Unmanned aerial vehicle for high and low speed flight
The wing design, which combines a rotating mechanism and an inflation/deflation system, resolves the performance contradictions of traditional UAVs during high and low speed flight, achieving optimal aerodynamic performance for UAVs under different flight conditions and improving economic efficiency and adaptability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CHENGDU AERONAUTIC POLYTECHNIC
- Filing Date
- 2023-09-21
- Publication Date
- 2026-05-19
AI Technical Summary
Traditional drones suffer from performance conflicts when flying at high and low speeds, making it impossible to meet both high and low speed performance requirements, resulting in insufficient economic benefits and adaptability.
The wing design incorporates a rotating mechanism and an inflation/deflation system. The wing assembly includes a rotatable first wing and a second wing. The wingspan is changed through the inflation/deflation system and the telescopic system. The wing is extended and folded using an elastomer material. Combined with a slant wing structure, it can adapt to different flight conditions.
It improves the economic efficiency and adaptability of UAVs during high and low speed flight, reduces air resistance and aerodynamic torque, and achieves intelligent and multi-functional flight performance to meet different mission requirements.
Smart Images
Figure CN117022698B_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a UAV that can handle both high and low speed flight. Background Technology
[0002] Traditional fixed-wing aircraft have fixed parameters such as wing position, wing length, and sweep angle. For unmanned aerial vehicles (UAVs) primarily engaged in low-speed flight, their wingspan is large (sweep angle is small) to generate greater lift; while for UAVs requiring high-speed flight, they often employ small aspect ratio, large sweep wings to reduce drag. However, small aspect ratio, large sweep wings result in low aerodynamic efficiency and poor lift characteristics at low speeds, while small sweep angle, large aspect ratio wings degrade high-speed performance.
[0003] Therefore, there is a need for a UAV design scheme that can resolve the contradiction between high and low speed performance requirements and improve the economic efficiency and adaptability of aircraft at both high and low speeds. Summary of the Invention
[0004] The purpose of this application is to provide a drone that can balance high and low speed flight, in order to solve the problem that there is a lack of drone design solutions in the prior art that can solve the contradiction between high and low speed performance requirements and improve the economic efficiency and adaptability of the aircraft to high and low speeds.
[0005] To achieve the above objectives, this application provides a drone that can accommodate both high and low speed flight, comprising: a fuselage, a wing assembly, a rotating mechanism disposed on the fuselage, an inflation / deflation system and a telescopic system disposed in the wing assembly, wherein...
[0006] The middle part of the wing assembly is fixedly connected to the rotating mechanism so that the wing assembly can rotate relative to the fuselage;
[0007] The wing assembly includes a first wing at both ends and a second wing in the middle. Each of the first wings at both ends of the wing assembly has a cavity and a folding structure. The first wings can be extended and retracted by the inflation / deflation system and the telescopic system to change the wingspan. The folding structure includes annular first creases and second creases on the inner liner material at each telescopic position of the first wing. The inner liner material at the first crease includes an elastomer.
[0008] Optionally, the telescopic system includes electric actuators for controlling the telescopic movement of the first wing. The electric actuators are mounted on the second wing, and the telescopic ends of the two electric actuators are respectively fixedly connected to the first wing ribs at both ends of the first wing.
[0009] Optionally, the inflation / deflation system includes a gas cylinder, a gas pump, pipelines, and a pressure sensor;
[0010] The gas cylinder is used to store the gas used to fill the cavity;
[0011] The air pump is used to draw gas from the gas cylinder through the pipeline when the first wing is deployed, and to send the gas into the cavity through the pipeline; and to draw gas out of the cavity and compress it into the gas cylinder through the pipeline when the first wing is retracted.
[0012] The pressure sensor is used to monitor the gas pressure in the cavity. During the deployment or retraction of the first wing, when the threshold set by the pressure sensor is reached, the air pump stops working.
[0013] Optionally, the inner liner material of the first wing includes an elastomer and a fabric. The fabric covers the first wing and forms the cavity. An annular elastomer material is laminated onto the fabric at the first crease. When the first wing retracts, the annular elastomer material at the first crease folds and retracts into the first wing under the action of elastic force, thereby realizing the folding of the inner liner material.
[0014] Optionally, the folding structure further includes a first wing rib, and the second crease of the inner liner material is disposed at the first wing rib. When the first wing retracts, the inner liner material on both sides of the second crease folds inward into the first wing under the support of the first wing rib on the second crease.
[0015] Optionally, the second wing includes a second rib, a stringer, and a spars. The second rib and the stringer are used to maintain the shape of the second wing, and the spars are used to bear the main load of the wing assembly.
[0016] Optionally, the rotating mechanism is a high-torque harmonic deceleration rotating mechanism.
[0017] Optionally, the inflation / deflation system further includes solenoid valves disposed at both ends of the first wing for releasing gas pressure when the first wing retracts.
[0018] Optionally, the wing assembly adopts a high-wing configuration.
[0019] Optionally, the fuselage further includes a skin, a bulkhead, a truss, and a battery. The skin covers the fuselage and is used to bear aerodynamic loads. The bulkhead is used to maintain the shape of the fuselage. The truss is used to bear the main loads of the fuselage. The battery is used to supply power to the rotating mechanism, the charging and discharging system, the telescopic system, and the power unit.
[0020] The embodiments of this application have the following advantages:
[0021] This application provides an unmanned aerial vehicle (UAV) that can accommodate both high and low speed flight, including: a fuselage, a wing assembly, a rotating mechanism disposed on the fuselage, an inflation / deflation system and a telescopic system disposed in the wing assembly, wherein the middle part of the wing assembly is fixedly connected to the rotating mechanism so that the wing assembly can rotate relative to the fuselage; the wing assembly includes first wings at both ends and a second wing in the middle, and each of the first wings at both ends of the wing assembly is provided with a cavity and a folding structure, wherein the first wings are extended and retracted by the inflation / deflation system and the telescopic system to change the wingspan, wherein the folding structure includes annular first creases and second creases disposed on the inner liner material at each extension position of the first wing, and the inner liner material at the first crease includes an elastomer.
[0022] Compared with existing technologies, this application provides a UAV with two different wing construction forms: a slanted wing (a combination of wing components and a rotation mechanism) and an inflatable retractable wing (first wing). By combining these two forms through new structures and materials, it accommodates low-speed, subsonic, and supersonic flight configurations, thereby reducing air resistance and aerodynamic torque, improving economic efficiency and flight performance, and enabling more intelligent and multifunctional aircraft designs. The inflatable retractable slanted wing aircraft provided by this application can adapt to different mission requirements, namely, it can perform both high- and low-speed missions, solving the problem in existing technologies of lacking a UAV design solution that can address the contradiction between high and low-speed performance requirements and improve the economic efficiency and adaptability of aircraft at both speeds. Attached Figure Description
[0023] To more clearly illustrate the embodiments of this application or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are merely exemplary, and those skilled in the art can derive other embodiments based on the provided drawings without creative effort.
[0024] Figure 1 A schematic diagram of the high-speed configuration of an unmanned aerial vehicle (UAV) that accommodates both high and low-speed flight, provided as an embodiment of this application;
[0025] Figure 2 A schematic diagram of the internal structure of a high-speed configuration of an unmanned aerial vehicle that can accommodate both high and low-speed flight, provided as an embodiment of this application;
[0026] Figure 3 A schematic diagram of a high-speed configuration of an unmanned aerial vehicle (UAV) that balances high and low-speed flight, provided as an embodiment of this application;
[0027] Figure 4A schematic diagram of a low-speed configuration of an unmanned aerial vehicle that balances high and low-speed flight, provided for another embodiment of this application;
[0028] Figure 5 A schematic diagram of the first wing cross-section at the first crease of a drone that can accommodate both high and low speed flight, provided for another embodiment of this application;
[0029] Figure 6 A schematic diagram of the folding position of the first wing of a drone that can accommodate both high and low speed flight, provided for another embodiment of this application;
[0030] Figure 7 This is a schematic diagram of the fuselage structure of a drone that can accommodate both high and low speed flight, provided as another embodiment of this application. Detailed Implementation
[0031] The following specific embodiments illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0032] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Unless otherwise expressly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal communication of two elements. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.
[0033] Furthermore, the technical features involved in the different embodiments of this application described below can be combined with each other as long as they do not conflict with each other.
[0034] One embodiment of this application provides a drone that can accommodate both high and low speed flight, with reference to... Figure 1 and Figure 2It includes: fuselage 1, wing assembly, rotating mechanism disposed on fuselage 1, inflation / deflation system and telescopic system disposed in wing assembly.
[0035] Specifically, one embodiment of the above-described inflatable drone that can accommodate both high and low speed flight includes: a fuselage 1 made of composite materials and a wing assembly. In some embodiments, the wing assembly adopts a high-wing configuration. The middle part of the wing assembly is fixedly connected to a controllable angle high-torque harmonic deceleration rotating mechanism. The rotating mechanism is connected to the fuselage 1, allowing the wing assembly to rotate relative to the fuselage 1. The wing assembly includes a first wing 2 at both ends and a second wing 3 in the middle. The two ends of the wing assembly are retractable and variable-span inflatable telescopic wings 2 (i.e., the first wing 2), and are provided with cavities and folding structures. The wingspan can be extended and retracted and changed through an inflation / deflation system and a telescopic system (see reference). Figure 3 and Figure 4 ).
[0036] refer to Figure 5 and Figure 6 The folding structure includes an annular first crease 22 and a second crease 23 provided on the inner liner material at each telescopic position of the first wing 2, wherein the inner liner material at the first crease 22 includes an elastomer (15 and 17).
[0037] In some embodiments, the inner liner material of the first wing 2 includes an elastomer and a fabric. The fabric covers the first wing 2 and forms the cavity. An annular elastomer material is laminated onto the fabric at the first crease 22. When the first wing 2 retracts, the annular elastomer material at the first crease 22 folds and retracts into the first wing 2 under the action of elastic force, thereby realizing the folding of the inner liner material.
[0038] In some embodiments, the folding structure further includes a first rib 24, and the second crease 23 of the inner liner material is disposed at the first rib 24. When the first wing 2 is retracted, the inner liner material on both sides of the second crease 23 is folded inward into the first wing 2 under the support of the first rib 24 on the second crease 23.
[0039] Specifically, the inner liner of the inflatable telescopic wing 2 is made of a composite material of fatigue-resistant elastomer (high-performance polymer) and high-strength fabric (aramid fiber). After inflation, the wing airfoil maintains good shape. (Reference) Figure 5 At the first crease 22, on the cross-section of the first wing 2, the inner liner of the inflatable telescopic wing 2 (i.e., the first wing 2) is made of a composite material of fatigue-resistant elastomer (materials 15 and 17) and high-strength fabric (material 16); the first wing extends and retracts by inflating and deflating through cavities set at both ends of the wing assembly. Inflating is simple and rapid. Furthermore, refer to... Figure 6 The first wing 2 has a first crease 22, a first wing rib 24, and a low-stiffness, high-strength elastomer at each telescopic circumferential position. These creases include a first crease 22, a first wing rib 24, and a low-stiffness second crease 23 (i.e., the crease at the first wing rib 24). This structure meets the requirements for folding and shaping. After folding, the shape of the inner liner material of the first wing 2 is referenced. Figure 6 As shown.
[0040] The inflatable telescopic wing constructed using the structure described in the above embodiments is a wing whose wingspan can be adjusted by inflating and deflating gas. Using an inflatable telescopic wing can reduce the structural weight and power consumption of an aircraft, while also enhancing its high- and low-speed adaptability and flight performance.
[0041] Like traditional retractable wings, inflatable retractable wings serve the same purpose: to achieve optimal aerodynamic performance for an aircraft under various flight conditions. Specifically, inflatable retractable wings improve flight efficiency and performance by increasing or decreasing the air pressure inside the gas cylinder (7) to extend or retract the wing surface. This allows the aircraft to maintain an optimal wing shape under different flight conditions, increasing lift and reducing drag. Compared to traditional retractable wings, inflatable retractable wings can employ simpler mechanical structures, thus reducing aircraft weight and cost. In summary, the advantages of the inventive retractable wing aircraft lie primarily in its excellent flight performance, automatic balancing function, energy efficiency, environmental friendliness, lightweight design, and innovative features. These advantages enable the aircraft to perform exceptionally well under diverse flight requirements while meeting modern society's demands for safety, environmental protection, and efficiency.
[0042] refer to Figure 1 In some embodiments, it also includes a tail fin (including a first tail fin 4 and a second tail fin 5) and a power unit 6, etc.
[0043] refer to Figure 2 In some embodiments, the installation angle between the wing assembly and the fuselage 1 is determined by the high-torque harmonic deceleration group 14, that is, the change of the wing rotation angle is controlled by a lightweight harmonic deceleration rotation mechanism with controllable angle.
[0044] Specifically, the oblique wing structure is composed of wing components, fuselage 1, and harmonic reduction and rotation mechanism. An oblique wing is an airfoil in which the left and right halves are a single unit and can rotate around a vertical pivot axis of the fuselage. Compared to traditional straight wings, oblique wings can reduce the area affected by drag during aircraft flight, thereby reducing air resistance and aerodynamic torque, and improving economic efficiency and flight performance.
[0045] The advantages of cantilever wings primarily lie in their superior flight performance, energy efficiency, environmental friendliness, lightweight design, and innovative features. These advantages meet modern society's demands for safety, environmental protection, and efficiency, while also providing passengers with greater comfort and a better flight experience. The cantilever design allows the aircraft to maintain stability and controllability at both low and high speeds, enabling short takeoffs and landings. Lighter and more space-efficient than traditional wings, the cantilever design reduces wing area, making the aircraft lighter and saving space. It also reduces drag, improving speed and fuel efficiency. Furthermore, the cantilever design reduces noise and contrails, enhancing the environmental friendliness of flight.
[0046] Slanted wings and inflatable telescopic wings are two different wing construction forms. By combining the two through new structures, new materials, and new drive forms, and taking into account the low-speed, subsonic, and supersonic configurations of the aircraft, more intelligent and multifunctional aircraft designs can be achieved.
[0047] In some embodiments, the telescopic system includes electric actuators 12 for controlling the telescopic extension and retraction of the first wing 2. The electric actuators 12 are disposed on the second wing 3, and the telescopic ends of the two electric actuators 12 are respectively fixedly connected to the first wing ribs 24 at both ends of the first wing 2 (specifically the two first wing ribs 24 furthest from the fuselage 1).
[0048] Specifically, the telescopic system uses a lightweight electric actuator 12 to extend and retract a specific stroke to achieve changes in wing span, and the electric actuator 12 can also serve as a load-bearing structure to assist the wing spars 13 in bearing the wing load.
[0049] In some embodiments, the inflation / deflation system includes a gas cylinder 7, a gas pump 10, control valves, pipelines, pressure sensors, etc. Inflation is used to fill the wing with gas at a specific pressure to maintain its shape.
[0050] The gas cylinder 7 is used to store gas for inflating the cavity; the air pump 10 is used to draw gas from the gas cylinder 7 through the pipeline when the first wing 2 is deployed, and to send the gas into the cavity through the pipeline, and to draw gas out of the cavity and compress it into the gas cylinder 7 through the pipeline when the first wing 2 is retracted; the pressure sensor is used to monitor the gas pressure in the cavity, and the air pump 10 stops working when the pressure sensor reaches a threshold during the deployment or retraction of the first wing 2.
[0051] Specifically, during inflation, the control valve is opened, and the air pump 10 assists in inflation. When the threshold set by the pressure sensor is reached, the air pump 10 stops working, and the control valve closes. When the wing retracts, the control valve opens, and the air pump 10 compresses the gas, which is then compressed into the gas cylinder 7 through the pipeline. When the threshold set by the pressure sensor is reached, the air pump 10 stops working, and the control valve closes.
[0052] refer to Figure 2 In some embodiments, the inflation / deflation system further includes an electromagnetic valve 11, which is disposed at both ends of the first wing 2 and is used to release gas pressure when the first wing 2 is retracted.
[0053] refer to Figure 2 In some embodiments, the second wing 3 includes a second wing rib 8, a stringer 9, and a spar 13. The second wing rib 8 and the stringer 9 are used to maintain the shape of the second wing 3, and the spar 13 is used to bear the main load of the wing assembly.
[0054] refer to Figure 7 In some embodiments, the fuselage 1 of an inflatable drone that can accommodate both high and low speed flight is composed of a skin 21, a bulkhead 20, a truss 18, a battery 19, and a carbon fiber gas cylinder 7. The skin 21 is used to bear aerodynamic loads, the bulkhead 20 is used to maintain the shape of the fuselage 1, the truss 18 is used to bear the main loads of the fuselage 1, and the battery 19 supplies power to the power unit 6, the solenoid valve 11, the electric actuator 12, etc.
[0055] In summary, compared with existing technologies, this application provides a UAV with two different wing construction forms: a slanted wing (a combination of wing components and a rotation mechanism) and an inflatable retractable wing (first wing). By combining these two forms through new structures and materials, it accommodates low-speed, subsonic, and supersonic configurations, thereby reducing air resistance and aerodynamic torque, improving economic efficiency and flight performance, and enabling more intelligent and multifunctional aircraft designs. The inflatable retractable slanted wing aircraft provided by this application can adapt to different mission requirements, namely, it can perform both high- and low-speed missions, solving the problem in existing technologies of lacking a UAV design solution that can address the contradiction between high and low-speed performance requirements and improve the economic efficiency and adaptability of aircraft at both speeds.
[0056] Note that, unless otherwise explicitly stated, all features disclosed in this specification (including any appended claims, abstract, and drawings) may be replaced by alternative features for achieving the same, equivalent, or similar purpose. Therefore, unless explicitly stated otherwise, each disclosed feature is merely one example of a set of equivalent or similar features. Where used, "further," "preferably," "even further," and "more preferably" are simple starting points for describing another embodiment based on the foregoing embodiments, the combination of which with the foregoing embodiments constitutes the complete configuration of another embodiment. Any combination of several "further," "preferably," "even further," or "more preferably" settings following the same embodiment constitutes yet another embodiment.
[0057] Although this application has been described in detail above with general descriptions and specific embodiments, some modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, all such modifications or improvements made without departing from the spirit of this application fall within the scope of protection claimed in this application.
Claims
1. A drone that can operate at both high and low speeds, characterized in that: include: The fuselage, wing assembly, rotating mechanism mounted on the fuselage, inflation / deflation system and telescopic system mounted in the wing assembly, wherein, The middle part of the wing assembly is fixedly connected to the rotating mechanism so that the wing assembly can rotate relative to the fuselage; The wing assembly includes a first wing and a second wing. The first wing is disposed at both ends of the second wing. Each end of the first wing has a cavity and a folding structure. The first wing can extend and retract through the inflation / deflation system and the telescopic system to change the wingspan. The folding structure includes annular first creases and second creases on the inner liner material at each telescopic position of the first wing. The inner liner material at the first crease includes an elastomer. The gas filling and discharging system includes a gas cylinder, a gas pump, pipelines, and a pressure sensor; The gas cylinder is used to store the gas used to inflate the cavity; The air pump is used to draw gas from the gas cylinder through the pipeline when the first wing is deployed, and to send the gas into the cavity through the pipeline; and to draw gas out of the cavity and compress it into the gas cylinder through the pipeline when the first wing is retracted. The pressure sensor is used to monitor the gas pressure in the cavity. During the deployment or retraction of the first wing, when the threshold set by the pressure sensor is reached, the air pump stops working. The inner liner material of the first wing includes an elastomer and a fabric. The fabric covers the first wing and forms the cavity. An annular elastomer material is laminated on the fabric at the first crease. When the first wing retracts, the annular elastomer material at the first crease folds and retracts into the first wing under the action of elastic force, so as to realize the folding of the inner liner material. The folding structure also includes a first wing rib, and the second crease of the inner liner material is located at the first wing rib. When the first wing retracts, the inner liner material on both sides of the second crease folds inward into the first wing under the support of the first wing rib on the second crease.
2. The UAV that combines high and low speed flight according to claim 1, characterized in that, The telescopic system includes an electric actuator for controlling the extension and retraction of the first wing. The electric actuator is mounted on the second wing, and the telescopic end of the electric actuator is fixedly connected to a first wing rib at the distal end of the first wing.
3. The UAV that combines high and low speed flight according to claim 1, characterized in that, The second wing includes a second rib, a stringer, and a spars. The second rib and the stringer are used to maintain the shape of the second wing, and the spars are used to bear the main load of the wing assembly.
4. The UAV that combines high and low speed flight according to claim 1, characterized in that, The rotating mechanism is a high-torque harmonic deceleration rotating mechanism.
5. The UAV that combines high and low speed flight according to claim 1, characterized in that, The inflation / deflation system also includes solenoid valves, which are located at both ends of the first wing and are used to release gas pressure when the first wing retracts.
6. The UAV that combines high and low speed flight according to claim 1, characterized in that, The wing assembly adopts a high-wing configuration.
7. The UAV that combines high and low speed flight according to claim 1, characterized in that, The fuselage also includes a skin, a bulkhead, a truss, and a battery. The skin covers the fuselage and is used to bear aerodynamic loads. The bulkhead is used to maintain the shape of the fuselage. The truss is used to bear the main loads of the fuselage. The battery is used to supply power to the rotating mechanism, the charging and discharging system, the telescopic system, and the power unit.