Air-ground aircraft with telescopic side wings and telescopic empennage

Abstract

The invention relates to an air-ground aircraft with telescopic side wings and telescopic empennages. The air-ground aircraft is characterized by comprising a cabin body, driving wheel mechanisms, the telescopic side wings, telescopic empennage mechanisms and horizontal flight propellers. When running on the road, the three-dimensional parking garage does not occupy too much road space, does not cross several lanes to run, does not affect normal running of vehicles on other lanes, can be driven into a garage to be parked and can also be parked everywhere like common cars and vehicles, the parking range is greatly widened, and the parking efficiency is improved. The horizontal flight propeller can be driven into a field of municipal public charging facilities for charging and energy supply, charging and energy supply are more convenient, airflow output of the horizontal flight propeller is not blocked, better flight propulsive force can be obtained, and flight is more reliable. Meanwhile, the telescopic empennage mechanism can stretch and contract, the balance and stability of flight can be guaranteed during stretching flight, and the occupied road space can be reduced when the telescopic empennage mechanism walks on the land after contraction.

Description

Technical Field

[0001] The present invention relates to the field of land-air dual-purpose vehicles, and in particular to a land-air vehicle with retractable side wings and a retractable tail wing. Background Art

[0002] A land-air dual-purpose vehicle refers to a vehicle that can both travel on the ground and fly in the air. Among the existing land-air dual-purpose vehicles, for example, a technical solution disclosed in a Chinese patent document with a patent application number of 201710989360.2 and a title of "Control System for Land-Air Dual-Purpose Vehicle" mainly consists of a vehicle, a left wing disposed on the left side of the vehicle, a foldable left small wing, a right wing disposed on the right side of the vehicle, a foldable right small wing, and a rotatable rotor engine disposed on the left wing and the right wing. In the takeoff state, the axis of the rotor engine is perpendicular to the horizontal plane to achieve the purpose of ascending and descending in the air. In the flight gliding state, the axis of the rotor engine is parallel to the horizontal plane, and the wings on both left and right sides of the vehicle are used to achieve the purpose of flying in the air by gliding. In the ground travel state, the wheels of the vehicle itself are used to achieve the purpose of traveling on land. However, in practical applications, the land-air dual-purpose vehicle still has the following deficiencies: First, although both the left and right wings can be folded and stored to reduce the overall volume of the land-air dual-purpose vehicle, even after the wings are folded, they are still exposed outside and protrude significantly from the fuselage. When traveling on the road, it will occupy a large amount of road space, span several lanes, affect the normal driving of vehicles in other lanes, and cannot be driven into a garage for parking like a vehicle. It can only be parked in an open area or a dedicated helicopter apron. Even when parked in a surface parking lot, it also requires several parking spaces, affecting the normal parking of other vehicles, and its parking range is very limited. At the same time, due to its large volume, it cannot drive into the site of municipal public charging facilities for charging and energy supply like a vehicle, resulting in very inconvenient charging and energy supply. Second, during flight, the tail gas output of the rotor engine is blocked by the wings, resulting in unsmooth air flow, affecting power output, greatly reducing the flight propulsion force, and also affecting flight safety. Third, since the land-air dual-purpose vehicle lacks a flight tail wing, it is difficult to ensure flight balance and stability during flight, easily causing serious accidents such as loss of control and rollover, and having low flight safety. Therefore, based on the above deficiencies, the applicant believes that further improvements need to be made to the existing land-air dual-purpose vehicle to better meet the actual application needs of people. Summary of the Invention

[0003] The object of the present invention is to solve the above problems and deficiencies, and provide an air-land vehicle with retractable side wings and a retractable tail wing. When the air-land vehicle is traveling on the road, it will not occupy too much road space, nor will it straddle several lanes, and will not affect the normal driving of vehicles in other lanes. It can drive into the garage for parking, and can also be parked everywhere like an ordinary car, greatly improving the parking range. It can also drive into the site of municipal public charging facilities for charging and energy supply, making the charging and energy supply more convenient. Moreover, the air flow output of the horizontal flight propeller is not blocked, and better flight propulsion force can be obtained, making the flight more reliable. At the same time, the retractable tail wing mechanism can be extended and retracted. When extended during flight, it can ensure the balance and stability of flight, and when retracted, it can also reduce the occupation of road space during land travel.

[0004] The technical solution of the present invention is realized as follows: An air-land vehicle with retractable side wings and a retractable tail wing, characterized in that it includes a cabin body for carrying goods or passengers; a plurality of drive wheel mechanisms arranged at the bottom of the cabin body for traveling on land; a pair of retractable side wings arranged on the left and right sides of the cabin body, which are in an extended state during gliding flight and are in a state of being stored inside the left and right sides of the cabin body during land travel; a retractable tail wing mechanism arranged at the rear end of the cabin body, which is composed of a vertical fixed column, a retractable tail beam, a retractable horizontal tail wing and a vertical tail wing. When the retractable tail wing mechanism is in gliding flight, the retractable tail beam and the retractable horizontal tail wing are in an extended state, and when traveling on land, the retractable tail beam and the retractable horizontal tail wing are in a retracted state; a horizontal flight propeller arranged at the rear end of the cabin body.

[0005] Preferably, the retractable tail beam includes a first tail beam shell, a second tail beam shell and a third tail beam shell sleeved together in sequence. A tail beam telescopic push rod for driving the second tail beam shell and the third tail beam shell to move is also arranged in the first tail beam shell; the first tail beam shell is fixed on the vertical fixed column, and a sleeve hole for sleeving and fixing the retractable horizontal tail wing is also arranged on the third tail beam shell.

[0006] Preferably, the retractable horizontal tail wing is composed of a left retractable tail wing and a right retractable tail wing assembled together; the left retractable tail wing and the right retractable tail wing respectively include a first tail wing shell, a second tail wing shell and a third tail wing shell sleeved together in sequence. A tail wing telescopic push rod for driving the second tail wing shell and the third tail wing shell to move is also arranged in the first tail wing shell.

[0007] Preferably, the retractable side wing includes a first wing shell, a second wing shell and a third wing shell sleeved together in sequence. A wing telescopic push rod for driving the second wing shell and the third wing shell to move is also arranged in the first wing shell.

[0008] Preferably, the horizontal flight thruster is composed of a telescopic support rod and a power propulsion rotor mechanism connected to the rear end of the cabin body through the telescopic support rod; a storage cavity is provided at the rear end of the cabin body, and a back cover door that can be electrically opened and closed is also provided at the rear end of the cabin body to cover the storage cavity. The power propulsion rotor mechanism is received into the storage cavity or extended out of the storage cavity through the telescopic support rod.

[0009] Preferably, the present invention further includes an extensible frame mechanism provided on the cabin body and four flight rotor mechanisms that are distributed around the cabin body by using the extensible frame mechanism. The extensible frame mechanism is in an extended state during takeoff and landing and drives the four flight rotor mechanisms to extend out of the cabin body, and is in a contracted state during gliding flight or land walking and drives the four flight rotor mechanisms to be received and hidden inside the cabin body.

[0010] Preferably, the cabin body includes a cockpit and storage compartments that can be electrically opened and closed provided on both the left and right sides of the cockpit; the cockpit is composed of a cockpit cover and a cockpit chassis connected together, and a manned and cargo-carrying driving space is formed between the cockpit cover and the cockpit chassis; the storage compartment is composed of a storage cover, a storage chassis, and an electric opening and closing mechanism. The storage cover is electrically connected to the storage chassis or the cockpit cover through the electric opening and closing mechanism. A storage space for receiving and hiding the flight rotor mechanism and the extensible frame mechanism is formed between the storage cover and the storage chassis, and the storage chassis and the cockpit chassis are of an integral structure.

[0011] Preferably, a hemispherical disc cover is further provided on the bottom of the cabin body to cover the telescopic side wing, and the movable end of the telescopic side wing and the bottom end of the drive wheel mechanism respectively extend out of the hemispherical disc cover; the drive wheel mechanism includes a walking wheel and a vertical telescopic leg, and the walking wheel is connected to the bottom of the cabin body through the vertical telescopic leg.

[0012] Advantages of the present invention: Since the telescopic side wings on both left and right sides of the cabin body are in a state of being stored inside the cabin body on both left and right sides when walking on land, when driving on the road, the overall width dimension of the land-air vehicle after storage can be greatly reduced, without occupying too much road space, nor driving across several lanes, thus not affecting the normal driving of vehicles in other lanes. At the same time, it can reduce the wind resistance when driving on land or on the road, reduce energy consumption, and at the same time enable it to drive into the garage for parking, and can also be parked everywhere like an ordinary car, greatly improving the parking range of the land-air vehicle. It can also drive into the site of municipal public charging facilities for charging and energy supply at will like a new energy vehicle, and the charging and energy supply are more convenient. Moreover, the horizontal flight propeller is arranged at the rear end of the cabin body, and the air flow output will not be blocked, which will not affect the power output, so as to obtain better flight propulsion force and make the flight more reliable. At the same time, since the land-air vehicle is provided with a telescopic tail wing mechanism; when flying, the telescopic tail beam and the telescopic horizontal tail wing are in an extended state, which can greatly improve the flight balance and stability, greatly reduce the occurrence of serious accidents such as out of control and rollover, and improve flight safety; when walking on land, the telescopic tail beam and the telescopic horizontal tail wing are in a contracted state, which can greatly reduce the overall volume of the land-air vehicle after storage, so as to reduce the occupation of road space. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a three-dimensional structural schematic diagram of the present invention in the land driving state.

[0014] Figure 2 It is a three-dimensional structural schematic diagram of the present invention in the state of unfolding the telescopic tail wing mechanism and the telescopic side wings.

[0015] Figure 3 It is a sectional structural schematic diagram of the telescopic tail beam in the present invention.

[0016] Figure 4 It is a sectional structural schematic diagram of the telescopic horizontal tail wing in the present invention.

[0017] Figure 5 It is a sectional structural schematic diagram of the telescopic side wing in the present invention.

[0018] Figure 6 It is a three-dimensional structural schematic diagram of the first embodiment of the present invention with an extended skeleton mechanism.

[0019] Figure 7 It is a three-dimensional structural schematic diagram of the first embodiment of the present invention in the state of unfolding the extended skeleton mechanism.

[0020] Figure 8 It is a three-dimensional structural schematic diagram of the first embodiment of the extended skeleton mechanism in the present invention.

[0021] Figure 9 Schematic three-dimensional structure diagram of the storage cavity at the rear end of the cabin body of the present invention in the open state.

[0022] Figure 10 Schematic cross-sectional structure diagram of the present invention.

[0023] Figure 11 Schematic three-dimensional structure diagram of the second embodiment of the present invention with an extensible frame mechanism.

[0024] Figure 12 Schematic three-dimensional structure diagram of the present invention in the second embodiment of deploying the extensible frame mechanism.

[0025] Figure 13 Schematic disassembly structure diagram of the second embodiment of the extensible frame mechanism and the cabin body of the present invention.

[0026] Figure 14 Schematic cross-sectional structure diagram of the first embodiment of the tail beam telescopic push rod, tail wing telescopic push rod, wing telescopic push rod, telescopic support rod, vertical telescopic leg, left telescopic cross bar, right telescopic cross bar, front telescopic longitudinal bar, and rear telescopic longitudinal bar of the present invention.

[0027] Figure 15 Schematic cross-sectional structure diagram of the second embodiment of the tail beam telescopic push rod, tail wing telescopic push rod, wing telescopic push rod, telescopic support rod, vertical telescopic leg, left telescopic cross bar, right telescopic cross bar, front telescopic longitudinal bar, and rear telescopic longitudinal bar of the present invention.

[0028] Figure 16 Schematic cross-sectional structure diagram of the horizontal flight thruster and the flight rotor mechanism of the present invention.

[0029] Figure 17 Schematic three-dimensional structure diagram of the walking wheel of the present invention.

[0030] Figure 18 Schematic cross-sectional structure diagram of the electric roller of the present invention. Detailed implementation manners

[0031] Such as Figure 1 And Figure 2As shown in the figure, an air-land vehicle with retractable side wings and a retractable tail includes a cabin body 1 for carrying goods or passengers; a plurality of drive wheel mechanisms 2 arranged at the bottom of the cabin body 1 for walking on land; a pair of retractable side wings 3 arranged on the left and right sides of the cabin body 1, which are in an extended state during gliding flight and are in a state of being stored inside the left and right sides of the cabin body 1 during land travel; a retractable tail mechanism 4 arranged at the rear end of the cabin body 1, which is composed of a vertical fixed column 41, a retractable tail beam 42, a retractable horizontal tail 43 and a vertical tail 44. When the retractable tail mechanism 4 is in gliding flight, the retractable tail beam 42 and the retractable horizontal tail 43 are in an extended state, and when traveling on land, the retractable tail beam 42 and the retractable horizontal tail 43 are in a contracted state; a horizontal flight thruster 5 arranged at the rear end of the cabin body 1. By setting the retractable tail beam 42, during flight, the length of the retractable tail beam 42 can be extended. From a mechanical perspective, a longer tail beam can increase the length of the force arm, thereby increasing the torque, which helps to balance and stabilize the flight state of the air-land vehicle. By setting the retractable horizontal tail 43, it can be responsible for controlling the pitch attitude of the aircraft and preventing it from getting out of control due to diving or raising the head. By setting the vertical tail 44, it can be used to control the yaw of the aircraft, that is, left and right turning, so that the air-land vehicle can maintain a straight course during flight and prevent deviation from the predetermined route.

[0032] In order to further improve the structure of the retractable tail beam 42, as Figure 3 shown, the retractable tail beam 42 includes a first tail beam housing 421, a second tail beam housing 422, and a third tail beam housing 423 that are sleeved together in sequence. A tail beam telescopic push rod 424 for driving the second tail beam housing 422 and the third tail beam housing 423 to move is also provided in the first tail beam housing 421; the first tail beam housing 421 is fixed on the vertical fixed column 41, and a sleeve hole 425 for the retractable horizontal tail 43 to be sleeved and fixed is also provided on the third tail beam housing 423. Specifically, the second tail beam housing 422 is sleeved in the first tail beam housing 421, and the third tail beam housing 423 is sleeved in the second tail beam housing 422. Through such a three-stage telescopic structure, the length of the retractable tail beam 42 can be long enough after extension and short enough after contraction, which is very practical. By setting the sleeve hole 425, it is convenient to be sleeved and connected with the retractable horizontal tail 43. In actual installation, the retractable horizontal tail 43 can also be further fixedly connected by connection methods such as welding and screw locking to make the connection more stable and reliable. In order to make the telescopic structure of the retractable tail beam 42 have the characteristics of simple structure, easy implementation, high reliability, etc., as Figure 3As shown, both ends of the tail beam telescopic push rod 424 are respectively fixed on the first tail beam housing 421 and the third tail beam housing 423. A first guiding anti - detachment convex ring portion 426 and a second guiding anti - detachment convex ring portion 427 which are matched with each other are respectively arranged between the first tail beam housing 421 and the second tail beam housing 422, and between the second tail beam housing 422 and the third tail beam housing 423. A first convex block portion 428 which can push the second tail beam housing 422 to perform a retracting movement action is further arranged on the third tail beam housing 423. Specifically, the second guiding anti - detachment convex ring portion 427 of the third tail beam housing 423 is arranged at the inner end of the third tail beam housing 423, and the second guiding anti - detachment convex ring portion 427 of the third tail beam housing 423 is arranged in a manner of abutting against the inner wall of the second tail beam housing 422. The first guiding anti - detachment convex ring portion 426 of the second tail beam housing 422 is arranged at the outer end of the second tail beam housing 422, and the first guiding anti - detachment convex ring portion 426 of the second tail beam housing 422 is arranged in a manner of abutting against the outer side wall of the third tail beam housing 423. When the telescopic tail beam 42 needs to be deployed, the third tail beam housing 423 is pushed by the tail beam telescopic push rod 424 to move. When the second guiding anti - detachment convex ring portion 427 of the third tail beam housing 423 hooks the first guiding anti - detachment convex ring portion 426 of the second tail beam housing 422, the second tail beam housing 422 can be driven to move so as to realize the deployment. The second guiding anti - detachment convex ring portion 427 of the second tail beam housing 422 is arranged at the inner end of the second tail beam housing 422, and the second guiding anti - detachment convex ring portion 427 of the second tail beam housing 422 is arranged in a manner of abutting against the inner wall of the first tail beam housing 421. The first guiding anti - detachment convex ring portion 426 of the first tail beam housing 421 is arranged at the outer end of the first tail beam housing 421, and the first guiding anti - detachment convex ring portion 426 of the first tail beam housing 421 is arranged in a manner of abutting against the outer side wall of the second tail beam housing 422. When the telescopic tail beam 42 needs to be deployed, it can prevent the second tail beam housing 422 and the first tail beam housing 421 from loosening and falling off. More specifically, the first convex block portion 428 is arranged at the outer end of the third tail beam housing 423. When the telescopic tail beam 42 needs to be retracted, the third tail beam housing 423 is pulled by the tail beam telescopic push rod 424 to perform a retracting movement. And when the third tail beam housing 423 retracts into the second tail beam housing 422, the first convex block portion 428 can abut against the second tail beam housing 422 so that the third tail beam housing 423 and the second tail beam housing 422 move into the first tail beam housing 421 together to realize the retraction. In actual production and manufacturing, the first convex block portion 428 is fixed on the third tail beam housing 423 by means of welding or screw locking. In actual application, the number of the vertical fixing columns 41 and the telescopic tail beams 42 is two, and the two vertical fixing columns 41 and the two telescopic tail beams 42 are arranged at intervals in a left - right symmetric manner. More specifically, the vertical fixing columns 41 are fixed on the back cover door 102.

[0033] In order to further improve the structure of the retractable horizontal tail 43, as Figure 4 shown, the retractable horizontal tail 43 is composed of a left retractable tail 431 and a right retractable tail 432 assembled together; the left retractable tail 431 and the right retractable tail 432 respectively include a first tail housing 433, a second tail housing 434, and a third tail housing 435 sleeved together in sequence, and a tail retractable push rod 436 for driving the second tail housing 434 and the third tail housing 435 to move is further provided in the first tail housing 433. Specifically, the second tail housing 434 is sleeved in the first tail housing 433, and the third tail housing 435 is sleeved in the second tail housing 434. Through such a three-stage telescopic structure, the lengths of the left retractable tail 431 and the right retractable tail 432 can be long enough after expansion and short enough after contraction, which is very practical. In actual installation, the first tail housing 433 of the left retractable tail 431 and the first tail housing 433 of the right retractable tail 432 are fixed together by connection methods such as welding and screw locking; and the vertical tail 44 is fixed on the third tail housing 435 by connection methods such as welding and screw locking. In order to make the telescopic structure of the left retractable tail 431 and the right retractable tail 432 have the characteristics of simple structure, easy implementation, high reliability, etc., as Figure 4As shown, both ends of the tail wing telescopic push rod 436 are respectively fixed on the first tail wing housing 433 and the third tail wing housing 435. A third guiding and anti - detachment convex ring part 437 and a fourth guiding and anti - detachment convex ring part 438 which are matched with each other are respectively arranged between the first tail wing housing 433 and the second tail wing housing 434, and between the second tail wing housing 434 and the third tail wing housing 435. A second convex block part 439 which can push the second tail wing housing 434 to perform a retracting movement action is also arranged on the third tail wing housing 435. Specifically, one of the fourth guiding and anti - detachment convex ring parts 438 is arranged at the inner end of the third tail wing housing 435, and this fourth guiding and anti - detachment convex ring part 438 is arranged in a manner of abutting against the inner wall of the second tail wing housing 434. The other fourth guiding and anti - detachment convex ring part 438 is arranged at the inner end of the second tail wing housing 434, and this fourth guiding and anti - detachment convex ring part 438 is arranged in a manner of abutting against the inner wall of the first tail wing housing 433. One of the third guiding and anti - detachment convex ring parts 437 is arranged at the outer end of the second tail wing housing 434, and this third guiding and anti - detachment convex ring part 437 is arranged in a manner of abutting against the outer side wall of the third tail wing housing 435. The other third guiding and anti - detachment convex ring part 437 is arranged at the outer end of the first tail wing housing 433, and this third guiding and anti - detachment convex ring part 437 is arranged in a manner of abutting against the outer side wall of the second tail wing housing 434. In actual production and manufacturing, the second convex block part 439 is fixed on the outer end of the third tail wing housing 435 by welding or screw locking. Thus, it can be known that the telescopic working principle of the left telescopic tail wing 431 and the right telescopic tail wing 432 is the same as that of the telescopic tail beam 42. Therefore, the telescopic movement process of the left telescopic tail wing 431 and the right telescopic tail wing 432 will not be elaborated too much here.

[0034] In order to further improve the structure of the telescopic side wing 3, as Figure 5 shown, the telescopic side wing 3 includes a first wing housing 31, a second wing housing 32, and a third wing housing 33 which are sleeved together in sequence. A wing telescopic push rod 34 for driving the second wing housing 32 and the third wing housing 33 to move is also arranged in the first wing housing 31. Specifically, the second wing housing 32 is sleeved in the first wing housing 31, and the third wing housing 33 is sleeved in the second wing housing 32. Through such a three - stage telescopic structure, the telescopic side wing 3 can have a long enough length after being deployed and a short enough length after being retracted, which is very practical. In actual installation, the first tail wing housings 433 of the two telescopic side wings 3 are fixed together by connection methods such as welding and screw locking. In order to make the telescopic structure of the telescopic side wing 3 have the characteristics of simple structure, easy implementation, high reliability, etc., as Figure 5As shown, the two ends of the wing telescopic push rod 34 are respectively fixed on the first wing shell 31 and the third wing shell 33, and a matching fifth guide anti-slip convex ring portion 35 and a sixth guide anti-slip convex ring portion 36 are respectively provided between the first wing shell 31 and the second wing shell 32, and between the second wing shell 32 and the third wing shell 33. The third wing shell 33 is also provided with a third convex block portion 37 that can push the second wing shell 32 to retract. Specifically, one of the sixth guide anti-slip convex ring portions 36 is arranged on the inner end of the third wing shell 33, and the sixth guide anti-slip convex ring portion 36 is arranged against the inner wall of the second wing shell 32, another sixth guide anti-slip convex ring portion 36 is arranged on the inner end of the second wing shell 32, and the sixth guide anti-slip convex ring portion 36 is arranged against the inner wall of the first wing shell 31, one of the fifth guide anti-slip convex ring portions 35 is arranged on the outer end of the second wing shell 32, and the fifth guide anti-slip convex ring portion 35 is arranged against the outer side wall of the third wing shell 33, another fifth guide anti-slip convex ring portion 35 is arranged on the outer end of the first wing shell 31, and the fifth guide anti-slip convex ring portion 35 is arranged against the outer side wall of the second wing shell 32, and in actual production and manufacturing, the third protrusion portion 37 is fixed to the outer end of the third wing shell 33 by welding or screw locking. It can be seen that the telescopic working principle of the telescopic side wing 3 is the same as the telescopic working principle of the telescopic tail beam 42. Therefore, the telescopic movement process of the telescopic side wing 3 will not be elaborated in detail here.

[0035] In order to further improve the structure of the horizontal flight propeller 5 and enable the horizontal flight propeller 5 to be hidden and stored in the cabin body 1, as shown in FIG. Figure 9 As shown, the horizontal flight propeller 5 is composed of a telescopic support rod 51 and a power propulsion rotor mechanism 52 connected to the rear end of the cabin body 1 through the telescopic support rod 51; the rear end of the cabin body 1 is provided with a storage cavity 101, and the rear end of the cabin body 1 is also provided with a back cover door 102 that can be electrically opened and closed and placed in the storage cavity 101, and the power propulsion rotor mechanism 52 is stored in the storage cavity 101 or extended out of the storage cavity 101 through the telescopic support rod 51. During land travel, the horizontal flight propeller 5 can also be used to increase the land travel speed of the land-to-air vehicle. Specifically, the storage cavity 101 is opened at the rear end of the cockpit cover 111. By providing the storage cavity 101, the power propulsion rotor mechanism 52 and the telescopic support rod 51 can be hidden, and when parked, the overall volume of the land-to-air vehicle can be further reduced. In order to reduce flight resistance, such as Figure 9 As shown, the back cover door 102 is provided with a clearance notch 100 which is sleeved on the telescopic support rod 51. In this way, the back cover door 102 can be closed back in the flight state to reduce the flight resistance. Figure 13As shown, one end of the telescopic support rod 51 is fixed on the load-bearing platform 9, and the other end of the telescopic support rod 51 is connected to the power propulsion rotor mechanism 52. In actual applications, an electric pitch and flip joint is also provided between the power propulsion rotor mechanism 52 and the other end of the telescopic support rod 51. The electric pitch and flip joint is composed of a Y-shaped seat body and a mounting sleeve connected to the Y-shaped seat body in a pitch and flip manner through a flip motor. The power propulsion rotor mechanism 52 is fixed on the mounting sleeve, which makes it easier to store the power propulsion rotor mechanism 52. In actual applications, the top of the back cover door 102 is hinged on the cockpit cover 111 of the cockpit 11, and its bottom is propped open by an electric push rod of the prior art to realize electric door opening and closing. Specifically, the storage cavity 101 can be connected to the manned and cargo driving space 113, or the two can be separated by a partition. In actual applications, the power propulsion rotor mechanism 52 can also be replaced by an existing fuel engine used in aircraft, which can more conveniently increase the range of the land-to-air aircraft, extend the endurance time, and increase the flight distance.

[0036] In order to achieve the take-off and landing in situ, Figure 6 and Figure 7 As shown, the present invention also includes an extendable skeleton mechanism 6 arranged on the cabin body 1, and four flight rotor mechanisms 7 arranged around the cabin body 1 by using the extendable skeleton mechanism 6. The extendable skeleton mechanism 6 is in an extended state during lifting, taking off or landing and drives the four flight rotor mechanisms 7 to extend out of the cabin body 1, and is in a retracted state during gliding flight or walking on land and drives the four flight rotor mechanisms 7 to be stored and hidden in the cabin body 1. In this way, not only can the lifting, taking off and landing on the spot be realized without the need for a specific take-off runway, but it is very suitable for taking off on urban roads, and the range of take-off locations is very wide. Similarly, landing does not require a landing runway, and can land anywhere. Moreover, after rising into the air, the four flight rotor mechanisms are folded, and the telescopic side wings 3 and the horizontal flight thrusters 5 are used for gliding flight to obtain a faster flight speed, and the flight energy consumption can also be greatly reduced.

[0037] In order to further improve the structure of the cabin body 1, as Figure 10As shown in the figure, the cabin body 1 includes a cockpit 11 and storage compartments 12 that can be electrically opened and closed on the left and right sides of the cockpit 11; the cockpit 11 is composed of a cockpit housing 111 and a cockpit chassis 112 connected together, and a manned and cargo-carrying driving space 113 is formed between the cockpit housing 111 and the cockpit chassis 112; the storage compartment 12 is composed of a storage housing 121, a storage chassis 122, and an electric opening and closing mechanism 10. The storage housing 121 is electrically connected to the storage chassis 122 or the cockpit housing 111 through the electric opening and closing mechanism 10. A storage space 123 for storing and hiding the flight rotor mechanism 7 and the extensible skeleton mechanism 6 is formed between the storage housing 121 and the storage chassis 122, and the storage chassis 122 and the cockpit chassis 112 are of an integral structure. This has the characteristics of simple structure, easy implementation, high reliability, etc. When taking off, first open the storage compartment 12, and then extend the extensible skeleton mechanism 6 and the flight rotor mechanism 7 outside the storage compartment 12; when driving on land, just operate in reverse.

[0038] In order to further improve the structure of the electric opening and closing mechanism 10, the present invention provides two implementation schemes for the electric opening and closing mechanism 10: The first one is as Figure 6 and Figure 10 shown, the electric opening and closing mechanism 10 includes a vertical slide rail 101, a vertical slider 102, and a vertical push rod 103. The vertical slide rail 101 is fixed on the cockpit housing 111, the vertical slider 102 is fixed on the storage housing 121, and the vertical slider 102 is slidably arranged on the vertical slide rail 101. The two ends of the vertical push rod 103 are respectively fixed on the cockpit housing 111 and the vertical slider 102 to drive the vertical slider 102 and the storage housing 121 to move along the vertical slide rail 101 through the vertical push rod 103. When in use, the vertical push rod 103 can push the vertical slider 102 and the storage housing 121 to perform upward movement, downward movement, and hovering movement. The second one is as Figure 11 shown, the electric opening and closing mechanism 10 includes a first fixed seat 104, a second fixed seat 105, two connecting rods 106, and an electric push rod 107. The two connecting rods 106 are connected between the first fixed seat 104 and the second fixed seat 105 at intervals in parallel up and down. One end of the electric push rod 107 abuts against the first fixed seat 104, and the other end of the electric push rod 107 and the second fixed seat 105 are fixed on the storage chassis 122 or the cockpit housing 111, and the first fixed seat 104 is fixed on the storage housing 121. Preferably, the other end of the electric push rod 107 and the second fixed seat 105 are fixed on the cockpit housing 111 to reduce the influence on the storage of the extensible skeleton mechanism 6 and the flight rotor mechanism 7. When in use, the electric push rod 107 can push the first fixed seat 104 and the storage housing 121 to perform upward movement, downward movement, and hovering movement.

[0039] In order to further improve the structure of the extendable skeleton mechanism 6, the present invention provides two implementation schemes of the extendable skeleton mechanism 6: The first one, such as Figure 6 , Figure 7 and Figure 8 As shown, the extendable skeleton mechanism 6 is composed of four swing arm assemblies 63, and the swing arm assembly 63 includes an articulated seat 631, a swing arm 632, and a swing drive motor 633. The articulated seat 631 is fixed on the cockpit 11, and one end of the swing arm 632 is provided with a hinge part 634, and the swing arm 632 is hinged on the articulated seat 631 through the articulated part 634. The power output end of the swing drive motor 633 is connected to the articulated part 634 to drive the articulated part 634 to rotate so that the swing arm 632 can swing. A locking hole 635 is provided on the articulated part 634, and a locking assembly 64 for locking and releasing the locking hole 635 is also provided on the articulated seat 631. The locking assembly 64 is composed of a locking push rod 641 and a locking part 642 arranged on the movable end of the locking push rod 641; the flight rotor mechanism 7 is fixed to the other end of the swing arm 632. In this way, the flight rotor mechanism 7 can be sent out of the storage cabin 12 or sent back into the storage cabin 12 by swinging. In actual applications, a reduction gear box 65 is also connected between the swing drive motor 633 and the hinge part 634. This can reduce the swing speed of the swing arm 632 to reduce the probability of damage by bumps and collisions, and the collision noise is also reduced. In actual applications, the locking assembly 64 can also be fixed to the reduction gear box 65. After the swing arm 632 is unfolded, the locking part 642 is driven by the locking push rod 641 to lock into the locking hole 635 to achieve locking and positioning; when the swing arm 632 is folded, the locking part 642 is driven by the locking push rod 641 to leave the locking hole 635, so that the swing arm 632 is not restricted and can be rotated and folded by the swing drive motor 633. In actual installation, if Figure 7 As shown, the other end of the swing arm 632 is also provided with a sleeve 66, and each flight rotor mechanism 7 is respectively installed on the corresponding sleeve 66. In order to further improve the stability of the swing arm 632 after it is deployed, so that it will not swing randomly during the flight, as shown in FIG. Figure 1 As shown, the storage cover 121 is also provided with a clearance notch 100 that can be placed on the swing arm 632. This can limit the swing of the swing arm 632, making the flight more stable and reliable. In addition, the storage cover 121 can be closed back to reduce flight resistance.

[0040] The second type, such as Figure 11 , Figure 12 and Figure 13As shown, the extendable skeleton mechanism 6 includes two transverse telescopic rods 61 and two longitudinal telescopic rods 62, the two transverse telescopic rods 61 are connected to the inactive ends of the two longitudinal telescopic rods 62 at intervals, so that the two transverse telescopic rods 61 and the two longitudinal telescopic rods 62 are connected to form a rectangular skeleton structure 60 with adjustable overall transverse and longitudinal dimensions, the inactive ends of the two transverse telescopic rods 61 are fixed in the cabin 11, the two longitudinal telescopic rods 62 can be stored and hidden in two storage compartments 12 through the two transverse telescopic rods 61, and the four flight rotor mechanisms 7 are respectively arranged at the two ends of the two longitudinal telescopic rods 62. By setting the rectangular skeleton structure 60 with adjustable overall transverse and longitudinal dimensions, not only can the stability of the structure be ensured, but also when the rectangular skeleton structure 60 is extended, the distance between the four flight rotor mechanisms 7 is sufficiently far apart, which can greatly improve the stability of the flight. In order to make the transverse telescopic rod 61 and the longitudinal telescopic rod 62 have the characteristics of simple structure, easy implementation, high reliability, etc., the transverse telescopic rod 61 is composed of a left telescopic cross bar 611 and a right telescopic cross bar 612 assembled together, and the telescopic direction of the left telescopic cross bar 611 is opposite to the telescopic direction of the right telescopic cross bar 612; the longitudinal telescopic rod 62 is respectively composed of a front telescopic longitudinal rod 621 and a rear telescopic longitudinal rod 622 assembled together, and the telescopic direction of the front telescopic longitudinal rod 621 is opposite to the telescopic direction of the rear telescopic longitudinal rod 622. In this way, the transverse telescopic rod 61 and the longitudinal telescopic rod 62 can be configured as a double-end telescopic rod structure, wherein the left telescopic cross bar 611, the right telescopic cross bar 612, the front telescopic longitudinal rod 621, and the rear telescopic longitudinal rod 622 are all single-end telescopic rod structures. During actual assembly, the inactive end of the left telescopic cross bar 611 and the inactive end of the right telescopic cross bar 612 are fixed together by screw locking or welding; similarly, the inactive end of the front telescopic longitudinal rod 621 and the inactive end of the rear telescopic longitudinal rod 622 are also fixed together by screw locking or welding. In order to further improve the stability of the lateral telescopic rod 61 after it is unfolded, so that it will not swing randomly during flight, such as Figure 13 As shown, the storage cover 121 is also provided with a clearance notch 100 that can be placed on the transverse telescopic rod 61. This can limit the swing of the transverse telescopic rod 61 and the longitudinal telescopic rod 62, making the flight more stable and reliable. In addition, the storage cover 121 can be closed back to reduce flight resistance. In actual installation, Figure 12 As shown, the movable ends of the front telescopic longitudinal rod 621 and the rear telescopic longitudinal rod 622 are also provided with sleeves 66 respectively, and each flight rotor mechanism 7 is installed on the corresponding sleeve 66 respectively.

[0041] In order to make the flight rotor mechanism 7 and the power propulsion rotor mechanism 52 of the present invention have the characteristics of simple structure, easy implementation, high reliability, etc. Figure 16As shown in the figure, the flight rotor mechanism 7 and the power propulsion rotor mechanism 52 respectively include a driving motor 71, a connecting shaft 72, a connecting seat 73, a first rotor blade 74, a second rotor blade 75, and two rotating motors 76. The connecting seat 73 is connected to the power output end of the driving motor 71 through the connecting shaft 72. The first rotor blade 74 and the second rotor blade 75 are respectively rotatably folded and rotatably unfolded through the rotating motors 76 and connected to the connecting seat 73. Positioning holes 77 are respectively provided on the first rotor blade 74 and the second rotor blade 75. Two locking pin push rod assemblies 70 for locking into and leaving the two positioning holes 77 are respectively provided on the connecting seat 73. The locking pin push rod assembly 70 is composed of an electric push rod 78 and a locking pin 79 provided on the movable end of the electric push rod 78. After the first rotor blade 74 and the second rotor blade 75 are unfolded, the locking pin 79 is driven by the electric push rod 78 to lock into the positioning hole 77 to achieve locking and positioning. When the first rotor blade 74 and the second rotor blade 75 are folded, the locking pin 79 is driven by the electric push rod 78 to leave the positioning hole 77, so that the first rotor blade 74 and the second rotor blade 75 are not restricted and can be rotatably folded through the rotating motor 76. In actual installation, the power output shafts of the two rotating motors 76 are both spline shafts (not shown in the figure), and spline holes (not shown in the figure) nested and matched with the spline shafts are respectively provided on the first rotor blade 74 and the second rotor blade 75, which can ensure the reliability of connection and rotation.

[0042] In order to further reduce the wind resistance during flight, as Figure 10 shown, a hemispherical disc cover 13 covering the telescopic side wing 3 is further provided on the bottom of the cabin body 1. The movable end of the telescopic side wing 3 and the bottom end of the driving wheel mechanism 2 respectively extend out of the hemispherical disc cover 13. By providing the hemispherical disc cover 13, during flight, the airflow can smoothly slide over the bottom of the cabin body 1, avoiding the airflow hitting the telescopic side wing 3 and the driving wheel mechanism 2 below the cabin body 1 and generating a large wind resistance, so as to improve the flight speed.

[0043] In order to further improve the structure of the driving wheel mechanism 2, as Figure 10 shown, the driving wheel mechanism 2 includes a traveling wheel 21 and a vertical telescopic leg 22. The traveling wheel 21 is connected to the bottom of the cabin body 1 through the vertical telescopic leg 22. Preferably, the number of the driving wheel mechanisms 2 is four. By providing four vertical telescopic legs 22, the traveling wheel 21 can be lifted by using the vertical telescopic legs 22 to cross road obstacles, adapt to various terrains, and can also adjust the center of gravity height of the entire air-land vehicle, making the movement more stable.

[0044] In order to make the traveling wheel 21 of the present invention have the characteristics of simple structure, easy implementation, high reliability, etc., as Figure 17As shown, the walking wheel 21 includes a mounting seat 211, a connecting rod 212, a shock absorbing spring 213, and an electric roller 214. One end of the connecting rod 212 is hinged on the bottom of the mounting seat 211, and the two ends of the shock absorbing spring 213 are respectively connected to the other end of the connecting rod 212 and the mounting seat 211. The electric roller 214 is rotatably connected to the connecting rod 212. The mounting seat 211 is arranged at the bottom of the vertical telescopic leg 22; a horizontal steering motor 215 is also arranged between the mounting seat 211 and the vertical telescopic leg 22. In this way, it can play a role in shock absorption when walking on a bumpy road, so that the movement of the land-air vehicle is more stable. In practical applications, by setting a horizontal steering motor 215, the power output end of the horizontal steering motor 215 is fixed to the bottom of the vertical telescopic leg 22, so that the walking wheel 21 can achieve steering.

[0045] In order to make the electric roller 214 of the present invention have the characteristics of simple structure, easy implementation, high reliability, etc. Figure 18 As shown, the electric roller 214 is composed of a tire 2100, a wheel hub 2101, a permanent magnet 2102, a motor rotor 2103, a motor stator 2104, a motor winding 2105, a motor controller 2106, a bearing 2107, a brake shoe 2108, a brake caliper 2109, and a suspension shaft 2110, and the suspension shaft 2110 is connected to the connecting rod 212. In this way, the electric roller 214 can achieve electric drive movement and braking. And these structures make the electric roller 214 constitute a roller with a hub motor in the prior art. Its specific connection structure and working principle can refer to the technical solution disclosed in the patent document with the Chinese patent announcement number CN221042575U and the name "A hub motor assembly", which will not be elaborated here.

[0046] In order to make each telescopic rod of the present invention have the characteristics of simple structure, easy implementation, high reliability, etc. Figure 14 and Figure 15As shown, the tail beam telescopic push rod 424, the tail wing telescopic push rod 436, the wing telescopic push rod 34, the telescopic support rod 51, the vertical telescopic leg 22, the left telescopic cross bar 611, the right telescopic cross bar 612, the front telescopic longitudinal bar 621, and the rear telescopic longitudinal bar 622 respectively include a first cylinder 1001, a second cylinder 1002, and a third cylinder 1003 that are sleeved together. An electric motor 1004 and a reduction gear component 1005 are provided inside or outside the first cylinder 1001. A first lead screw 1006 is further provided inside the first cylinder 1001. The first lead screw 1006 is drivingly connected to the electric motor 1004 through the reduction gear component 1005. A threaded connection block 1007 that is screwed to the first lead screw 1006 is fixedly provided in the second cylinder 1002. A bearing 1008 is provided on the threaded connection block 1007. The inner ring of the bearing 1008 is fixedly connected to a second lead screw 1009 disposed in the second cylinder 1002. The second lead screw 1009 is provided with an external thread 1010 and an internal thread hole 1011. The internal thread hole 1011 is screwed to the first lead screw 1006. An internal thread hole 1012 that is screwed to the external thread 1010 of the second lead screw 1009 is provided on the third cylinder 1003. Specifically, the first cylinder 1001, the second cylinder 1002, and the third cylinder 1003 are all square cylinders. When the first cylinder 1001, the second cylinder 1002, and the third cylinder 1003 are all circular cylinders, a limiting guide groove (not shown) and a limiting guide protrusion (not shown) that are slidably nested together are further provided between the first cylinder 1001 and the second cylinder 1002 and between the second cylinder 1002 and the third cylinder 1003. In this way, when the first lead screw 1006 rotates, the second cylinder 1002 and the third cylinder 1003 can be simultaneously driven to extend or retract. In practical applications, each telescopic rod can also adopt an existing electric telescopic rod, such as the technical solution disclosed in the patent document with the Chinese patent application number 201911294043.4 and the name "multi-section electric push rod".

[0047] In order to reduce the harm caused by a plane crash, a pop-up safety buffer airbag (not shown in the figure) is further provided at the bottom of the cockpit 11. The pop-up safety buffer airbag is covered in a hemispherical disc cover 13, and an electric door (not shown in the figure) that can be electrically opened and closed and through which the pop-up safety buffer airbag can pop out is further provided on the hemispherical disc cover 13. In this way, it can play a buffering role when the plane crashes and lands or lands on the water surface.

[0048] The pop-up safety airbag adopts the safety airbag of the prior art, such as the technical solution disclosed in the patent document with the Chinese patent application number CN112721851A and the name "Airbag, Airbag System and Aircraft". The specific structure and working principle of the airbag will not be elaborated here. During application, the volume of the airbag can be enlarged and then applied to the land-air aircraft of the present invention. To further reduce the speed of crashing and thus reduce the damage caused by crashing, a pop-up parachute (not shown in the figure) can be additionally provided at the top of the cockpit 11. The pop-up parachute adopts the pop-up parachute of the prior art, such as the technical solution disclosed in the patent document with the Chinese patent application number CN118907496A and the name "An Unmanned Aerial Vehicle Parachute Device, a Parachute Control System and Its Landing Method". The specific structure and working principle of the pop-up parachute will not be elaborated here. During application, the volume of the pop-up parachute can be enlarged and then applied to the land-air aircraft of the present invention.

[0049] In practical applications, such as Figure 10 and Figure 13 shown, a load platform 9 is provided in the manned and cargo-carrying driving space 113. A driving control device 91 and a seat 92 are provided on the upper end surface of the load platform 9. The driving control device 91 controls the operation of each electrical component of the land-air aircraft respectively. The driving control device 91 adopts the driving control device applied to an aircraft in the prior art, and its specific structure and working principle will not be elaborated here. A power supply battery 93 is provided below the load platform 9 to supply electrical energy to each electrical component of the land-air aircraft. The solution of the present invention can be designed to work in a manually controlled mode, that is, a manned mode, or can also be designed to work without manual operation, that is, an unmanned mode. At the same time, the solution of the present invention can be used for carrying people, can also be used for transporting goods, and can also be used for unmanned aircraft, drones, etc.

[0050] In practical applications, such as Figure 9 shown, a front cover door 94 for people to enter and exit the manned and cargo-carrying driving space 113 is further provided at the front end of the cockpit housing 111. The front cover door 94 can be opened or closed manually or electrically. The specific opening or closing structure of the front cover door 94 is the existing conventional technology and will not be elaborated here.

Claims

1. A land-to-air aircraft having retractable side wings and a retractable tail, characterized in that: include A cabin body (1) for carrying goods or passengers; A plurality of driving wheel mechanisms (2) arranged at the bottom of the cabin body (1) for traveling on land; A pair of retractable side wings (3) arranged on the left and right sides of the cabin body (1), wherein the retractable side wings (3) are in an extended state during gliding flight and are in a retracted state within the left and right sides of the cabin body (1) during land travel; A telescopic tail mechanism (4) is arranged at the rear end of the cabin body (1), the telescopic tail mechanism (4) being composed of a vertical fixed column (41), a telescopic tail beam (42), a telescopic horizontal tail wing (43) and a vertical tail wing (44); the telescopic tail beam (42) and the telescopic horizontal tail wing (43) of the telescopic tail mechanism (4) are in an extended state during gliding flight, and the telescopic tail beam (42) and the telescopic horizontal tail wing (43) are in a retracted state during walking on land; A horizontal flight propeller (5) is arranged at the rear end of the cabin body (1).

2. The land-to-air aircraft with retractable side wings and retractable tail wing according to claim 1, characterized in that: The telescopic tail beam (42) comprises a first tail beam shell (421), a second tail beam shell (422), and a third tail beam shell (423) which are sleeved together in sequence; the first tail beam shell (421) is also provided with a tail beam telescopic push rod (424) for driving the second tail beam shell (422) and the third tail beam shell (423) to move; the first tail beam shell (421) is fixed on a vertical fixed column (41); the third tail beam shell (423) is also provided with a sleeve hole (425) for sleeve-fitting and fixing the telescopic horizontal tail wing (43).

3. The land-to-air aircraft with retractable side wings and retractable tail wing according to claim 1, characterized in that: The telescopic horizontal tail (43) is composed of a left telescopic tail (431) and a right telescopic tail (432) assembled together; the left telescopic tail (431) and the right telescopic tail (432) respectively comprise a first tail shell (433), a second tail shell (434), and a third tail shell (435) which are sleeved together in sequence; the first tail shell (433) is also provided with a tail telescopic push rod (436) for driving the second tail shell (434) and the third tail shell (435) to move.

4. The land-to-air aircraft with retractable side wings and retractable tail wing according to claim 1, characterized in that: The telescopic side wing (3) comprises a first wing shell (31), a second wing shell (32), and a third wing shell (33) which are sleeved together in sequence, and the first wing shell (31) is also provided with a wing telescopic push rod (34) for driving the second wing shell (32) and the third wing shell (33) to move.

5. The land-to-air aircraft with retractable side wings and retractable tail wing according to claim 1, characterized in that: The horizontal flight propeller (5) is composed of a telescopic support rod (51) and a power propulsion rotor mechanism (52) connected to the rear end of the cabin body (1) via the telescopic support rod (51); a storage cavity (101) is provided at the rear end of the cabin body (1), and a back cover door (102) is also provided at the rear end of the cabin body (1) that can be opened and closed electrically and is placed in the storage cavity (101); the power propulsion rotor mechanism (52) is stored in the storage cavity (101) or extended out of the storage cavity (101) via the telescopic support rod (51).

6. The land-to-air aircraft with retractable side wings and retractable tail wing according to claim 1, characterized in that: It also includes an extendable skeleton mechanism (6) arranged on the cabin body (1), and four flight rotor mechanisms (7) arranged around the cabin body (1) using the extendable skeleton mechanism (6); the extendable skeleton mechanism (6) is in an extended state during take-off or landing and drives the four flight rotor mechanisms (7) to extend out of the cabin body (1); and is in a retracted state during gliding flight or land travel and drives the four flight rotor mechanisms (7) to be stored and hidden in the cabin body (1).

7. The land-to-air aircraft with retractable side wings and retractable tail wing according to claim 6, characterized in that: The cabin body (1) comprises a cabin (11) and electrically openable storage compartments (12) arranged on the left and right sides of the cabin (11); the cabin (11) is composed of a cabin cover (111) and a cabin chassis (112) connected together, and a driving space (113) for carrying people and goods is formed between the cabin cover (111) and the cabin chassis (112); the storage compartment (12) is composed of a storage cover (121), a storage chassis (122), an electrically The storage cover (121) is connected to a storage chassis (122) or a cockpit cover (111) in an electrically openable and closable manner through the electric opening and closing mechanism (10); a storage space (123) for storing and hiding the flight rotor mechanism (7) and the extendable skeleton mechanism (6) is formed between the storage cover (121) and the storage chassis (122); and the storage chassis (122) and the cockpit chassis (112) are an integrated structure.

8. The land-to-air aircraft with retractable side wings and retractable tail wing according to claim 7, characterized in that: The extendable skeleton structure (6) comprises two transverse telescopic rods (61) and two longitudinal telescopic rods (62), wherein the two transverse telescopic rods (61) are connected to the inactive ends of the two longitudinal telescopic rods (62) at intervals, so that the two transverse telescopic rods (61) are connected to the two longitudinal telescopic rods (62) to form a rectangular skeleton structure (60) with adjustable overall transverse and longitudinal dimensions, wherein the inactive ends of the two transverse telescopic rods (61) are fixed in the cabin (11), and the two longitudinal telescopic rods (62) can be stored and hidden in the two transverse telescopic rods (61) respectively. In a storage cabin (12), the four flight rotor mechanisms (7) are respectively arranged on the two ends of two longitudinal telescopic rods (62); the transverse telescopic rod (61) is composed of a left telescopic cross rod (611) and a right telescopic cross rod (612) assembled together, and the telescopic direction of the left telescopic cross rod (611) is opposite to the telescopic direction of the right telescopic cross rod (612); the longitudinal telescopic rod (62) is respectively composed of a front telescopic longitudinal rod (621) and a rear telescopic longitudinal rod (622) assembled together, and the telescopic direction of the front telescopic longitudinal rod (621) is opposite to the telescopic direction of the rear telescopic longitudinal rod (622).

9. The land-to-air aircraft with retractable side wings and retractable tail wing according to claim 7, characterized in that: The extendable skeleton mechanism (6) is composed of four swing arm assemblies (63), wherein the swing arm assemblies (63) include an articulated seat (631), a swing arm (632), and a swing drive motor (633). The articulated seat (631) is fixed to the cabin (11). One end of the swing arm (632) is provided with a hinged portion (634), and the swing arm (632) is hinged to the articulated seat (631) via the hinged portion (634). The power output end of the swing drive motor (633) is connected to the articulated portion (631). 4) to drive the hinge part (634) to rotate so as to make the swing arm (632) swing, the hinge part (634) is provided with a locking hole (635), the hinge seat (631) is also provided with a locking assembly (64) for locking in and out of the locking hole (635), the locking assembly (64) is composed of a locking push rod (641) and a locking part (642) arranged on the movable end of the locking push rod (641); the flying rotor mechanism (7) is fixed to the other end of the swing arm (632).

10. The land-to-air aircraft with retractable side wings and retractable tail wing according to claim 1, characterized in that: The bottom of the cabin body (1) is also provided with a hemispherical disc cover (13) which covers the telescopic side wing (3); the movable end of the telescopic side wing (3) and the bottom end of the driving wheel mechanism (2) respectively extend out of the hemispherical disc cover (13); the driving wheel mechanism (2) comprises a running wheel (21) and a vertical telescopic leg (22); the running wheel (21) is connected to the bottom of the cabin body (1) via the vertical telescopic leg (22).

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