platform 1006 can serve as a receiving platform; the other end of the auxiliary flying frame 1007 is provided with an auxiliary flying frame 1007, a movable table 1011 is arranged in the auxiliary flying frame 1007, the rear end of the auxiliary flying frame 1007 is provided with an auxiliary flying sloping plate 1012, the auxiliary flying sloping plate 1012 is an upward inclined plane according to the requirement of a takeoff elevation angle, and the movable table 1011 passes through the auxiliary flying frame 1007 and the lower part of the auxiliary flying sloping plate 1012, so that the movable table can stretch out and draw back.

When the airplane needs to be accepted for landing, two preparations can be made: first, the auxiliary platform 1006 is lifted to be flush with the upper end surface of the carrier 1004, and the movable platform 1011 is retracted to be flush with the front end of the auxiliary frame 1007. Second, the dial 1001 and the shaft 1002 are engaged with each other via a clutch. The aircraft 1008 lands on the auxiliary landing runway 1009 and slides through the auxiliary landing platform 1006 into the carrier plate 1004 and is positioned at the moment the rear wheels are blocked by the blocking element 1010, quickly lowering the auxiliary landing platform 1006 to be level with the ground. At this time, the inertial impulse of the airplane 1008 drives the carrier plate 1004 to rotate along the ring 1005, and meanwhile, the pulling member disposed on the wheel 1001 stores the inertial impulse until the carrier plate 1004 stops stably.

When the airplane needs to be assisted to take off, two preparations are also made firstly: as also shown in fig. 18, first, the clutch is set to neutral, and then the disc 1001 is started to rotate at high speed. Second, after the aircraft is allowed to enter the carrier plate 1004 and is gripped by the discourager 1010, the auxiliary landing stage 1006 is lowered. Thirdly, the clutch is adjusted to make the wheel disc 1001 rotating at high speed drive the rotating shaft 1002, the link 1003 and the carrier plate 1004 to rotate, and the rotation can be one circle or two or three circles. Fourthly, after the airplane on the carrier plate 1004 has stored enough centrifugal force or take-off power, the clutch is adjusted to be neutral, the movable table 1011 is enabled to move forward rapidly at a proper time, and the control of the airplane by the barrier 1010 is released at the moment before the carrier plate 1004 collides with the movable table 1011, so that the airplane can be lifted off along the guiding trend of the movable table 1011 and the flight assisting sloping plate 1012 by means of and by combining various take-off forces after the carrier plate 1004 collides with the movable table 1011.

As shown in fig. 19, an auxiliary frame 1102 is provided on a base plane 1101, a spiral track 1103 is provided on an upper section of the auxiliary frame 1102, and one end of a link 1104 is movably inserted into the auxiliary frame 1102 and can slide along the track 1103. When the tail hook of the wheel-less airplane hooks the rear end edge of the carrier plate 1105 and is attracted by the electromagnetic force of the carrier plate 1105, the inertial impulse of the airplane drives the carrier plate 1105 and the link 1104 to slide along the spiral surface 1106, the movement of the carrier plate 1105 drives the stopper 1107 to move along the track 1108, and the stopper 1107 controls the movement speed of the carrier plate 1105 through the spring device disposed in the spiral surface 1106. At the same time, the auxiliary frame 1102 is retracted downward, bringing the underside of the helicoid 1106 into close proximity with the base plane 1101, facilitating the transfer of the parked aircraft to the ground.

Claims

1. A method and its apparatus that can let the aircraft take off and land in the short distance, take off and land the runway of the aircraft with taking off and land the apparatus to replace completely or partly, take off and land the apparatus can be regarded as the take-off or landing device or launcher or recoverer of the aircraft; the method is characterized in that:

arranging the lifting device or the main body part of the lifting device above or beside a basic plane, wherein the basic plane comprises the ground or the water surface or the deck surface or the platform surface or the building plane;

the lifting mode of the device is rotary, the rotary lifting device is formed by combining at least four parts, namely a link rod or a rotating piece, a carrier plate, a rotating shaft or an auxiliary frame and a restraining piece, and the link rod, the rotating piece, the rotating shaft and the auxiliary frame can be used as different parts and exist in the same lifting device at the same time; one end of the link rod is connected with the carrier plate, the other end of the link rod is connected with a rotating shaft, and the rotating shaft is directly or indirectly connected with the basic plane; the rotating piece and the rotating shaft are coaxial or different in axial lead, the rotating piece can rotate around the axial lead of the rotating shaft, and the rotating shaft is connected with the basic plane through an auxiliary frame; the support plate is arranged on the link rod or the rotating piece; the carrier plate can move along the surface or the side surface of the cylindrical or wheel disc-shaped rotating piece, and the carrier plate is connected with the rotating piece or is connected with the rotating piece through a restraining piece; the carrier plate can drive the link rod or the link rod can drive the carrier plate to rotate on the surface or the side surface of the rotating part;

or the rotating piece does not rotate, and the carrier plate can move along the circular surface of the cylindrical or wheel disc-shaped rotating piece or along a preset arc track on the cylindrical or wheel disc-shaped rotating piece;

the rotating piece is in a ring shape, the ring can rotate around the rotating shaft, and the carrier plate can rotate around the ring of the ring;

the connecting rod is connected with the auxiliary frame; the connecting rod or the support plate is connected with the auxiliary frame or the basic plane directly through a pulling piece; the connecting rod or the support plate is connected with the restraining part through the auxiliary frame through a rope or a chain; the pulling piece is arranged on the connecting rod or the support plate directly; a clutch device is arranged between the link rod or the rotating piece and the restraining piece; the link rod or the support plate can extend and retract; the auxiliary frame can be either telescopic or rotary or foldable or movable;

carrying the aircraft by using a carrier plate; the traction piece is used for increasing power for takeoff of the aircraft or controlling the speed for landing of the aircraft; the main body of the traction piece comprises an elastic device, an electromagnetic device, an air pressure device, a hydraulic device, a power driving device, a counterweight device, a wheel disc device, a steam type ejection device, an electromagnetic damper, a gear set, a pulley block, a winch or a linear tension type mechanism, and the power driving of the power driving device comprises electric power driving, fuel oil driving and fuel driving;

the traction part is a power accumulator which can store the inertial impulsive force generated by the landing of the aircraft, and the power storage mode of the power accumulator comprises the steps of storing the power by adopting a spring, the air pressure or the hydraulic pressure or storing the kinetic energy or the potential energy after converting the kinetic energy or the potential energy into the electric energy; the pulling piece can assist the aircraft to take off by the stored capacity;

the rotary type lifting device at least comprises a rotating mode of three-dimensional rotation, horizontal rotation, inclined rotation or spiral rotation;

the rotary type take-off and landing device can enable the carrier plate to bear the aircraft in the air for landing, and then the aircraft is directly conveyed to the basic plane through the gradual downward rotation or movement of the carrier plate; or the aircraft can be landed on the basic plane only through shortening or descending of the auxiliary frame;

the horizontal rotating take-off and landing device is internally or additionally provided with an auxiliary flying frame, a movable platform is arranged in the middle of the upper end surface of the auxiliary flying frame, a flying assisting inclined plane is arranged at the rear end or the upper end of the auxiliary flying frame, the movable platform penetrates through the middle of the auxiliary flying frame and the lower part of the flying assisting inclined plane, and the movable platform can stretch or move under the help of a restraining piece; the aircraft on the carrier plate can be quickly transferred onto the movable table through butt joint or collision of the movable table and the carrier plate, and the aircraft takes off along the flight assisting inclined plane through contraction or movement of the movable table;

the carrier plate can slide along the spiral surface of the spirally rotating lifting device;

2. The method and apparatus as claimed in claim 1, wherein:

one end of a link rod or a rotating member is arranged on the stern or the side of the ship, and the landing aircraft can be directly sent to a top deck or a lower deck of the ship from the air through the bearing of a carrier plate and the rotation of the link rod or the rotating member;

the carrier plate can alternatively be adjusted to be a sail of a vessel.

3. The method and apparatus as claimed in claim 1, wherein:

the take-off and landing device is provided with auxiliary accessories, and the auxiliary accessories comprise: an angle control device or a state constancy device is arranged between the connecting rod and the carrier plate; arranging a barrier or a protective cover on the carrier plate, wherein the barrier can be used as a positioning piece; the protective cover is in a three-dimensional triangle shape, an arc shape or a diamond shape; an ejection device is arranged between the protective cover and the aircraft or between the protective cover and the carrier plate; elastic means are provided at the junction of the link and said base plane.

4. The method and apparatus as claimed in claim 1, wherein:

the flight assisting process of the rotary type take-off and landing device comprises the following steps: firstly, rotating the connecting position of the link rod or the rotating piece and the carrier plate to a low position to ensure that the carrier plate is butted with the receiving and conveying table; secondly, enabling the aircraft to drive into the carrier plate from the receiving and delivering platform; thirdly, the starting barrier piece is propped against the rear end of the belly of the aircraft and protects the two sides of the belly or is propped against the rear part of the front wheels or the rear wheels of the aircraft and protects the left side and the right side of the front wheels or the rear wheels; fourthly, or the carrier plate needs to be rotated to be in an inclined upward bending state; meanwhile, or the pneumatic device or the hydraulic device on the containment part needs to be vacuumized; fifthly, the link rod or the rotating part is rapidly pulled to enable the carrier plate to be lifted from the low position to the high position or to rotate around in a horizontal mode by means of the elasticity of the elastic device in the pulling part or by means of the atmospheric pressure generated by the vacuum or by means of steam type ejecting force or electromagnetic type ejecting force or by means of power driving; sixthly, the arresting member on the carrier plate selects the airplane to quickly release the control on the belly of the aircraft or the front wheel or the rear wheel, and the aircraft is assisted to take off by the centrifugal force generated by rotation or the acting force of the traction member on the carrier plate;

the landing assisting process of the rotary lifting device comprises the following steps: firstly, or a carrier plate on a link rod or a rotating part needs to be lifted to a high position; secondly, a barrier on the carrier plate blocks a wheel or a wheel carrier of the aircraft in flight or after landing, or a tail hook of the aircraft hooks the barrier, so that the aircraft can drive a connecting rod or a rotating piece to rotate through the carrier plate; thirdly, the towing part is used for consuming the inertia kinetic energy of the aircraft, or the towing part is used for storing the inertia kinetic energy of the aircraft;

5. The method and apparatus as claimed in claim 1, wherein:

the take-off and landing device is used for assisting the take-off and landing of the aircraft in an inclined mode or a bent mode or a vertical mode;

the inclined lifting device is formed by combining at least three parts, namely a carrier plate, an inclined plane frame or an inclined plane plate and a traction piece, wherein the inclined plane frame is in a three-dimensional type, the upper end surface of the inclined plane frame is a section of inclined plane or a zigzag inclined plane, and a guide piece is arranged at or near the top end of the inclined plane frame; the carrier plate can be directly connected with the restraining part or connected with the restraining part through a guide part by a rope or a chain;

the flight assisting process of the inclined type take-off and landing device comprises the following steps: firstly, the carrier plate is stopped at the lower end of the inclined plane of the three-dimensional inclined plane frame or in front of the lower end of the inclined plane; secondly, enabling the aircraft to drive into the carrier plate from the receiving and delivering platform; thirdly, the starting barrier piece is propped against the rear end of the belly of the aircraft and protects the two sides of the belly or is propped against the rear part of the front wheels or the rear wheels of the aircraft and protects the left side and the right side of the front wheels or the rear wheels; fourthly, the support plate is rotated to be in an inclined upward bending state; meanwhile, or the pneumatic device or the hydraulic device in the pulling piece needs to be vacuumized; fifthly, the carrier plate and the aircraft are quickly pulled to move from a low position to a high position along the inclined plane of the inclined plane frame by means of the elastic force of an elastic device in the holdback, the atmospheric pressure generated by the vacuum, the steam type ejection force, the electromagnetic type ejection force or power drive;

the landing assisting process of the inclined type lifting device comprises the following steps: firstly, the carrier plate is stopped at the upper end of the inclined plane of the three-dimensional inclined plane frame; secondly, a barrier on the carrier plate blocks a wheel or a wheel carrier of the aircraft, or a tail hook of the aircraft hooks the barrier; thirdly, the aircraft can slide downwards from the upper end of the bevel rack through the carrier plate, and in the process, the carrier plate directly pulls the pulling piece to obtain braking force, or pulls the pulling piece through the rope to obtain braking force, or obtains braking force through the assistance of the motorized device or the electromagnetic damper; or the inertia kinetic energy of the aircraft is stored by utilizing the traction piece;

the bending type lifting device is formed by combining at least three parts, namely a support plate, a bending frame or a bending plate and a traction piece, wherein the bending frame is in a three-dimensional type, the upper end surface of the bending frame can be a section of arc surface or wave shape, and the support plate can be directly connected with the traction piece or connected with the traction piece through a guide piece through a rope or a chain;

the flight assisting process of the bending type take-off and landing device comprises the following steps: firstly, lifting the aircraft to one end of the section of cambered surface by using a lifting platform; secondly, enabling the aircraft to enter the carrier plate from the lifting platform and be positioned on the carrier plate; thirdly, the carrier plate slides along the descending inclined plane of the cambered surface, and the aircraft on the carrier plate obtains initial speed or acceleration through gravity or acting force of the traction piece; fourthly, when the carrier plate reaches the lowest part of the section of the cambered surface, the carrier plate or the aircraft is quickly adjusted to be in an inclined upward pitching state; fifthly, the aircraft takes off along the ascending slope of the cambered surface by means of inertia kinetic energy of the carrier plate, traction force of the traction piece or power of the aircraft;

the landing assisting process of the bending type lifting device comprises the following steps: firstly, a blocking piece on the carrier plate blocks a wheel or a wheel carrier of the aircraft, or a tail hook of the aircraft hooks the blocking piece, so that the aircraft drives the carrier plate to slide along a descending inclined plane of the cambered surface, and then the carrier plate continues to slide along an ascending inclined plane until the carrier plate is stopped stably; the carrier plate is braked or accumulated by the restraining piece in the sliding process; secondly, transferring the aircraft which is stably stopped from the carrier plate to a lifting platform, and then transferring the aircraft to the ground through the lifting platform; the lifting platform can be used as a power accumulator to store the gravity of the aircraft during descending;

the inclined plane plate or the bent plate can be folded; the inclined plane plate or the bent plate is provided with a track;

the vertical lifting device can be vertically telescopic, the lower section of the lifting device is arranged below the basic plane, a support plate or a carrying net or a clamp or a buffer is arranged above the middle section of the lifting device, the carrying net comprises a net-shaped object or a cloth-shaped object, and the carrying net is elastic;

the vertical lifting device is formed by combining at least four parts, namely a telescopic part, a carrier plate or a carrier net, an auxiliary frame and a restraining part; the telescopic piece and the auxiliary frame can be combined into a whole;

a method comprises the following steps: when the top end or the upper section of the lifting device is provided with a clamp or a buffer, a carrying plate is arranged below the clamp or the buffer, and the landing assisting step of the vertical lifting device comprises the following steps: firstly, enabling an aircraft to vertically land above the carrier plate; secondly, enabling the tail part of the aircraft to be close to the carrier plate, and enabling the tail part to be close to the carrier plate by a set distance through reverse-thrust flame sprayed by the aircraft; thirdly, the aircraft, the carrier plate and the telescopic piece descend at the same speed at the same time, and the descending speed can be controlled by controlling the contraction speed of the telescopic piece or controlling the reverse thrust of the aircraft; in the descending process, the tail part of the aircraft can be gradually close to the carrier plate, and meanwhile, the clamp or the buffer object arranged at the top end or the upper section of the lifting device can rapidly move towards the position of the aircraft; fourthly, the aircraft is stopped on the carrier plate, and the body of the aircraft is clamped, wrapped or enclosed by the clamp or the buffer; fifthly, closing the reverse thrust power of the aircraft, and transferring or consuming the inertial kinetic energy of the aircraft landing by controlling the traction force of the traction piece or controlling the contraction speed of the telescopic piece;

a method comprises the following steps: when the top end or the upper section of the lifting device is provided with a net or a clamp or a buffer, the landing assisting step of the vertical lifting device comprises the following steps: firstly, enabling an aircraft to vertically land in the carrier net by closing reverse thrust power in advance, and enabling the carrier net to descend along with the aircraft; secondly, the carrier net drives the telescopic piece to contract, and inertial kinetic energy of the aircraft landing is transferred or consumed by controlling the contraction speed of the telescopic piece or controlling the traction force of the telescopic piece; thirdly, the clamp or the buffer object arranged on the lifting device moves towards the aircraft rapidly until the body of the aircraft is clamped or wrapped or surrounded;

6. The method and apparatus as claimed in claim 1, 2, 3, 4 or 5, wherein:

the rotary type lifting device or the inclined type lifting device or the bending type lifting device or the vertical type lifting device are combined together for use;

in the rotary type lifting device, at least one link rod is arranged; or two or more than two connecting rods are combined in the same lifting device for use;

in each lifting device, the holdback is at least one piece; or two or more traction pieces are combined in the same lifting device for use;

a magnetic suspension device or a power driving device or a steam type ejection device or an electromagnetic type ejection device or a braking device or a gliding device or a damping device or a pressure transmission device or a power driving device or a fire extinguishing and explosion preventing device or a medical rescue device is arranged on the carrier plate or the inclined plane frame or the bending frame or the movable table or the flight assisting inclined plane;

7. A method and apparatus as claimed in claim 1 or 3, wherein:

the main body of the angle control device is a pressure piece, and the shape of the pressure piece comprises a straight shape, a square shape, an annular shape, a semi-annular shape or an arc shape;

the angle control device determines or controls the input amount of liquid or gas in the pressure piece B arranged between the carrier plate and the link rod according to the change of the rotation angle of the link rod, or the height change of one end of the link rod, or the telescopic distance of a piston rod in the pressure piece A arranged on the auxiliary frame or the basic plane, thereby regulating the telescopic distance of the piston rod of the pressure piece B and enabling the carrier plate to be in a horizontal state or an inclined upward-facing state all the time;

8. The method and device as claimed in claim 1, 2, 3 or 4, wherein:

the state constancy device is formed by at least three major components of a controller in the form of a circuit board, an attitude keeping instrument in the form of a gyroscope and an actuator in the form of a motor.

9. The method and apparatus as claimed in claim 1, 2, 3, 4 or 5, wherein:

and an air flight assisting and landing assisting runway or a flight assisting and landing assisting guide device or a sensor or a detector is arranged beside the connecting rod or the wheel disc or at the upper end or the side of the inclined plane frame or the upper end or the side of the bent frame or the upper end or the side of the auxiliary frame.

10. The method and apparatus as claimed in claim 9, wherein:

one end or two ends of the air flying-assisting landing-assisting runway can be lifted, and the lifting mode is as follows: a telescopic supporting column or a supporting piece is arranged below the runway;

the guiding device comprises a signal transmitting device or a signal receiving device or a device for setting a virtual runway by using light or waves;

the guide means are either arranged on the carrier plate or on the barrier.