CN116834945A - Variant fixed wing aircraft capable of folding wings - Google Patents

Abstract

The invention belongs to the technical field of aircrafts, and particularly discloses a variant fixed wing aircrafts capable of folding wings, which comprises a machine body, wherein one side of the machine body is provided with a wing, the inner wall of the machine body is fixedly connected with a first fixed rod, one side of the wing, which is close to the machine body, is provided with a first fixed frame, the first fixed frame is L-shaped, one side of the first fixed frame, which is close to the first fixed rod, is rotationally connected with the surface of the first fixed rod, one side of the first fixed frame, which is far away from the first fixed rod, is rotationally connected with a first transmission rod.

Description

Variant fixed wing aircraft capable of folding wings

Technical Field

The invention relates to the technical field of aircrafts, in particular to a variant fixed wing aircraft capable of folding wings.

Background

With the continuous expansion of the application field of the current vertical take-off and landing aircraft, the problem that the application of the existing vertical take-off and landing aircraft technology is hindered in certain specific environments is gradually obvious, the vehicle-mounted vertical take-off and landing aircraft takes off and lands in a narrow space, the flying efficiency of the fixed-wing aircraft in the vertical take-off and landing state is low, the problem that the vertical take-off and landing mode and the fixed-wing mode are difficult to switch and the like is solved, an innovative vertical take-off and landing aircraft design configuration is provided, the problem in the take-off and landing process and the mode switching process of the vertical take-off and landing aircraft can be effectively solved, the operability and the safety of the aircraft are enhanced, and the development of the aircraft industry is promoted.

The wings of the traditional vertical take-off and landing aircraft can not be folded in the vertical take-off and landing mode, larger moment of inertia can be generated during yaw, roll, pitch and other actions, the control of the aircraft is adversely affected, the deflection angular speed of the conventional fixed-wing aircraft in the vertical take-off and landing state is limited, and the control response time is prolonged.

Disclosure of Invention

The invention aims to provide a variant fixed wing aircraft capable of folding wings, which aims to solve the problem that the wings of the conventional vertical take-off and landing aircraft in the background art cannot be folded in a vertical take-off and landing mode.

In order to achieve the above purpose, the present invention provides the following technical solutions: the utility model provides a fixed wing aircraft of variant that can fold wing, includes the organism, one side of organism is provided with the wing, the inner wall fixedly connected with first dead lever of organism, one side that the wing is close to the organism is provided with first mount, first mount is the L shape, one side that first mount is close to first dead lever rotates with the surface of first dead lever to be connected, one side that first dead lever was kept away from to first mount rotates to be connected with first transfer line, one side that first transfer line was kept away from to first transfer line rotates to be connected with the head rod, one side that first transfer line was kept away from to the head rod rotates to be connected with the slip table, the inside fixedly connected with first motor of organism, the output fixedly connected with first threaded rod of first motor, the surface of first threaded rod and the inside threaded connection of slip table.

Preferably, the inside of organism is provided with the second motor, and the top fixedly connected with second transfer line of second motor, one side that the second transfer line kept away from the second motor rotates and is connected with the second connecting rod, and the inside fixedly connected with second dead lever of organism, one side fixedly connected with second mount that the wing is close to the organism, one side that the second mount is close to the second dead lever rotate with the surface of second dead lever to be connected, and one side that the second mount kept away from the second dead lever rotates with the surface of second connecting rod to be connected.

Preferably, the inside of wing is provided with the dead lever that extends to the wing outside, the inside fixedly connected with third motor of organism, the output fixedly connected with second threaded rod of third motor, the surface threaded connection of second threaded rod has the balladeur train, the balladeur train is the T font, the inside of balladeur train has been seted up and has been extended to the outside movable groove of balladeur train, the inside swing joint of movable groove has the movable rod that extends to the movable groove outside, one side and the surface rotation of dead lever of movable groove are connected in the movable rod, one side fixedly connected with third mount that the wing is close to the organism, one side that the third mount is close to the organism is rotated with the surface of organism and is connected.

Preferably, the inside fixedly connected with accommodate motor of organism, accommodate motor's output fixedly connected with driving gear, the inside of organism is provided with the rack, and one side that the rack is close to driving gear is provided with the tooth, and the rack passes through the tooth and is connected with the surface engagement of driving gear, and the bottom rotation of movable rod is connected with the universal joint, and the inside rotation of universal joint is connected with the driven gear that extends to the universal joint outside.

Preferably, the surface of the driven gear is in meshed connection with the surface of the rack.

Preferably, the inside fixedly connected with spacing of organism, one side of rack slip runs through the inside of spacing and extends to the outside of spacing, the inside sliding connection of surface and spacing of rack, and the cross-section of spacing is font.

Preferably, the inside fixedly connected with gear motor of wing, gear motor's output rotates the inside that runs through the wing and extends to the outside of wing, and gear motor's output fixedly connected with adjusting gear.

Preferably, an adjusting rod extending to the outside of the wing is rotatably connected to the inside of the wing, a fixed gear is fixedly connected to the outer surface of the adjusting rod, the fixed gear is in meshed connection with the surface of the adjusting gear, and one end, close to the first fixing frame, of the adjusting rod is rotatably connected with the first fixing frame through a bearing.

Compared with the prior art, the invention has the beneficial effects that: 1. this can fold variant fixed wing aircraft of wing makes first motor start through external control device, and first motor drives the slip table and removes under the restriction of first mount to make the slip table drive head rod and first transfer line and rotate, thereby make first mount rotate on first dead lever, thereby realize the backward folding of wing, utilize the longitudinal movement initiative control aircraft centre of gravity position of slide rail in the fuselage, or install the load of great weight on aircraft outer section wing, through increasing or reducing outer section wing folding angle control aircraft centre of gravity change.

2. This can fold variant fixed wing aircraft of wing makes gear motor start through the staff, gear motor rotates on fixed gear's surface through adjusting gear to make the wing rotate as the axis of rotation with adjusting the pole, thereby make the inclination of wing obtain changing, can effectively reduce aircraft windward area under the vertical take off and land mode, reduce flight resistance, obtain higher flight speed, and reduce aircraft wing span, the gesture of reinforcing perpendicular to the open air process controls ability and trafficability characteristic.

3. According to the variant fixed wing aircraft capable of folding the wing, the cross section of the limiting frame is -shaped, so that the moving direction of the rack is limited, and the position of the rack is positioned, so that the driving gear can drive the driven gear to rotate more smoothly through the rack, and the device can operate more smoothly.

Drawings

FIG. 1 is a schematic illustration of a modified fixed wing aircraft with foldable wings in accordance with the present invention;

FIG. 2 is a schematic view of a first fixing rod according to the present invention;

FIG. 3 is a schematic view of a second connecting rod according to the present invention;

FIG. 4 is a schematic view of a fixing rod according to the present invention;

FIG. 5 is a schematic view of the wing structure of the present invention;

FIG. 6 is a schematic view of the structure of the adjusting lever of the present invention.

In the figure: 1. a body; 2. a wing; 3. a first motor; 4. a first threaded rod; 5. a sliding table; 6. a first connecting rod; 7. a first transmission rod; 8. a first fixing rod; 9. a first fixing frame; 10. a second motor; 11. a second connecting rod; 12. the second fixing frame; 13. a second fixing rod; 14. a second transmission rod; 15. a third fixing frame; 16. a third motor; 17. a rack; 18. a universal joint; 19. a carriage; 20. a second threaded rod; 21. a movable groove; 22. a movable rod; 23. a driven gear; 24. a fixed rod; 25. adjusting a motor; 26. a drive gear; 27. a speed reducing motor; 28. an adjusting gear; 29. a fixed gear; 30. an adjusting rod; 31. and a limiting frame.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

Embodiment one:

referring to fig. 1-2, the present invention provides a technical solution: the utility model provides a can fold fixed wing aircraft of variant of wing, including organism 1, organism 1 is current structure, do not do too much in this, one side of organism 1 is provided with wing 2, the first dead lever 8 of inner wall fixedly connected with of organism 1, one side that wing 2 is close to organism 1 is provided with first mount 9, first mount 9 is L shape, one side that first mount 9 is close to first dead lever 8 is rotated with the surface of first dead lever 8 and is connected, one side that first mount 9 kept away from first dead lever 8 is rotated and is connected with first transfer line 7, one side that first transfer line 7 kept away from first mount 9 is rotated and is connected with head rod 6, one side that head rod 6 kept away from first transfer line 7 is rotated and is connected with slip table 5, the inside fixedly connected with first motor 3 of organism 1, first motor 3 is current structure, do not do too much in this, the output fixedly connected with first threaded rod 4 of first motor 3, the surface of first threaded rod 4 and the inside threaded connection of slip table 5.

The staff makes first motor 3 start through external control device, and first motor 3 drives slip table 5 under the restriction of first mount 9 and removes to make slip table 5 drive head rod 6 and first transfer line 7 and rotate, thereby make first mount 9 rotate on first dead lever 8, thereby realize the folding backward of wing 2, utilize the longitudinal movement of slide rail in the fuselage to initiatively control the aircraft centre of gravity position, or install the load of great weight on aircraft outer section wing 2, control aircraft centre of gravity change through increasing or reducing outer section wing 2 folding angle.

Embodiment two:

referring to fig. 3, the present invention provides a technical solution: the utility model provides a can fold variant fixed wing aircraft of wing, including organism 1, one side of organism 1 is provided with wing 2, the inside of organism 1 is provided with second motor 10, the top fixedly connected with second transfer line 14 of second motor 10, one side that second transfer line 14 kept away from second motor 10 rotates and is connected with second connecting rod 11, the inside fixedly connected with second dead lever 13 of organism 1, one side that wing 2 is close to organism 1 fixedly connected with second mount 12, one side that second mount 12 is close to second dead lever 13 rotates with the surface of second dead lever 13 to be connected, one side that second mount 12 kept away from second dead lever 13 rotates with the surface of second connecting rod 11 to be connected.

The second motor 10 is started by a worker, the second motor 10 drives the second transmission rod 14 to rotate, the second transmission rod 14 and the second connecting rod 11 drive the second fixing frame 12 and the wing 2 to rotate, the wing 2 is folded, the wing generates a change of a sweepback angle, the wing box is connected with the wing box and simultaneously controls the rear slight angle of the wings at the left side and the right side, the independent wing box and the independent push rod are allowed to be adopted for independently controlling one side of the wing, and the positioning component adopts a linear potentiometer or any linear distance measuring device or a potentiometer arranged on a positioning shaft of the bearing rod and is arranged on the wing box or the actuating rod for detecting the execution distance of the actuating rod or the folding angle of the wing.

Embodiment III:

referring to fig. 4-5, the present invention provides a technical solution: the utility model provides a can fold variant fixed wing aircraft of wing, including organism 1, one side of organism 1 is provided with wing 2, the inside of wing 2 is provided with the dead lever 24 that extends to the outside of wing 2, the inside fixedly connected with third motor 16 of organism 1, the output fixedly connected with second threaded rod 20 of third motor 16, the surface threaded connection of second threaded rod 20 has balladeur train 19, balladeur train 19 is the T font, the inside of balladeur train 19 has seted up the movable groove 21 that extends to the outside of balladeur train 19, the inside swing joint of movable groove 21 has the movable rod 22 that extends to the outside of movable groove 21, one side that movable rod 22 kept away from movable groove 21 and the surface swivelling joint of dead lever 24, one side that wing 2 is close to organism 1 is fixedly connected with third mount 15, one side that third mount 15 is close to organism 1 and the surface swivelling joint of organism 1.

The third motor 16 is started by a worker, the third motor 16 drives the second threaded rod 20 to rotate, the second threaded rod 20 drives the sliding frame 19 to move under the limit of the fixed rod 24, the movable rod 22 moves along with the sliding frame 19, the movable rod rotates and moves in the movable groove 21, and meanwhile the fixed rod 24 is driven to rotate, so that the wing 2 is folded.

Further, the inside fixedly connected with accommodate motor 25 of organism 1, accommodate motor 25 is the existing structure, do not do too much here and do not add in detail, accommodate motor 25's output fixedly connected with driving gear 26, the inside of organism 1 is provided with rack 17, one side that rack 17 is close to driving gear 26 is provided with the tooth, rack 17 is connected with the surface engagement of driving gear 26 through the tooth, the bottom rotation of movable rod 22 is connected with universal joint 18, the inside rotation of universal joint 18 is connected with the driven gear 23 that extends to the universal joint 18 outside, the surface engagement of driven gear 23 and rack 17 is connected.

Further, the reduction limiting frame 31 is fixedly connected to the inside of the machine body 1, one side of the rack 17 penetrates through the inside of the reduction limiting frame 31 in a sliding mode and extends to the outside of the reduction limiting frame 31, the surface of the rack 17 is connected with the inside of the reduction limiting frame 31 in a sliding mode, and the section of the reduction limiting frame 31 is -shaped.

By reducing the cross section of the limit frame 31 to be , the moving direction of the rack 17 is limited, and the position of the rack 17 is positioned, so that the driving gear 26 can drive the driven gear 23 to rotate more smoothly through the rack 17, and the device can operate more smoothly.

The operator starts the adjusting motor 25, so that the adjusting motor 25 drives the rack 17 to move through the driving gear 26, and the driven gear 23 rotates.

Embodiment four:

based on the first embodiment:

referring to fig. 6, the present invention provides a technical solution: the utility model provides a can fold fixed wing aircraft of variant of wing, including organism 1, organism 1 is current structure, do not do too much in this, one side of organism 1 is provided with wing 2, the first dead lever 8 of inner wall fixedly connected with of organism 1, one side that wing 2 is close to organism 1 is provided with first mount 9, first mount 9 is L shape, one side that first mount 9 is close to first dead lever 8 is rotated with the surface of first dead lever 8 and is connected, one side that first mount 9 kept away from first dead lever 8 is rotated and is connected with first transfer line 7, one side that first transfer line 7 kept away from first mount 9 is rotated and is connected with head rod 6, one side that head rod 6 kept away from first transfer line 7 is rotated and is connected with slip table 5, the inside fixedly connected with first motor 3 of organism 1, first motor 3 is current structure, do not do too much in this, the output fixedly connected with first threaded rod 4 of first motor 3, the surface of first threaded rod 4 and the inside threaded connection of slip table 5.

Further, the inside fixedly connected with gear motor 27 of wing 2, gear motor 27 is current structure, does not do too much in this and does not overlap, and gear motor 27's output rotates and runs through the inside of wing 2 and extend to the outside of wing 2, and gear motor 27's output fixedly connected with adjusting gear 28.

Further, an adjusting rod 30 extending to the outside of the wing 2 is rotatably connected to the inside of the wing 2, a fixed gear 29 is fixedly connected to the outer surface of the adjusting rod 30, the fixed gear 29 is in meshed connection with the surface of the adjusting gear 28, and one end, close to the first fixing frame 9, of the adjusting rod 30 is rotatably connected with the first fixing frame 9 through a bearing.

The gear motor 27 is started by a worker, the gear motor 27 rotates on the surface of the fixed gear 29 through the adjusting gear 28, so that the wing 2 rotates by taking the adjusting rod 30 as a rotating shaft, the inclination angle of the wing 2 is changed, the windward area of the aircraft can be effectively reduced in a vertical take-off and landing mode, the flying resistance is reduced, the higher flying speed is obtained, the wing of the aircraft is reduced, and the attitude control capability and the trafficability in the vertical take-off process are enhanced.

The main actuating mechanism of the configuration is a tilting mechanism and a folding mechanism, wherein the tilting mechanism is defined as a mechanism for changing the installation angle between the wing and the horizontal line, the folding mechanism is defined as a mechanism for changing the rear slight angle of the wing, and the two mechanisms can be independently operated or simultaneously operated.

The tilting mechanism mainly comprises a fixed rod 24, an actuating component and a positioning component, wherein the fixed rod 24 is overlapped with a wing bearing shaft and is connected with a wing box, the fixed rod 24 can rotate around the axis of the fixed rod 24 relative to the wing box, the fixed rod 24 is rigidly connected with a wing connecting part, when the fixed rod 24 rotates, the wing can be driven to rotate simultaneously,

the actuating element may consist of a steering engine, hydraulic lever, electric worm, gear set, in one example consisting of gear set, the actuating element is designed as a face gear mounted on the wing box and a circular gear mounted on the fixed lever 24 intermesh, the wing produces a change in sweep angle when the aircraft performs a folding action, and interacts with the face gear fixed to the fuselage, driving the circular gear to rotate with the fixed lever 24. Wherein the plane gear fixed on the machine body can be independently controlled by the steering engine.

The positioning component detects the tilting angle of the wing, and the positioning is realized by a potentiometer on the steering engine or a potentiometer independently arranged on the fixed rod 24, a linear potentiometer or an encoder on the face gear, and the like.

Four propulsion systems are symmetrically arranged on left and right wings of the fuselage in a 2+2 tilting arrangement, wherein the propulsion systems can be arranged on an upper wing surface, a lower wing surface, a front edge or a rear edge of the wings in the 2+2 tilting arrangement, and the wings can be designed to tilt forwards or backwards in the tilting arrangement.

The tilting mechanism and the folding mechanism are connected with each side wing, the folding mechanism can be arranged inside or outside the fuselage, and the tilting mechanism is arranged at one end of the movable wing close to the fuselage.

When the 2+2 tilting layout is adopted, the aircraft needs to adopt a variable gravity center design, the aircraft is controlled by the sliding rail in the aircraft body or energy supply equipment such as a battery is arranged on the wing, the gravity center position of the aircraft is actively controlled by utilizing the longitudinal movement of the sliding rail in the aircraft body, or a load with larger weight is arranged on the outer section wing of the aircraft, and the gravity center change of the aircraft is controlled by increasing or reducing the folding angle of the outer section wing.

When the structure adopts 2+1 tilting layout, a group of propulsion systems are symmetrically arranged on the left side and the right side of the wing, wherein the propulsion systems can be designed on the front edge, the rear edge, the upper wing surface and the lower wing surface of the wing. When a conventional or double tail boom configuration is employed, a downward propulsion system is designed at the rear of the fuselage or nose, which requires at a minimum a vector thrust control capability with a heading (yaw) axis, while a vector thrust control capability with a pitch (pitch) axis can be selectively added, and when the tail propulsion system has a pitch axis vector thrust control capability, the propulsion system will be used simultaneously for fixed wing mode operation. When the main wing face is designed later or in a duck wing configuration, a downward propulsion system is designed below the nose that requires at a minimum a vector thrust control capability with a heading (yaw) axis.

When the structure adopts a 2+1 tilting layout and the downward propulsion system of the tail or the head lacks vector control capability, the aileron control surface can be adopted to perform yaw control, and when the control is performed, the propulsion system installed on the wing is installed in the direction of tilting to the wing tip and the propulsion airflow passes through the aileron control surface

When the aircraft adopts the 2+1 tilting layout, no additional gravity center control device or a relatively small gravity center control device is required, the configuration needs to adopt 2 tilting forces at least, when the 2 tilting layout is adopted and vector power is not available, the configuration needs to adopt a tilting take-off mode when vertical take-off and landing activities are executed, namely only the wing installation angle is changed, at the moment, the folding mechanism is forbidden to use, and the thrust line of the tilting layout power system passes through the gravity center of the aircraft in the vertical direction.

When the 2-tilting layout is adopted and the three-element vector power is provided, the flying can take off in a tilting and folding mode, under the vertical take-off and landing mode, the folding mechanism is completely folded and the tilting mechanism acts to enable the front edge to vertically face upwards, the thrust line passes through the gravity center of the aircraft, the attitude of the aircraft is controlled by utilizing the vector direction parallel to the front edge of the wing, and in the process of switching from the vertical take-off and landing mode to the fixed wing mode, the stable flying in the switching process is realized through vector control equipment parallel to and perpendicular to the front edge of the aircraft.

The ternary vector power in the example is power capable of randomly changing the thrust angle in the directions of a transverse axis and a longitudinal axis, wherein the power source can be a gas turbine, a piston engine, a motor and the like, and the power equipment is installed in a direction that the chord line of the power equipment faces to the flight direction. The thrust direction is controlled to move along the plane direction formed by the vertical axis of the aircraft and the longitudinal axis of the aircraft by the vector control group in the vertical take-off and landing stage, and the thrust direction is controlled to move along the plane direction formed by the vertical axis of the aircraft and the longitudinal axis of the aircraft in the transition stage, and the thrust direction is turned from being parallel to the vertical axis direction to being parallel to the longitudinal axis of the aircraft and is not deflected in the transverse axis direction.

The aircraft described herein is capable of achieving stable flight during transitions between forward flight and hover configurations, and in some embodiments, may utilize a flight control system to achieve stability during hover and slow flight. Typical flight control systems are known in the art for four-axis aircraft and other aircraft using multiple engines and tilting engines. Typically, these systems employ proportional-integral control (P1D) control feedback loops to adjust the throttle of each engine or other propulsion unit in response to aircraft speed, attitude, altitude, and other flight parameters detected using various sensors, such as gyroscopes, altimeters, GPS and other position data, and the like. When an aircraft wing adopts a vertical take-off mode, the front edge of the wing is required to be upwards relative to the ground in a vertical take-off and landing state. When the aircraft wing is in a forward tilting mode, a duck wing structure is required, and a horizontal stabilizer is arranged in front of the main wing, wherein the power aircraft can adopt a V22 hawk control mode.

The structure is designed with a locking mechanism or a stop block when the tilting angle is 0 and 90 degrees, and the locking mechanism can adopt modes including but not limited to a bolt, a dead point of a connecting rod mechanism, a worm self-locking mode and the like, and can be inserted into the front edge of an outer wing from a wing root by utilizing a bearing shaft capable of moving in a straight line in a fixed wing flight mode, and the rear edge or the vicinity of a pneumatic focus is used as a bearing mechanism. The tilt angle and the folding angle of the outer section wing of the structure can be reduced along with the increase of airspeed. The wing mounting angle can be independently changed in the fixed wing flight mode, and a larger lift coefficient can be obtained in the short-distance take-off and landing mode, so that a shorter take-off distance can be obtained.

The conversion speed of the tilting mechanism is not in absolute relation with the conversion of the folding mechanism, the whole process of the tilting action can be controlled to a certain extent, the range or the whole process of the tilting action, the state that the folding mechanism operates or is static but the tilting mechanism maintains any tilting angle for a certain time is allowed to occur in the process of implementing the tilting action, and the state that the tilting mechanism operates or is static but the folding mechanism maintains any folding angle for a certain time is also allowed to occur.

Working principle: for the variant fixed wing aircraft capable of folding the wing, firstly, a speed reducing motor 27 is started by a worker, the speed reducing motor 27 rotates on the surface of a fixed gear 29 through an adjusting gear 28, so that the wing 2 rotates on the first fixed rod 8 by taking an adjusting rod 30 as a rotating shaft, the inclination angle of the wing 2 is changed, the windward area of the aircraft can be effectively reduced, the flying resistance is reduced, the higher flying speed is obtained, the wing spread of the aircraft is reduced, the attitude control capability and the trafficability in the vertical lifting process are enhanced, the first motor 3 is started by an external control device, the first motor 3 drives a sliding table 5 to move under the limitation of a first fixing frame 9, the sliding table 5 drives a first connecting rod 6 to rotate with a first transmission rod 7, the first fixing frame 9 rotates on the first fixed rod 8, the backward folding of the wing 2 is realized, the longitudinal movement of a sliding rail in a fuselage is utilized to actively control the heavy load on the outer section 2 of the aircraft, and the folding angle of the aircraft is controlled to change by increasing or decreasing the folding angle of the outer section 2 of the wing.

Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims (8)

1. The utility model provides a can fold variant fixed wing aircraft of wing, includes organism (1), and one side of organism (1) is provided with wing (2), its characterized in that: the inner wall fixedly connected with first dead lever (8) of organism (1), one side that wing (2) is close to organism (1) is provided with first mount (9), first mount (9) are L shape, one side that first mount (9) is close to first dead lever (8) rotates with the surface of first dead lever (8) to be connected, one side that first mount (9) was kept away from first dead lever (8) rotates and is connected with first transfer line (7), one side that first transfer line (7) was kept away from first mount (9) rotates and is connected with head rod (6), one side that head rod (6) was kept away from first transfer line (7) rotates and is connected with slip table (5), the inside fixedly connected with first motor (3) of organism (1), the output fixedly connected with first threaded rod (4) of first motor (3), the surface of first threaded rod (4) and the internal thread connection of slip table (5).

2. A variable fixed wing aircraft with foldable wings as claimed in claim 1, wherein: the inside of organism (1) is provided with second motor (10), the top fixedly connected with second transfer line (14) of second motor (10), one side that second transfer line (14) kept away from second motor (10) rotates and is connected with second connecting rod (11), the inside fixedly connected with second dead lever (13) of organism (1), one side fixedly connected with second mount (12) that wing (2) is close to organism (1), one side that second mount (12) is close to second dead lever (13) rotates with the surface of second dead lever (13) to be connected, one side that second mount (12) kept away from second dead lever (13) rotates with the surface of second connecting rod (11) to be connected.

3. A variable fixed wing aircraft with foldable wings as claimed in claim 2, wherein: the inside of wing (2) is provided with dead lever (24) that extend to wing (2) outside, the inside fixedly connected with third motor (16) of organism (1), the output fixedly connected with second threaded rod (20) of third motor (16), the surface threaded connection of second threaded rod (20) has balladeur train (19), balladeur train (19) are T font, movable groove (21) that extend to balladeur train (19) outside are seted up to the inside of balladeur train (19), the inside swing joint of movable groove (21) has movable rod (22) that extend to movable groove (21) outside, one side that movable rod (22) kept away from movable groove (21) is connected with the surface rotation of dead lever (24), one side that wing (2) are close to organism (1) is fixedly connected with third mount (15), one side that third mount (15) are close to organism (1) is connected with the surface rotation of organism (1).

4. A variable fixed wing aircraft with foldable wings as claimed in claim 1, wherein: the inside fixedly connected with accommodate motor (25) of organism (1), the output fixedly connected with driving gear (26) of accommodate motor (25), the inside of organism (1) is provided with rack (17), one side that rack (17) is close to driving gear (26) is provided with tooth, rack (17) are connected through tooth and the surface engagement of driving gear (26), the bottom rotation of movable rod (22) is connected with universal joint (18), the inside rotation of universal joint (18) is connected with driven gear (23) that extend to the outside of universal joint (18).

5. A variable geometry fixed wing aircraft with foldable wings as claimed in claim 4, wherein: the surface of the driven gear (23) is connected with the surface of the rack (17) in a meshed manner.

6. A variable fixed wing aircraft with foldable wings as claimed in claim 1, wherein: the inside fixedly connected with spacing (31) of organism (1), one side of rack (17) slip runs through the inside of spacing (31) and extends to the outside of spacing (31), the inside sliding connection of surface and spacing (31) of rack (17), and the cross-section of spacing (31) is font.

7. A variable fixed wing aircraft with foldable wings as claimed in claim 1, wherein: the inside fixedly connected with gear motor (27) of wing (2), the output of gear motor (27) rotates and runs through the inside of wing (2) and extends to the outside of wing (2), and the output fixedly connected with adjusting gear (28) of gear motor (27).

8. A variable fixed wing aircraft with foldable wings as claimed in claim 1, wherein: the inside rotation of wing (2) is connected with and extends to the outside regulation pole (30) of wing (2), and the surface fixedly connected with fixed gear (29) of regulation pole (30), the surface engagement of fixed gear (29) and regulation gear (28) is connected, and the one end that is close to first mount (9) of regulation pole (30) is rotated with first mount (9) through the bearing and is connected.