Hidden type telescopic wing and telescopic lifting paddle air-ground aircraft

Abstract

The invention relates to an air-ground aircraft with hidden telescopic wings and telescopic lifting blades. The air-ground aircraft comprises a cabin body, a telescopic arm skeleton mechanism, four flying rotor mechanisms, a walking wheel mechanism, a telescopic glider wing mechanism and a telescopic power propulsion mechanism. According to the unmanned aerial vehicle, in-situ lifting takeoff can be achieved, gliding flight can also be achieved, the flight speed is higher, flight energy consumption is low, airflow output of the telescopic power propelling mechanism is not blocked, and the telescopic gliding wing mechanisms on the two sides, the telescopic power propelling mechanism and the four flight rotor wing mechanisms cannot protrude out of the cabin body after being stored; when the vehicle runs on the road, only the cabin body and the walking wheel mechanism located at the bottom of the cabin body are exposed outside, the road space cannot be occupied too much, normal running of other vehicles cannot be affected, the vehicle can be driven into a garage to be parked and can also be parked everywhere like a common car, and the parking range is greatly widened; and the vehicle can also be driven into a site of municipal public charging facilities for charging and energy supply, and charging and energy supply are more convenient.

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 a hidden retractable wing and retractable lift propellers. Background Art

[0002] A land-air dual-purpose vehicle refers to a vehicle that can travel on the ground and fly in the air. Currently, there are the following two types of land-air dual-purpose vehicles: First, as disclosed in a Chinese patent document with a patent application number of 201610607162.0 and a title of "A Future New Land-Air Dual-Purpose Vehicle", the solution mainly consists of a fuselage, a plurality of wheels distributed around the fuselage through a plurality of telescopic direction adjustment mechanisms, a propeller and a power mechanism arranged inside the wheels. In the flight state, the direction adjustment mechanism drives the wheels to move above the fuselage so that the axis of the wheels is perpendicular to the horizontal plane to achieve the purpose of flying in the air; in the ground driving state, the direction adjustment mechanism drives the wheels to move below the fuselage so that the outer circumferential surface of the wheels contacts the ground to achieve the purpose of land driving.

[0003] Second, as disclosed in a Chinese patent document with a patent application number of 201710989360.2 and a title of "Control System of a Land-Air Dual-Purpose Vehicle", the solution mainly consists of a vehicle, a left wing arranged on the left side of the vehicle and a foldable left small wing, a right wing arranged on the right side of the vehicle and a foldable right small wing, and a rotatable rotor engine arranged on the left wing and the right wing. In the flight 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 sides of the vehicle are used to achieve the purpose of flying in the air by gliding; in the ground driving state, the vehicle's own wheels are used to achieve the purpose of land driving.

[0004] However, in practical applications, the above two types of air-land dual-purpose aircraft still have the following deficiencies: First, although the flight components of the above two types of air-land dual-purpose aircraft can be folded to reduce the overall volume of the air-land dual-purpose aircraft, even after the flight components are folded, they are still exposed outside, protruding significantly outside the fuselage. When driving on the road, it will occupy a large amount of road space, affecting the normal driving of other vehicles. It cannot be parked in a garage like a vehicle and can only be parked in an open area or a dedicated helicopter apron. Even when parked in a surface parking lot, it needs to occupy 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, since the rotor blades of the above two types of air-land dual-purpose aircraft are still exposed outside in the folded state, during the driving process on the road, the rotor blades are easily damaged by external objects, affecting flight safety. Third, when using the first type of air-land dual-purpose aircraft for flight, it needs four wheeled propeller engines to work simultaneously, which not only requires generating lift but also more power to overcome gravity, making its energy consumption higher than that of a fixed-wing aircraft. Fourth, when using the second type of air-land dual-purpose aircraft for flight, the tail gas output of the rotor engine is blocked by the wing, resulting in unsmooth air flow, affecting power output, greatly reducing the flight propulsion force, and also affecting flight safety.

[0005] Therefore, based on the above deficiencies, the applicant believes that further improvements need to be made to the existing air-land dual-purpose aircraft to better meet the actual application needs of people. Summary of the Invention

[0006] The purpose of the present invention is to solve the above problems and deficiencies, and provide a concealed retractable wing and retractable lift rotor air-land aircraft. This air-land aircraft can achieve vertical takeoff and landing in place through the flight rotor mechanism, and then achieve gliding flight through the retractable gliding wing mechanism and the retractable power propulsion mechanism. The flight speed is faster, greatly reducing the flight energy consumption. The air flow output of the retractable power propulsion mechanism is not blocked, and the flight is more reliable. Moreover, after the retractable gliding wing mechanism, the retractable power propulsion mechanism, and the four flight rotor mechanisms are retracted, they will not protrude outside the cabin body. When driving on the road, only the cabin body and the walking wheel mechanism located at its bottom are exposed outside, not occupying too much road space, not affecting the normal driving of other vehicles, can drive into the garage for parking, and can also be parked everywhere like an ordinary sedan, greatly improving the parking range, and can also drive into the site of municipal public charging facilities for charging and energy supply, making the charging and energy supply more convenient.

[0007] The technical solution of the present invention is implemented as follows: A concealed retractable wing and retractable lift propeller land-air vehicle includes a cabin body, four flight rotor mechanisms distributed around the cabin body, and a walking wheel mechanism provided at the bottom of the cabin body. It is characterized in that the cabin body is further provided with a retractable gliding wing mechanism that extends and retracts in the left and right directions, and in the retracted state, the overall lateral dimension A of the retractable gliding wing mechanism is smaller than the overall lateral dimension B of the cabin body; the cabin body is composed of a cockpit and storage compartments that can be electrically opened and closed on the left and right sides of the cockpit. The cockpit is provided with a retractable arm skeleton mechanism that can extend outside the storage compartment or be retracted and hidden in the storage compartment. The four flight rotor mechanisms can be retracted and hidden in the two storage compartments respectively through the retractable arm skeleton mechanism; a retractable power propulsion mechanism that can be retracted and hidden in the cockpit or extended outside the cockpit and generate a forward propulsion force is further provided on the back of the cockpit.

[0008] Preferably, the retractable gliding wing mechanism is composed of a left wing and a right wing assembled together; the left wing and the right wing respectively include a first wing housing, a second wing housing movably sleeved in the first wing housing, and a third wing housing movably sleeved in the second wing housing. A telescopic drive push rod for driving the second wing housing and the third wing housing to move is further provided in the first wing housing.

[0009] Preferably, both ends of the telescopic drive push rod are respectively fixed on the first wing housing and the third wing housing. A first guiding anti-disengagement convex ring portion and a second guiding anti-disengagement convex ring portion that are matched with each other are further provided between the first wing housing and the second wing housing, and between the second wing housing and the third wing housing. A convex block portion that can push the second wing housing to perform a retracting movement action is further provided on the third wing housing.

[0010] Preferably, the retractable arm skeleton mechanism includes two transverse telescopic rods and two longitudinal telescopic rods. The two transverse telescopic rods are connected to the non-movable ends of the two longitudinal telescopic rods at intervals, so that the two transverse telescopic rods and the two longitudinal telescopic rods are connected to form a rectangular skeleton structure with adjustable overall lateral dimension and longitudinal dimension. The non-movable ends of the two transverse telescopic rods are fixed in the cockpit. The two longitudinal telescopic rods can be retracted and hidden in the two storage compartments respectively through the two transverse telescopic rods. The four flight rotor mechanisms are respectively arranged at both ends of the two longitudinal telescopic rods.

[0011] Preferably, the transverse telescopic rod is composed of a left telescopic cross bar and a right telescopic cross bar assembled together, and the telescopic directions of the left telescopic cross bar and the right telescopic cross bar are opposite; the longitudinal telescopic rods are respectively composed of a front telescopic longitudinal rod and a rear telescopic longitudinal rod assembled together, and the telescopic directions of the front telescopic longitudinal rod and the rear telescopic longitudinal rod are opposite.

[0012] Preferably, the telescopic power propulsion mechanism includes a power propulsion rotor mechanism and a telescopic support rod. A storage cavity is provided on the back of the cockpit, and a back cover door that can be electrically opened and closed is also provided on the back of the cockpit to cover the storage cavity. The power propulsion rotor mechanism is stored in the storage cavity or extended out of the storage cavity through the telescopic support rod.

[0013] Preferably, the flight rotor mechanism and the power propulsion rotor mechanism each include a drive motor, a connecting shaft, a connecting seat, a first rotor blade, a second rotor blade, and two rotating motors. The connecting seat is connected to the power output end of the drive motor through the connecting shaft. The first rotor blade and the second rotor blade are respectively rotatably folded and rotatably deployed on the connecting seat through the rotating motors. Positioning holes are respectively provided on the first rotor blade and the second rotor blade, and two locking pin push rod assemblies for locking into and leaving the two positioning holes are respectively provided on the connecting seat; the locking pin push rod assembly is composed of an electric push rod and a locking pin provided on the movable end of the electric push rod.

[0014] Preferably, a hemispherical disc cover is further provided on the bottom of the cabin body to cover the telescopic gliding wing mechanism. Both ends of the telescopic gliding wing mechanism and the bottom end of the walking wheel mechanism respectively extend out of the hemispherical disc cover.

[0015] Advantages of the present invention: Since the telescopic gliding wing mechanism, the telescopic power propulsion mechanism, and the four flight rotor mechanisms do not protrude out of the cabin body after being stored, when driving on the road, the overall volume of the land-air vehicle after storage can be greatly reduced. Only the cabin body and the walking wheel mechanism located at its bottom are exposed, which will not overly occupy the road space and will not affect the normal driving of other vehicles. It can 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 the municipal public charging facilities for charging and energy supply like a new energy vehicle, making the charging and energy supply more convenient.

[0016] Moreover, by storing all four flight rotor mechanisms in the storage compartment, the flight rotor mechanisms can be protected, and during the road surface driving process, they can be avoided from being damaged by external impacts, greatly improving the service life and flight safety of the flight rotor mechanisms. At the same time, by hiding the telescopic arm skeleton mechanism and each flight rotor mechanism inside the cabin body, during the road surface driving, the wind resistance of the flight rotor mechanisms can also be reduced to obtain a higher driving speed, improve the driving stability, and reduce energy consumption.

[0017] Meanwhile, when the land-air vehicle of the present invention is in flight, four flight rotor mechanisms are used for vertical takeoff and landing in place. In this way, during takeoff, there is no need for a specific takeoff runway, which is very suitable for taking off on urban roads. The range of takeoff locations is very wide. After ascending into the air, a retractable gliding wing mechanism and a retractable power propulsion mechanism are used for gliding flight, and the four flight rotor mechanisms are retracted to obtain a faster flight speed and greatly reduce flight energy consumption. Moreover, after the retractable gliding wing mechanism is deployed, the vehicle has the function of gliding, which is beneficial to improving the flight safety of the vehicle. It can use gliding to achieve an emergency landing and avoid the danger of a direct crash.

[0018] In addition, the retractable power propulsion mechanism is arranged on the back of the cockpit, 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. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a three-dimensional structure schematic diagram of the present invention in the land driving state.

[0020] Figure 2 It is a three-dimensional structure schematic diagram with partial section of the present invention in the state of opening the storage compartment.

[0021] Figure 3 It is a sectional structure schematic diagram of the present invention in the state of opening the storage compartment.

[0022] Figure 4 It is a three-dimensional structure schematic diagram of the present invention in the state of deploying the retractable arm skeleton mechanism.

[0023] Figure 5 It is a three-dimensional structure schematic diagram of the present invention in the state of opening the cockpit.

[0024] Figure 6 It is a three-dimensional structure schematic diagram of the present invention with the retractable power propulsion mechanism extended.

[0025] Figure 7 It is a three-dimensional structure schematic diagram of the present invention in the gliding flight state.

[0026] Figure 8 It is a three-dimensional structure schematic diagram of the present invention in the state of disassembling the cockpit body.

[0027] Figure 9 It is a structure schematic diagram of the retractable arm skeleton mechanism of the present invention.

[0028] Figure 10 It is a sectional structure schematic diagram of the first embodiment of the retractable drive push rod, left retractable cross bar, right retractable cross bar, front retractable longitudinal bar, rear retractable longitudinal bar, retractable support bar, and vertical retractable support leg of the present invention.

[0029] Figure 11 This is a schematic cross-sectional structure diagram of the second embodiment of the telescopic drive push rod, left telescopic cross bar, right telescopic cross bar, front telescopic longitudinal bar, rear telescopic longitudinal bar, telescopic support bar, and vertical telescopic support leg of the present invention.

[0030] Figure 12 This is a schematic cross-sectional structure diagram of the power propulsion rotor mechanism of the present invention.

[0031] Figure 13 This is a three-dimensional structure diagram of the walking wheel of the present invention.

[0032] Figure 14 This is a schematic cross-sectional structure diagram of the electric roller of the present invention.

[0033] Figure 15 This is a schematic cross-sectional structure diagram of the telescopic gliding wing mechanism of the present invention. Specific Embodiment

[0034] As Figure 1 、 Figure 3 And Figure 5 As shown, a hidden telescopic wing and telescopic lift propeller land-air vehicle of the present invention includes a cabin body 1, four flight rotor mechanisms 3 arranged around the cabin body 1, and a walking wheel mechanism 4 provided at the bottom of the cabin body 1. To achieve the purpose proposed by the present invention, the cabin body 1 is further provided with a telescopic gliding wing mechanism 8 that can extend and retract in the left and right directions, and in the retracted state, the overall lateral dimension A of the telescopic gliding wing mechanism 8 is smaller than the overall lateral dimension B of the cabin body 1; the cabin body 1 is composed of a cockpit 11 and retractable storage compartments 12 that can be electrically opened and closed on the left and right sides of the cockpit 11. The cockpit 11 is provided with a telescopic arm skeleton mechanism 2 that can extend out of the retractable storage compartment 12 or be retracted and hidden in the retractable storage compartment 12. The four flight rotor mechanisms 3 can be retracted and hidden in the two retractable storage compartments 12 through the telescopic arm skeleton mechanism 2 respectively; the back of the cockpit 11 is further provided with a telescopic power propulsion mechanism 60 that can be retracted and hidden in the cockpit 11 or extend out of the cockpit 11 and generate a forward propulsion force.

[0035] To further improve the structure of the telescopic gliding wing mechanism 8, as Figure 15As shown, the retractable gliding wing mechanism 8 is composed of a left wing 81 and a right wing 82 assembled together; the left wing 81 and the right wing 82 respectively include a first wing housing 811, a second wing housing 812 movably sleeved in the first wing housing 811, and a third wing housing 813 movably sleeved in the second wing housing 812. A telescopic drive push rod 814 for driving the movement of the second wing housing 812 and the third wing housing 813 is further provided in the first wing housing 811. Through such a three-stage telescopic structure, the left wing 81 and the right wing 82 can have a sufficiently long length after deployment and a sufficiently short length after contraction, which is very practical.

[0036] In order to make the telescopic structure of the retractable gliding wing mechanism 8 have the characteristics of simple structure, easy implementation, high reliability, etc., such as Figure 15As shown, both ends of the telescopic drive push rod 814 are respectively fixed on the first wing housing 811 and the third wing housing 813. A first guiding and anti-loosening convex ring portion 815 and a second guiding and anti-loosening convex ring portion 816 which are matched with each other are respectively arranged between the first wing housing 811 and the second wing housing 812 and between the second wing housing 812 and the third wing housing 813. A convex block portion 817 capable of pushing the second wing housing 812 to perform a retracting movement is further arranged on the third wing housing 813. Specifically, the second guiding and anti-loosening convex ring portion 816 of the third wing housing 813 is arranged at the inner end of the third wing housing 813, and the second guiding and anti-loosening convex ring portion 816 of the third wing housing 813 is arranged in a manner of abutting against the inner wall of the second wing housing 812. The first guiding and anti-loosening convex ring portion 815 of the second wing housing 812 is arranged at the outer end of the second wing housing 812, and the first guiding and anti-loosening convex ring portion 815 of the second wing housing 812 is arranged in a manner of abutting against the outer side wall of the third wing housing 813. When the telescopic gliding wing mechanism 8 needs to be deployed, the third wing housing 813 is pushed by the telescopic drive push rod 814 to move. When the second guiding and anti-loosening convex ring portion 816 of the third wing housing 813 hooks the first guiding and anti-loosening convex ring portion 815 of the second wing housing 812, the second wing housing 812 can be driven to move so as to realize deployment. The second guiding and anti-loosening convex ring portion 816 of the second wing housing 812 is arranged at the inner end of the second wing housing 812, and the second guiding and anti-loosening convex ring portion 816 of the second wing housing 812 is arranged in a manner of abutting against the inner wall of the first wing housing 811. The first guiding and anti-loosening convex ring portion 815 of the first wing housing 811 is arranged at the outer end of the first wing housing 811, and the first guiding and anti-loosening convex ring portion 815 of the first wing housing 811 is arranged in a manner of abutting against the outer side wall of the second wing housing 812. When the telescopic gliding wing mechanism 8 needs to be deployed, it can prevent the second wing housing 812 and the first wing housing 811 from loosening and falling off. More specifically, the convex block portion 817 is arranged at the outer end of the third wing housing 813. When the telescopic gliding wing mechanism 8 needs to be retracted, the third wing housing 813 is pulled by the telescopic drive push rod 814 to perform a retracting movement. And when the third wing housing 813 retracts into the second wing housing 812, the convex block portion 817 can abut against the second wing housing 812 so that the third wing housing 813 and the second wing housing 812 can move into the first wing housing 811 together to realize retraction. In actual production and manufacturing, the convex block portion 817 is fixed on the third wing housing 813 by means of welding or screw locking.

[0037] To further improve the structure of the telescopic arm skeleton mechanism 2, as Figure 9As shown, the telescopic arm skeleton mechanism 2 includes two transverse telescopic rods 21 and two longitudinal telescopic rods 22. The two transverse telescopic rods 21 are connected to the non-movable ends of the two longitudinal telescopic rods 22 at intervals, so that the two transverse telescopic rods 21 and the two longitudinal telescopic rods 22 are connected to form a rectangular skeleton structure 20 with adjustable overall transverse and longitudinal dimensions. The non-movable ends of the two transverse telescopic rods 21 are fixed in the cockpit 11. The two longitudinal telescopic rods 22 can be respectively received and hidden in two storage compartments 12 through the two transverse telescopic rods 21. The four flight rotor mechanisms 3 are respectively arranged at both ends of the two longitudinal telescopic rods 22. By providing the rectangular skeleton structure 20 with adjustable overall transverse and longitudinal dimensions, not only can the structural stability be ensured, but also when the rectangular skeleton structure 20 is extended, the distance between the four flight rotor mechanisms 3 is far enough apart, which can greatly improve the flight stability.

[0038] In order to make the transverse telescopic rod 21 and the longitudinal telescopic rod 22 have the characteristics of simple structure, easy implementation, high reliability, etc., as Figure 9 shown, the transverse telescopic rod 21 is composed of a left telescopic crossbar 211 and a right telescopic crossbar 212 assembled together, and the telescopic directions of the left telescopic crossbar 211 and the right telescopic crossbar 212 are opposite; the longitudinal telescopic rods 22 are respectively composed of a front telescopic longitudinal rod 221 and a rear telescopic longitudinal rod 222 assembled together, and the telescopic directions of the front telescopic longitudinal rod 221 and the rear telescopic longitudinal rod 222 are opposite. In this way, the transverse telescopic rod 21 and the longitudinal telescopic rod 22 can be configured into a double-ended telescopic rod structure. Among them, the left telescopic crossbar 211, the right telescopic crossbar 212, the front telescopic longitudinal rod 221, and the rear telescopic longitudinal rod 222 are all single-ended telescopic rod structures. During actual assembly, the non-movable end of the left telescopic crossbar 211 and the non-movable end of the right telescopic crossbar 212 are butt-jointed and fixed together by means of screwing or welding; similarly, the non-movable end of the front telescopic longitudinal rod 221 and the non-movable end of the rear telescopic longitudinal rod 222 are also butt-jointed and fixed together by means of screwing or welding.

[0039] In order to further improve the structures of the cockpit 11 and the storage compartment 12, as Figure 3As shown, the cockpit 11 is composed of a cockpit cover 111 and a cockpit chassis 112 connected together, a driving space 113 for carrying people and goods is formed between the cockpit cover 111 and the cockpit chassis 112, and the inactive ends of the two transverse telescopic rods 21 are respectively fixed on the cockpit cover 111 and the cockpit chassis 112; the storage cabin 12 is composed of a storage cover 121 and a storage chassis 122 arranged on the bottom of the storage cover 121, and a storage space 123 for storing and hiding the flight rotor mechanism 3 and the longitudinal telescopic rod 22 is formed between the storage cover 121 and the storage chassis 122, and the storage cover 121 can be electrically opened and closed by the electric opening and closing mechanism 5. The two storage chassis 122 and the cockpit chassis 112 are an integrated structure. This has the characteristics of simple structure, easy implementation, high reliability, etc. When taking off, the storage compartment 12 is opened first, and then the transverse telescopic rod 21 is extended to push the longitudinal telescopic rod 22 and the flight rotor mechanism 3 out of the storage compartment 12, and then the longitudinal telescopic rod 22 is extended to increase the distance between the four flight rotor mechanisms 3; when driving on land, the reverse operation can be performed. In order to reduce flight resistance, such as Figure 1 As shown, the storage housing 121 is also provided with a clearance notch 100 sleeved on the two transverse telescopic rods 21. In this way, the storage housing 121 can be closed back in the flight state to reduce flight resistance.

[0040] In order to further improve the structure of the electric opening and closing mechanism 5, Figure 3 As shown, the electric opening and closing mechanism 5 includes a first fixed seat 51, a second fixed seat 52, two connecting rods 53, and an electric push rod 54. The two connecting rods 53 are connected to the first fixed seat 51 and the second fixed seat 52 in parallel and at intervals. One end of the electric push rod 54 is pressed against the first fixed seat 51, and the other end of the electric push rod 54 and the second fixed seat 52 are fixed to the storage chassis 122 or the cabin cover 111, and the first fixed seat 51 is fixed to the storage cover 121. Preferably, the other end of the electric push rod 54 and the second fixed seat 52 are fixed to the cabin cover 111 to reduce the impact on the storage of the longitudinal telescopic rod 22 and the flight rotor mechanism 3. When in use, the electric push rod 54 can push the first fixed seat 51 and the storage cover 121 to perform ascending action, descending action and hovering action.

[0041] In order to further improve the structure of the telescopic power propulsion mechanism 60, as Figure 5As shown, the telescopic power propulsion mechanism 60 includes a power propulsion rotor mechanism 6 and a telescopic support rod 600. A storage cavity 114 is provided on the back of the cockpit 11, and a back cover door 115 that can be electrically opened and closed and is placed in the storage cavity 114 is provided on the back of the cockpit 11. The power propulsion rotor mechanism 6 is stored in the storage cavity 114 or extended out of the storage cavity 114 through the telescopic support rod 600. During land travel, the power propulsion rotor mechanism 6 can also be used to increase the land travel speed of the land-to-air vehicle. By providing the storage cavity 114, the power propulsion rotor mechanism 6 and the telescopic support rod 600 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 5 As shown, the back cover door 115 is also provided with a clearance notch 100 which is sleeved on the telescopic support rod 600. In this way, the back cover door 115 can be closed back in the flight state to reduce the flight resistance. Figure 9 As shown, a mounting seat body 601 is connected between the left telescopic cross bar 211 and the right telescopic cross bar 212 near the back cover door 115, one end of the telescopic support rod 600 is fixed on the mounting seat body 601, and the other end of the telescopic support rod 600 is connected to the power propulsion rotor mechanism 6. Figure 9 As shown, an electric pitch and flip joint 602 is also provided between the power propulsion rotor mechanism 6 and the other end of the telescopic support rod 600. The electric pitch and flip joint 602 is composed of a Y-shaped seat body 603 and a mounting sleeve 605 connected to the Y-shaped seat body 603 in a pitch and flip manner through a flip motor 604, so that the storage of the power propulsion rotor mechanism 6 is easier. In practical applications, the top of the back cover door 115 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 114 can be connected to the manned and cargo driving space 113, or the two can be separated by a partition. In practical applications, the power propulsion rotor mechanism 6 can also be replaced by an existing fuel engine used in aircraft, which can more conveniently increase the range of the aircraft, with longer endurance and greater flight distance.

[0042] In order to make the flight rotor mechanism 3 and the power propulsion rotor mechanism 6 of the present invention have the characteristics of simple structure, easy implementation, high reliability, etc. Figure 12As shown, the flight rotor mechanism 3 and the power propulsion rotor mechanism 6 respectively include a driving motor 311, a connecting shaft 312, a connecting seat 313, a first rotor blade 314, a second rotor blade 315, and two rotating motors 316. The connecting seat 313 is connected to the power output end of the driving motor 311 through the connecting shaft 312. The first rotor blade 314 and the second rotor blade 315 are respectively connected to the connecting seat 313 through the rotating motors 316 so as to be rotatably folded and rotatably deployed. Positioning holes 317 are respectively provided on the first rotor blade 314 and the second rotor blade 315. Two locking pin push rod assemblies 310 for respectively locking into and leaving the two positioning holes 317 are further provided on the connecting seat 313. The locking pin push rod assembly 310 is composed of an electric push rod 318 and a locking pin 319 provided on the movable end of the electric push rod 318. After the first rotor blade 314 and the second rotor blade 315 are deployed, the locking pin 319 is driven by the electric push rod 318 to lock into the positioning hole 317 to achieve locking and positioning. When the first rotor blade 314 and the second rotor blade 315 are folded, the locking pin 319 is driven by the electric push rod 318 to leave the positioning hole 317, so that the first rotor blade 314 and the second rotor blade 315 are not restricted and can be rotatably folded through the rotating motors 316. In actual installation, as Figure 9 shown, socket seats 220 are respectively provided at both ends of the two longitudinal telescopic rods 22. The driving motors 311 of the respective flight rotor mechanisms 3 are respectively installed on the corresponding socket seats 220. In actual application, the power output shafts of the two rotating motors 316 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 314 and the second rotor blade 315, which can ensure the reliability of connection and rotation.

[0043] In order to further improve the structure of the walking wheel mechanism 4, as Figure 3 shown, the walking wheel mechanism 4 includes a plurality of walking wheels 41 and a plurality of vertical telescopic legs 42. The respective walking wheels 41 are respectively connected to the bottom of the cockpit 11 through the respective vertical telescopic legs 42. By providing four vertical telescopic legs 42, the walking wheels 41 can be lifted by using the vertical telescopic legs 42 to cross road surface obstacles, adapt to various terrains, and can also adjust the center of gravity height of the entire land-air vehicle, making the movement more stable.

[0044] In order to make the walking wheels 41 of the present invention have the characteristics of simple structure, easy implementation, high reliability, etc., as Figure 13As shown, the traveling wheel 41 includes a mounting base 411, a connecting rod 412, a shock-absorbing spring 413, and an electric roller 414. One end of the connecting rod 412 is hinged to the bottom of the mounting base 411. Both ends of the shock-absorbing spring 413 are respectively connected to the other end of the connecting rod 412 and the mounting base 411. The electric roller 414 is rotatably connected to the connecting rod 412. The mounting base 411 is arranged at the bottom of the vertical telescopic leg 42. A horizontal steering motor 415 is further provided between the mounting base 411 and the vertical telescopic leg 42. This can play a shock-absorbing role when traveling on a bumpy road surface, making the movement of the land-air vehicle more stable. In practical applications, by setting the horizontal steering motor 415, the power output end of the horizontal steering motor 415 is fixed to the bottom of the vertical telescopic leg 42, so that the traveling wheel 41 can achieve steering.

[0045] In order to make the electric roller 414 of the present invention have the characteristics of simple structure, easy implementation, high reliability, etc., as Figure 14 shown, the electric roller 414 is composed of a tire 4100, a wheel hub 4101, a permanent magnet 4102, a motor rotor 4103, a motor stator 4104, a motor winding 4105, a motor controller 4106, a bearing member 4107, a brake shoe 4108, a brake caliper 4109, and a suspension shaft 4110. The suspension shaft 4110 is connected to the connecting rod 412. This can enable the electric roller 414 to achieve electric drive movement and braking. And these structures make the electric roller 414 constitute a roller with a hub motor in the prior art. For its specific connection structure and working principle, reference can be made to the technical solution disclosed in the patent document with the Chinese patent publication number CN221042575U and the name "A Hub Motor Assembly", and no further elaboration will be made here.

[0046] In order to further reduce the wind resistance during flight, as Figure 3 shown, a hemispherical disc cover 80 covering the retractable gliding wing mechanism 8 is further provided on the bottom of the cabin body 1. Both ends of the retractable gliding wing mechanism 8 and the bottom end of the traveling wheel mechanism 4 respectively extend out of the hemispherical disc cover 80. By setting the hemispherical disc cover 80, during flight, the airflow can smoothly slide over the bottom of the cabin body 1, avoiding the airflow hitting the retractable gliding wing mechanism 8 and the traveling wheel mechanism 4 below the cabin body 1 and generating a large wind resistance, so as to increase the flight speed.

[0047] In order to make each telescopic rod of the present invention have the characteristics of simple structure, easy implementation, high reliability, etc., as Figure 10 and Figure 11As shown, the telescopic drive push rod 814, left telescopic cross bar 211, right telescopic cross bar 212, front telescopic longitudinal bar 221, rear telescopic longitudinal bar 222, telescopic support rod 600, and vertical telescopic support leg 42 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 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. An 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 threaded hole 1011. The internal threaded hole 1011 is screwed to the first lead screw 1006. An internal threaded hole 1012 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 limit guiding groove (not shown) and a limit guiding 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".

[0048] To further improve the stability of the land-air vehicle during flight and land travel, as Figure 1 shown, a tail wing 7 is further provided on the back of the cockpit 11. In this way, during the process of flight and land travel, air resistance can be reduced to improve the stability of flight and land travel.

[0049] To reduce the injuries caused by a plane crash, a pop-up safety airbag (not shown in the figure) is further provided at the bottom of the cockpit 11. The pop-up safety airbag is covered in a hemispherical disc housing 80, and an electric door (not shown in the figure) that can be electrically opened and closed and allows the pop-up safety airbag to pop out is further provided on the hemispherical disc housing 80. In this way, it can play a buffering role when landing in a plane crash or landing on water. The pop-up safety airbag adopts a safety airbag of the prior art. For example, the technical solution disclosed in the patent document with the Chinese patent application number CN112721851A and the title "Airbag, Airbag System and Aircraft". The specific structure and working principle of the airbag will not be elaborated here too much. When applying, the volume of the airbag can be enlarged, and it can be applied to the land-air aircraft of the present invention. To further reduce the speed of the plane crash and thus reduce the injuries caused by the plane crash, a pop-up parachute (not shown in the figure) can be further provided at the top of the cockpit 11. The pop-up parachute adopts a pop-up parachute of the prior art. For example, the technical solution disclosed in the patent document with the Chinese patent application number CN118907496A and the title "An Unmanned Aerial Vehicle Parachute Device, Parachute Control System and Landing Method Thereof". The specific structure and working principle of the pop-up parachute will not be elaborated here too much. When applying, the volume of the pop-up parachute can be enlarged, and it can be applied to the land-air aircraft of the present invention.

[0050] In practical applications, as Figure 8 shown, a load platform 9 is provided in the manned and cargo-carrying driving space 113 and is connected to the non-movable ends of two transverse telescopic rods 21. 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 a driving control device applied to an aircraft in the prior art, and its specific structure and working principle will not be elaborated here too much. A power supply battery 93 is provided below the load platform 9 to provide electrical energy for each electrical component of the land-air aircraft. The solution of the present invention can be designed into a working mode that requires manual control, that is, a manned mode, or a working mode that does not require manual operation, that is, an unmanned mode. At the same time, the solution of the present invention can be used for manned, can also be used for transporting goods, and can also be used for unmanned aircraft, drones, and so on.

[0051] In practical applications, as Figure 5 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 a conventional technology in the prior art and will not be elaborated here too much.

Claims

1. A hidden telescopic wing and telescopic lift propeller land-air vehicle, characterized in that: It includes a cabin body (1), four flight rotor mechanisms (3) arranged around the cabin body (1), and a walking wheel mechanism (4) provided at the bottom of the cabin body (1), and is characterized in that: The cabin body (1) is further provided with a telescopic gliding wing mechanism (8) that makes stretching and retracting movements in the left and right directions, and in the retracted state, the overall lateral dimension A of the telescopic gliding wing mechanism (8) is smaller than the overall lateral dimension B of the cabin body (1); The cabin body (1) is composed of a cockpit (11) and storage compartments (12) that can be electrically opened and closed on the left and right sides of the cockpit (11). A telescopic arm skeleton mechanism (2) that can extend outside the storage compartment (12) or be stored and hidden in the storage compartment (12) is provided in the cockpit (11). The four flight rotor mechanisms (3) can be stored and hidden in the two storage compartments (12) respectively through the telescopic arm skeleton mechanism (2); A telescopic power propulsion mechanism (60) that can be stored and hidden in the cockpit (11) or extend outside the cockpit (11) and generate a forward propulsion force is further provided on the back of the cockpit (11).

2. The concealed telescopic wing and telescopic lift propeller land-air vehicle according to claim 1, wherein: The telescopic gliding wing mechanism (8) is composed of a left wing (81) and a right wing (82) assembled together; the left wing (81) and the right wing (82) respectively include a first wing housing (811), a second wing housing (812) movably sleeved in the first wing housing (811), and a third wing housing (813) movably sleeved in the second wing housing (812). A telescopic drive push rod (814) for driving the second wing housing (812) and the third wing housing (813) to move is further provided in the first wing housing (811).

3. The concealed retractable wing and retractable lift propeller land-air vehicle according to claim 2, characterized in that: Both ends of the telescopic drive push rod (814) are respectively fixed on the first wing housing (811) and the third wing housing (813). A first guiding anti - detachment convex ring portion (815) and a second guiding anti - detachment convex ring portion (816) are respectively provided between the first wing housing (811) and the second wing housing (812), and between the second wing housing (812) and the third wing housing (813). A convex block portion (817) that can push the second wing housing (812) to make a retracting movement is further provided on the third wing housing (813).

4. The concealed telescopic wing and telescopic lift propeller land-air vehicle according to claim 1, wherein: The telescopic arm skeleton mechanism (2) includes two transverse telescopic rods (21) and two longitudinal telescopic rods (22). The two transverse telescopic rods (21) are connected to the non - movable ends of the two longitudinal telescopic rods (22) at intervals, so that the two transverse telescopic rods (21) and the two longitudinal telescopic rods (22) are connected to form a rectangular skeleton structure (20) with adjustable overall lateral dimension and longitudinal dimension. The non - movable ends of the two transverse telescopic rods (21) are fixed in the cockpit (11). The two longitudinal telescopic rods (22) can be stored and hidden in the two storage compartments (12) respectively through the two transverse telescopic rods (21). The four flight rotor mechanisms (3) are respectively arranged at the two ends of the two longitudinal telescopic rods (22).

5. The hidden telescopic wing and telescopic lift propeller land-air vehicle according to claim 4, characterized in that: The horizontal telescopic rod (21) is composed of a left telescopic cross rod (211) and a right telescopic cross rod (212) assembled together, and the telescopic direction of the left telescopic cross rod (211) is opposite to that of the right telescopic cross rod (212); the vertical telescopic rod (22) is respectively composed of a front telescopic longitudinal rod (221) and a rear telescopic longitudinal rod (222) assembled together, and the telescopic direction of the front telescopic longitudinal rod (221) is opposite to that of the rear telescopic longitudinal rod (222).

6. The hidden retractable wing and retractable lift propeller land-air vehicle according to claim 4, characterized in that: The cockpit (11) is composed of a cockpit cover (111) and a cockpit chassis (112) connected together. A manned and cargo-carrying driving space (113) is formed between the cockpit cover (111) and the cockpit chassis (112). The non-movable ends of the two horizontal telescopic rods (21) are respectively fixed on the cockpit cover (111) and the cockpit chassis (112); the storage compartment (12) is composed of a storage cover (121) and a storage chassis (122) provided at the bottom of the storage cover (121). A storage space (123) for storing and hiding the flight rotor mechanism (3) and the vertical telescopic rod (22) is formed between the storage cover (121) and the storage chassis (122). The storage cover (121) is electrically connected to the storage chassis (122) or the cockpit cover (111) through an electric opening and closing mechanism (5) and can be electrically opened and closed. The two storage chassis (122) and the cockpit chassis (112) are of an integral structure; the electric opening and closing mechanism (5) includes a first fixed seat (51), a second fixed seat (52), two connecting rods (53), and an electric push rod (54). The two connecting rods (53) are connected between the first fixed seat (51) and the second fixed seat (52) at upper and lower parallel intervals. One end of the electric push rod (54) abuts against the first fixed seat (51), and the other end of the electric push rod (54) and the second fixed seat (52) are fixed on the storage chassis (122) or the cockpit cover (111), and the first fixed seat (51) is fixed on the storage cover (121).

7. The concealed retractable wing and retractable lifting propeller land-air vehicle according to claim 1, characterized in that: The telescopic power propulsion mechanism (60) includes a power propulsion rotor mechanism (6) and a telescopic support rod (600). A storage cavity (114) is provided on the back of the cockpit (11), and a back cover door (115) that can be electrically opened and closed is also provided on the back of the cockpit (11) and covers the storage cavity (114). The power propulsion rotor mechanism (6) is stored in or extended out of the storage cavity (114) through the telescopic support rod (600).

8. The concealed retractable wing and retractable lift rotor land-air vehicle according to claim 7, characterized in that: The flight rotor mechanism (3) and the power propulsion rotor mechanism (6) respectively include a drive motor (311), a connecting shaft (312), a connecting seat (313), a first rotor blade (314), a second rotor blade (315), and two rotating motors (316). The connecting seat (313) is connected to the power output end of the drive motor (311) through the connecting shaft (312). The first rotor blade (314) and the second rotor blade (315) are respectively connected to the connecting seat (313) through the rotating motors (316) so as to be rotatably folded and rotatably deployed. Positioning holes (317) are respectively provided on the first rotor blade (314) and the second rotor blade (315). Two locking pin push rod assemblies (310) for locking into and leaving the two positioning holes (317) are respectively provided on the connecting seat (313). The locking pin push rod assembly (310) is composed of an electric push rod (318) and a locking pin (319) provided on the movable end of the electric push rod (318).

9. The concealed retractable wing and retractable lifting propeller land-air vehicle according to claim 1, characterized in that: The walking wheel mechanism (4) includes a plurality of walking wheels (41) and a plurality of vertical telescopic legs (42). Each walking wheel (41) is respectively connected to the bottom of the cockpit (11) through each vertical telescopic leg (42). The walking wheel (41) includes a mounting seat (411), a connecting rod (412), a shock absorption spring (413), and an electric roller (414). One end of the connecting rod (412) is hinged to the bottom of the mounting seat (411). The two ends of the shock absorption spring (413) are respectively connected to the other end of the connecting rod (412) and the mounting seat (411). The electric roller (414) is rotatably connected to the connecting rod (412). The mounting seat (411) is arranged at the bottom of the vertical telescopic leg (42). A horizontal steering motor (415) is further provided between the mounting seat (411) and the vertical telescopic leg (42). The electric roller (414) is composed of a tire (4100), a wheel hub (4101), a permanent magnet (4102), a motor rotor (4103), a motor stator (4104), a motor winding (4105), a motor controller (4106), a bearing member (4107), a brake shoe (4108), a brake caliper (4109), and a suspension shaft (4110). The suspension shaft (4110) is connected to the connecting rod (412).

10. The concealed retractable wing and retractable lifting propeller land-air vehicle according to claim 1, characterized in that: A hemispherical disc cover (80) covering the retractable gliding wing mechanism (8) is further provided on the bottom of the cabin body (1). The two ends of the retractable gliding wing mechanism (8) and the bottom ends of the walking wheel mechanism (4) respectively extend out of the hemispherical disc cover (80).

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