Vertical take-off and landing fixed-wing aircraft
By designing a vertical takeoff and landing fixed-wing aircraft, and combining detachable wings, tilting mechanisms, and a power system, the problems of traditional fixed-wing aircraft's dependence on runways and poor maneuverability have been solved. This enables efficient switching and attitude control between vertical takeoff and landing and level flight, adapting to diverse mission requirements.
Patent Information
- Application Number
- CN202520330006.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-26
- Publication Date
- 2025-12-30
- Estimated Expiration
- 2035-02-26
AI Technical Summary
Traditional fixed-wing aircraft require runways for takeoff and landing, have poor maneuverability, and are particularly weak in low-speed flight and vertical takeoff and landing. Furthermore, existing aircraft with vertical takeoff and landing capabilities are complex in design, have low integration of power systems, and are difficult to control in flight attitude, making them unable to meet diverse mission requirements.
A vertical takeoff and landing fixed-wing aircraft was designed, which adopts a combination of detachable wings, tilt mechanism, power mechanism and tail servo to achieve smooth switching between vertical takeoff and landing and level flight. Through the coordinated work of tilt mechanism and power mechanism, the thrust is coordinated and consistent, and the aileron servo and tail servo precisely adjust the flight attitude.
It improves the flight efficiency and safety of aircraft, enables stable switching and precise control in different flight modes, and adapts to take-off, landing and parking in various scenarios.
Smart Images
Figure CN223736237U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to unmanned aerial vehicle technical field, concretely is a kind of vertical take-off fixed wing aircraft. BACKGROUND
[0002] In the field of aircraft, the traditional fixed wing aircraft usually needs a runway of a certain length to realize take-off and landing, relies on the relative motion of wing and airflow to generate lift during flight, and relies on tail to control flight attitude. Such aircraft can normally operate in some sites with suitable runway, such as airport and the like, and the pure vertical take-off aircraft has the disadvantage of insufficient flight time, and the combination of vertical take-off and fixed wing is the optimal solution to solve the difficulty of take-off and landing and insufficient flight time.
[0003] The existing fixed wing aircraft relies heavily on runway, and needs a long sliding distance to reach the required take-off speed, which greatly limits its use scenarios and cannot perform tasks in areas without runway conditions, such as narrow mountainous areas and urban central areas. Moreover, the maneuverability of the traditional fixed wing aircraft during flight is relatively poor, especially in low-speed flight and vertical take-off. In addition, some existing aircrafts that attempt to combine vertical take-off function are often complex in design, have low power system integration, high flight attitude control difficulty, and poor conversion fluency between different flight modes. For example, in the design of tilting mechanism, precise and stable angle control cannot be achieved, resulting in reduced safety and reliability during flight. In terms of power distribution, it is difficult to maintain efficient power output during vertical take-off and horizontal flight, affecting the flight efficiency of the whole machine. These deficiencies make the existing aircraft difficult to adapt to diversified task requirements and unable to cope with some special task scenarios. SUMMARY
[0004] The utility model aims at providing a vertical take-off fixed wing aircraft to solve the problems raised in the background art.
[0005] To achieve the above-mentioned purpose, the utility model provides the following technical scheme: a vertical take-off fixed wing aircraft, comprising: a body and detachable wings, two detachable wings are respectively installed on both sides of the body, and the bottom end of the body is further provided with a plurality of vertical wings; first tubular links, two first tubular links are respectively arranged at the junctions of the body and the two detachable wings; a tail, the tail is arranged in inverted V shape, and the tail is installed on the rear side of the body; second tubular links, the second tubular links are fixedly installed at the top of the inverted V-shaped tail; tilting mechanisms, the tilting mechanisms are arranged in three groups and are respectively installed at the ends of the second tubular links and the two first tubular links; power mechanisms, the three groups of power mechanisms are respectively arranged on the three groups of tilting mechanisms.
[0006] In an implementable embodiment, the detachable wings are further provided with: aileron rudders, two aileron rudders are respectively arranged on the two sides of the body; ailerons, one end of two ailerons is rotatably arranged on the end of the two detachable wings, and the other end is fixedly connected with the rotating shaft of the two aileron rudders.
[0007] In an implementable embodiment, the tail wings are further provided with: tail rudders, two tail rudders are respectively arranged at the ends of the two first tubular links; tail rudders, one end of two tail rudders is rotatably arranged on the tail wing, and the other end is arranged on the driving shaft of the tail rudder; tail rudder covers, two tail rudder covers are respectively arranged at the ends of the two first tubular links, and are used for fixed and protecting the tail rudders.
[0008] In an implementable embodiment, the tilting mechanism comprises: tilting rudders, a plurality of tilting rudders are respectively arranged at the ends of the second tubular link and the two first tubular links through tilting rudder supports; motor seats, a plurality of motor seats are arranged in a U shape, the motor seats are rotatably arranged at the ends of the tilting rudder supports through bearing screws and tilting rudder shafts, and the other ends are fixedly connected with the driving ends of the plurality of tilting rudders.
[0009] In an implementable embodiment, the power mechanism comprises: motors, a plurality of motors are respectively fixedly arranged on the plurality of motor seats; propellers, a plurality of propellers are respectively arranged on the driving ends of the plurality of motors.
[0010] Compared with the prior art, the vertical take-off and landing fixed-wing aircraft has the following beneficial effects: when the vertical take-off and landing fixed-wing aircraft takes off vertically, the tilting mechanism at the first tubular link at the joint between the body and the detachable wing and the second tubular link at the top of the inverted V-shaped tail wing is tilted upward, the power mechanism generates downward thrust, vertical take-off and hovering are realized, and the first tubular link reduces lift to offset; when the aircraft flies forward, the tilting mechanism is tilted forward, the power mechanism generates rearward thrust, the inverted V-shaped tail wing simplifies the steering mechanism and solves the space interference problem. The aileron rudder drives the aileron to move, the roll attitude of the aircraft can be accurately adjusted, the tail rudder controls the angle change of the tail rudder surface, and the yaw attitude adjustment can be realized. The tilting rudder drives the motor seat to change the angle of the power mechanism, and the flight state conversion and attitude control are realized. and pitch motor The driving propeller rotates to generate thrust, and the tilting rudder and the motor cooperate to adjust the angle and the speed, so that the thrust is consistent in different flight stages, the smooth switching of multiple flight modes and the accurate adjustment of the flight attitude are realized, the flight efficiency of the whole machine is improved, and the safe, efficient and stable flight of the aircraft is ensured. BRIEF DESCRIPTION OF DRAWINGS
[0011] Fig. 1 It is the explosion structure schematic view of the utility model;
[0012] Fig. 2 It is the vertical take-off and landing state schematic view of the utility model;
[0013] Fig. 3 It is the flight state schematic view of the utility model.
[0014] In the drawing: 1, machine body, 2, detachable wing, 3, first tubular connecting rod, 4, tail wing, 5, second tubular connecting rod, 6, aileron servo, 7, aileron, 8, tail wing servo, 9, tail wing control surface, 10, tail wing servo cover, 11, tilt servo, 12, motor seat, 13, motor, 14, propeller, 15, vertical wing. DETAILED DESCRIPTION
[0015] The technical scheme in the embodiments of the utility model will be apparently and completely described in conjunction with the drawings in the embodiments of the utility model, and obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by the person skilled in the art without creative labor belong to the protection scope of the utility model.
[0016] Please refer to Figs. 1 to 3 The utility model provides a kind of technical scheme: a vertical take-off and landing fixed wing aircraft, comprising: machine body 1, detachable wing 2, first tubular connecting rod 3, tail wing 4, second tubular connecting rod 5, tilting mechanism and power mechanism, two detachable wings 2 are respectively installed in the two sides of machine body 1, and the bottom end of machine body 1 is also equipped with multiple vertical wings;Two first tubular connecting rods 3 are respectively arranged in the junction of machine body 1 and two sides detachable wing 2;Tail wing 4 is set as inverted V type, and tail wing 4 is installed in the back side of machine body 1;Second tubular connecting rod 5 is fixedly installed at the top of inverted V tail wing 4;Tilting mechanism is set as three groups, and is respectively installed in the end of second tubular connecting rod 5 and two first tubular connecting rods 3;Three groups of power mechanisms are respectively arranged on three groups of tilting mechanisms.
[0017] It should be noted that when taking off vertically, the three sets of tilting mechanisms at the junctions of the two first tubular links 3 on both sides of the fuselage 1 and the second tubular link 5 at the top of the inverted V-shaped tail 4 are tilted upward, at this time, the power mechanisms installed on the three sets of tilting mechanisms generate downward thrust, so that the aircraft can realize vertical take-off and hovering action; when it is needed to fly forward, the three sets of tilting mechanisms are tilted forward, and the power mechanisms generate rearward thrust, in the whole process, the inverted V-shaped tail 4 simplifies the tilting process of the power mechanisms on the tail 4 and effectively solves the problem of space interference in the tilting process of the power mechanisms on the tail 4, at the same time, the three sets of power mechanisms are all in working state during vertical take-off and horizontal flight, thereby improving the flight efficiency of the whole machine, when parking on the ground, the vertical wings provide stable support to prevent the fuselage 1 from tilting, sinking or moving, facilitate maintenance and other operations, the vertical wings play a supporting role when the aircraft is stationary and a longitudinal stabilizer role when flying, adapt to the ground through their own characteristics and ensure safe take-off and landing.
[0018] In some examples, the detachable wings 2 are also provided with: aileron rudders 6 and ailerons 7, two aileron rudders 6 are arranged on both sides of the fuselage 1, and one end of the two ailerons 7 is rotatably arranged at the end of the two detachable wings 2, and the other end is connected with the rotating shaft of the two aileron rudders 6.
[0019] It should be noted that in the vertical take-off fixed-wing aircraft, when the aircraft is in a flight state, the aileron rudders 6 start to work. The aileron rudders 6 installed on both sides of the fuselage 1 through the aileron rudder brackets will produce corresponding actions according to the flight control instructions of the controller inside the fuselage 1. The action of the aileron rudders 6 will drive the ailerons 7 fixedly connected thereto to move, since one end of the ailerons 7 is rotatably arranged at the end of the detachable wings 2, the rotation of the aileron rudders 6 can control the angle change of the ailerons 7. During flight, by changing the angle of the ailerons 7, the rolling attitude of the aircraft can be adjusted, for example, when one side of the ailerons 7 is rotated upward and the other side of the ailerons 7 is rotated downward by the aileron rudders 6, the aircraft will generate corresponding force, thereby realizing precise control of the flight direction and attitude, and ensuring the aircraft to fly stably according to the predetermined route.
[0020] In some examples, the tail 4 is also provided with: a tail rudder 8, a tail rudder surface 9 and a tail rudder cover 10, two tail rudders 8 are arranged at the ends of the two first tubular links 3 through tail rudder brackets; one end of the two tail rudder surfaces 9 is rotatably arranged on the tail 4, and the other end is fixedly arranged on the driving end of the tail rudder 8; two tail rudder covers 10 are arranged at the ends of the two first tubular links 3 to protect the tail rudder 8.
[0021] It should be noted that when the aircraft is in flight, the tail rudder 8 (protected by the tail rudder cover 10) installed at the end of the two first tubular links 3 starts to work under the instruction of the flight control system. The tail rudder 8 is stably installed at the end of the first tubular link 3 through the tail rudder support, and the driving end of the tail rudder 8 drives the tail rudder surface 9 fixedly connected thereto to move. Since one end of the tail rudder surface 9 is rotatably installed on the tail fin 4, the movement of the tail rudder 8 can control the angle change of the tail rudder surface 9. During flight, the tail rudder 8 controls the angle change of the tail rudder surface 9, so as to realize the adjustment of the yaw attitude of the aircraft, so that the aircraft can stably fly in the desired direction, and ensure the accuracy and stability of flight. and pitch
[0022] In some examples, the tilting mechanism includes: a tilting rudder 11 and a motor seat 12. A plurality of tilting rudders 11 are respectively installed at the end of the second tubular link 5 and the two first tubular links 3 through the tilting rudder support; a plurality of motor seats 12 are arranged in a U shape, and the motor seat 12 is rotatably installed at the end of the tilting rudder support through a bearing screw and a tilting rudder shaft, and the other end is fixedly connected with the driving end of the plurality of tilting rudders 11.
[0023] It should be noted that when the tilting mechanism of the vertical take-off and landing fixed-wing aircraft works, when the aircraft needs to convert between vertical take-off and horizontal flight state or adjust other flight attitude, the tilting rudder 11 (stably installed through the tilting rudder support) installed at the end of the second tubular link 5 and the two first tubular links 3 starts to work under the control signal. The driving end of the tilting rudder 11 drives the U-shaped motor seat 12 fixedly connected thereto to move. Since one end of the motor seat 12 is rotatably installed at the end of the second tubular link 5 and the first tubular link 3, the rotation of the tilting rudder 11 can make the motor seat 12 rotate around the installation point. pre-set angle When the tilting rudder 11 drives the motor seat 12 to rotate, the power mechanism installed on the motor seat 12 will change the angle together with the motor seat 12, so as to change the direction of the thrust, realize the conversion between different flight states such as upward tilting to generate downward thrust during vertical take-off and forward tilting to generate backward thrust during forward flight, and further accurately control the flight attitude and movement direction of the aircraft, and ensure the normal flight and performance of the aircraft.
[0024] In some examples, the power mechanism includes: a motor 13 and a propeller 14. A plurality of motors 13 are respectively fixedly arranged on a plurality of motor seats 12; and a plurality of propellers 14 are respectively installed on the driving end of the plurality of motors 13.
[0025] It should be noted that when the aircraft is in flight preparation or flight state, the motor 13 fixedly arranged on the motor seat 12 receives corresponding control instructions. The motor 13 starts according to the instructions, and the driving end starts to rotate. Since the propeller 14 is installed on the driving end of the motor 13, with the rotation of the driving end of the motor 13, the propeller 14 starts to rotate at high speed. In the vertical take-off stage, the motor 13 controls the propeller 14 to rotate to generate downward thrust, which overcomes the gravity of the aircraft to enable it to take off vertically and hover. When the aircraft needs to fly forward, the tilting mechanism tilts the motor seat 12 and the motor 13 as a whole forward, at this time the motor 13 continues to drive the propeller 14 to rotate, generating backward thrust to push the aircraft to fly forward. During the entire flight process, the tilting rudder 11 cooperates with the motor 13 to control the rotation speed and direction of the propeller 14 to adapt to the needs of different flight states, ensuring that the aircraft can fly stably and efficiently, realizing smooth switching of various flight modes such as vertical take-off and horizontal flight and precise adjustment of flight attitude.
[0026] In the description of the present application, it should be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "the other end", "upper", "one side", "top", "inner", "front", "both ends" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation; at the same time, unless otherwise explicitly specified and limited, the terms "arrangement", "installation", "connection", "fixed installation" and the like should be understood in a broad sense, for example, it can be fixed connection, or detachable connection, or integrated; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise explicitly limited, the above-mentioned terms in the present application can be understood according to the specific meaning of the specific circumstances by the ordinary skilled in the art.
[0027] Although the embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, replacements and variations can be made to these embodiments without departing from the principles and spirits of the present application, and the scope of the present application is defined by the appended claims and their equivalents.
Claims
1. A vertical take-off and landing fixed wing aircraft characterised in that, The utility model relates to a kind of unmanned aerial vehicle, including: Machine body and detachable wings, two the detachable wings are respectively installed in the two sides of machine body, the bottom end of the machine body is also equipped with two vertical wings; First tubular link, two the first tubular link is respectively arranged in the junction of machine body and two sides detachable wings; Tail wing, the tail wing is set to inverted V type, and the tail wing is installed in the back of machine body; Second tubular link, the second tubular link is fixedly installed in the top of inverted V tail wing; Tilt mechanism, the tilt mechanism is set to three groups, and is respectively installed in the end of second tubular link and two the first tubular link; Power mechanism, three groups the power mechanism is respectively arranged on three groups the tilt mechanism.
2. The vertical take-off and landing fixed-wing aircraft according to claim 1, characterized in that: The detachable wing is also equipped with: Aileron servo, two the aileron servo is respectively arranged in the two sides of machine body; Ailerons, one end of two ailerons is rotatably arranged at the end of two detachable wings respectively, and the other end is connected with two aileron steering engines Shaft respectively.
3. The vertical take-off and landing fixed-wing aircraft according to claim 1, characterized in that: The tail wing is also equipped with: Tail wing servo, two the tail wing servo is respectively in the end of two the first tubular link; Tail wing rudder, one end of two the tail wing rudder is rotatably installed on tail wing, and the other end is fixedly installed on the drive shaft of tail wing servo; Tail fin rudder machine cover, two said tail fin rudder machine cover is installed in two said first tubular connecting rod end, for Solid and The tilt mechanism includes: Protect the tail fin rudder machine.
4. The vertical take-off and landing fixed-wing aircraft according to claim 1, characterized in that: Tilt servo, several the tilt servo is respectively installed in the end of second tubular link and two the first tubular link by tilt servo support; Motor seat, several the motor seat is set to U shape, the motor seat is rotatably installed in the end of tilt servo support by bearing screw and tilt servo shaft, and the other end is fixedly connected with the drive end of several the tilt servo. The power mechanism includes:
5. The vertical take-off and landing fixed-wing aircraft according to claim 4, characterized in that: Motor, several the motor is respectively fixedly arranged on several the motor seat; Propeller, several the propeller is respectively installed on the drive end of several the motor.