CN113291460B - A short-range/vertical take-off and landing vehicle with variant landing gear - Google Patents

Abstract

The invention relates to a short-distance/vertical take-off and landing aircraft adopting a variant landing gear, belonging to the technical field of aviation. The wings of the short-distance/vertical take-off and landing aircraft adopting the variant landing gear are fixed on the aircraft body, and a power system is arranged on the wings; the wings are provided with ailerons; a wheel type nose landing gear is arranged on the body; the wing top surface and the wing bottom surface of the wing are respectively provided with a tail support system for vertical take-off and landing or short-distance take-off and landing of the aircraft; a wheel type front and rear falling frame is arranged in the tail support system positioned on the bottom surface of the wing; the tail support system is in an outward opening and closing posture or an inward closing and closing posture; the short-distance/vertical take-off and landing aircraft adopting the variant landing gear provided by the invention has the advantages that the posture mode can be adjusted according to the task and environment requirements, and the adaptability to task work in a future complex environment is enhanced.

Description

A short-range/vertical take-off and landing aircraft with variant landing gear

technical field

The invention relates to a short-distance/vertical take-off and landing aircraft adopting a variant landing gear, which belongs to the field of aviation technology.

Background technique

Referring to other new vertical take-off and landing models, the design indicators are mostly set as STOVL (short vertical take-off and landing) aircraft rather than pure VTOL (vertical take-off and landing) aircraft, the purpose is to avoid the strict requirements of vertical take-off on engine power, As a result, the take-off weight is limited, and it is impossible to take off with full fuel or full load.

For example, the F35-B in the United States, when taking off vertically, its take-off weight is limited to only 16.8 tons, but the empty weight of the F35-B itself has reached 14.7 tons, so after deducting the empty weight, only 2.1 tons of weight can be for payload. In this case, even without any ammunition, the F35-B can only be loaded with 34% of the fuel. To carry the ammunition, the fuel has to be further reduced. If it carries 1 ton of ammunition, the fuel of the F35-B will drop to a poor 18%. , which has almost no combat radius.

When the F35-B adopts short-distance takeoff, in this mode: the lift fan also needs to work, and the tail nozzle also needs to deflect, but it does not need to provide full lift. In fact, the jet of the lift fan is tilted back 15 degrees during takeoff, and the main engine of the aircraft is tilted 65 degrees downward. The engine will produce about 72% of the total thrust in the horizontal direction and 68% of the total thrust. In this case, the F35-B can reach a take-off weight of 22.7 tons by running 122 meters. After deducting 14.7 tons of empty weight, there is still 8 tons of payload, can be filled with fuel (6.1 tons) and carry 1.9 tons of ammunition. If the glide distance of the short takeoff is further extended and combined with the glide deck (the British Queen Elizabeth-class aircraft carrier has prepared a 167-meter glide runway for the F35-B), the F35-B can even take off with a designed maximum takeoff weight of 27 tons. At this time, the payload is up to 12.3 tons, which has a very strong combat capability.

The North Atlantic Treaty Organization (NATO) defines the variant aircraft as follows: by changing the shape of the aircraft locally or as a whole, the aircraft can adapt to the needs of various missions in real time and enable the aircraft to maintain optimal performance and efficiency in various environments. However, the current main development directions are variable rear (front) sweep aircraft, variable-span aircraft, inclined-wing variant aircraft, curved-wing wing aircraft, and combined variant aircraft. There are relatively few variant technologies for landing gear, and the realization of The purpose is mostly for the retractable function design of the landing gear.

Contents of the invention

The present invention provides a short-distance/vertical take-off and landing aircraft that adopts variant landing gears for the above-mentioned problems.

The present invention adopts following technical scheme:

The STOL/VTOL aircraft adopting variant landing gear according to the present invention includes a power system, a fuselage, a wing, an aileron, a tail support system, a wheeled front landing gear, and a wheeled rear landing gear; The wing is fixed on the fuselage, and the power system is installed on the wing; the aileron is arranged on the wing; the wheeled front landing gear is arranged on the fuselage; Tail brace system for vertical take-off and landing or short take-off and landing; the tail brace system located on the underside of the wing is equipped with a wheeled rear landing gear; the tail brace system is in an outward opening and closing posture or an inward retracting and closing posture;

The tail brace system positioned at the underside of the wing supports the aircraft for STOL mode through the wheeled rear landing gear and the wheeled front landing gear of the fuselage;

The tail brace system located on the top surface of the wing and the tail brace system on the bottom surface of the wing are opened and closed outwards to form a support posture for the vertical take-off and landing mode of the aircraft.

According to the STOL/VTOL aircraft using variant landing gear according to the present invention, the wings on both sides of the fuselage are respectively provided with a tail brace system for controlling the top surface of the wing and a tail brace system for the bottom surface of the wing. The strut controls the steering gear and the tail brace controls the steering gear;

The tail brace system positioned on the top surface of the wing comprises a support rod one, a tail brace one, a tail brace horizontal tailplane, a tailstay vertical tailplane, a brace rod pull rod one and a tail brace pull rod one; 1. There are at least two groups of tail braces, which are located on the top surface of the wings on both sides of the fuselage. One end of the support rods is hinged to the wing through a shaft body, and the other end of the support rods is connected to one end of the tail braces through a shaft. The shaft body is hinged, and the other end of the tail brace one is arranged with a tail brace vertical tail fin 1; a tail brace horizontal tail fin 1 parallel to the wing is arranged between the tail brace one; The shaft body of the wing part of one is fixedly connected, and the other end of the support rod pull rod one is connected with the driving end of the support rod control steering gear on the top surface of the wing; On the shaft body, the other end of the tail brace rod one is connected with the tail brace control steering gear on the top surface of the wing;

The tail brace system located on the bottom surface of the wing includes support rod two, tail brace two, tail brace horizontal tail two, tail brace vertical tail two; support rod pull rod two and tail brace pull rod two;

The two supporting rods and the two tail supporting rods are at least two groups, which are located on the top surface of the wing on both sides of the fuselage. One end of the rod two is hinged through a shaft body, and the other end of the tail brace two is arranged with a tail brace vertical empennage two; a tail brace horizontal empennage two parallel to the wing is arranged between the two tail braces; One end of the support rod 2 is fixedly connected with the wing shaft body of the support rod 2, and the other end of the support rod 2 is connected with the driving end of the support rod controlling the steering gear on the bottom surface of the wing; On the shaft body at two one ends, the other end of the tail stay rod two is connected with the tail stay control servo on the bottom surface of the wing.

According to the STOL/VTOL aircraft using variant landing gear according to the present invention, the wheeled front landing gear includes: fuselage connection drive mechanism, retracting rod, pull rod, retracting rod connecting piece, main buffer, rotating mechanism , wheel connector and front wheel;

The main buffer is hinged with the fuselage through the fuselage connection drive mechanism, and the connecting piece of the pull rod is fixedly connected with the main buffer as an outer cylinder;

The top of the retracting rod extends to the inner abdomen of the fuselage, the tail end of the retracting rod is connected with the top of the pull rod, the tail end of the pull rod is hinged with the connecting piece of the retracting rod, the front wheel is fixedly connected with the main buffer through the wheel connecting piece, and It can be rotated around the axis of the main buffer by a rotating mechanism, and the rotation angle is 90°.

According to the STOL/VTOL aircraft using variant landing gear according to the present invention, the wheeled rear landing gear includes a rear landing gear connector, a rear landing gear slide rail, a semi-retractable shell, an upper rocker arm, a buffer device, lower rocker arm and rear wheel; the tail brace vertical tail 2 is provided with a rear landing gear slide rail and a rear landing gear connector; the semi-retractable shell is assembled on the rear landing gear slide rail, and slides along the The rail extends in the direction of sliding; the bottom end of the semi-retractable shell is provided with an axle hole for the wheel axle after assembly;

The lower end of the rear landing gear connector fixes the buffer, the outer wall of the buffer is hinged to one end of the upper rocker arm, the other end of the upper rocker arm is hinged to one end of the lower rocker arm, the other end of the lower rocker arm is hinged to the rear wheel The wheel shaft is hinged; the bottom end of the buffer is also hinged with the middle of the lower rocker arm body;

When the wheeled rear landing gear is loaded, the semi-retractable shell moves up and down in the rear landing gear slide rail with the action of the wheeled rear landing gear;

According to the STOL/VTOL aircraft adopting variant landing gear according to the present invention, the distance between the tail brace horizontal empennage one and the center of gravity of the aircraft is the support rod one and the tail brace one or the support rod two and the tail brace two the sum of the lengths of .

According to the STOL/VTOL aircraft using variant landing gear according to the present invention, when the aircraft performs self-adaptive vertical landing, the support rod controls the steering gear and the tail stay controls the steering gear to drive the support rod one and the tail stay one 1. Rotate the support bar 2 and the tail support bar 2, adjust the support bar 1, the tail support bar 1, the support bar 2 and the tail support bar 2 to a posture that is highly compatible with the landing area environment for landing.

According to the STOL/VTOL aircraft adopting variant landing gear according to the present invention, the symmetrical planes of the tail brace vertical empennage two, the semi-retractable shell, the upper rocker arm, the buffer, the lower rocker arm, and the rear wheel are unified and coplanar .

Beneficial effect

The short-distance/vertical take-off and landing aircraft using the variant landing gear provided by the present invention integrates the advantages of fixed-wing and rotary-wing aircraft, which can not only significantly reduce the requirements of the aircraft for take-off and landing conditions, but also possess strong flight combat capabilities. It has the remarkable characteristics of using small platforms such as small and medium-sized aircraft carriers, amphibious assault ships, transport ships and ocean islands and reefs to exert great power.

The short-distance/vertical take-off and landing aircraft provided by the present invention adopts a variant landing gear, and the adopted variant landing gear can adjust the attitude mode according to the task and the environment. The strut supports and protects the aircraft parked on the ground. When the aircraft is in the cruising state of level flight, it can actively control the symmetrically deployed tail braces on both sides to connect with the support rods. After docking, the tail braces and the support rods are not only lowered The additional resistance brought by the structure itself, because the main body is located at the tail of the fuselage, and the horizontal tail and vertical tail on the tail brace are far away from the center of gravity of the aircraft, the moment arm used for trim and control is long, the control ability is strong, and the additional resistance of trim is small. Improve the control ability and flight efficiency of the aircraft during flight. When the aircraft mode is switched and vertically landed, the symmetrical two-stage controllable landing gear can perform adaptive auxiliary trim adjustment and landing, which enhances the mission work in the complex environment in the future adaptability.

The short-distance/vertical take-off and landing aircraft that adopts the variant landing gear provided by the present invention can choose the mode of taxi take-off and landing according to actual environmental factors. The rear landing gear is supported on the surface of the take-off/parking area, bearing the main weight of the aircraft and maintaining the attitude balance. To change the take-off and landing mode, it is only necessary to control the retraction of the wheel-type front landing gear and the attitude change of the support bar and tail bar. The support bar, tail brace, tail brace horizontal tail and tail brace vertical tail on the supporting side are adjusted to the level flight state to assist the control and adjustment of the short-range/vertical take-off and landing aircraft, and the flexible function is increased through simple structural changes. accomplish.

Description of drawings

Fig. 1 is a schematic diagram of adaptive adjustment of the landing gear in a mode switching state of a short-range/vertical take-off and landing aircraft using a variant landing gear;

Fig. 2 is a structural schematic diagram of a wheeled front landing gear of a short-range/vertical take-off and landing aircraft that adopts a variant landing gear;

Fig. 3 is a structural schematic diagram of a wheeled rear landing gear of a short-range/vertical take-off and landing aircraft that adopts a variant landing gear;

Fig. 4 is a schematic diagram of a taxiing takeoff and landing and parking state of a short-distance/vertical take-off and landing aircraft that adopts a variant landing gear;

Fig. 5 is a schematic diagram of a vertical take-off and landing and parking state of a short-distance/vertical take-off and landing aircraft that adopts a variant landing gear;

Fig. 6 is a schematic diagram of an adaptive landing state on the right side of a short-range/vertical take-off and landing aircraft using a variant landing gear;

Fig. 7 is a schematic diagram of an adaptive landing state on the left side of a short-range/vertical take-off and landing aircraft using a variant landing gear;

Fig. 8 is a schematic diagram of ground self-adaptive attitude adjustment of a short-distance/vertical take-off and landing aircraft using variant landing gear;

Fig. 9 is a schematic diagram of the cruising state of a short-distance/vertical take-off and landing aircraft that adopts a variant landing gear;

Figure 10 is a schematic diagram of the two-stage straight state of the landing gear attitude driving structure;

Figure 11 is a schematic diagram of the two-stage bending state of the attitude driving structure of the landing gear;

Figure 12 is a schematic diagram of the control steering gear and connection of the support rod located in the wing;

Figure 13 is a schematic diagram of the steering gear and connection of the tail brace located in the middle of the wing;

Among them, 1-power system, 2-fuselage, 3-wing, 4-strut control steering gear, 5-aileron, 6-tail strut control steering gear, 7-strut one, 8-tail strut 1. 9-tail support horizontal tail 1, 10-tail support vertical tail 1, 71-support rod 2, 81-tail support rod 2, 91-tail support horizontal tail 2, 101-tail support vertical tail 2, 11-wheel Type front landing gear, 111-Fuselage connection drive mechanism, 112-Retraction rod, 113-Tie rod, 114-Retraction rod connection piece, 115-Main buffer, 116-Rotary mechanism, 117-Wheel connection piece, 118-Front Wheel, 12-wheeled rear landing gear, 121-rear landing gear connector, 122-rear landing gear slide rail, 123-semi-retractable shell, 124-upper rocker arm, 125-buffer, 126-lower rocker arm , 127-rear wheel, 13-support rod pull rod one, 14-tail stay rod one, 131-support rod pull rod two, 141-tail stay rod two.

Detailed ways

The present invention will be described in more detail below with reference to schematic diagrams, wherein preferred embodiments of the present invention are shown, and it should be understood that those skilled in the art can modify the present invention described herein while still achieving the advantageous effects of the present invention. Therefore, the following description should be understood as the broad knowledge of those skilled in the art, but not as a limitation of the present invention.

As shown in Figure 1: the STOL/VTOL aircraft adopting variant landing gear, including power system 1, fuselage 2, wing 3, aileron 5, tail brace system, wheeled nose landing gear 11, wheeled Rear landing gear 12; Described wing 3 is fixed on the fuselage 2, and power system 1 is installed on the wing 3; Aileron 5 is set on the wing 3; The fuselage 2 is provided with wheeled front landing gear 11; The wing top surface and the wing bottom surface of the wing 3 are respectively provided with a tail brace system for vertical take-off and landing or short take-off and landing of the aircraft; the tail brace system positioned at the wing bottom surface is provided with a wheeled rear landing gear 12; Opening and closing posture or inwardly retracting and closing posture; the tail support system located on the underside of the wing supports the aircraft for STOL mode through the wheeled rear landing gear 12 and the wheeled front landing gear 11 of the fuselage 2; The support system and the tail support system on the underside of the wing are opened and closed outwards to form a support attitude for the vertical take-off and landing mode of the aircraft. The power system 1 provides lift for the STOL/VTOL aircraft and has attitude control capability, and the motion envelope of the power system 1 does not overlap with the motion envelope of the landing gear variant.

The wings 3 on both sides of the fuselage 2 are respectively provided with a strut control steering gear 4 and a tail strut control steering gear 6 for controlling the tail brace system on the top surface of the wing and the tail brace system on the bottom surface of the wing;

The tail brace system positioned on the top surface of the wing 3 includes a support rod-7, a tail brace-8, a tail brace horizontal tail-9, a tail brace vertical tail-10, a support rod pull rod-13 and a tail brace pull rod-14; Support bar one 7, tail support bar one 8 are at least two groups, are positioned at the wing 3 wing top surface of fuselage 2 both sides, one end of support bar one 7 is hinged with wing 3 by axle body, and support bar one 7 The other end is hinged with one end of the tail brace-8 through a shaft body, and the other end of the tail brace-8 is arranged with a tail brace vertical tail wing-10; a tail brace parallel to the wing 3 is arranged between the tail brace-8 Horizontal stabilizer-9; one end of said support rod pull rod-13 is fixedly connected with the wing 3 shaft bodies of support rod-7, and the other end of support rod pull rod-13 controls the steering gear 4 with the support rod of the wing top surface The driving end is connected; one end of the tail stay rod-14 is fixedly connected to the shaft body at one end of the tail stay rod-8, and the other end of the tail stay rod-14 is connected with the tail stay control steering gear 6 on the top surface of the wing;

The described tail brace system positioned at the bottom surface of wing 3 includes support rod two 71, tail brace two 81, tail brace horizontal empennage two 91, tail brace vertical empennage two 101; 141;

The two supporting rods 71 and the two tail supporting rods 81 are at least two groups, located on the top surface of the wing 3 on both sides of the fuselage 2, one end of the supporting rod 71 is hinged with the wing 3 through the shaft, and the supporting rods The other end of two 71 and one end of tail brace two 81 are hinged through the shaft body, and the other end of tail brace two 81 is arranged with tail brace vertical empennage two 101; Tail support horizontal empennage two 91; one end of said support rod pull rod two 131 is fixedly connected with the wing 3 shafts of support rod two 71, and the other end of support rod pull rod two 131 is connected with the support rod control servo on the bottom surface of the wing The driving end of 4 links to each other; One end of tail brace pull rod two 141 is fixedly connected on the axle body of tail brace two 81 one ends, and the other end of tail brace pull rod two 141 links to each other with the tail brace control steering gear 6 of wing bottom surface.

Before and after the vertical take-off and landing of the short-range/vertical take-off and landing aircraft, the short-range/vertical take-off and landing aircraft passes through the support rod-7, the tail-stay-8, the tail-stay horizontal tail-9, the tail-stay vertical tail-10, and the support rod-2 71. Tail brace two 81, tail brace horizontal tail two 91, and tail brace vertical tail two 101 are supported on the surface of the takeoff/parking area to bear the main weight of the short-distance/vertical take-off and landing aircraft and maintain attitude balance;

During the mode conversion process of the short-distance/vertical take-off and landing aircraft from hovering to level flight or from level flight to hovering, the strut control steering gear 4 and the tail strut control steering gear 6 drive the strut-7 and tail-strut-8 , support rod two 71 and tail stay two 81 rotate, so that support rod one 7, tail stay one 8, support rod two 71 and tail stay two 81 carry out posture adjustment relative to the fuselage 2;

To assist the short-range/vertical take-off and landing aircraft trim, the two tail braces and the ailerons 5 cooperate to adjust to adapt to the direction of the airflow, and generate aerodynamic force that helps the fuselage 2 to fly. After the short-range/vertical take-off and landing aircraft is stabilized, take off The landing gear is gradually closed, and the overall structure is located at the tail end of the fuselage 2. The distance between the two tail braces and the center of gravity of the short-range/vertical take-off and landing aircraft is support rod one 7, tail stay one 8 or support rod two 71, tail stay The sum of the lengths of two 81, the length parameters of support rod one 7, tail stay one 8 or support rod two 71, tail stay two 81 need to ensure that tail stay horizontal empennage 9 possesses good maneuverability.

When the short-distance/vertical take-off and landing aircraft performs adaptive vertical landing, the support rod controls the steering gear 4 and the tail brace controls the steering gear 6 to drive the support rod 1 7, the tail rod 1 8, the support rod 2 71 and the tail rod 2 81 Rotate, adjust support rod 1 7, tail stay 1 8, support rod 2 71 and tail stay 2 81 to change to a posture with a high degree of coordination with the landing area environment for landing.

As shown in Figure 2: a short-range/vertical take-off and landing aircraft adopting a variant landing gear, the wheeled front landing gear 11 includes a fuselage connection drive mechanism 111, a retracting rod 112, a pull rod 113, a retracting rod connector 114, and a main buffer 115, rotating mechanism 116, machine wheel connector 117 and front machine wheel 118;

The main buffer 115 is hinged with the fuselage 2 through the fuselage connection drive mechanism 111, and the draw rod connector 114 is fixedly connected with the main buffer 115 as an outer cylinder; The tail end of the rod 112 is connected to the top of the pull rod 113, and the tail end of the pull rod 113 is hinged with the pull rod connecting piece 114. The front wheel 118 is fixedly connected with the main buffer 115 through the wheel connecting piece 117, and can be rotated around the main buffer by the rotating mechanism 116. Device 115 axis rotation, rotation angle is 90 °.

As shown in Figure 3: the wheeled rear landing gear 12 includes a rear landing gear connector 121, a rear landing gear slide rail 122, a semi-retractable shell 123, an upper rocker arm 124, a buffer 125, a lower rocker arm 126 and a rear wheel 127; Tail brace vertical tail 2 101 is provided with rear landing gear slide rail 122 and rear landing gear connector 121; the semi-retractable shell 123 is assembled on the rear landing gear slide rail 122, and slides along the extension direction of rear landing gear slide rail 122 ; The bottom end of the semi-retractable shell 123 is provided with an axle hole of the assembled rear wheel 127 axle;

The lower end of the rear landing gear connector 121 fixes the buffer 125, the outer wall of the buffer 125 is hinged with one end of the upper rocker 124, the other end of the upper rocker 124 is hinged with one end of the lower rocker 126, and the other end of the lower rocker 126 is hinged. One end is hinged with the wheel shaft of the rear wheel 127; the bottom end of the buffer 125 is also hinged with the middle part of the lower rocker arm 126 arm body; Interfering with the semi-retractable shell 123, the symmetry planes of the tail brace vertical tail 10, the semi-retractable shell 123, the upper rocker arm 124, the buffer 125, the lower rocker arm 126 and the rear wheel 127 are coplanar, and the wheeled rear landing gear 12 During loading, the semi-retractable shell 123 moves up and down in the rear landing gear slide rail 122 with the action of the wheeled rear landing gear 12 .

As shown in Figure 4: before the short-range/vertical take-off and landing vehicle rolls and after landing, the short-range/vertical take-off and landing vehicle is supported on the surface of the take-off/parking area by the wheeled front landing gear 11 and the wheeled rear landing gear 12, Undertake the main weight of the short-range/vertical take-off and landing aircraft and maintain the attitude balance. When parking and taxiing, under the control of the fuselage connection drive mechanism 111, the wheeled front landing gear 11 is unfolded, and the short-range/vertical take-off and landing aircraft is unilaterally The posture of the support bar 7 and the tail support bar 8 far away from the ground is closed to the tail of the fuselage, adjusted to the level flight state, and the auxiliary short-distance/vertical take-off and landing aircraft is controlled and adjusted, and the support bar 7 and the tail support bar 8 on the other side are The attitude of the wheel is adjusted to the coaxial state and opened at a certain angle to ensure that when the wheeled front landing gear 1 and the wheeled rear landing gear 12 touch the ground, the parts of the power system 1 will not interfere with the ground.

Shown in Fig. 5: the vertical take-off and landing and parking state of the STOL/VTOL aircraft adopting variant landing gear; support bar one 7, tail support bar one 8, support bar two 71, tail support bar two 81 are controlled by the support bar Steering gear 4 and tail stay rod control steering gear 6 are controlled to spread out mutually, and support rod one 7, tail stay rod one 8 are deformed into a straight line, and support rod two 71, tail stay rod two 81 form a straight line; The first brace 8, the second brace 71 and the second tail brace 81 form a "herringbone" support structure.

As shown in Figure 6: for a STOL/VTOL aircraft with modified landing gear, when the aircraft lands rapidly and the tail brace system on one side of the aircraft touches the ground, the rebound time of the tail brace system is longer than that of the support rod and the tail brace itself. Adapt to the adjustment time; at this time, the support rod one 7 and the tail stay one 8 are deformed into a straight line and touch the ground first, and the support rod two 71 and the tail stay two 81 are formed into an inwardly folded shape and touch the ground for the second time.

As shown in Figure 7: for a STOL/VTOL aircraft using a variant landing gear, when the aircraft lands rapidly and the tail brace system on one side of the aircraft touches the ground, the rebound time of the tail brace system is shorter than that of the support rod and the tail brace itself. Adapt to the adjustment time; at this time, the first support rod 7 and the first tail support rod 8 are deformed into a straight line to touch the ground first, and the second support rod 71 and the second tail support rod 81 are deformed into an outwardly curved shape and touch the ground for the second time.

As shown in Figure 8: during the landing process, due to the impact of asymmetry, gravity, and crosswind on the aircraft, after touching the ground, the first support rod 7, the first tail stay 8, the second support rod 71 and the second tail stay 81 Secondary adjustments to stabilize the fuselage.

The foregoing are only preferred embodiments of the present invention, and do not limit the present invention in any way. Any person skilled in the technical field, within the scope of the technical solution of the present invention, makes any form of equivalent replacement or modification to the technical solution and technical content disclosed in the present invention, which does not depart from the technical solution of the present invention. The content still belongs to the protection scope of the present invention.

Claims (6)

1. A short-range/vertical take-off and landing aircraft adopting a variant landing gear, characterized in that it includes a power system (1), a fuselage (2), a wing (3), an aileron (5), and a tail support system , wheeled front landing gear (11), wheeled rear landing gear (12); the wing (3) is fixed on the fuselage (2), and the power system (1) is installed on the wing (3); An aileron (5) is arranged on the wing (3); a wheeled front landing gear (11) is arranged on the fuselage (2); the wing top surface and the wing bottom surface of the wing (3) are respectively equipped with Tail support system for landing or short take-off and landing; wheeled rear landing gear (12) is arranged in the tail support system located on the underside of the wing; the tail support system is in an outward opening and closing posture or an inward retracting closed posture; The tail brace system located on the underside of the wing supports the aircraft in STOL mode through the wheeled rear landing gear (12) and the wheeled front landing gear (11) of the fuselage (2); The tail brace system located on the top of the wing and the tail brace system on the bottom of the wing are opened and closed outwards to form a support posture for the vertical take-off and landing mode of the aircraft; The wings (3) on both sides of the fuselage (2) are respectively provided with a support rod control steering gear (4) and a tail brace control system for controlling the tail brace system on the top surface of the wing and the tail brace system on the bottom surface of the wing. steering gear (6); The tail support system located on the top surface of the wing (3) includes a support rod one (7), a tail support rod one (8), a tail support horizontal tail wing one (9), a tail support vertical tail wing one (10), Support rod one (13) and tail brace one (14); said support rod one (7) and tail brace one (8) are at least two groups, located on the wings on both sides of the fuselage (2) (3) On the top surface of the wing, one end of the support rod one (7) is hinged with the wing (3) through the shaft body, and the other end of the support rod one (7) is hinged with one end of the tail support rod one (8) through the shaft body , the other end of tail brace one (8) is arranged with tail brace vertical tailplane one (10); said tailstay one (8) is provided with tailstay horizontal tailplane one (9) parallel to the wing (3) ; One end of the support rod pull rod one (13) is fixedly connected with the wing (3) shaft of the support rod one (7), and the other end of the support rod pull rod one (13) is controlled by the support rod on the top surface of the wing. The driving end of the steering gear (4) is connected; one end of the tail stay rod one (14) is fixedly connected to the shaft body at one end of the tail stay rod one (8), and the other end of the tail stay rod one (14) is connected to the top of the wing connected to the rear tailstay control steering gear (6); The tail support system located on the underside of the wing (3) includes two support rods (71), two tail support rods (81), two tail support horizontal tail fins (91), and two tail support vertical tail fins (101); Rod pull rod two (131) and tail brace pull rod two (141); The two supporting rods (71) and the two tail supporting rods (81) are at least two groups, which are located on the wing top surfaces of the wings (3) on both sides of the fuselage (2), and one end of the supporting rod two (71) is connected to The wing (3) is hinged through the shaft body, the other end of the support rod 2 (71) is hinged with the end of the tail brace 2 (81) through the shaft body, and the other end of the tail brace 2 (81) is arranged with a vertical tail fin 2 (101); the two tail braces (81) are provided with tail braces two (91) parallel to the wing (3); one end of the two support rods (131) is connected to the two support rods ( 71) The shafts of the wings (3) are fixedly connected, and the other end of the support rod two (131) is connected with the driving end of the support rod control steering gear (4) on the bottom surface of the wing; the tail support rod two (141) One end of one end is fixedly connected on the axle body of tail stay two (81) one ends, and the other end of tail stay pull bar two (141) links to each other with the tail stay control steering gear (6) of wing bottom surface. 2. The STOL/VTOL aircraft adopting variant landing gear according to claim 1, characterized in that: the wheeled front landing gear (11) includes: a fuselage connection drive mechanism (111), a rod retraction (112), pull rod (113), pull rod connector (114), main buffer (115), rotation mechanism (116), wheel connector (117) and front wheel (118); The main buffer (115) is hinged to the fuselage (2) through the fuselage connection drive mechanism (111), and the tie rod connecting piece (114) is fixedly connected to the main buffer (115) as an outer cylinder; The top end of the retracting rod (112) extends to the inner belly of the fuselage (2), the tail end of the retracting rod (112) is connected to the top end of the pull rod (113), and the tail end of the pull rod (113) is connected to the pull rod connector (114) Hinged, the front wheel (118) is fixedly connected with the main buffer (115) through the wheel connector (117), and can rotate around the axis of the main buffer (115) through the rotating mechanism (116), and the rotation angle is 90°. 3. The STOL/VTOL aircraft adopting variant landing gear according to claim 1, characterized in that: the wheeled rear landing gear (12) includes a rear landing gear connector (121), a rear landing gear Falling frame slide rail (122), semi-retractable shell (123), upper rocker arm (124), buffer (125), lower rocker arm (126) and rear wheel (127); said tail brace vertical empennage two ( 101) is equipped with a rear landing gear slide rail (122) and a rear landing gear connector (121); the semi-retractable shell (123) is assembled on the rear landing gear slide rail (122), and along the rear landing gear slide rail (122) ) to slide in the direction of extension; the bottom end of the semi-retractable casing (123) is provided with an axle hole for the wheel shaft of the assembled rear wheel (127); The lower end of the rear landing gear connector (121) fixes the buffer (125), the outer wall of the buffer (125) is hinged to one end of the upper rocker arm (124), and the other end of the upper rocker arm (124) is connected to the lower rocker One end of the arm (126) is hinged, and the other end of the lower rocker arm (126) is hinged with the axle of the rear wheel (127); the bottom end of the buffer (125) is also hinged with the middle of the lower rocker arm (126) ; When the wheeled rear landing gear (12) is loaded, the semi-retractable shell (123) moves up and down in the rear landing gear slide rail (122) with the action of the wheeled rear landing gear (12). 4. The STOL/VTOL aircraft adopting variant landing gear according to claim 1, characterized in that: the distance between the tail support horizontal tail (9) and the center of gravity of the aircraft is the support rod (7) And the sum of the lengths of the tail brace one (8) or the brace brace two (71) and the tail brace two (81). 5. The STOL/VTOL aircraft using variant landing gear according to claim 1, characterized in that: when the aircraft performs adaptive vertical landing, the strut controls the steering gear (4) and the tail strut controls The steering gear (6) drives the first support rod (7), the first tail stay (8), the second support rod (71) and the second tail stay (81) to rotate, and adjust the first support rod (7), the first tail stay ( 8) The second support pole (71) and the second tail support pole (81) change to a posture that is highly compatible with the environment of the landing area to land. 6. The STOL/VTOL aircraft adopting variant landing gear according to claim 1 or 3, characterized in that: tail support vertical tail 2 (101), half retractable shell (123), upper rocker arm ( 124), bumper (125), lower rocker arm (126), the symmetry plane of rear wheel (127) unified coplanar.

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