A combined aircraft based on aerodynamic separation

Abstract

The application relates to the technical field of aircrafts, in particular to a combined aircraft based on aerodynamic separation, which comprises a power mechanism for providing flight power for the combined aircraft, a combined separation mechanism arranged at one end of the power mechanism, and a plurality of unmanned aerial vehicle bodies arranged in an array around the combined separation mechanism; when the combined separation mechanism is in a first state, the unmanned aerial vehicle bodies are combined and wrapped outside the combined separation mechanism to form a pyramid-shaped outer surface, and the combined separation mechanism limits and maintains the pyramid-shaped outer surface; when the combined separation mechanism is in a second state, the combined separation mechanism releases the limitation on the pyramid-shaped outer surface and assists in pushing the plurality of unmanned aerial vehicle bodies to separate from each other to form a positive angle of attack posture relative to the direction of the wind flow until the plurality of unmanned aerial vehicle bodies are separated from the combined separation mechanism. The application can balance the high thrust-to-weight ratio and the flexible multi-load delivery, and can effectively convert the aerodynamic interference into aerodynamic separation force, so that the timeliness and stability of the unmanned aerial vehicle delivery are improved.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, specifically to a combined aircraft based on aerodynamic separation. Background Technology

[0002] Drone delivery technology is widely used in emergency rescue, material distribution, and plant protection. Current delivery methods primarily include mechanical dropping, electromagnetic release, and servo motor traction. The assembly methods of drones and transport carriers mainly include external attachment, internal attachment, tail delivery, top-mounted delivery, and backpack mounting.

[0003] There is a fundamental technical contradiction in the existing assembly methods of conventional drones and transport vehicles: in order to achieve a high thrust-to-weight ratio, ensure flight power and delivery stability, a single drone simplifies the delivery mechanism and compresses the effective payload space, making it difficult to meet the needs of simultaneous delivery of drone swarms; while multiple deliveries require increasing the load on the transport vehicle or adding a complex delivery mechanism, which limits the range of transport vehicle options and significantly reduces the thrust-to-weight ratio. Meanwhile, existing delivery devices are limited by their own layout and structure. During the delivery process, aerodynamic interference causes a low-pressure area between the drone and the transport vehicle, resulting in unstable drone attitude during separation and slow separation speed. In summary, there is an urgent need for a combined aircraft that can balance high thrust-to-weight ratio and flexible deployment of multiple payloads, and can effectively convert aerodynamic interference into aerodynamic separation, in order to improve the timeliness and stability of UAV deployment. Summary of the Invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide a combined aircraft based on aerodynamic separation, comprising: A power mechanism, which provides flight power to the combined aircraft; A combined separation mechanism is disposed at one end of the power mechanism; The drone body includes multiple drone fuselages arranged around the array of combined separation mechanisms; The combined separation mechanism has a first state and a second state. When the combined separation mechanism is in the first state, the multiple drone fuselages are combined and covered by the combined separation mechanism to form a pyramidal outer surface, and the combined separation mechanism limits and holds the pyramidal outer surface. When the combined separation mechanism switches from the first state to the second state, the combined separation mechanism releases the limit on the pyramidal outer surface and assists in pushing the multiple drone fuselages to separate from each other to form a positive angle of attack attitude relative to the windward airflow until they detach from the combined separation mechanism under the action of the windward airflow.

[0005] According to the technical solution provided in this application, the cross-sectional area of ​​the drone fuselage perpendicular to its axis gradually increases from the head of the drone fuselage to the tail of the drone fuselage.

[0006] According to the technical solution provided in this application, the bottom surface of the UAV fuselage is an arc-shaped lifting surface.

[0007] According to the technical solution provided in this application, multiple drone wings are equally spaced on the top surface of the drone fuselage, and drone air rudders are provided on the drone wings. The drone air rudders are used to adjust the flight attitude of the drone fuselage.

[0008] According to the technical solution provided in this application, the combined separation mechanism includes: A hydraulic rod assembly is disposed at one end of the power mechanism, and a fairing is disposed at the end of the hydraulic rod assembly away from the power mechanism; A support rod assembly, one end of which is rotatably connected to the power mechanism, and the support rod assembly is drive-connected to the hydraulic rod assembly; When the combined separation mechanism is in the first state, the fairing is fastened to the head of the multiple drone fuselages, and the support rod assembly is engaged with the tail of the multiple drone fuselages through the limiting assembly to limit and retain the pyramidal outer surface; When the combined separation mechanism switches from the first state to the second state, the hydraulic rod assembly drives the fairing to detach from the head of the UAV fuselage, and at the same time drives the support rod assembly to move along the axis of the power mechanism, releasing the restriction on the pyramidal outer surface and assisting in pushing the multiple UAV fuselages to separate from each other until they detach from the support rod assembly under the action of the windward airflow.

[0009] According to the technical solution provided in this application, the hydraulic rod assembly includes: A hydraulic actuator, which is fixedly mounted on the power mechanism, with the axis of its drive end coaxial with the axis of the power mechanism; A hydraulic strut, one end of which is fixedly connected to the drive end of the hydraulic device, and the other end of which is fixedly connected to the fairing, the fairing being matched with the head contour of the pyramidal outer surface; A hydraulic positioner is fixedly sleeved on the hydraulic support rod. When the combined separation mechanism switches from the first state to the second state, the hydraulic positioner is used to transmit the driving force of the hydraulic device to the support rod assembly. A support locator, one end of which is fixedly connected to the hydraulic device, and the other end of which is used to abut against the support rod assembly.

[0010] According to the technical solution provided in this application, the support rod assembly includes: A limiting chuck is movably sleeved on the hydraulic support rod and located on the side of the hydraulic positioner away from the hydraulic actuator; Active rods, one of which correspond to one of the multiple drone bodies, with one end of each active rod hinged to the limiting chuck; A passive rod, one end of which is hinged to the end of the active rod away from the limiting chuck.

[0011] According to the technical solution provided in this application, the support positioner includes a plurality of support rods corresponding one-to-one with the fuselage of the UAV; the end of the support rod away from the hydraulic device is used to abut against the hinged part of the active rod and the passive rod.

[0012] According to the technical solution provided in this application, the limiting component includes: A limiter is fixedly connected to the end face of the power mechanism near the UAV body and hinged to the other end of the passive rod. A limiting block is fixedly connected to the side of the passive rod away from the hydraulic support rod; When the combined separation mechanism is in the first state, the limiter abuts against the top surface of the drone fuselage, and the limit block abuts against the bottom surface of the drone fuselage, so that the passive rod engages with the tail of the drone fuselage; the end of the support rod away from the hydraulic unit abuts against the hinge of the active rod and the passive rod, so as to limit the relative positions of the active rod and the passive rod, as well as the passive rod and the power mechanism.

[0013] According to the technical solution provided in this application, the power mechanism includes: The booster transition section has an edge profile that matches the pyramidal outer surface at the connection point between the outer surface of the booster transition section and the outer surface of the pyramidal outer surface. A hydraulic groove for installing the hydraulic device is opened along the axial direction on one end face of the booster transition section near the UAV body. The power compartment has multiple power compartment wings evenly spaced on its periphery, and the power compartment wings are equipped with power compartment air rudders for controlling the flight attitude of the power mechanism.

[0014] The beneficial effects of this application are as follows: In the initial assembled state, the assembly and separation mechanism is in its first state. Since multiple UAV fuselages are wrapped around the assembly and separation mechanism to form a pyramidal shape, the pyramidal shape can reduce the flight drag of the combined aircraft during flight. This layout can also reduce the space occupied by the UAV bodies in the combined aircraft, allowing more UAV fuselages to be arranged in a limited space, thereby improving the effective volume ratio of the combined aircraft. During the flight phase, the power mechanism of the combined aircraft provides unified flight power to each UAV fuselage. Each UAV fuselage does not need to be equipped with a separate power propulsion system, reducing the weight ratio of the UAV fuselage and thus improving the thrust-to-weight ratio of the combined aircraft. After the multiple UAV fuselages are separated from the power mechanism, they can carry different types of payloads to different target areas, thereby realizing flexible deployment of multiple payloads.

[0015] When the UAV body and power mechanism need to be separated, the combined separation mechanism switches from the first state to the second state. The combined separation mechanism releases the restriction on the pyramidal outer surface and assists in pushing multiple UAV bodies to separate from each other to form a positive angle of attack attitude relative to the windward airflow direction. Due to the pressure on the windward side of the UAV body, a high-pressure zone is formed on the windward side of the UAV body, while a low-pressure zone is formed on the leeward side of the UAV body. This generates a normal aerodynamic force on the UAV body that is away from the windward direction. This normal aerodynamic force can accelerate the separation of the UAV body from the power mechanism and ensure the stability of the UAV body's flight attitude. It effectively converts aerodynamic interference into aerodynamic separation force, improving the timeliness and stability of UAV body deployment. Attached Figure Description

[0016] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 An exploded structural diagram of a combined aircraft based on aerodynamic separation is provided for an embodiment of this application; Figure 2 A schematic diagram of the combined separation mechanism of a combined aircraft based on aerodynamic separation in a first state, provided in an embodiment of this application; Figure 3 for Figure 2 A schematic diagram of the internal support rod assembly and hydraulic rod assembly; Figure 4 A schematic diagram of the intermediate process of a combined aircraft based on aerodynamic separation switching from a first state to a second state, provided for an embodiment of this application; Figure 5 for Figure 4 A schematic diagram of the internal support rod assembly and hydraulic rod assembly; Figure 6 A schematic diagram of the combined separation mechanism of a combined aircraft based on aerodynamic separation in a second state, provided in an embodiment of this application; Figure 7 for Figure 6 A schematic diagram of the internal support rod assembly and hydraulic rod assembly; Figure 8 for Figure 1 A schematic diagram of the fuselage of a medium-sized unmanned aerial vehicle (UAV); Figure 9 for Figure 1 Another structural diagram of the UAV fuselage; Figure 10 for Figure 1 Schematic diagram of the middle support rod assembly; Figure 11 for Figure 6 Schematic diagram of the middle section; Figure 12 for Figure 1 Schematic diagram of the hydraulic rod assembly; Figure 13 for Figure 1 A schematic diagram of the assembly structure of the middle support rod assembly and the hydraulic rod assembly; Figure 14 for Figure 1 Schematic diagram of the power mechanism; Figure 15 A schematic diagram of the connection structure between the support rod assembly and the power mechanism of a combined aircraft based on aerodynamic separation, provided in an embodiment of this application; Numbering on the map: 1. UAV body; 101. UAV fuselage; 102. UAV wing; 103. UAV air control; 104. Bottom surface; 105. Top surface; 2. Power mechanism; 201. Boost transition section; 202. Limiter; 203. Hydraulic groove; 204. Power compartment section; 205. Power compartment section wing; 3. Support rod assembly; 301. Limit chuck; 302. Active rod; 303. Passive rod; 304. Limit block; 4. Hydraulic rod assembly; 401. Fairing; 402. Hydraulic strut; 403. Hydraulic positioner; 404. Support positioner; 405. Hydraulic unit. Detailed Implementation

[0017] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings.

[0018] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0019] Please refer to Figures 1-15 A combined aircraft based on aerodynamic separation, comprising: Power mechanism 2, which provides flight power for the combined aircraft; A combined separation mechanism is disposed at one end of the power mechanism 2; The drone body 1 includes a plurality of drone fuselages 101 arranged around the array of combined separation mechanisms; The combined separation mechanism has a first state and a second state. When the combined separation mechanism is in the first state, multiple UAV fuselages 101 are combined and covered to form a pyramidal outer surface, and the combined separation mechanism limits and holds the pyramidal outer surface. When the combined separation mechanism switches from the first state to the second state, the combined separation mechanism releases the limit on the pyramidal outer surface and assists in pushing the multiple UAV fuselages 101 to separate from each other to form a positive angle of attack attitude relative to the windward airflow until they detach from the combined separation mechanism under the action of the windward airflow.

[0020] Specifically, such as Figure 2 As shown, in the initial combined state, the combination separation mechanism is in the first state, with three UAV fuselages 101 covering the outside of the combination separation mechanism, forming a pyramidal outer surface set at one end of the power mechanism 2. The adjacent sides of the pyramidal outer surface are transitioned by rounded curved surfaces. The pyramidal outer surface can reduce the flight drag of the combined aircraft, and the pyramidal layout can integrate the originally dispersed multiple UAV fuselages 101 into a whole, allowing more UAV fuselages 101 to be arranged in a limited space. Compared with the traditional assembly method of UAVs and transport carriers, the pyramidal layout integrates more UAV fuselages 101 in the same transport space, improving the space utilization and effective volume ratio of the combined aircraft. Furthermore, in the traditional single-drone deployment method, a single drone undertakes both flight propulsion and the entire payload. The higher the payload, the lower its thrust-to-weight ratio, resulting in reduced flight power and stability of the single drone. In this application, the power mechanism 2 provides unified flight power for each drone fuselage 101, eliminating the need for separate power propulsion systems for each drone fuselage 101. This reduces the weight ratio of the drone fuselage 101 and thus improves the thrust-to-weight ratio of the combined aircraft. Furthermore, after the drone body 1 is transported to the target area by the power mechanism 2, each drone fuselage 101 separates from the power mechanism 2. Since each drone fuselage 101 is independent of each other, it can carry different types of payloads and fly to different target areas, thereby realizing flexible deployment of multiple payloads.

[0021] Specifically, when the UAV body 1 and the power mechanism 2 need to separate, the combined separation mechanism switches from the first state to the second state. The combined separation mechanism releases the restriction on the pyramidal outer surface and assists in pushing multiple UAV bodies 101 to separate from each other to form a positive angle of attack attitude relative to the windward airflow direction. Due to the pressure on the windward side of the UAV body 101, a high-pressure area is formed on the windward side of the UAV body 101, while a low-pressure area is formed on the leeward side of the UAV body 101, which is opposite to the high-pressure area. This generates a normal aerodynamic force on the UAV body 101 that is away from the windward direction. This normal aerodynamic force can accelerate the separation of the UAV body 101 from the power mechanism 2 and ensure the stability of the flight attitude of the UAV body 101. It effectively converts aerodynamic interference into aerodynamic separation force, improving the timeliness and stability of the UAV body 101 deployment.

[0022] In a preferred embodiment, the cross-sectional area of ​​the drone fuselage 101 perpendicular to its axis gradually increases from the head of the drone fuselage 101 to the tail of the drone fuselage 101.

[0023] Specifically, such as Figure 2 , Figure 8 and Figure 9 As shown, when the UAV body 1 and the power mechanism 2 fly together, the cross-sectional area of ​​the UAV fuselage 101 gradually increases from the head of the UAV fuselage 101 to the tail of the UAV fuselage 101, so that the windward airflow flows continuously along the top surface 105 of the UAV fuselage 101, which can reduce the resistance generated by the windward airflow and improve the aerodynamic stability of the combined aircraft.

[0024] In a preferred embodiment, the bottom surface 104 of the drone fuselage 101 is an arc-shaped lifting surface.

[0025] Specifically, such as Figure 8 As shown, the cross-sectional profile is a triangle with an inwardly concave arc side at the bottom. The triangle extends continuously along the axial direction of the UAV fuselage 101 to form the UAV fuselage 101, and the bottom surface 104 of the UAV fuselage 101 forms the arc-shaped lifting surface. Furthermore, when the UAV body 1 and the power mechanism 2 need to separate, the combined separation mechanism pushes multiple UAV bodies 101 to separate from each other to form a positive angle of attack attitude relative to the windward airflow direction. At this time, the arc-shaped lifting surface is the windward surface, and the arc-shaped lifting surface can form a larger pressure-bearing area, which improves the normal aerodynamic force generated on the UAV body 101, thereby increasing the separation speed of the UAV body 101 and the power mechanism 2.

[0026] In a preferred embodiment, a plurality of drone wings 102 are equally spaced on the top surface 105 of the drone fuselage 101, and drone air rudders 103 are provided on the drone wings 102. The drone air rudders 103 are used to adjust the flight attitude of the drone fuselage 101.

[0027] Specifically, such as Figure 2 and Figure 9 As shown, three drone wings 102 are equally spaced on the top surface 105 of the drone fuselage 101. In the initial combined state, the drone wings 102 of adjacent drone fuselages 101 in the drone body 1 fit together without gaps. Furthermore, the UAV air rudder 103 is located at the tail of the UAV wing 102. When each UAV fuselage 101 is separated from the power mechanism 2, the UAV air rudder 103 can deflect relative to the UAV wing 102 under the action of the UAV air rudder 103 drive mechanism, thereby controlling the flight attitude of the UAV fuselage 101 and enabling each UAV fuselage 101 to fly to different target areas.

[0028] In a preferred embodiment, the combined separation mechanism includes: Hydraulic rod assembly 4, wherein the hydraulic rod assembly 4 is disposed at one end of the power mechanism 2, and a fairing 401 is disposed at the end of the hydraulic rod assembly 4 away from the power mechanism 2; Support rod assembly 3, one end of which is rotatably connected to the power mechanism 2, and the support rod assembly 3 is drive-connected to the hydraulic rod assembly 4; When the combined separation mechanism is in the first state, the fairing 401 is fastened to the head of the plurality of UAV fuselages 101, and the support rod assembly 3 is engaged with the tail of the plurality of UAV fuselages 101 through the limiting assembly to limit and retain the pyramidal outer surface. When the combined separation mechanism switches from the first state to the second state, the hydraulic rod assembly 4 drives the fairing 401 to detach from the head of the UAV fuselage 101, and at the same time drives the support rod assembly 3 to move along the axis of the power mechanism 2, thereby releasing the restriction on the pyramidal outer surface and assisting in pushing multiple UAV fuselages 101 to separate from each other until they detach from the support rod assembly 3 under the action of the windward airflow.

[0029] Specifically, the fairing 401 is installed at the head of the UAV body 1 to centrally constrain the heads of multiple UAV fuselages 101. When the UAV body 1 and the power mechanism 2 fly together, the fairing 401 can cover the splicing gap between multiple UAV fuselages 101, which can reduce the airflow separation caused by the splicing gap in the head area of ​​the UAV body 1, and make the windward airflow flow stably along the head of the UAV body 1, thereby ensuring the stability of the flight attitude of the combined aircraft. Furthermore, since the fairing 401 only needs to centrally constrain the heads of multiple UAV fuselages 101, the structural size of the fairing 401 is smaller than that of the UAV body 1, which can reduce the overall weight of the combined aircraft and reduce the impact of the fairing 401 itself on the thrust-to-weight ratio of the combined aircraft.

[0030] In a preferred embodiment, the hydraulic rod assembly 4 includes: Hydraulic actuator 405, which is fixedly mounted on the power mechanism 2, with the axis of its drive end coaxial with the axis of the power mechanism 2; Hydraulic strut 402, one end of which is fixedly connected to the drive end of the hydraulic device 405, and the other end of which is fixedly connected to the fairing 401, the fairing 401 matching the head contour of the pyramidal outer surface; A hydraulic positioner 403 is fixedly sleeved on the hydraulic support rod 402; the hydraulic positioner 403 is connected to the support rod assembly 3 for transmitting the driving force of the hydraulic device 405 to the support rod assembly 3. The support positioner 404 is fixedly connected at one end to the hydraulic device 405, and at the other end is used to abut against the support rod assembly 3.

[0031] Specifically, the hydraulic actuator 405 is used to drive the hydraulic strut 402 to move along the axis of the power mechanism 2, so that the hydraulic strut 402 drives the fairing 401 to move closer to or away from the head of the UAV body 1, and at the same time drives the hydraulic positioner 403 to move closer to or away from the hydraulic actuator 405. Specifically, when the combined separation mechanism is in the first state, the support locator 404 abuts against the support rod assembly 3, so that the support rod assembly 3 is stably engaged with the tail of multiple UAV fuselages 101 by the limiting component.

[0032] In a preferred embodiment, the support rod assembly 3 includes: The limiting chuck 301 is movably sleeved on the hydraulic support rod 402 and is located on the side of the hydraulic positioner 403 away from the hydraulic device 405. Active rod 302, multiple active rods 302 correspond one-to-one with multiple UAV bodies 101, one end of which is hinged to the limiting chuck 301; A passive rod 303, one end of which is hinged to the end of the active rod 302 away from the limiting chuck 301.

[0033] Specifically, such as Figure 13 As shown, the limiting chuck 301 is annular, and the outer diameter of the hydraulic positioner 403 is larger than the inner diameter of the limiting chuck 301. Specifically, such as Figure 4 and Figure 5 As shown, when the UAV body 1 needs to be separated from the power mechanism 2, the drive end of the hydraulic unit 405 drives the hydraulic strut 402 to move the fairing 401 away from the head of the UAV body 1, releasing the fairing 401 from the constraint of the head of the UAV fuselage 101. At the same time, the hydraulic strut 402 drives the hydraulic positioner 403 to move closer to the limit chuck 301. After the hydraulic positioner 403 abuts against the limit chuck 301, it pushes the limit chuck 301 along the hydraulic strut 402 away from the hydraulic unit 405; Figure 6 and Figure 7 As shown, as the limiting chuck 301 moves away from the hydraulic unit 405 along the hydraulic support rod 402, the limiting chuck 301 pulls the active rod 302. The active rod 302 drives the passive rod 303 to rotate around the hinge point between the passive rod 303 and the power mechanism 2. As the passive rod 303 rotates, the support positioner 404 gradually releases the restriction on the support rod assembly 3. The passive rod 303 drives the UAV fuselage 101 to rotate away from the power mechanism 2, thereby causing the UAV fuselage 101 to form a positive angle of attack attitude relative to the windward airflow direction.

[0034] In a preferred embodiment, the support locator 404 includes a plurality of support rods corresponding one-to-one with the fuselage 101 of the UAV; the end of the support rod away from the hydraulic device 405 is used to abut against the hinge portion of the active rod 302 and the passive rod 303.

[0035] Specifically, the support rod forms a preset angle with the axis of the drive end of the hydraulic device 405. The preset angle causes the end of the support rod away from the hydraulic device 405 to form an oblique support with the hinge portion of the corresponding active rod 302 and passive rod 303.

[0036] In a preferred embodiment, the limiting component includes: Limiter 202 is fixedly connected to the end face of the power mechanism 2 near the UAV body 1 and is hinged to the other end of the passive rod 303. Limiting block 304, the limiting block 304 is fixedly connected to the side of the passive rod 303 away from the hydraulic support rod 402; When the combined separation mechanism is in the first state, the limiter 202 abuts against the top surface 105 of the drone fuselage 101, and the limit block 304 abuts against the bottom surface 104 of the drone fuselage 101, so that the passive rod 303 is engaged with the tail of the drone fuselage 101; the end of the support rod away from the hydraulic device 405 abuts against the hinge portion of the active rod 302 and the passive rod 303, so as to limit the relative position of the active rod 302 and the passive rod 303 and the passive rod 303 and the power mechanism 2.

[0037] Specifically, the limiter 202 is semi-cylindrical, with its planar side fixedly connected to the end face of the power mechanism 2, and its arc-shaped side hinged to the passive rod 303; Specifically, such as Figure 10 As shown, the limiting block 304 has two mutually perpendicular limiting surfaces. One limiting surface is fixedly connected to the passive rod 303, and the other limiting surface abuts against the bottom surface 104 of the tail of the UAV fuselage 101 when the combined separation mechanism is in the first state.

[0038] Furthermore, such as Figure 9 As shown, the top surface 105 of the tail of the UAV fuselage 101 is provided with a limiting groove that matches the arc-shaped side of the limiter 202. When the combined aircraft is in the initial combined state, the combination separation mechanism is in the first state, the arc-shaped side of the limiter 202 abuts against the limiting groove, and the limiting block 304 cooperates with the limiter 202 to limit the tail of the UAV fuselage 101.

[0039] In a preferred embodiment, the power mechanism 2 includes: The boost transition section 201 has its edge contours matched at the connection between its outer surface and the pyramidal outer surface. The boost transition section 201 has a hydraulic groove 203 for mounting the hydraulic device 405 on one end face near the UAV body 1 along its axial direction. The power compartment section 204 has multiple power compartment wings 205 evenly spaced on its peripheral side. Each power compartment wing 205 is equipped with a power compartment air rudder for controlling the flight attitude of the power unit 2.

[0040] Specifically, such as Figure 14 As shown, the booster transition section 201 is a triangular prism, the power compartment section 204 is a cylinder, and four power compartment wings 205 are equally spaced on the peripheral side of the tail of the power compartment section 204.

[0041] Furthermore, the power section air rudder is located at the tail of the power section wing 205. The power section air rudder can deflect relative to the power section wing 205 under the action of the power section air rudder drive mechanism, thereby controlling the flight attitude of the power unit 2.

[0042] The operational process of the combined aircraft in this application: like Figure 2 and Figure 3 As shown, in the initial combined state, the combination separation mechanism is in the first state. Multiple UAV fuselages 101 are covered by the combination separation mechanism, forming a pyramidal outer surface set at one end of the power mechanism 2. The fairing 401 provides concentrated constraint on the head of the multiple UAV fuselages 101. At the same time, the limiting block 304 and the limiter 202 limit the bottom surface 104 and top surface 105 of the tail of the UAV fuselage 101 respectively, so that the UAV body 1 is stably fixed at one end of the power mechanism 2. When the combined aircraft is in flight, the power mechanism 2 provides unified flight power to each UAV fuselage 101. At the same time, the aerodynamic control of the power compartment adjusts the flight attitude of the power mechanism 2, so that the power mechanism 2 can smoothly propel the combined aircraft to the target area. After the combined aircraft flies to the target area, such as Figure 4 and Figure 5 As shown, the hydraulic actuator 405 operates, driving the hydraulic strut 402 to move along its own axis. The hydraulic strut 402 drives the fairing 401 to move away from the head of the UAV body 1, thereby releasing the fairing 401 from the constraint of the heads of multiple UAV bodies 101. At the same time, the hydraulic strut 402 drives the hydraulic positioner 403 to move towards the limit chuck 301. After the hydraulic positioner 403 comes into contact with the limit chuck 301, it pushes the limit chuck 301 to move away from the hydraulic actuator 405 along the hydraulic strut 402. like Figure 6 and Figure 7 As shown, during the movement of the limiting chuck 301, the active rod 302 is pulled to rotate, and the active rod 302 further drives the passive rod 303 to rotate around the limiter 202; as the passive rod 303 rotates, the support rod of the support positioner 404 gradually releases the restriction on the hinge joint between the active rod 302 and the passive rod 303, as shown. Figure 6 and Figure 11As shown, the passive rod 303 drives the corresponding drone body 101 to deflect away from the hydraulic support rod 402 with the limiter 202 as the fulcrum, so that the drone body 101 forms a positive angle of attack attitude relative to the windward airflow direction. In the positive angle of attack state, the arc-shaped lifting surface is the windward surface. The arc-shaped lifting surface causes the airflow to form a high-pressure area on the arc-shaped lifting surface side of the drone body 101, while a low-pressure area is formed on the leeward side of the drone body 101, which is opposite to the high-pressure area. This generates a normal aerodynamic force on the drone body 101 that is away from the windward direction. Under the combined action of the normal aerodynamic force and the rotation of the passive rod 303, the drone body 101 is stably separated from the power mechanism 2. After separation, each UAV fuselage 101 uses its own UAV air rudder 103 to adjust its flight attitude and carry the corresponding payload to different target areas, thereby achieving flexible deployment of multiple payloads.

[0043] The above description is merely a preferred embodiment of this application and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention involved in this application is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the inventive concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this application.

Claims

1. A combined aircraft based on aerodynamic separation, characterized in that, include: Power mechanism (2), which is used to provide flight power for the combined aircraft; A combined separation mechanism is disposed at one end of the power mechanism (2); The unmanned aerial vehicle (UAV) body (1) includes multiple UAV fuselages (101) arranged around the array of combined separation mechanisms. The combined separation mechanism has a first state and a second state. When the combined separation mechanism is in the first state, multiple UAV fuselages (101) are combined and covered to form a pyramidal outer surface, and the combined separation mechanism limits and holds the pyramidal outer surface. When the combined separation mechanism switches from the first state to the second state, the combined separation mechanism releases the limit on the pyramidal outer surface and assists in pushing the multiple UAV fuselages (101) to separate from each other to form a positive angle of attack attitude relative to the windward airflow direction until they detach from the combined separation mechanism under the action of the windward airflow. The bottom surface (104) of the UAV fuselage (101) is an arc-shaped lifting surface; The combined separation mechanism includes: Hydraulic rod assembly (4), the hydraulic rod assembly (4) is disposed at one end of the power mechanism (2), and a fairing (401) is disposed at the end away from the power mechanism (2). Support rod assembly (3), one end of which is rotatably connected to the power mechanism (2), and the support rod assembly (3) is drive-connected to the hydraulic rod assembly (4); When the combined separation mechanism is in the first state, the fairing (401) is fastened to the head of the multiple UAV fuselages (101), and the support rod assembly (3) is engaged with the tail of the multiple UAV fuselages (101) through the limiting assembly to limit and retain the pyramidal outer surface. When the combined separation mechanism switches from the first state to the second state, the hydraulic rod assembly (4) drives the fairing (401) to separate from the head of the UAV fuselage (101), and at the same time drives the support rod assembly (3) to move along the axis of the power mechanism (2), releasing the restriction on the pyramidal outer surface and assisting in pushing multiple UAV fuselages (101) to separate from each other until they are separated from the support rod assembly (3) under the action of the windward airflow. The hydraulic rod assembly (4) includes: Hydraulic actuator (405), the hydraulic actuator (405) is fixedly mounted on the power mechanism (2), and the axis of its driving end is coaxial with the axis of the power mechanism (2); A hydraulic strut (402) is provided, one end of which is fixedly connected to the drive end of the hydraulic actuator (405), and the other end is fixedly connected to the fairing (401). The fairing (401) is matched with the head contour of the pyramidal outer surface. A hydraulic positioner (403) is fixedly sleeved on the hydraulic support rod (402). When the combined separation mechanism switches from the first state to the second state, the hydraulic positioner (403) is used to transmit the driving force of the hydraulic device (405) to the support rod assembly (3). Support locator (404), one end of which is fixedly connected to the hydraulic device (405), and the other end is used to abut against the support rod assembly (3).

2. The combined aircraft based on aerodynamic separation according to claim 1, characterized in that, The cross-sectional area of ​​the drone fuselage (101) perpendicular to its axis gradually increases from the head of the drone fuselage (101) to the tail of the drone fuselage (101).

3. A combined aircraft based on aerodynamic separation according to claim 1, characterized in that, Multiple drone wings (102) are evenly spaced on the top surface (105) of the drone fuselage (101). Drone air rudders (103) are provided on the drone wings (102), and the drone air rudders (103) are used to adjust the flight attitude of the drone fuselage (101).

4. A combined aircraft based on aerodynamic separation according to claim 1, characterized in that, The support rod assembly (3) includes: A limiting chuck (301) is movably sleeved on the hydraulic support rod (402) and located on the side of the hydraulic positioner (403) away from the hydraulic device (405); Active rod (302), multiple active rods (302) correspond one-to-one with multiple UAV bodies (101), one end of which is hinged to the limiting chuck (301); A passive rod (303) is hinged at one end to the active rod (302) at the end away from the limiting chuck (301).

5. A combined aircraft based on aerodynamic separation according to claim 4, characterized in that, The support locator (404) includes a plurality of support rods corresponding one-to-one with the fuselage (101) of the UAV; the end of the support rod away from the hydraulic device (405) is used to abut against the hinge portion of the active rod (302) and the passive rod (303).

6. A combined aircraft based on aerodynamic separation according to claim 5, characterized in that, The limiting component includes: Limiter (202), the limiter (202) is fixedly connected to the end face of the power mechanism (2) near the UAV body (1), and is hinged to the other end of the passive rod (303); A limiting block (304) is fixedly connected to the side of the passive rod (303) away from the hydraulic support rod (402); When the combined separation mechanism is in the first state, the limiter (202) abuts against the top surface (105) of the drone fuselage (101), and the limit block (304) abuts against the bottom surface (104) of the drone fuselage (101), so that the passive rod (303) is engaged with the tail of the drone fuselage (101); the end of the support rod away from the hydraulic device (405) abuts against the hinge of the active rod (302) and the passive rod (303), so as to limit the relative position of the active rod (302) and the passive rod (303) and the passive rod (303) and the power mechanism (2).

7. A combined aircraft based on aerodynamic separation according to claim 6, characterized in that, The power mechanism (2) includes: The boost transition section (201) has its edge contours matched at the connection between the outer surface of the boost transition section (201) and the pyramidal outer surface. The boost transition section (201) has a hydraulic groove (203) for installing the hydraulic device (405) along its axial direction on one end face near the UAV body (1). The power compartment (204) has multiple power compartment wings (205) evenly spaced on its periphery. The power compartment wings (205) are equipped with power compartment air rudders for controlling the flight attitude of the power mechanism (2).

Images