Multi-control surface tail support vertical take-off and landing aircraft
Through the design of vertical take-off and landing aircraft supported by the tail of the multi-rudder surface, the existing aircraft have solved the problems of slow flight speed, large energy consumption and low payload, and achieved the effects of rapid flight, energy conservation and payload improvement.
Patent Information
- Application Number
- CN202421265716.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-05
- Publication Date
- 2025-04-08
- Estimated Expiration
- 2034-06-05
AI Technical Summary
Existing helicopters and multi-rotor aircraft have slow flight speed and high energy consumption. The helicopter power units and rotors are idle when the aircraft is level, reducing the payload of the aircraft.
The vertical take-off and landing aircraft design is designed with multiple rudder-face tail support, including the aircraft fuselage, thruster, controllable wing and tail wing, landing support frame and corresponding control devices. By coordinating the angle changes of the wing and tail wing, the aircraft's vertical take-off and landing and lift utilization during the peaceful flight.
It realizes rapid flight and energy saving of the aircraft, while making full use of the aircraft's power device and increasing the payload of the aircraft.
Smart Images
Figure CN222728239U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of aircraft, in particular to a vertical take-off and landing aircraft. Background Art
[0002] Fixed-wing aircraft require a certain speed to generate lift and maintain stable flight, so they generally require a runway for takeoff and landing. Existing helicopters and multirotors can take off and land vertically, but these systems are slow and energy-intensive. Some aircraft also incorporate fixed wings and forward propulsion systems into helicopters or multirotors. However, this approach leaves the lift propulsion system and rotors idle during level flight, and the forward propulsion system idle during takeoff and landing, reducing the aircraft's payload. Utility Model Content
[0003] The present invention addresses the above-mentioned problems, remedies the deficiencies of the prior art, and provides a multi-control surface tail-supported vertical take-off and landing aircraft. The present invention can realize vertical take-off and landing of the aircraft, utilizes the aircraft wings to provide lift during level flight, has a high flight speed, saves energy, and fully utilizes the aircraft's power device, thereby increasing the aircraft's payload.
[0004] In order to achieve the above-mentioned purpose, the present utility model adopts the following technical solutions.
[0005] The utility model provides a multi-control surface tail-supported vertical take-off and landing aircraft, which is characterized in that: the multi-control surface tail-supported vertical take-off and landing aircraft comprises an aircraft fuselage, a propeller, a controllable left wing, a controllable right wing, a controllable longitudinal wing, a landing support frame, a left wing control device, a right wing control device, and a longitudinal wing control device; the left wing control device is connected to the controllable left wing, and the movement of the left wing control device can drive the angle between the controllable left wing or a part of its area and the plane formed by the roll axis and the pitch axis of the aircraft to change; the right wing control device is connected to the controllable left wing, and the movement of the left wing control device can drive the controllable left wing or a part of its area and the plane formed by the roll axis and the pitch axis of the aircraft to change; The wing control device is connected to the controllable right wing. Through the movement of the right wing control device, the angle between the controllable right wing or part of its area and the plane formed by the roll axis and pitch axis of the aircraft can be changed; the longitudinal wing control device is connected to the controllable longitudinal wing. Through the movement of the longitudinal wing control device, the angle between the controllable longitudinal wing or part of its area and the plane formed by the roll axis and yaw axis of the aircraft can be changed; the angle formed by the plane formed by the support point of the landing support frame and the roll axis of the aircraft is greater than 60 degrees.
[0006] Furthermore, the propeller is located in front of the movable parts of the controllable left wing, the controllable right wing, and the controllable longitudinal wing, and the airflow generated by the propeller when it is working flows through part or all of the area of the controllable left wing, the controllable right wing, and the controllable longitudinal wing.
[0007] Furthermore, the multi-control surface tail-supported vertical take-off and landing aircraft also includes a controllable left tail, a controllable right tail, a controllable longitudinal tail, a left tail control device, a right tail control device, and a longitudinal tail control device; the controllable left tail is installed behind the controllable left wing; the controllable right tail is installed behind the controllable right wing; the controllable longitudinal tail is installed behind the controllable longitudinal wing; the left tail control device is connected to the controllable left tail, and the movement of the left tail control device can drive the controllable left tail or a part of its area to be aligned with the aircraft The angle between the plane formed by the roll axis and the pitch axis of the aircraft changes; the right tail control device is connected to the controllable right tail, and the movement of the right tail control device can drive the angle between the controllable right tail or part of its area and the plane formed by the roll axis and the pitch axis of the aircraft to change; the longitudinal tail control device is connected to the controllable longitudinal tail, and the movement of the longitudinal tail control device can drive the angle between the controllable longitudinal tail or part of its area and the plane formed by the roll axis and the yaw axis of the aircraft to change.
[0008] Furthermore, the landing support frame is provided with a shock absorber and is connected to one or more components of the aircraft fuselage, the controllable left wing, the controllable right wing, the controllable longitudinal wing, the controllable left tail, the controllable right tail, and the controllable longitudinal tail, or the landing support frame is connected to one or more components of the aircraft fuselage, the controllable left wing, the controllable right wing, the controllable longitudinal wing, the controllable left tail, the controllable right tail, and the controllable longitudinal tail through the shock absorber.
[0009] Furthermore, the angle between the controllable left wing, the controllable right wing and the plane formed by the roll axis and the pitch axis of the aircraft is no more than 30 degrees.
[0010] Furthermore, the angle between the controllable longitudinal wing and the plane formed by the roll axis and yaw axis of the aircraft is no more than 45 degrees.
[0011] Furthermore, the angle between the controllable left tail wing, the controllable right tail wing and the plane formed by the roll axis and the pitch axis of the aircraft is no more than 30 degrees.
[0012] Furthermore, the included angle between the controllable longitudinal tail and the plane formed by the roll axis and yaw axis of the aircraft is no greater than 45 degrees.
[0013] Furthermore, the angle between the controllable left wing or part of its area and the plane formed by the roll axis and pitch axis of the aircraft varies in a range of not less than -5 degrees to +5 degrees; the angle between the controllable right wing or part of its area and the plane formed by the roll axis and pitch axis of the aircraft varies in a range of not less than -5 degrees to +5 degrees; the angle between the controllable longitudinal wing or part of its area and the plane formed by the roll axis and yaw axis of the aircraft varies in a range of not less than -5 degrees to +5 degrees.
[0014] Furthermore, the angle between the controllable left tail or part of its area and the plane formed by the roll axis and pitch axis of the aircraft varies in the range of not less than -5 degrees to +5 degrees; the angle between the controllable right tail or part of its area and the plane formed by the roll axis and pitch axis of the aircraft varies in the range of not less than -5 degrees to +5 degrees; the angle between the controllable longitudinal tail or part of its area and the plane formed by the roll axis and yaw axis of the aircraft varies in the range of not less than -5 degrees to +5 degrees.
[0015] The beneficial effects of the utility model.
[0016] The multi-control surface tail-supported vertical take-off and landing aircraft of the utility model realizes vertical take-off and landing of the aircraft in a relatively simple and reliable manner, thereby increasing the effective load of the aircraft and saving energy consumption. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.
[0018] Figure 1 It is a schematic diagram of the overall structure of the utility model.
[0019] Markings in the figure: 1 is the aircraft fuselage, 2 is the propeller, 3 is the controllable left wing, 4 is the controllable right wing, 5 is the controllable longitudinal wing, 6 is the landing support, 7 is the left wing control device, 8 is the right wing control device, 9 is the longitudinal wing control device, 10 is the roll axis, 11 is the pitch axis, 12 is the yaw axis, 13 is the controllable left tail, 14 is the controllable right tail, 15 is the controllable longitudinal tail, 16 is the left tail control device, 17 is the right tail control device, 18 is the longitudinal tail control device, and 19 is the shock absorber. DETAILED DESCRIPTION
[0020] As shown in the accompanying drawings, this embodiment provides a multi-control surface tail-supported vertical take-off and landing aircraft including an aircraft fuselage 1, a propeller 2, a controllable left wing 3, a controllable right wing 4, a controllable longitudinal wing 5, a landing support frame 6, a left wing control device 7, a right wing control device 8, and a longitudinal wing control device 9.
[0021] The left wing control device 7 of the aircraft is connected to the controllable left wing 3 of the aircraft. Through the movement of the left wing control device 7, the angle between the controllable left wing 3 or a part of its area and the plane formed by the roll axis 10 and the pitch axis 11 of the aircraft can be changed. When air flows through this part of the area of the controllable left wing 3 with a changed angle, the change in its angle will change the outflow direction of the airflow, thereby changing the force condition of the controllable left wing 3 of the aircraft; the right wing control device 8 of the aircraft is connected to the controllable right wing 4 of the aircraft. Through the movement of the right wing control device 8, the angle between the controllable right wing 4 or a part of its area and the plane formed by the roll axis 10 and the pitch axis 11 of the aircraft can be changed. When air flows through this part of the area of the controllable right wing 4 with a changed angle When the angle of the controllable longitudinal wing 5 is changed, the change of its angle will change the outflow direction of the airflow, thereby changing the force condition of the controllable right wing 4 of the aircraft; the longitudinal wing control device 9 of the aircraft is connected to the controllable longitudinal wing 5 of the aircraft. Through the movement of the longitudinal wing control device 9, the angle between the controllable longitudinal wing 5 or part of its area and the plane formed by the roll axis 10 and the yaw axis 12 of the aircraft can be changed. When air flows through this part of the area of the controllable longitudinal wing 5 with changed angle, the change of its angle will change the outflow direction of the airflow, thereby changing the force condition of the controllable longitudinal wing 5 of the aircraft; through the coordinated actions of the left wing control device 7, the right wing control device 8, and the longitudinal wing control device 9, the aircraft can realize rolling, pitching and yaw movements as needed.
[0022] The plane formed by the supporting points where the aircraft's landing support frame 6 contacts the landing site is substantially perpendicular to the aircraft's roll axis 10 , so the aircraft's nose is facing upward during takeoff and landing.
[0023] When a multi-control surface tail-supported vertical take-off and landing aircraft is taking off or landing, the aircraft's speed is very low, and there is essentially no relative motion between the aircraft and the surrounding atmosphere, resulting in no airflow. The aircraft's propeller 2 is placed in front of the movable portions of the controllable left wing 3, the controllable right wing 4, and the controllable longitudinal wing 5. When the propeller 2 is operating, the airflow it generates can flow through part or all of the areas of the controllable left wing 3, the controllable right wing 4, and the controllable longitudinal wing 5, allowing the aircraft to achieve roll, pitch, and yaw movements as needed during takeoff or landing.
[0024] The multi-control surface tail support vertical take-off and landing aircraft also includes a controllable left tail 13, a controllable right tail 14, a controllable longitudinal tail 15, a left tail control device 16, a right tail control device 17, and a longitudinal tail control device 18, which can further improve the controllability of the aircraft; the controllable left tail 13 is installed behind the controllable left wing 3; the controllable right tail 14 is installed behind the controllable right wing 4; the controllable longitudinal tail 15 is installed behind the controllable longitudinal wing 5; the left tail control device 16 is connected to the controllable left tail 13, and the movement of the left tail control device 16 can drive the angle between the controllable left tail 13 or part of its area and the plane formed by the aircraft roll axis 10 and pitch axis 11 to change, so that when air flows through the controllable left tail 13, its force condition can be changed; the right tail control device 17 is connected to the controllable right tail 14, and the movement of the right tail control device 17 can change the controllable left tail 13. The movement of the longitudinal tail control device 18 can drive the angle between the controllable right tail 14 or a part of its area and the plane formed by the roll axis 10 and the pitch axis 11 of the aircraft to change, and when air flows through the controllable right tail 14, its force condition can be changed; the longitudinal tail control device 18 is connected to the controllable longitudinal tail 15, and through the movement of the longitudinal tail control device 18, the angle between the controllable longitudinal tail 15 or a part of its area and the plane formed by the roll axis 10 and the yaw axis 12 of the aircraft can be changed, and when air flows through the controllable longitudinal tail 15, its force condition can be changed; through the coordinated actions of the left wing control device 7, the right wing control device 8, the longitudinal wing control device 9, the left tail control device 16, the right tail control device 17, and the longitudinal tail control device 18, the aircraft can be made to move up and down or left and right as needed without changing the direction of the nose or tail.
[0025] The landing gear 4 is provided with a shock absorber 19 or the landing gear 4 is connected to other parts of the aircraft via the shock absorber 19 to reduce damage to the aircraft caused by mechanical shock during the landing process.
[0026] The included angle between the controllable left wing 3, the controllable right wing 4 and the plane formed by the roll axis 10 and the pitch axis 11 of the aircraft is not greater than 30 degrees, so that the aircraft has sufficient lift when flying horizontally.
[0027] The included angle between the controllable longitudinal wing 5 and the plane formed by the roll axis 10 and the yaw axis 12 of the aircraft is not greater than 45 degrees, so that the aircraft can generate sufficient yaw moment during flight.
[0028] The included angle between the controllable left tail 13, the controllable right tail 14 and the plane formed by the roll axis 10 and the pitch axis 11 of the aircraft is not greater than 30 degrees, so that the tail of the aircraft has sufficient pitch moment when flying.
[0029] The included angle between the controllable longitudinal tail 15 and the plane formed by the roll axis 10 and the yaw axis 12 of the aircraft is not greater than 45 degrees, so that the tail of the aircraft has sufficient yaw moment when flying.
[0030] The included angle between the controllable left wing 3 or a part of its area and the plane formed by the roll axis 10 and the pitch axis 11 of the aircraft varies in a range of not less than -5 degrees to +5 degrees; the included angle between the controllable right wing 4 or a part of its area and the plane formed by the roll axis 10 and the pitch axis 11 of the aircraft varies in a range of not less than -5 degrees to +5 degrees; the included angle between the controllable longitudinal wing 5 or a part of its area and the plane formed by the roll axis 10 and the yaw axis 12 of the aircraft varies in a range of not less than -5 degrees to +5 degrees, so that the pitch and yaw moments generated by the aircraft can be controlled within a certain range, so that the aircraft can achieve rolling, pitching and yaw movements as needed.
[0031] The included angle between the controllable left tail 13 or a part of its area and the plane formed by the roll axis 10 and the pitch axis 11 of the aircraft varies in a range of not less than -5 degrees to +5 degrees; the included angle between the controllable right tail 14 or a part of its area and the plane formed by the roll axis 10 and the pitch axis 11 of the aircraft varies in a range of not less than -5 degrees to +5 degrees; the included angle between the controllable longitudinal tail 15 or a part of its area and the plane formed by the roll axis 10 and the yaw axis 12 of the aircraft varies in a range of not less than -5 degrees to +5 degrees, so that the pitch and yaw moments generated by the tail of the aircraft can be controlled within a certain range, so that the aircraft can achieve up and down or left and right movement as needed while the nose or tail pointing remains unchanged.
[0032] It can be understood that the above specific description of the present invention is only used to illustrate the present invention and is not limited to the technical solutions described in the implementation methods of the present invention. Ordinary technicians in this field should understand that the present invention can still be modified or replaced by equivalents to achieve the same technical effects; as long as the use requirements are met, they are within the scope of protection of the present invention.
Claims
1. A multi-control surface tail-supported vertical take-off and landing aircraft, characterized in that: The multi-control surface tail-supported vertical take-off and landing aircraft comprises an aircraft fuselage (1), a propeller (2), a controllable left wing (3), a controllable right wing (4), a controllable longitudinal wing (5), a landing support frame (6), a left wing control device (7), a right wing control device (8), and a longitudinal wing control device (9); the left wing control device (7) is connected to the controllable left wing (3), and the movement of the left wing control device (7) can drive the angle between the controllable left wing (3) or a part of its area and the plane formed by the aircraft roll axis (10) and the pitch axis (11) to change; the right wing control device (8) is connected to the controllable left wing (3) and the right wing control device (8). The right wing (4) is connected to the controllable right wing (4), and the movement of the right wing control device (8) can drive the angle between the controllable right wing (4) or a part of its area and the plane formed by the roll axis (10) and the pitch axis (11) of the aircraft to change; the longitudinal wing control device (9) is connected to the controllable longitudinal wing (5), and the movement of the longitudinal wing control device (9) can drive the angle between the controllable longitudinal wing (5) or a part of its area and the plane formed by the roll axis (10) and the yaw axis (12) of the aircraft to change; the plane formed by the support point of the landing support frame (6) and the roll axis (10) of the aircraft forms an angle greater than 60 degrees.
2. The multi-control surface tail-supported vertical take-off and landing aircraft according to claim 1, characterized in that: The propeller (2) is located in front of the movable parts of the controllable left wing (3), the controllable right wing (4), and the controllable longitudinal wing (5); the airflow generated by the propeller (2) when it is in operation flows through part or all of the areas of the controllable left wing (3), the controllable right wing (4), and the controllable longitudinal wing (5).
3. The multi-control surface tail-supported vertical take-off and landing aircraft according to claim 2, characterized in that: The multi-control surface tail-supported vertical take-off and landing aircraft further comprises a controllable left tail (13), a controllable right tail (14), a controllable longitudinal tail (15), a left tail control device (16), a right tail control device (17), and a longitudinal tail control device (18); the controllable left tail (13) is installed behind the controllable left wing (3); the controllable right tail (14) is installed behind the controllable right wing (4); the controllable longitudinal tail (15) is installed behind the controllable longitudinal wing (5); the left tail control device (16) is connected to the controllable left tail (13); and the controllable left tail (13) or a part of its area can be driven to contact the controllable left tail (13) with the aircraft through the movement of the left tail control device (16). The angle of the plane formed by the roll axis (10) and the pitch axis (11) of the aircraft changes; the right tail control device (17) is connected to the controllable right tail (14), and through the movement of the right tail control device (17), the angle of the plane formed by the controllable right tail (14) or a part of its area and the aircraft roll axis (10) and the pitch axis (11) can be changed; the longitudinal tail control device (18) is connected to the controllable longitudinal tail (15), and through the movement of the longitudinal tail control device (18), the angle of the plane formed by the controllable longitudinal tail (15) or a part of its area and the aircraft roll axis (10) and the yaw axis (12) can be changed.
4. The multi-control surface tail-supported vertical take-off and landing aircraft according to claim 3, characterized in that: The landing support frame (6) is provided with a shock absorber (19) and is connected to one or more of the aircraft fuselage (1), the controllable left wing (3), the controllable right wing (4), the controllable longitudinal wing (5), the controllable left tail (13), the controllable right tail (14), and the controllable longitudinal tail (15); or the landing support frame (6) is connected to one or more of the aircraft fuselage (1), the controllable left wing (3), the controllable right wing (4), the controllable longitudinal wing (5), the controllable left tail (13), the controllable right tail (14), and the controllable longitudinal tail (15) via the shock absorber (19).
5. The multi-control surface tail-supported vertical take-off and landing aircraft according to claim 4, characterized in that: The included angle between the controllable left wing (3), the controllable right wing (4) and the plane formed by the roll axis (10) and the pitch axis (11) of the aircraft is no greater than 30 degrees.
6. The multi-control surface tail-supported vertical take-off and landing aircraft according to claim 5, characterized in that: The angle between the controllable longitudinal wing (5) and the plane formed by the roll axis (10) and the yaw axis (12) of the aircraft and the angle between the plane formed by the roll axis and the pitch axis of the aircraft is not greater than 45 degrees.
7. The multi-control surface tail-supported vertical take-off and landing aircraft according to claim 6, characterized in that: The included angle between the controllable left tail wing (13), the controllable right tail wing (14), the plane formed by the roll axis (10) and the pitch axis (11) of the aircraft is not greater than 30 degrees.
8. The multi-control surface tail-supported vertical take-off and landing aircraft according to claim 7, characterized in that: The angle between the controllable longitudinal tail (15) and the plane formed by the roll axis (10) and the yaw axis (12) of the aircraft and the angle between the plane formed by the roll axis and the pitch axis of the aircraft is not greater than 45 degrees.
9. The multi-control surface tail-supported vertical take-off and landing aircraft according to claim 8, characterized in that: The angle between the controllable left wing (3) or a part of its area and the plane formed by the roll axis (10) and the pitch axis (11) of the aircraft varies within a range of not less than -5 degrees to +5 degrees; the angle between the controllable right wing (4) or a part of its area and the plane formed by the roll axis (10) and the pitch axis (11) of the aircraft varies within a range of not less than -5 degrees to +5 degrees; the angle between the controllable longitudinal wing (5) or a part of its area and the plane formed by the roll axis (10) and the yaw axis (12) of the aircraft varies within a range of not less than -5 degrees to +5 degrees.
10. The multi-control surface tail-supported vertical take-off and landing aircraft according to claim 9, characterized in that: The angle between the controllable left tail (13) or a part of its area and the plane formed by the roll axis (10) and the pitch axis (11) of the aircraft varies within a range of not less than -5 degrees to +5 degrees; the angle between the controllable right tail (14) or a part of its area and the plane formed by the roll axis (10) and the pitch axis (11) of the aircraft varies within a range of not less than -5 degrees to +5 degrees; the angle between the controllable longitudinal tail (15) or a part of its area and the plane formed by the roll axis (10) and the yaw axis (12) of the aircraft varies within a range of not less than -5 degrees to +5 degrees.