Self-rotor aircraft with separated wings and multi-shaft tilting rotors

Abstract

The invention relates to the technical field of aircrafts, in particular to a self-rotor aircraft with vehicle wings separated from multi-shaft tilting rotors, which comprises an aircraft bracket, self-rotors, a trolley, a cross rod, side rotors, a propeller, an empennage, a rudder, an empennage connecting plate and an empennage frame push rod assembly, the aircraft support is of an inverted-U-shaped structure and installed at the upper end of the trolley, the upper end of the aircraft support is provided with the self-rotor, the outer walls of the left end and the right end of the aircraft support are fixedly connected with the transverse rods, one end of each transverse rod is provided with the side rotor, and the rear end of the trolley is provided with the propeller. The empennages are installed in the empennage frame push rod assembly, rudders are installed in the empennages, and an empennage connecting plate is fixedly connected between every two adjacent empennages. The trolley can be rapidly transported at different places, in addition, through the empennage frame push rod assembly and the sliding groove locking structure, the empennage can be automatically recycled, and an aircraft can be rapidly separated from and fix the trolley.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a gyro-wing aircraft with a multi-axis tilt-rotor separated from its wing. Background Art

[0002] With its unique rotor design, rotorcraft has the ability to take off and land vertically, hover and fly at high speed. It is widely used in emergency rescue, aerial reconnaissance, environmental monitoring and cargo transportation. Its high maneuverability and flexibility make it more efficient and accurate to perform tasks in complex environments. It is an indispensable and important tool in modern aviation technology.

[0003] However, due to their limited load capacity, high energy consumption, and short endurance, rotorcraft usually do not have the ability to carry vehicles during flight, which limits their application in certain scenarios that require large load transportation, thereby reducing their flexibility of use.

[0004] Therefore, in view of the fact that the above-mentioned rotorcraft does not have the ability to carry a vehicle during flight, thereby reducing its flexibility of use, a gyroplane aircraft with a multi-axis tilt-rotor separated from the vehicle and wing can be designed. Through a spring locking structure and a tail wing frame push rod structure, the tail wing can be automatically retracted or unfolded while the vehicle is firmly fixed, thereby assisting the flight of the aircraft. Summary of the invention

[0005] In order to overcome the problem that rotorcraft does not have the ability to carry vehicles during flight, thereby reducing the flexibility of use.

[0006] The technical solution of the present invention is: a gyro-wing aircraft with a multi-axis tilt-rotor separated from the vehicle and the wing, comprising an aircraft bracket, a gyro-wing, a trolley, a crossbar, a side rotor, a propeller, a tail wing, a rudder, a tail wing connecting plate and a tail wing frame push rod assembly; the aircraft bracket is an inverted U-shaped structure and is installed on the upper end of the trolley, the gyro-wing is installed on the upper end of the aircraft bracket, the left and right outer walls of the aircraft bracket are fixedly connected with a crossbar, one end of the crossbar is installed with a side rotor, the rear end of the trolley is installed with a propeller, the tail wing frame push rod assembly is installed on the left and right ends of the trolley, the tail wing is installed in the tail wing frame push rod assembly, the rudder is installed in the tail wing, and a tail wing connecting plate is fixedly connected between two adjacent tail wings.

[0007] Preferably, the aircraft bracket serves as the skeleton of the entire aircraft, carrying components such as the autogyro and crossbar to ensure the overall stability of the aircraft and structural safety during flight. The trolley serves as a vehicle for transporting the aircraft, and the crossbar not only serves to strengthen the structure of the aircraft, but also serves as the installation base for the side rotor. The side rotor provides lift and propulsion for the aircraft, and works in conjunction with the autogyro to ensure the flight stability of the aircraft. The propeller provides additional power for the aircraft, so that when the side rotor loses power, the aircraft can continue to fly in the air. The tail and rudder are jointly responsible for the heading stability and directional control of the aircraft. The tail provides stability, while the rudder achieves steering of the aircraft by changing the direction of the airflow. The tail connecting plate strengthens the connection strength between the tails, and the tail frame push rod assembly facilitates the automatic retraction of the tail, so that the tail automatically fits onto the tail of the trolley.

[0008] Preferably, the inner walls at the left and right ends and the upper end of the aircraft bracket are fixedly connected with connecting blocks, and the connecting blocks are fixedly connected with slides at the ends facing the trolley. The connecting blocks serve as intermediary structures to firmly connect the slides to the aircraft bracket. The slides are slidably connected to the slide grooves on the trolley and cooperate with the locking pins on the trolley to firmly fix the aircraft bracket on the trolley.

[0009] Preferably, the left and right ends and the upper end of the trolley are both penetrated by sliding grooves adapted to the skateboard, and the skateboard is slidably connected to the sliding groove through a connecting block. A locking hole is provided at the end of the skateboard facing the trolley, and the sliding groove provides a sliding track for the skateboard to ensure that the skateboard can move smoothly. The locking hole is used to cooperate with the locking pin to realize the locking function between the skateboard and the trolley, ensuring that the skateboard will not slide accidentally during flight.

[0010] Preferably, a through groove is provided at one end of the slide groove toward the skateboard, the through groove is fixedly connected to one end of the locking spring, and the other end of the locking spring is fixedly connected to a locking pin adapted to the locking hole. The through groove provides installation space for the locking spring and the locking pin, so that the locking pin can enter or exit the locking hole under the action of the spring force. The locking spring provides elastic force for the locking pin, so that the locking pin can always maintain a trend in the direction of the locking hole to achieve the locking function. The locking pin enters the locking hole under the elastic force of the locking spring to achieve locking between the skateboard and the trolley; during the unlocking operation, the locking pin exits the locking hole to allow the skateboard to slide, thereby allowing the trolley to leave the aircraft bracket.

[0011] Preferably, tail wing frame grooves are provided on the outer walls at both ends of the trolley and the tail wing frame grooves are located at the upper end of the slide grooves. The front end inner wall of the tail wing frame grooves is symmetrically fixedly connected with tail wing recovery springs. One end of the tail wing recovery spring is fixedly connected to the tail wing bracket. The rear end of the tail wing bracket is equipped with a tail wing. The tail wing frame grooves provide installation and sliding space for the tail wing bracket, so that the tail wing can be recovered. The tail wing recovery spring provides recovery force for the tail wing bracket to ensure that the tail wing bracket can be automatically recovered into the tail wing frame groove when the trolley leaves the aircraft bracket. The tail wing bracket serves as the installation base of the tail wing and drives the tail wing to move at the same time.

[0012] Preferably, the tail wing frame push rod assembly includes a return spring, an arm, a push rod and a bearing and a fixing frame; a hole groove is opened on the inner wall of the left and right ends of the aircraft bracket, and the fixing frame is connected to the inner wall of the aircraft bracket by a fastening bolt, the push rod is adapted to the tail wing frame groove and one end of the push rod is sleeved with a return spring, one end of the push rod is inserted into the hole groove and the return spring is located outside the hole groove, and the other end of the push rod passes through the fixing frame, the arm rod is fixedly connected to the push rod and has a cross-shaped structure, both ends of the arm rod are rotatably connected to the bearing, the return spring provides a restoring force to ensure that the push rod can automatically return to the initial position when the external force is lost, the arm rod is a key component connecting the push rod and the bearing, and provides an installation basis for the bearing, the push rod extends the tail wing bracket by moving in the tail wing frame groove, and the bearing is used to cooperate with the inclined block to control the extension and retraction of the return spring.

[0013] Preferably, the outer walls at both ends of the trolley are fixedly connected with inclined blocks, which are located at the upper end of the slide groove. The inclined blocks are right-angled trapezoidal structures. When the trolley moves, the bearings roll on the outer wall of the trolley. When they contact the inclined surface of the inclined block, the distance between the outer wall of the trolley and the arm rod is reduced, thereby squeezing the return spring, thereby causing the push rod to leave the tail wing frame groove.

[0014] Beneficial effects of the present invention:

[0015] 1. This autogyro aircraft adopts a multi-axis tilt-rotor design, which not only realizes the convenient transportation function, but also can quickly transport the trolley at different locations. In addition, through the tail wing frame push rod assembly and the slide slot locking structure, the aircraft can automatically retract the tail wing and quickly separate and fix the trolley. These designs enhance the versatility and practicality of the aircraft;

[0016] 2. The aircraft is equipped with propellers to provide additional power, effectively avoiding the risk of falling when the side rotor fails. At the same time, with the precise control of the tail and rudder, the stability and directional control of the aircraft during navigation are ensured. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The first stereoscopic structure schematic diagram of the gyro-wing aircraft with separated multi-axis tilt-rotor wings of the present invention is shown;

[0018] Figure 2 The second stereoscopic structure schematic diagram of the gyro-wing aircraft with separated multi-axis tilt-rotor wings of the present invention is shown;

[0019] Figure 3 The schematic diagram of the disassembled three-dimensional structure of the gyro-wing aircraft with separated multi-axis tilt-rotor wings of the present invention is shown;

[0020] Figure 4 Shown is a front view schematic diagram of a gyro-wing aircraft with a multi-axis tilt-rotor with separated vehicle and wing according to the present invention;

[0021] Figure 5 Shown is a top view schematic diagram of a gyro-wing aircraft with a multi-axis tilt-rotor with separated wings and a vehicle according to the present invention;

[0022] Figure 6 Shown is a schematic diagram of the three-dimensional structure of the tail wing frame push rod assembly of the gyroplane aircraft with a multi-axis tilt-rotor with separated wings according to the present invention.

[0023] Explanation of the reference numerals in the accompanying drawings: 1. aircraft bracket; 2. autogyro; 3. trolley; 4. cross bar; 5. side rotor; 6. propeller; 7. tail; 8. rudder; 9. tail connecting plate; 10. connecting block; 11. slide plate; 12. slide groove; 13. lock hole; 14. locking spring; 15. locking pin; 16. tail bracket groove; 17. tail recovery spring; 18. tail bracket; 19. reset spring; 20. arm; 21. push rod; 22. bearing; 23. fixing frame; 24. inclined block. DETAILED DESCRIPTION

[0024] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0025] See also Figure 1-Figure 6The present invention provides an embodiment: a gyro wing aircraft with a multi-axis tilt-rotor separated from a vehicle and a wing, comprising an aircraft bracket 1, a gyro wing 2, a trolley 3, a crossbar 4, a side rotor 5, a propeller 6, a tail wing 7, a rudder 8, a tail connecting plate 9 and a tail frame push rod assembly; the aircraft bracket 1 is an inverted U-shaped structure and is installed on the upper end of the trolley 3, the gyro wing 2 is installed on the upper end of the aircraft bracket 1, the left and right outer walls of the aircraft bracket 1 are fixedly connected with the crossbar 4, one end of the crossbar 4 is installed with the side rotor 5, the rear end of the trolley 3 is installed with the propeller 6, the tail frame push rod assembly is installed on the left and right ends of the trolley 3, the tail wing 7 is installed in the tail frame push rod assembly, the rudder 8 is installed in the tail wing 7, and the tail connecting plate 9 is fixedly connected between two adjacent tail wings 7. The aircraft bracket 1 serves as the skeleton of the entire aircraft, carrying the gyro wing 2, the crossbar 4, the side rotor 5, the tail wing 7 ... 4 and other components to ensure the overall stability of the aircraft and the structural safety during flight. The trolley 3 is used as a vehicle for transporting the aircraft. The crossbar 4 not only strengthens the structure of the aircraft, but also serves as the installation basis for the side rotor 5. The side rotor 5 provides lift and propulsion for the aircraft, and works in conjunction with the autogyro 2 to jointly ensure the flight stability of the aircraft. The propeller 6 provides additional power for the aircraft, so that when the side rotor 5 loses power, the aircraft can continue to fly in the air. The tail 7 and the rudder 8 are jointly responsible for the heading stability and direction control of the aircraft. The tail 7 provides stability, and the rudder 8 achieves the steering of the aircraft by changing the direction of the airflow. The tail connecting plate 9 strengthens the connection strength between the tails 7. The tail frame push rod assembly facilitates the automatic retraction of the tail 7, so that the tail 7 automatically fits the tail of the trolley 3.

[0026] See also Figure 3In this embodiment, the inner walls of the left and right ends and the upper end of the aircraft bracket 1 are fixedly connected with connecting blocks 10, and the ends of the connecting blocks 10 facing the trolley 3 are fixedly connected with slide plates 11. The left and right ends and the upper end of the trolley 3 are penetrated by sliding grooves 12 adapted to the slide plates 11. The slide plates 11 are slidably connected to the slide grooves 12 through the connecting blocks 10. The end of the slide plate 11 facing the trolley 3 is provided with a locking hole 13, and the end of the slide groove 12 facing the slide plate 11 is provided with a through groove, and the through groove is fixedly connected to one end of the locking spring 14, and the other end of the locking spring 14 is fixedly connected with a locking pin 15 adapted to the locking hole 13. The connecting block 10 serves as an intermediary structure to firmly connect the slide plate 11 to the aircraft bracket 1, and the slide plate 11 is slidably connected to the slide groove 12 on the trolley 3, and cooperates with the locking pin 15 on the trolley 3, so as to lock the aircraft. The aircraft bracket 1 is firmly fixed on the trolley 3, and the slide groove 12 provides a sliding track for the slide plate 11 to ensure that the slide plate 11 can move smoothly. The locking hole 13 is used to cooperate with the locking pin 15 to realize the locking function between the slide plate 11 and the trolley 3 to ensure that the slide plate 11 will not slide accidentally during the flight. The through groove provides an installation space for the locking spring 14 and the locking pin 15, so that the locking pin 15 can enter or exit the locking hole 13 under the action of the spring force. The locking spring 14 provides elastic force for the locking pin 15, so that the locking pin 15 can always maintain a trend in the direction of the locking hole 13 to realize the locking function. The locking pin 15 enters the locking hole 13 under the elastic force of the locking spring 14 to realize the locking between the slide plate 11 and the trolley 3; exits the locking hole 13 during the unlocking operation, allowing the slide plate 11 to slide, thereby allowing the trolley 3 to leave the aircraft bracket 1.

[0027] See also Figure 6In this embodiment, the left and right outer walls of the trolley 3 are provided with tail frame grooves 16, and the tail frame grooves 16 are located at the upper end of the slide slot 12. The front inner wall of the tail frame groove 16 is symmetrically fixedly connected with a tail recovery spring 17, one end of the tail recovery spring 17 is fixedly connected with a tail bracket 18, and the rear end of the tail bracket 18 is installed with a tail 7. The tail frame push rod assembly includes a reset spring 19, an arm 20, a push rod 21, a bearing 22 and a fixing frame 23; the left and right inner walls of the aircraft bracket 1 are provided with hole grooves, and the fixing frame 23 is connected to the inner wall of the aircraft bracket 1 through a fastening bolt, the push rod 21 is adapted to the tail frame slot 16 and one end of the push rod 21 is sleeved with a return spring 19, one end of the push rod 21 is inserted into the hole slot and the return spring 19 is located outside the hole slot, the other end of the push rod 21 passes through the fixing frame 23, the arm 20 is fixedly connected to the push rod 21 and has a cross-shaped structure, both ends of the arm 20 are rotatably connected to the bearing 22, the left and right outer walls of the trolley 3 are fixedly connected with an inclined block 24, the inclined block 24 is located at the upper end of the slide slot 12, and the tail frame slot 16 The tail support 18 is provided with a space for installation and sliding, so that the tail 7 can be recovered. The tail recovery spring 17 provides recovery force for the tail support 18, ensuring that when the trolley 3 leaves the aircraft support 1, the tail support 18 can be automatically recovered into the tail support slot 16. The tail support 18 serves as the installation basis of the tail 7 and drives the tail 7 to move. The reset spring 19 provides a restoring force to ensure that when the external force is lost, the push rod 21 can automatically return to the initial position. The arm 20 is connected to the push rod 21 and the bearing 2 2, providing a mounting base for the bearing 22. The push rod 21 stretches the tail bracket 18 by moving in the tail bracket slot 16. The bearing 22 is used to cooperate with the inclined block 24 to control the extension and contraction of the return spring 19. The inclined block 24 is a right-angled trapezoidal structure. When the trolley 3 moves, the bearing 22 rolls on the outer wall of the trolley 3. When it contacts the inclined surface of the inclined block 24, the distance between the outer wall of the trolley 3 and the arm 20 is reduced, thereby squeezing the return spring 19, and then causing the push rod 21 to leave the tail bracket slot 16.

[0028] During the operation, the staff needs to accurately drive the trolley 3 into the aircraft support 1. At this time, the slide plate 11 on the aircraft support 1 will be accurately embedded in the slide groove 12. When the trolley 3 enters the predetermined position, the locking pin 15 in the trolley 3 will be stuck in the locking hole 13 on the slide plate 11, thereby tightly fixing the aircraft support 1 and the trolley 3.

[0029] At the same time, as the trolley 3 enters the aircraft bracket 1, the push rod 21 will enter the tail bracket slot 16 and push the tail bracket 18, so that the tail bracket 18 can unfold the tail 7 backward in the slot to assist the flight of the aircraft;

[0030] When the aircraft lands, the locking pin 15 will be unlocked and the trolley 3 will move out of the aircraft bracket 1. During this process, the bearing 22 will roll on the outer wall of the tail wing frame slot 16 of the trolley 3. When it contacts the inclined surface of the inclined block 24, the bearing 22 drives the arm 20 to rise, so that the push rod 21 leaves the tail wing frame slot 16, and the tail 7 is automatically retracted to the tail of the trolley 3 under the action of the tail wing recovery spring 17.

[0031] Through the above steps, the rotorcraft 2 adopts a multi-axis tilt-rotor design, which not only realizes the convenient transportation function, but also can quickly transport the trolley 3 at different locations. In addition, through the tail wing frame push rod assembly and the slide groove 12 locking structure, the aircraft can automatically retract the tail wing 7 and quickly separate and fix the trolley 3. These designs enhance the versatility and practicality of the aircraft, and solve the problem that the rotorcraft does not have the ability to carry a vehicle to fly, thereby reducing the flexibility of use.

[0032] The embodiments of the present invention are described in detail above with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge scope of those skilled in the art without departing from the spirit of the present invention.

Claims

1. A gyro-wing aircraft with a multi-axis tilt-rotor separated from a vehicle and a wing, comprising an aircraft support (1), a gyro-wing (2), a trolley (3), a crossbar (4) and a side rotor (5); characterized in that: The invention also comprises a propeller (6), a tail wing (7), a rudder (8), a tail wing connecting plate (9) and a tail wing frame push rod assembly; the aircraft support (1) is an inverted U-shaped structure and is installed on the upper end of the trolley (3); the upper end of the aircraft support (1) is installed with a rotating wing (2); the left and right outer walls of the aircraft support (1) are fixedly connected with a cross bar (4); one end of the cross bar (4) is installed with a side rotor (5); the rear end of the trolley (3) is installed with a propeller (6); the tail wing frame push rod assembly is installed at the left and right ends of the trolley (3); the tail wing (7) is installed in the tail wing frame push rod assembly; the rudder (8) is installed in the tail wing (7); and a tail wing connecting plate (9) is fixedly connected between two adjacent tail wings (7).

2. The gyroplane with separated multi-axis tilt-rotor according to claim 1, characterized in that: The inner walls at the left and right ends and the inner wall at the upper end of the aircraft bracket (1) are fixedly connected with connection blocks (10), and the end of the connection block (10) facing the trolley (3) is fixedly connected with a slide plate (11).

3. The gyro-wing aircraft with separated multi-axis tilt-rotor according to claim 2, characterized in that: The left and right ends and the upper end of the trolley (3) are both penetrated by a slide groove (12) adapted to the slide plate (11), the slide plate (11) is slidably connected in the slide groove (12) through a connecting block (10), and a locking hole (13) is provided at one end of the slide plate (11) facing the trolley (3).

4. The gyro-wing aircraft with separated multi-axis tilt-rotor wings according to claim 3, characterized in that: A through slot is formed at one end of the slide groove (12) facing the slide plate (11), and the through slot is fixedly connected to one end of a locking spring (14). The other end of the locking spring (14) is fixedly connected to a locking pin (15) adapted to the locking hole (13).

5. The gyroplane with separated multi-axis tilt-rotor according to claim 4, characterized in that: The left and right outer walls of the trolley (3) are provided with tail wing frame grooves (16), and the tail wing frame grooves (16) are located at the upper end of the slide groove (12). The front inner wall of the tail wing frame groove (16) is symmetrically fixedly connected with a tail wing recovery spring (17) in an upper and lower manner. One end of the tail wing recovery spring (17) is fixedly connected with a tail wing bracket (18), and the rear end of the tail wing bracket (18) is equipped with a tail wing (7).

6. The gyroplane with separated multi-axis tilt-rotor according to claim 5, characterized in that: The tail frame push rod assembly comprises a return spring (19), an arm (20), a push rod (21), a bearing (22) and a fixing frame (23); the inner walls of the left and right ends of the aircraft frame (1) are provided with hole grooves, the fixing frame (23) is connected to the inner wall of the aircraft frame (1) through fastening bolts, the push rod (21) is adapted to the tail frame groove (16) and one end of the push rod (21) is sleeved with the return spring (19), one end of the push rod (21) is inserted into the hole groove and the return spring (19) is located outside the hole groove, the other end of the push rod (21) passes through the fixing frame (23), the arm (20) is fixedly connected to the push rod (21) and forms a cross-shaped structure, and both ends of the arm (20) are rotatably connected to the bearing (22).

7. The gyroplane with separated multi-axis tilt-rotor according to claim 6, characterized in that: The outer walls at the left and right ends of the trolley (3) are fixedly connected with inclined blocks (24), and the inclined blocks (24) are located at the upper end of the slide groove (12).

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