CN111731472B

CN111731472B - Retractable landing gear of light aircraft

Info

Publication number: CN111731472B
Application number: CN202010437582.5A
Authority: CN
Inventors: 欧阳星; 霍甜; 曾晓康; 陈博; 龚倩玉
Original assignee: Zhuoer Aircraft Manufacturing Wuhan Co ltd
Current assignee: Zhuoer Aircraft Manufacturing Wuhan Co ltd
Priority date: 2020-05-21
Filing date: 2020-05-21
Publication date: 2022-02-08
Anticipated expiration: 2040-05-21
Also published as: CN111731472A

Abstract

The invention provides a retractable landing gear of a light airplane, which comprises an electric telescopic rod for retracting the landing gear, a longitudinal shock absorber for mainly absorbing vertical shock and a yielding type self-adaptive wheel mechanism for adaptively adjusting ground impact force and rapidly decelerating, and relates to the field of landing gears. This light-duty aircraft retractable undercarriage is according to the problem to current light-duty aircraft undercarriage existence, the design out can shift and can greatly weaken the special construction of impact force, these structures need not too much electrical equipment's installation, simple structure is light, convenient to use, thereby the effectual general light-duty aircraft undercarriage of having solved includes that the wheel design is comparatively light, be difficult to install too much auxiliary device on the undercarriage, when bearing powerful thrust and resistance interact, the undercarriage takes place to bend easily and damages, the wheel receives the ground environment influence with ground friction easily, the problem of the safety of aircraft has been influenced to a certain extent.

Description

Retractable landing gear of light aircraft

Technical Field

The invention relates to the technical field of undercarriage, in particular to a retractable undercarriage of a light airplane.

Background

The undercarriage is an accessory device which is used for supporting the aircraft and moving on the ground when the aircraft is in landing and landing taxiing, the undercarriage is the only part for supporting the whole aircraft, therefore, the undercarriage is an integral part of the aircraft, after the aircraft takes off, the undercarriage can be retracted according to the performance of the aircraft, the undercarriage is retracted so as to reduce the air resistance and reduce the energy consumption, and simultaneously, the undercarriage is protected, in order to meet the requirements of the aircraft on the landing, landing and taxiing, the lowest end of the undercarriage is provided with a wheel with an inflatable tire, in order to shorten the landing and taxiing distance, the wheel is provided with a brake or an automatic brake device, and the undercarriage also comprises a retraction mechanism, a front wheel shimmy damper, a turning control mechanism and the like, however, when the aircraft lands and contacts the ground, the wheel is instantaneously converted from a stall state or a slow rotation state to a fast rotation state, and the resistance borne by the wheel in the process is extremely large, the resistance plays a great impact role on a support for supporting the airplane wheel, particularly a foldable support, particularly under the special conditions of water accumulation in rainy days and the like, the airplane wheel impacts a water accumulation area, the collision between instant extrusion force borne by the airplane wheel and the resistance easily causes the bending and even damage of the support frame, so that the safe landing and landing of the airplane are influenced, the instant resistance is easily increased and the damage effect is enhanced if the surface friction of the airplane wheel is large, but the slipping phenomenon is easily caused in special weather, particularly on frozen ground if the surface friction of the airplane wheel is small, which is quite contradictory, and the friction resistance of the airplane wheel is increased, the surface of a tire is easily worn and smoothly under the action of frequent instant impact resistance, although shock absorption devices such as shock absorbers and the like are installed on the airplane wheel at present, on the premise that the support strength cannot be reduced, its absorbing range in the direction of going ahead receives the restriction, if the aircraft is fast, ground resistance is big, still there is very big potential safety hazard, general light aircraft undercarriage includes that the wheel design is comparatively light, be difficult to at the undercarriage installation too much auxiliary device, when bearing powerful thrust and resistance interact, the undercarriage takes place to bend easily and damages, the wheel receives the ground environment influence easily with ground friction, the safety of aircraft has been influenced to a certain extent and has risen, so need a light aircraft retractable undercarriage.

Disclosure of Invention

Technical problem to be solved

Aiming at the defects of the prior art, the invention provides a retractable landing gear of a light airplane, which solves the problems that the landing gear of the general light airplane is light in design and is difficult to install too many auxiliary devices on the landing gear, when the landing gear bears the interaction of strong thrust and resistance, the landing gear is easy to bend and damage, the friction between the wheels and the ground is easy to be influenced by the ground environment, and the safe landing of the airplane is influenced to a certain extent.

(II) technical scheme

In order to achieve the purpose, the invention is realized by the following technical scheme: the utility model provides a light aircraft retractable undercarriage, includes the electric telescopic handle that is used for retracting the undercarriage, plays main cushioning effect's vertical bumper shock absorber, reply ground impact force self-adaptation to vibrations from top to bottom, makes the adjustment and play the yield formula self-adaptation mechanism of quick deceleration effect and the vibrations that are used for confronting the vibrations that the direction of advance resistance produced to the switching mechanism, electric telescopic handle installs the bottom at light aircraft with articulated mode, vertical bumper shock absorber setting is articulated in light aircraft's bottom and with light aircraft's bottom, electric telescopic handle's one end articulates on vertical bumper shock absorber, yield formula self-adaptation mechanism sets up the bottom at vertical bumper shock absorber, vibrations are to the switching mechanism setting on yield formula self-adaptation mechanism.

Preferably, the structure of vertical bumper shock absorber includes top articulated dish, bottom connecting seat, three spacing telescopic link and vertical damping spring, and is three the one end of spacing telescopic link is connected with the fixed surface of the articulated dish in top, and is three the one end that the articulated dish in top was kept away from to spacing telescopic link is connected with the fixed surface of bottom connecting seat, vertical damping spring has been cup jointed on the surface of spacing telescopic link, the surface of the articulated dish in top is articulated with the bottom of light aircraft, the one end that light aircraft bottom was kept away from to electric telescopic handle is articulated with the side of bottom connecting seat.

Preferably, the yielding type self-adaptive wheel mechanism comprises two bending angle supporting plates, a connecting supporting block and two self-adaptive negative suction wheels, the lower surface of the bottom connecting seat is fixedly connected with the connecting supporting block, a bearing is arranged on the connecting supporting block, an articulated shaft is fixedly connected with an inner ring of the bearing on the connecting supporting block and penetrates through the connecting supporting block, two ends of the articulated shaft are respectively fixedly connected with the surfaces of the two bending angle supporting plates, the surfaces of the bending angle supporting plates are in a bent shape, and the bent parts of the bending angle supporting plates incline towards the advancing direction of the wheel.

Preferably, two be provided with the bearing in the bent angle backup pad, the inner circle fixed connection of the bearing in two bent angle backup pads has the locomotive axle, two wheel hub of both ends fixedly connected with of locomotive axle, a self-adaptation negative suction wheel has all been cup jointed on two wheel hub's surface, two the central line that self-adaptation negative suction wheel used the locomotive axle surface is the symmetric distribution as the symmetrical line, the fixed surface of locomotive axle is connected with a plurality of wind-force and changes flabellum in advance, a plurality of wind-force is changed flabellum in advance and is located between two bent angle backup pads.

Preferably, the self-adaptive negative suction wheel is made of rubber, the surface of the self-adaptive negative suction wheel is in a rough corrugated shape, the inner wall of the self-adaptive negative suction wheel is fixedly connected with a rigid gasket, the surface of the rigid gasket is fixedly connected with an elastic gasket, the material of the elastic gasket comprises spring steel, the surface of the elastic gasket is provided with a plurality of self-adaptive negative suction plates which are circumferentially distributed by taking the center of the self-adaptive negative suction wheel as the circle center, the self-adaptive negative suction plate is made of spring steel, the surface of the self-adaptive negative suction plate is lapped with the inner wall of the self-adaptive negative suction wheel, a negative suction cavity is arranged between the inner wall of the self-adaptive negative suction wheel and the self-adaptive negative suction plate, a plurality of negative suction holes are arranged on the surface of the self-adaptive negative suction wheel, the negative suction hole corresponds to the negative suction cavity, the back of the self-adaptive negative suction plate is fixedly connected with a return spring, and one end of the return spring is fixedly connected with the surface of the rigid washer.

Preferably, vibrations include arc bracing piece, extension straight-bar, first supporting shoe, second supporting shoe, impact sleeve, impact rod, spacing slider, slant buffer board and auxiliary wheel to switching mechanism, arc bracing piece's fixed surface is connected with first supporting shoe, arc bracing piece keeps away from the one end fixedly connected with extension straight-bar of first supporting shoe, the one end fixedly connected with second supporting shoe of extension straight-bar, the fixed surface of first supporting shoe is connected with auxiliary telescopic link, the fixed surface of second supporting shoe is connected with the impact sleeve, the inner wall sliding connection who strikes the sleeve has impact rod, the one end fixedly connected with rubber buffer of impact rod, the surface of impact rod and the surface of auxiliary telescopic link have all cup jointed the spring that shakes that resets, the equal fixedly connected with organism connecting bolt in top of impact rod and auxiliary telescopic link, the surface of the machine body connecting bolt is in threaded connection with the bottom of the light airplane, the surface of the second supporting block is provided with an inclined spraying groove communicated with the impact sleeve, and the bottom of the second supporting block is provided with an auxiliary wheel which is positioned below the inclined spraying groove.

Preferably, a limiting arc-shaped groove is formed in the upper surface of the arc-shaped supporting rod, the surface of the limiting sliding block is connected with the inner wall of the limiting arc-shaped groove in a sliding mode, an oblique buffering plate is inserted into the surface of the bent angle supporting plate in a inserting mode, the arc-shaped groove is formed in the surface of the arc-shaped supporting rod, an oblique buffering spring is fixedly connected to the inner wall of the arc-shaped groove, one end of the oblique buffering spring is in contact with the surface of the oblique buffering plate, and the surface of the oblique buffering plate is connected with the inner wall of the arc-shaped groove in a sliding mode.

(III) advantageous effects

(1) The flexible self-adaptive wheel mechanism is arranged, so that the wheel can be rapidly rotated by means of wind power when the wheel is not in contact with the ground and bounces, static friction force generated instantaneously is weakened by rolling friction when the wheel is in contact with the ground, impact force generated instantaneously to a supporting structure by the wheel can be weakened, the wheel can be prevented from being greatly damaged by the ground, the wheel with high friction force can be arranged on the basis, the requirement of rapid stop of the airplane in the smoothing process is met, the wheel with high friction force is designed, meanwhile, the wheel continuously generates ground-gripping adsorption capacity along the circumferential rotation direction when in contact with the ground by virtue of a special structure, the airplane can be rapidly stopped in the smoothing process, and the airplane is prevented from slipping on the smooth ground, particularly on the frozen ground, the safety is greatly improved.

(2) According to the invention, by arranging the vibration direction switching mechanism, on one hand, when the airplane wheel generates yielding rotation in the advancing direction, the elastic structure can generate a buffering effect on the wheel and the supporting structure, and meanwhile, when the elastic structure is pressed down, the auxiliary wheel can transfer more oblique impact force to vertically and upwards act on the airplane to play a role in supporting the airplane, so that the oblique impact force is greatly weakened, and the bending angle supporting plate can be prevented from being excessively bent.

(3) According to the invention, the auxiliary wheel is arranged, the auxiliary wheel is impacted by the airflow sprayed by the impact sleeve before contacting the ground and rotates rapidly, so that the great impact force can be offset when contacting the ground, and meanwhile, the stability of the stable rear machine body can be improved by matching the auxiliary wheel with the self-adaptive negative suction wheel.

According to the problems of the existing light aircraft landing gear, the invention designs special structures which can be transferred and can greatly weaken impact force, the structures do not need to be provided with excessive electric equipment, the structure is simple and light, and the use is convenient, thereby effectively solving the problems that the common light aircraft landing gear comprises wheels which are light in design and are difficult to be provided with excessive auxiliary devices, when the landing gear bears the interaction of strong thrust and resistance, the landing gear is easy to bend and damage, the friction between the wheels and the ground is easy to be influenced by the ground environment, and the safe landing of the aircraft is influenced to a certain extent.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is an enlarged view of the structure of FIG. 1 at A according to the present invention;

FIG. 3 is a cross-sectional view of the adaptive suction wheel structure of the present invention;

FIG. 4 is a cross-sectional view of an impingement sleeve configuration of the present invention.

The device comprises an electric telescopic rod 1, a longitudinal shock absorber 2, a 21 top hinged disk, a 22 bottom connecting seat, a 23 limit telescopic rod, a 24 longitudinal shock absorption spring, a 3 yielding type self-adaptive mechanism, a 31 corner supporting plate, a 32 connecting supporting block, a 33 reset spring, a 34 self-adaptive negative suction wheel, a 35 hinged shaft, a 36 mechanism wheel shaft, a 37 wheel hub, a 38 wind power pre-rotating fan blade, a 39 rigid gasket, a 310 elastic gasket, a 311 self-adaptive negative suction plate, a 312 negative suction cavity, a 313 negative suction hole, a 4 vibration direction switching mechanism, a 41 arc-shaped supporting rod, a 42 extending straight rod, a 43 first supporting block, a 44 second supporting block, a 45 impact sleeve, a 46 impact rod, a 47 limit sliding block, a 48 oblique buffer plate, a 49 auxiliary wheel, a 410 auxiliary telescopic rod, a 411 rubber plug, a 412 reset vibration spring, a 413 machine body connecting bolt, a 414 oblique jet groove, a 415 limit arc-shaped groove, a 416 arc-shaped buffer groove and an 417 oblique buffer spring.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

As shown in figures 1-4, the embodiment of the invention provides a retractable landing gear of a light airplane, which comprises an electric telescopic rod 1 for retracting the landing gear, a longitudinal shock absorber 2 for mainly absorbing up-and-down vibration, a yield type self-adaptive wheel mechanism 3 for adaptively adjusting ground impact force and rapidly reducing speed, and a vibration direction switching mechanism 4 for resisting vibration generated by resistance in the advancing direction, wherein the electric telescopic rod 1 is installed at the bottom of the light airplane in a hinged manner, the longitudinal shock absorber 2 is arranged at the bottom of the light airplane and is hinged with the bottom of the light airplane, one end of the electric telescopic rod 1 is hinged on the longitudinal shock absorber 2, the yield type self-adaptive wheel mechanism 3 is arranged at the bottom of the longitudinal shock absorber 2, the vibration direction switching mechanism 4 is arranged on the yield type self-adaptive wheel mechanism 3, and the structure of the longitudinal shock absorber 2 comprises a top disc hinge 21, Bottom connecting seat 22, three spacing telescopic link 23 and vertical damping spring 24, the one end of three spacing telescopic link 23 is connected with the fixed surface of the articulated dish 21 in top, the one end of the articulated dish 21 in top and the fixed surface of bottom connecting seat 22 are kept away from to three spacing telescopic link 23 are connected, vertical damping spring 24 has been cup jointed on the surface of spacing telescopic link 23, the surface of the articulated dish 21 in top is articulated with the bottom of light aircraft, electric telescopic handle 1 keeps away from the one end of light aircraft bottom and bottom connecting seat 22's side is articulated.

The yielding type self-adaptive mechanism 3 comprises two corner support plates 31, a connecting support block 32 and two self-adaptive negative suction wheels 34, wherein the lower surface of the bottom connecting seat 22 is fixedly connected with the connecting support block 32, a bearing is arranged on the connecting support block 32, an inner ring of the bearing on the connecting support block 32 is fixedly connected with a hinge shaft 35, the hinge shaft 35 penetrates through the connecting support block 32, two ends of the hinge shaft 35 are respectively and fixedly connected with the surfaces of the two corner support plates 31, the surface of the corner support plate 31 is in a bent shape, the bent part of the corner support plate 31 inclines towards the advancing direction of the airplane wheel, the two corner support plates 31 are provided with bearings, the inner rings of the bearings on the two corner support plates 31 are fixedly connected with an airplane wheel shaft 36, two ends of the airplane wheel shaft 36 are fixedly connected with two hubs 37, the surfaces of the two hubs 37 are respectively sleeved with one self-adaptive negative suction wheel 34, and the two self-adaptive negative suction wheels 34 are symmetrically distributed by taking the central line of the surface of the airplane wheel shaft 36 as a symmetrical line, the surface of the engine axle 36 is fixedly connected with a plurality of wind power pre-rotating fan blades 38, the plurality of wind power pre-rotating fan blades 38 are positioned between two bent angle support plates 31, the self-adaptive negative suction wheel 34 is made of rubber, the surface of the self-adaptive negative suction wheel 34 is in a rough corrugated shape, the inner wall of the self-adaptive negative suction wheel 34 is fixedly connected with a rigid gasket 39, the surface of the rigid gasket 39 is fixedly connected with an elastic gasket 310, the material of the elastic gasket 310 comprises spring steel, the surface of the elastic gasket 310 is provided with a plurality of self-adaptive negative suction plates 311 which are circumferentially distributed by taking the center of the self-adaptive negative suction wheel 34 as a circle center, the material of the self-adaptive negative suction plates 311 is spring steel, the surface of the self-adaptive negative suction plates 311 is lapped with the inner wall of the self-adaptive negative suction wheel 34, a negative suction cavity 312 is arranged between the inner wall of the self-adaptive negative suction wheel 34 and the self-adaptive negative suction plates 311, the surface of the self-adaptive negative suction wheel 34 is provided with a plurality of negative suction holes 313, the negative suction hole 313 corresponds to the negative suction cavity 312, the back surface of the adaptive negative suction plate 311 is fixedly connected with a return spring 33, and one end of the return spring 33 is fixedly connected with the surface of the rigid washer 39.

The vibration direction switching mechanism 4 comprises an arc-shaped support rod 41, an extension straight rod 42, a first support block 43, a second support block 44, an impact sleeve 45, an impact rod 46, a limit slide block 47, an oblique buffer plate 48 and an auxiliary wheel 49, wherein the surface of the arc-shaped support rod is fixedly connected with the first support block 43, one end of the arc-shaped support rod, which is far away from the first support block 43, is fixedly connected with the extension straight rod 42, one end of the extension straight rod 42 is fixedly connected with the second support block 44, the surface of the first support block 43 is fixedly connected with an auxiliary telescopic rod 410, the surface of the second support block is fixedly connected with the impact sleeve 45, the inner wall of the impact sleeve 45 is slidably connected with the impact rod 46, one end of the impact rod 46 is fixedly connected with a rubber plug 411, the surfaces of the impact rod 46 and the auxiliary telescopic rod 410 are both sleeved with a reset vibrating spring 412, the top of the impact rod 46 and the top of the auxiliary telescopic rod 410 are both fixedly connected with a machine body connecting bolt 413, organism connecting bolt 413's surface and light aircraft's bottom threaded connection, the slope that communicates with impact sleeve 45 is seted up on the surface of second supporting shoe spouts groove 414, the bottom of second supporting shoe is provided with auxiliary wheel 49, auxiliary wheel 49 is located the below that spouts groove 414 to the slope, spacing arc groove 415 has been seted up to the upper surface of arc bracing piece, spacing slider 47's surface and the inner wall sliding connection of spacing arc groove 415, oblique buffer plate 48 has been pegged graft on the surface of bent angle backup pad 31, arc buffer groove 416 has been seted up on the surface of arc bracing piece, the inner wall fixedly connected with slant buffering spring 417 of arc buffer groove 416, the one end of slant buffering spring 417 and the surface contact of slant buffer plate 48, the surface of slant buffer plate 48 and the inner wall sliding connection of arc buffer groove 416.

When the self-adaptive negative suction wheel 34 is in contact with the ground, the rolling self-adaptive negative suction wheel 34 offsets the maximum instantaneous impact force, meanwhile, the longitudinal shock absorber 2 absorbs part of shock through each limit telescopic rod 23 and the longitudinal shock absorption spring 24, the bottom of the airplane also impacts the impact rod 46 through the body connecting bolt 413 at the moment, the impact rod 46 drives the air flow generated by downward impact of the rubber plug 411 to blow to the auxiliary wheel 49 through the inclined spraying groove 414 to enable the auxiliary wheel 49 to rapidly rotate, when the aircraft presses the corner support plate 31 to bend the corner support plate 31 in the forward direction of the aircraft, the oblique buffer spring 417 absorbs part of the resistance, the limit slider 47 slides up in the arc buffer groove 416 to enable the auxiliary wheel 49 to contact the ground, the auxiliary wheel 49 plays a supporting role and transmits part of oblique pressure upwards through the second support block 44 and the impact sleeve 45, the body connecting bolt 413 absorbs part of external force, meanwhile, when the aircraft slides stably, the adaptive negative suction wheel 34 rotates forwards to enable the adaptive negative suction plate 311 which is about to contact the ground to bend inwards, the negative suction cavity 312 between the inward-bent adaptive negative suction plate 311 and the adaptive negative suction wheel 34 is unfolded, when the aircraft pressure is applied to the adaptive negative suction wheel 34, the negative suction cavity 312 deforms to a certain degree, part of gas is discharged from the inside of the negative suction cavity 312 and generates ground-grabbing adsorption force, the friction force with the ground is increased, and when the area leaves the ground, the gas pressure inside the adaptive negative suction wheel 34 and the elasticity of the return spring 33 can cause the adaptive negative suction plate 311 to be quickly attached to the inner wall of the adaptive negative suction wheel 34 again.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

Claims

1. The utility model provides a light aircraft retractable undercarriage, includes electric telescopic handle (1) that is used for receiving and releasing the undercarriage, plays main cushioning effect's vertical bumper shock absorber (2) to vibrations from top to bottom, reply ground impact force self-adaptation and make the adjustment and play surrender formula self-adaptation mechanism (3) of quick speed reduction effect and be used for confronting the vibrations of the production of direction of advance resistance to switching mechanism (4), its characterized in that: the electric telescopic rod (1) is installed at the bottom of the light airplane in an articulated mode, the longitudinal shock absorber (2) is arranged at the bottom of the light airplane and is articulated with the bottom of the light airplane, one end of the electric telescopic rod (1) is articulated with the longitudinal shock absorber (2), the yielding type self-adaptive mechanism (3) is arranged at the bottom of the longitudinal shock absorber (2), and the vibration direction switching mechanism (4) is arranged on the yielding type self-adaptive mechanism (3); the structure of the longitudinal shock absorber (2) comprises a top hinged disk (21), a bottom connecting seat (22), three limiting telescopic rods (23) and longitudinal shock absorbing springs (24), one ends of the three limiting telescopic rods (23) are fixedly connected with the surface of the top hinged disk (21), one ends of the three limiting telescopic rods (23) far away from the top hinged disk (21) are fixedly connected with the surface of the bottom connecting seat (22), the longitudinal shock absorbing springs (24) are sleeved on the surface of the limiting telescopic rods (23), the surface of the top hinged disk (21) is hinged with the bottom of the light airplane, and one end of the electric telescopic rod (1) far away from the bottom of the light airplane is hinged with the side face of the bottom connecting seat (22); bent formula self-adaptation wheel mechanism (3) include two bent angle backup pads (31), connect supporting shoe (32) and two self-adaptation burden suction wheel (34), the lower surface fixedly connected with of bottom connecting seat (22) connects supporting shoe (32), be provided with the bearing on connecting supporting shoe (32), the inner circle fixedly connected with articulated shaft (35) of the bearing on connecting supporting shoe (32), articulated shaft (35) run through connecting supporting shoe (32), the both ends of articulated shaft (35) are connected with the fixed surface of two bent angle backup pads (31) respectively, the surface of bent angle backup pad (31) is crooked shape, the crooked position of bent angle backup pad (31) inclines towards wheel advancing direction.

2. A light aircraft retractable landing gear according to claim 1, wherein: two be provided with the bearing on bent angle backup pad (31), inner circle fixed connection organic wheel axle (36) of the bearing on two bent angle backup pads (31), two wheel hub (37) of both ends fixedly connected with of organic wheel axle (36), one self-adaptation negative suction wheel (34) have all been cup jointed on the surface of two wheel hub (37), two self-adaptation negative suction wheel (34) use the central line on wheel axle (36) surface to be the symmetric distribution as the symmetric line, the fixed surface of organic wheel axle (36) is connected with a plurality of wind-force and changes flabellum (38), a plurality of wind-force is changeed flabellum (38) in advance and is located between two bent angle backup pads (31).

3. A light aircraft retractable landing gear according to claim 2, wherein: the material of self-adaptation burden suction wheel (34) is rubber, the surface of self-adaptation burden suction wheel (34) is crude corrugate, the inner wall fixedly connected with rigidity packing ring (39) of self-adaptation burden suction wheel (34), the fixed surface of rigidity packing ring (39) is connected with elastic gasket (310), elastic gasket's (310) material includes the spring steel, the surface of elastic gasket (310) is provided with a plurality of and uses the center of self-adaptation burden suction wheel (34) to be self-adaptation burden suction disc (311) that the circumference distributes as the centre of a circle, the material of self-adaptation burden suction disc (311) is the spring steel, the surface of self-adaptation burden suction disc (311) and the inner wall overlap joint of self-adaptation burden suction wheel (34), be provided with between the inner wall of self-adaptation burden suction wheel (34) and self-adaptation burden suction disc (311) and inhale the chamber (312), a plurality of burden suction hole (313) have been seted up on the surface of self-adaptation burden suction wheel (34), the negative suction hole (313) corresponds to the negative suction cavity (312), the back surface of the self-adaptive negative suction plate (311) is fixedly connected with a return spring (33), and one end of the return spring (33) is fixedly connected with the surface of the rigid washer (39).

4. A light aircraft retractable landing gear according to claim 3, wherein: the shock to the switching mechanism (4) includes arc bracing piece (41), extension straight-bar (42), first supporting block (43), second supporting block (44), impact sleeve (45), impact rod (46), limit slide block (47), slant buffer board (48) and auxiliary wheel (49), the fixed surface of arc bracing piece is connected with first supporting block (43), the one end fixedly connected with that the arc bracing piece kept away from first supporting block (43) extends straight-bar (42), the one end fixedly connected with second supporting block (44) of extending straight-bar (42), the fixed surface of first supporting block (43) is connected with auxiliary telescopic link (410), the fixed surface of second supporting block is connected with impact sleeve (45), the inner wall sliding connection that strikes sleeve (45) has impact rod (46), the one end fixedly connected with rubber buffer (411) of impact rod (46), the surface of the impact rod (46) and the surface of the auxiliary telescopic rod (410) are both sleeved with a reset vibrating spring (412), the top of the impact rod (46) and the top of the auxiliary telescopic rod (410) are both fixedly connected with an engine body connecting bolt (413), the surface of the engine body connecting bolt (413) is in threaded connection with the bottom of the light airplane, an inclined spraying groove (414) communicated with the impact sleeve (45) is formed in the surface of the second supporting block, an auxiliary wheel (49) is arranged at the bottom of the second supporting block, and the auxiliary wheel (49) is located below the inclined spraying groove (414).

5. A light aircraft retractable landing gear according to claim 4, wherein: spacing arc wall (415) have been seted up to the upper surface of arc bracing piece, the surface of spacing slider (47) and the inner wall sliding connection of spacing arc wall (415), the surface of bent angle backup pad (31) is pegged graft and is had slant buffer board (48), arc buffer slot (416) have been seted up to the surface of arc bracing piece, the inner wall fixedly connected with slant buffering spring (417) of arc buffer slot (416), the one end of slant buffering spring (417) and the surface contact of slant buffer board (48), the surface of slant buffer board (48) and the inner wall sliding connection of arc buffer slot (416).