Telescopic cross-shaped tail base assembly and vertical take-off and landing aircraft

Abstract

The telescopic cross-shaped tail base assembly and the vertical take-off and landing aircraft belong to the field of vertical take-off and landing aircrafts, the telescopic cross-shaped tail base assembly comprises an aircraft body, a coaxial reverse propeller power device is arranged at the front end of the aircraft body, a left wing and a right wing are symmetrically arranged on the two sides of the aircraft body, and a telescopic cross-shaped tail base is arranged at the middle axis position of the aircraft body; the telescopic cross-shaped tail base moves backwards by a certain distance to change the shape, the shape of the aircraft with the changed shape is close to that of a conventional fixed-wing aircraft, and the performance of the aircraft is close to that of the conventional fixed-wing aircraft.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to a retractable cross tail seat assembly and a vertical take-off and landing aircraft. Background Art

[0002] A tail-seat vertical take-off and landing aircraft has a high center of gravity during take-off and landing, which is not conducive to maintaining balance during take-off and landing. In order to lower the center of gravity during vertical take-off and landing, maintain balance and improve stability and safety, a retractable cross-machine tail seat assembly and a vertical take-off and landing aircraft are proposed. Summary of the invention

[0003] The present invention discloses a retractable cross tail seat assembly and a vertical take-off and landing aircraft. The cross-shaped tail seat retractable tail design is adopted. The center of gravity is lowered during vertical take-off and landing to maintain balance and improve safety. When used in combination with a vertical take-off and landing tilt-body horizontal cruise aircraft, good maneuverability and energy saving can be maintained when tilting to a horizontal posture for cruising flight.

[0004] In order to provide a tail-seat retractable tail vertical take-off and landing aircraft with relatively flexible and reliable control and relatively safe operation, the present invention provides the following technical solutions: The present invention provides a retractable cross tail seat assembly and a vertical take-off and landing aircraft, comprising a body, wherein a movable body is provided at the central axis of the body, the movable body is covered with a positioning sleeve, the movable body can only move forward and backward under the limitation of the positioning sleeve, and the positioning sleeve is fixed to the rear of the body.

[0005] Preferably, the front end of the movable body is provided with a left gear and a right gear, the left gear is positioned by a left gear positioning frame, the left gear positioning frame is fixed to the left side of the front end of the movable body, and the right gear is provided with a servo motor for positioning and powering it, and the servo motor is fixed to the right side of the front end of the movable body.

[0006] Preferably, the left gear and the right gear are mutually meshing gears with the same teeth and the same diameter.

[0007] Preferably, a left linear rack is provided in parallel on the left side of the movable body, and a right linear rack is provided in parallel on the right side of the movable body, and the left linear rack and the right linear rack are fixed in the body.

[0008] Preferably, the left linear rack is meshed with the left gear, and the right linear rack is meshed with the right gear.

[0009] Preferably, a limiting groove is provided on the right side of the front part of the movable body, and the limiting groove is half-sheathed on the right linear rack and can move forward and backward with the movable body, so as to prevent the movable body from rotating.

[0010] Preferably, the limiting groove is provided with a permanent magnet.

[0011] Preferably, a front magnetic sensor is provided at the front of the right linear rack and a rear magnetic sensor is provided at the rear, and the front magnetic sensor and the rear magnetic sensor correspond to the permanent magnets arranged between preset travels when the movable body moves forward and backward.

[0012] Preferably, a flexible load-bearing pad is provided at the rear end of the movable body, and the flexible load-bearing pad is located at the center of gravity and bears most of the weight of the aircraft.

[0013] Preferably, the movable body is provided with a left tail wing on the left rear side, a right tail wing on the right side, an upper tail wing on the upper side, and a lower tail wing on the lower side, and the four tail wings form a cross configuration.

[0014] Preferably, a left supporting foot is provided on the outer side of the left tail wing, the left supporting foot is provided with a left buffer spring and a left buffer pad, and a left horizontal rudder is provided on the rear edge of the left tail wing.

[0015] Preferably, a right supporting foot is provided on the outer side of the right tail wing, the right supporting foot is provided with a right buffer spring and a right buffer pad, and a right horizontal rudder is provided on the rear edge of the right tail wing.

[0016] Preferably, an upper supporting foot is provided on the outer side of the upper tail wing, the upper supporting foot is provided with an upper buffer spring and an upper buffer pad, and an upper vertical rudder wing is provided on the rear edge of the upper tail wing.

[0017] Preferably, a lower supporting foot is provided on the outer side of the lower tail wing, the lower supporting foot is provided with a lower buffer spring and a lower buffer pad, and a lower vertical rudder wing is provided at the rear edge of the lower tail wing.

[0018] Preferably, the left supporting foot, the right supporting foot, the upper supporting foot and the lower supporting foot serve to support the aircraft to maintain balance when the aircraft lands, and do not need to play a load-bearing role.

[0019] The above components constitute a retractable cross machine tailstock.

[0020] The present invention also provides a vertical take-off and landing aircraft, which is a vertical take-off and landing aircraft using the retractable cross tail seat assembly.

[0021] Preferably, a left wing and a right wing are provided on both sides of the fuselage, and a coaxial counter-propeller power device is provided at the front end of the fuselage.

[0022] Preferably, the aircraft is completely symmetrical left to right and belly to back, which is beneficial to dynamic balance when adjusting posture during vertical take-off and landing operations.

[0023] Preferably, after the retractable cross tail seat moves backwards a certain distance, the shape of the aircraft changes, and its shape is close to that of a conventional fixed-wing aircraft, and its performance is also close to that of a conventional fixed-wing aircraft.

[0024] The beneficial effects of the present invention are: The retractable cross tail seat assembly and vertical take-off and landing aircraft adopt a tail seat retractable tail design, which lowers the center of gravity to maintain balance and improve safety during vertical take-off and landing, and can also maintain good maneuverability during horizontal attitude cruising flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention.

[0026] In the attached picture: Figure 1 Schematic diagram of the back structure of the aircraft when the tail seat is not extended Figure 2 Schematic diagram of the back structure of the aircraft when the tail seat has been extended Figure 3 This is a schematic diagram of the right side structure of the aircraft when the tail seat is not extended. Figure 4 This is a schematic diagram of the right side structure of the aircraft when the tail seat has been extended. Figure 5 for Figure 3 Enlarged diagram of point C in the middle Figure 6 for Figure 1 Enlarged diagram of point B in the middle Figure 7 for Figure 1 Schematic diagram of cross section at point A Figure 8 Schematic diagram of the aircraft's takeoff, level flight, and landing posture changes Fig. 9 Schematic diagram of the tail seat configuration of the aircraft In the figure: 1, body 2, movable body 3, positioning sleeve 4, left linear rack 5, right linear rack 6, left gear 7, right gear 8, servo motor 9, limit slot 10, front magnetic sensor 11, rear magnetic sensor 12, flexible load-bearing pad 13, left tail 14, left supporting foot 15, left buffer spring 16, left buffer pad 17, left horizontal rudder wing 18, right tail 19, right supporting foot 20, right buffer spring 21, right buffer pad 22, right horizontal rudder wing 23, upper tail 24, upper supporting foot 25, upper buffer spring 26, upper buffer pad 27, upper vertical rudder wing 28, lower tail wing 29, lower supporting foot 30, lower buffer spring 31, lower buffer pad 32, lower vertical rudder wing 33, right wing 34, left wing 35, permanent magnet 36, left gear positioning frame 37, coaxial reverse propeller power device DETAILED DESCRIPTION

[0027] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0028] Example: Figure 3 Figure 8 As shown, the vertical take-off and landing aircraft starts the coaxial reverse propeller power device 37 to control the aircraft to leave the ground and move upward.

[0029] Further, if Figure 1 Figure 2 Figure 5 Figure 6 Figure 8 As shown, when the aircraft rises to a certain height, the servo motor 8 is started to drive the left gear 6 and the right gear 7 to rotate. The left gear 6 and the right gear 7 use the left linear rack 4 and the right linear rack 5 to push the movable body 2 to the rear of the body 1. When the permanent magnet 35 on the limit slot 9 moves to the position of the rear magnetic sensor 11, the movable body 2 reaches the preset position. The rear magnetic sensor 11 sends a signal to stop the servo motor 8 and then locks it. At this time, the aircraft has been changed into a shape close to that of a conventional fixed-wing aircraft.

[0030] Further, as 1 Figure 8 As shown, the left horizontal rudder wing 17 and the right horizontal rudder wing 22 are controlled to adjust the aircraft to a level flight cruising attitude. During the level flight cruising process, the aircraft can be controlled according to the control method of a conventional fixed-wing aircraft.

[0031] Further, if Figure 1 Figure 8 As shown, when flying forward to a high altitude close to the destination, the left horizontal rudder wing 17 and the right horizontal rudder wing 22 are manipulated to adjust the aircraft to a vertical attitude.

[0032] Further, if Figure 1 Figure 2 Figure 5 Figure 6 Figure 8 As shown, the servo motor 8 is started in reverse to drive the left gear 6 and the right gear 7 to rotate. The left gear 6 and the right gear 7 use the left linear rack 4 and the right linear rack 5 to move the movable body 2 to the front of the body 1. When the permanent magnet 35 on the limit slot 9 moves to the position of the front magnetic sensor 10, the body 2 reaches the preset position, and the front magnetic sensor 10 sends a signal to stop the body 8 and then locks it. At this time, the movable body 2 has retracted into place, and the aircraft is restored to the shape before take-off and can perform landing operations.

[0033] Further, if Figure 1 Figure 8 As shown, the coaxial reverse propeller power device 37 is controlled to make the aircraft slowly descend to the ground.

[0034] Further, if Figure 1 Figure 8 As shown, after the aircraft is stabilized at a stop, the coaxial reverse propeller power device 37 is shut down, and the flight process ends.

[0035] The above is only a specific implementation of the present invention, and the unexplained parts are conventional technologies, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention and ordinary technicians in the technical field should be included in the protection scope of the present invention without departing from the principle of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A retractable cross tailstock assembly, characterized in that: The invention comprises a machine body 1, wherein a movable machine body 2 is provided at the central axis position of the machine body 1, wherein the movable machine body 2 is sleeved with a positioning sleeve 3, wherein the movable machine body 2 can only move forward and backward under the limitation of the positioning sleeve 3, and the positioning sleeve 3 is fixed to the rear part of the machine body 1; a left gear 6 and a right gear 7 are provided at the front end of the movable machine body 2, wherein the left gear 6 is positioned by a left gear positioning frame 36, wherein the left gear positioning frame 36 is fixed to the left side of the front end of the movable machine body 2, wherein the right gear 7 is provided with a servo motor 8 for positioning and providing power therefor, wherein the servo motor 8 is fixed to the right side of the front end of the movable machine body 2; wherein the left gear 6 and the right gear 7 are mutually meshing gears with the same teeth and the same diameter; wherein the movable machine body 2 A left linear rack 4 is provided in parallel on the left side, and a right linear rack 5 is provided in parallel on the right side of the movable body 2. The left linear rack 4 and the right linear rack 5 are fixed in the body 1; the left linear rack 4 is meshed with the left gear 6, and the right linear rack 5 is meshed with the right gear 7; a limiting groove 9 is provided on the right side of the front of the movable body 2, and the limiting groove 9 is half-sheathed on the right linear rack 5 and can follow the movable body 2 to move forward and backward, and the function is to prevent the movable body 2 from rotating. The limiting groove 9 is provided with a permanent magnet 35; a front magnetic sensor 10 is provided at the front of the right linear rack 5, and a rear magnetic sensor 11 is provided at the rear, and the front magnetic sensor 10 and the rear magnetic sensor 11 correspond to the permanent magnet 35. The magnet 35 is arranged between the preset strokes when the movable body 2 moves forward and backward; the rear end of the movable body 2 is provided with a flexible load-bearing pad 12, and the flexible load-bearing pad 12 is located at the center of gravity and bears most of the weight of the aircraft; the movable body 2 is provided with a left tail 13 on the left side at the rear, a right tail 18 on the right side, an upper tail 23 on the upper side, and a lower tail 28 on the lower side, and the four tails are in a cross-shaped configuration; a left supporting foot 14 is provided on the outer side of the left tail 13, and the left supporting foot 14 is provided with a left buffer spring 15 and a left buffer pad 16, a left horizontal rudder 17 is provided on the rear edge of the left tail 13, and a right supporting foot 19 is provided on the outer side of the right tail 18, and the right supporting foot 19 is provided with a right buffer spring Spring 20 and right buffer pad 21, the rear edge of the right tail 18 is provided with a right horizontal rudder wing 22, the outer side of the upper tail 23 is provided with an upper supporting foot 24, the upper supporting foot 24 is provided with an upper buffer spring 25 and an upper buffer pad 26, the rear edge of the upper tail 23 is provided with an upper vertical rudder wing 27, the outer side of the lower tail 28 is provided with a lower supporting foot 29, the lower supporting foot 29 is provided with a lower buffer spring 30 and a lower buffer pad 31, the rear edge of the lower tail 28 is provided with a lower vertical rudder wing 32, the left supporting foot 14, the right supporting foot 19, the upper supporting foot 24, and the lower supporting foot 29 are used to support the aircraft to maintain balance when the aircraft lands, and do not need to play a load-bearing role; the above components constitute a retractable cross tail seat.

2. A vertical take-off and landing aircraft, characterized in that: The vertical take-off and landing aircraft is a vertical take-off and landing aircraft using the retractable cross tail seat. After the retractable cross tail seat moves backward a certain distance, the shape of the aircraft changes, and its shape is close to that of a conventional fixed-wing aircraft, and its performance is also close to that of a conventional fixed-wing aircraft.

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