A UAV rocket-assisted takeoff bearing device with a ventral air intake

Abstract

This application relates to the field of aerospace, and more particularly to a rocket-assisted takeoff bearing device for unmanned aerial vehicles (UAVs) with a ventral air intake, comprising: an adapter bracket, a separation device, a longitudinal fuselage stringer, a rear airbag box, a booster reinforcement frame, a thrust seat, a left engine thrust beam, a right engine thrust beam, a booster reinforcement beam, and a rear attachment point frame. This application can improve the reliability of UAVs during boosted flight, simplify the UAV's body bearing structure, making it simpler and more direct in force transmission, simplify the booster rocket installation process, increase the reliability of the booster rocket separation from the UAV, and reduce the cost of each UAV flight.

Description

Technical Field

[0001] The present application relates to the field of aerospace, and in particular to a rocket-assisted takeoff bearing device for a UAV with a ventral air inlet. Background Art

[0002] When a drone with a ventral air intake uses a rocket-assisted takeoff scheme, two forms are generally adopted: the first is a dual-rocket-assisted takeoff scheme, in which a booster rocket is mounted on each side of the drone's fuselage to provide initial power for the drone to take off; the second is a single-rocket-assisted takeoff scheme, in which the booster rocket is installed directly below the drone's body along the drone's thrust line, and the booster rocket structure is directly connected to the drone's body's thrust cone.

[0003] However, both the first and second boosting schemes have some shortcomings, as follows:

[0004] The main shortcomings of the first boosting scheme are: first, the use of a dual-rocket boosted takeoff scheme requires a high investment in the cost of the booster rockets; second, the installation and separation of the booster rockets on the UAV is relatively complicated; third, the use of a dual-rocket boosted takeoff scheme may result in inconsistent ignition timing of the booster rockets on both sides, thereby affecting the attitude of the UAV during takeoff.

[0005] The main shortcoming of the second boosting scheme is that the thrust line of the UAV with a ventral air intake usually passes near the air intake, but the air intake is not the load-bearing structure of the fuselage and cannot withstand the huge thrust of the booster rocket when it is working. In this case, the booster rocket is directly connected to the fuselage, and a load-bearing structure needs to be arranged near the air intake. This load-bearing structure is usually very complex, with a blocked force transmission path, heavy weight, and poor structural rigidity, which will increase the risk of the UAV during boosted flight.

[0006] Therefore, how to improve the reliability of the UAV during boosted flight, simplify the load-bearing structure of the UAV body, make the body structure simple and the force transmission direct, simplify the booster rocket installation process, increase the reliability of the separation of the booster rocket and the UAV, and reduce the cost of each UAV flight are technical problems that technical personnel in this field urgently need to solve. Summary of the Invention

[0007] The present application provides a rocket-assisted takeoff device for a UAV with a ventral air intake, thereby improving the reliability of the UAV during boosted flight, simplifying the load-bearing structure of the UAV body, making the body structure simple and the force transmission direct, simplifying the booster rocket installation process, increasing the reliability of the separation of the booster rocket from the UAV, and reducing the cost of each UAV flight.

[0008] To solve the above technical problems, this application provides the following technical solutions:

[0009] A rocket-assisted takeoff bearing device for a UAV with a ventral air intake comprises: an adapter bracket, a separation device, a longitudinal long stringer of the fuselage, a rear airbag box, a booster reinforcement frame, a thrust seat, a left thrust beam of the engine, a right thrust beam of the engine, a booster reinforcement beam, and a rear hanging point frame; the booster reinforcement frame and the rear hanging point frame are both annular, and the axes of the booster reinforcement frame and the rear hanging point frame are coaxial with the axis of the UAV; the rear end of the longitudinal long stringer of the fuselage is fixedly connected to the front end of the booster reinforcement frame, and the rear end of the rear airbag box is fixedly connected to the front end of the booster reinforcement frame , and the lower surface of the longitudinal long stringer of the fuselage is fixedly connected to the upper surface of the rear airbag box; the front ends of the left thrust beam of the engine and the right thrust beam of the engine are fixedly connected to the rear end of the booster reinforcement frame, and the rear ends of the left thrust beam of the engine and the right thrust beam of the engine are fixedly connected to the front end of the rear hanging point frame, and the left thrust beam of the engine and the right thrust beam of the engine are distributed side by side; the front end of the booster reinforcement beam is fixedly connected to the rear end of the booster reinforcement frame, and the rear end of the booster reinforcement beam is fixedly connected to the front end of the rear hanging point frame, and the left thrust beam of the engine and the engine The right thrust beam of the engine is located above the booster reinforcement beam; the lower surface of the rear hanging point frame has a downwardly extending support ear, and a hook hole is provided near the lower end of the support ear, the hook hole passes through the left and right sides of the support ear, and the hook hole is open towards the rear; the interior of the thrust seat has an installation cavity, the rear part of the installation cavity passes through the lower surface of the thrust seat, and the front part of the installation cavity does not pass through the lower surface of the thrust seat; and the upper surface of the thrust seat is fixedly connected to the lower surface of the booster reinforcement frame; the adapter bracket includes: an adapter bracket body, a front joint and a hanging ear; the front The lower end of the connector is fixed to the upper part of the adapter bracket body near its front end, the upper end of the front connector extends into the installation cavity, and the front part of the upper end of the front connector is inserted into the front part of the installation cavity from back to front; the lower end of the hanging ear is fixed to the upper part of the adapter bracket body near its rear end, and the upper end of the hanging ear is hung in the hook hole of the support ear; the adapter bracket body is used to be fixedly connected to the booster rocket; the separation device is compressed and placed between the upper part of the adapter bracket body and the drone body, and the separation device is close to the rear end of the adapter bracket body.

[0010] As described above, in the UAV rocket-assisted takeoff load-bearing device with a ventral air intake, preferably, the lower surface of the hook hole near the front is a horizontal plane, and the lower surface of the hook hole near the rear is a surface that gradually slopes downward from front to back.

[0011] As described above, in the UAV rocket-assisted takeoff load-bearing device with a ventral air inlet, preferably, the lower surface of the boost reinforcement frame is concave with a fixing groove, the thrust seat is located in the fixing groove, and the thrust seat is fixedly connected to the boost reinforcement frame by screws.

[0012] As described above, the rocket-assisted takeoff load-bearing device for a UAV with a ventral air intake, wherein preferably, the longitudinal long stringer of the fuselage and the rear airbag box are made of carbon fiber composite material; the booster reinforcement frame, the left thrust beam of the engine, the right thrust beam of the engine, the booster reinforcement beam, and the rear hanging point frame are made of metal aluminum alloy material, and the thrust seat is made of high-strength alloy steel material.

[0013] As described above, in the UAV rocket-assisted takeoff load-bearing device with a ventral air intake, preferably, a hook is formed on the upper end of the hanging ear, and the hook is hung in the hook hole of the supporting ear.

[0014] The UAV rocket-assisted takeoff load-bearing device with a ventral air intake as described above, wherein preferably, a first fixing hole is provided near the upper end of the hanging ear, and a second fixing hole is provided near the lower end of the support ear, and the first fixing hole is opposite to the second fixing hole; after the hanging ear and the support ear are hooked, the fixing rod is inserted into the first fixing hole and the second fixing hole to achieve temporary fixation of the hanging ear and the support ear; after the UAV and the booster rocket are hoisted onto the launch pad as a whole, the fixing rod is pulled out from the first fixing hole and the second fixing hole to release the temporary fixation of the hanging ear and the support ear.

[0015] As described above, in the UAV rocket-assisted takeoff load-bearing device with a ventral air intake, preferably, the first fixing hole and the second fixing hole are both threaded holes, and the fixing rod is a screw.

[0016] The UAV rocket-assisted takeoff load-bearing device with a ventral air intake as described above, wherein, preferably, the adapter bracket body includes: an upper frame, a front frame and a fixing hoop; the upper part of the front frame is fixed to the lower surface of the front end of the upper frame; the booster rocket is located below the upper frame and behind the front frame, the fixing hoop is used to hold the booster rocket, and the two ends of the fixing hoop are detachably connected to the upper frame; the lower end of the front joint is fixed to the upper part of the upper frame near its front end, and the lower end of the hanging ear is fixed to the upper part of the upper frame near its rear end.

[0017] As described above, the UAV rocket-assisted takeoff load-bearing device with a ventral air intake, wherein preferably, the separation device includes: a separation bracket and a separation spring; the upper end of the separation spring is connected to the lower end of the separation bracket, the lower end of the separation spring is in contact with the upper part of the adapter bracket body, and the upper end of the separation bracket is in contact with the UAV body.

[0018] As described above, in the UAV rocket-assisted takeoff load-bearing device with a ventral air intake, preferably, the upper end of the separation bracket has a downward auxiliary groove, and the auxiliary groove runs through both sides.

[0019] Compared with the above background technology, this application improves the reliability of the UAV during boosted flight, simplifies the load-bearing structure of the UAV body, making it simple and direct in force transmission; simplifies the booster rocket installation process, increases the reliability of the separation of the booster rocket and the UAV; and reduces the cost of each UAV flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments described in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0021] Figure 1 This is a schematic diagram of a UAV rocket-assisted takeoff load-bearing device with a ventral air intake;

[0022] Figure 2 This is a schematic diagram of the load-bearing structure of the fuselage portion of the UAV rocket-assisted takeoff load-bearing device with a ventral air intake;

[0023] Figure 3 This is a schematic diagram of the thrust seat of the UAV rocket-assisted takeoff support device with a ventral air intake. DETAILED DESCRIPTION

[0024] The following describes embodiments of the present invention in detail, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended only to explain the present invention and are not to be construed as limiting the present invention.

[0025] like Figure 1 and Figure 2 As shown, the present application provides a UAV rocket-assisted takeoff load-bearing device with a ventral air intake, including: an adapter bracket 100, a separation device 200, a longitudinal long stringer 310 of the fuselage, a rear airbag box 320, a booster reinforcement frame 330, a thrust seat 340, an engine left thrust beam 350, an engine right thrust beam 360, a booster reinforcement beam 370 and a rear hanging point frame 380.

[0026] The boost reinforcement frame 330 and the rear hanging point frame 380 are both annular, and the axes of the boost reinforcement frame 330 and the rear hanging point frame 380 are coaxial with the axis of the UAV; the rear end of the fuselage longitudinal long stringer 310 is fixedly connected to the front end of the boost reinforcement frame 330, the rear end of the rear airbag box 320 is fixedly connected to the front end of the boost reinforcement frame 330, and the lower surface of the fuselage longitudinal long stringer 310 is fixedly connected to the upper surface of the rear airbag box 320; the front ends of the engine left thrust beam 350 and the engine right thrust beam 360 are both fixedly connected to the rear end of the boost reinforcement frame 330, and the engine left thrust beam 350 and the engine right thrust beam 360 are fixedly connected to the rear end of the boost reinforcement frame 330. The rear end of the right thrust beam 360 of the aircraft is fixedly connected to the front end of the rear hanging point frame 380, and the left thrust beam 350 of the engine and the right thrust beam 360 of the engine are distributed side by side, that is, the left thrust beam 350 of the engine and the right thrust beam 360 of the engine are symmetrically distributed on both sides of the axis of the UAV and close to the belly of the UAV; the front end of the booster reinforcement beam 370 is fixedly connected to the rear end of the booster reinforcement frame 330, and the rear end of the booster reinforcement beam 370 is fixedly connected to the front end of the rear hanging point frame 380, and the left thrust beam 350 of the engine and the right thrust beam 360 of the engine are located above the booster reinforcement beam 370.

[0027] The UAV engine is located between the boost reinforcement frame 330 and the rear attachment point frame 380, and above the engine's left thrust beam 350 and the engine's right thrust beam 360; the UAV engine's air intake is located in front of the boost reinforcement frame 330 and above the fuselage's longitudinal stringer 310, used to provide air for the UAV engine; the air intake external rectifier is located below the fuselage's longitudinal stringer 310 and around the rear airbag box 320, used to organize and optimize the airflow around the air intake.

[0028] The booster reinforcement frame 330, along with the fuselage longitudinal stringers 310 and the rear airbag box 320, forms the forward-facing load-bearing structure for the booster rocket, responsible for bearing the thrust load of the booster rocket during operation and distributing the concentrated load of the booster rocket across the drone's airframe. The engine left thrust beam 350, engine right thrust beam 360, booster reinforcement beam 370, booster reinforcement frame 330, and rear attachment point frame 380 form the rearward-facing load-bearing structure for the booster rocket, distributing the concentrated load of the booster rocket across the drone's airframe. The booster reinforcement frame 330 is the primary load-bearing frame, bearing the majority of the booster rocket's thrust load. The rear attachment point frame 380 is the secondary load-bearing frame, primarily responsible for maintaining the booster rocket's operational posture stability and withstanding the eccentric force caused by the misalignment of the booster rocket's thrust and the thrust application point.

[0029] The lower surface of the rear attachment point frame 380 has a downwardly extending lug 381. A hook hole is formed near the lower end of the lug 381. The hook hole extends through both sides of the lug 381, that is, the direction of the hook hole is perpendicular to the axis of the drone. The hook hole is open to the rear, so as to facilitate the attachment of the lug 130 of the adapter bracket 100 to the hook hole and to be removed from the hook hole. Optionally, the lower surface of the hook hole near the front is horizontal, and the lower surface of the hook hole near the rear is a surface that gradually slopes downward from front to back, thereby facilitating the removal of the lug 130 of the adapter bracket 100 from the hook hole of the lug 381, thereby facilitating the removal of the booster rocket.

[0030] like Figure 3 As shown, the thrust seat 340 has an installation cavity inside, the rear part of the installation cavity passes through the lower surface of the thrust seat 340, and the front part of the installation cavity does not pass through the lower surface of the thrust seat 340; and the upper surface of the thrust seat 340 is fixedly connected to the lower surface of the boost reinforcement frame 330. Optionally, the shape of the installation cavity is rectangular, and its length direction is the same as the axis direction of the UAV. Also optionally, the thrust seat 340 is fixedly connected to the boost reinforcement frame 330 by screws. Still optionally, the lower surface of the boost reinforcement frame 330 is concave with a fixing groove, the thrust seat 340 is located in the fixing groove, and the thrust seat 340 is fixedly connected to the boost reinforcement frame 330 by screws. Still optionally, the thrust seat 340 has multiple through holes running through the top and bottom, and all the through holes surround the outside of the safety cavity. There are threaded holes at corresponding positions in the fixing groove. The screws pass through the through holes of the thrust seat 340 and are screwed into the threaded holes in the fixing groove, thereby realizing a fixed connection between the thrust seat 340 and the boost reinforcement frame 330.

[0031] Based on the above, the fuselage longitudinal stringers 310 and rear airbag box 320 can be made of carbon fiber composite materials, the booster reinforcement frame 330, the left engine thrust beam 350, the right engine thrust beam 360, the booster reinforcement beam 370, and the rear attachment point frame 380 can be made of aluminum alloy, and the thrust base 340 can be made of high-strength alloy steel. Optionally, the rear end of the fuselage longitudinal stringers 310 and the front end of the booster reinforcement frame 330 can be fixedly connected using a combination of screws and rivets. The upper surface of the rear airbag box 320 and the lower surface of the fuselage longitudinal stringers 310, as well as the rear end of the rear airbag box 320 and the front end of the booster reinforcement frame 330, can both be fixedly connected using screws.

[0032] The adapter bracket 100 includes an adapter bracket body 110, a front connector 120, and a mounting lug 130. The lower end of the front connector 120 is fixed to the upper portion of the adapter bracket body 110 near its front end, and the upper end of the front connector 120 extends into the mounting cavity of the thrust seat 340. The front portion of the upper end of the front connector 120 is inserted into the front portion of the mounting cavity from the back to the front, thereby achieving a snap connection between the front connector 120 and the thrust seat 340. The lower end of the mounting lug 130 is fixed to the upper portion of the adapter bracket body 110 near its rear end, and the upper end of the mounting lug 130 is hooked into the hook hole of the support lug 381 of the rear mounting point frame 380. The adapter bracket body 110 is used to be fixedly connected to the booster rocket. In this way, the thrust load of the booster rocket can be transferred to the booster reinforcement frame 330 and the rear mounting point frame 380 through the adapter bracket 100, thereby distributing the concentrated load of the booster rocket to the body structure of the UAV.

[0033] Optionally, a hook is formed at the upper end of the lug 130, so that the hook can be easily hooked into the hook hole of the support lug 381. Also optionally, a first fixing hole is formed near the upper end of the lug 130, and a second fixing hole is formed near the lower end of the support lug 381, with the first fixing hole and the second fixing hole being opposite each other. After the lug 130 and the support lug 381 are hooked, a fixing rod is inserted into the first fixing hole and the second fixing hole to temporarily fix the lug 130 and the support lug 381. After the drone and the booster rocket are hoisted onto the launch pad as a whole, the fixing rod is pulled out of the first fixing hole and the second fixing hole to release the temporary fixation between the lug 130 and the support lug 381. Furthermore, optionally, both the first fixing hole and the second fixing hole are threaded holes, and the fixing rod is a screw, so that the temporary fixation between the lug 130 and the support lug 381 is achieved through a threaded connection.

[0034] Alternatively, the adapter bracket body 110 includes an upper frame, a front frame, and a fixing hoop; the upper portion of the front frame is fixed to the lower surface of the front end of the upper frame; the booster rocket is located below the upper frame and behind the front frame; the fixing hoop is used to hold the booster rocket tightly, and both ends of the fixing hoop are detachably connected to the upper frame; the lower end of the front joint 120 is fixed to the upper portion of the upper frame near its front end, and the lower end of the lug 130 is fixed to the upper portion of the upper frame near its rear end. Alternatively, the upper frame is detachably connected to the two fixing hoops, one of which is detachably connected to the upper frame near its front end, and the other is detachably connected to the upper frame near its rear end.

[0035] The separation device 200 is compressed and placed between the upper part of the adapter bracket body 110 and the drone body, and the separation device 200 is close to the rear end of the adapter bracket body 110. In this way, when the hanging ear 130 falls off from the hook hole of the support ear 381, the compressed separation device 200 extends to drive the adapter bracket 100 and the booster rocket away from the drone body, thereby avoiding collision between the adapter bracket 100 and the booster rocket and the drone body.

[0036] Optionally, the separation device 200 includes a separation bracket 210 and a separation spring 220; the upper end of the separation spring 220 is connected to the lower end of the separation bracket 210, the lower end of the separation spring 220 contacts the upper portion of the adapter bracket body, and the upper end of the separation bracket 210 contacts the drone body. Optionally, the upper end of the separation bracket 210 has a downwardly facing auxiliary groove that extends through both sides. After the front connector 120 of the adapter bracket 100 is engaged with the thrust seat 340 and the lug 130 is engaged with the lug 381, a mounting rope can be inserted into the auxiliary groove. The mounting rope can then be used to compress the separation spring 220, thereby facilitating the placement of the separation device 200 between the upper portion of the adapter bracket body 110 and the drone body. After the connection is made, the mounting rope can be withdrawn, tightening the separation device 200 between the upper portion of the adapter bracket body 110 and the drone body.

[0037] When using this application, it is necessary to install and separate the booster rocket. The steps for installing the booster rocket are as follows:

[0038] 1. Connect and fix the booster rocket to the adapter bracket 100 to form a whole, and install the lower end of the separation device 200 on the adapter bracket 100;

[0039] 2. Attach the front connector 120 of the adapter bracket 100 to the thrust base 340, and align the mounting lug 130 of the adapter bracket 100 to the lug 381 of the rear mounting frame 380. Once fully attached, use screws to connect the mounting lug 130 of the adapter bracket 100 to the lug 381 of the rear mounting frame 380. Use a rope tightener to secure the front connector 120 of the adapter bracket 100 to the drone body. Finally, compress the separation device 200 and push the upper end of the separation device 200 against the drone body.

[0040] 3. Hoist the UAV and booster rocket onto the launch pad. Once in place, remove the screws connecting the mounting lug 130 of the adapter bracket 100 to the lug 381 of the rear mounting point frame 380. Remove the tether securing the front connector 120 of the adapter bracket 100 to the UAV body.

[0041] The steps for booster rocket separation are as follows:

[0042] After the booster rocket works, it moves in the opposite direction of the UAV's movement under the action of aerodynamic force and its own gravity. Under the action of the separation device 200, the booster rocket moves away from the UAV body, avoiding the booster rocket from colliding with the UAV during the separation process, which affects flight safety.

[0043] In this application, the booster rocket acts on the drone body via an adapter bracket. When the booster rocket is operating, the thrust is transmitted to the drone body structure through the adapter bracket. After the booster rocket is finished operating, the aerodynamic force and the separation device work together to achieve safe separation from the drone. This application improves the reliability of the drone during boosted flight, simplifies the drone body's load-bearing structure, making it simple and direct in force transmission; simplifies the booster rocket installation process, increases the reliability of the booster rocket's separation from the drone; and reduces the cost of each drone flight.

[0044] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the invention can be embodied in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the invention is defined by the appended claims, not the foregoing description, and all variations within the meaning and range of equivalents of the claims are intended to be included therein. Any reference sign in a claim should not be construed as limiting the claim to which it relates.

[0045] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

Claims

1. A UAV rocket-assisted takeoff bearing device with a ventral air inlet, characterized in that: include: Adapter bracket, separation device, fuselage longitudinal long stringer, rear airbag box, booster reinforcement frame, thrust seat, engine left thrust beam, engine right thrust beam, booster reinforcement beam and rear hardpoint frame; The boost reinforcement frame and the rear attachment point frame are both annular, and their axes are coaxial with the axis of the UAV; the rear end of the fuselage longitudinal stringer is fixedly connected to the front end of the boost reinforcement frame, the rear end of the rear airbag box is fixedly connected to the front end of the boost reinforcement frame, and the lower surface of the fuselage longitudinal stringer is fixedly connected to the upper surface of the rear airbag box; The front ends of the left and right engine thrust beams are fixedly connected to the rear ends of the booster reinforcement frame, and the rear ends of the left and right engine thrust beams are fixedly connected to the front ends of the rear attachment point frame, and the left and right engine thrust beams are arranged side by side; the front end of the booster reinforcement beam is fixedly connected to the rear end of the booster reinforcement frame, and the rear end of the booster reinforcement beam is fixedly connected to the front end of the rear attachment point frame, and the left and right engine thrust beams are located above the booster reinforcement beams; The lower surface of the rear hanging point frame has a downwardly extending ear, and a hook hole is opened near the lower end of the ear. The hook hole passes through the left and right sides of the ear and opens towards the rear; The thrust seat has an interior with a mounting cavity, the rear portion of the mounting cavity passes through the lower surface of the thrust seat, and the front portion of the mounting cavity does not pass through the lower surface of the thrust seat; and the upper surface of the thrust seat is fixedly connected to the lower surface of the boost reinforcement frame; The adapter bracket includes: an adapter bracket body, a front joint, and a mounting ear; the lower end of the front joint is fixed to the upper portion of the adapter bracket body near its front end, the upper end of the front joint extends into the installation cavity, and the front portion of the upper end of the front joint is inserted into the front portion of the installation cavity from back to front; the lower end of the mounting ear is fixed to the upper portion of the adapter bracket body near its rear end, and the upper end of the mounting ear is hooked into the hook hole of the mounting ear; the adapter bracket body is used to be fixedly connected to the booster rocket; The separation device is compressed and placed between the upper part of the adapter bracket body and the drone body, and the separation device is close to the rear end of the adapter bracket body.

2. The UAV rocket-assisted takeoff bearing device with a ventral air inlet according to claim 1 is characterized in that: The lower surface of the hook hole near the front is a horizontal surface, and the lower surface of the hook hole near the rear is a surface that gradually slopes downward from the front to the rear.

3. The UAV rocket-assisted takeoff bearing device with a ventral air inlet according to claim 1 or 2, characterized in that: The lower surface of the boost reinforcement frame is inwardly concave with a fixing groove, the thrust seat is located in the fixing groove, and the thrust seat is fixedly connected to the boost reinforcement frame by screws.

4. The UAV rocket-assisted takeoff bearing device with a ventral air inlet according to claim 1 or 2, characterized in that: The fuselage's longitudinal stringers and rear airbag box are made of carbon fiber composite material; The materials of the booster reinforcement frame, engine left thrust beam, engine right thrust beam, booster reinforcement beam and rear hanging point frame are metal aluminum alloy, and the thrust seat is made of high-strength alloy steel.

5. The UAV rocket-assisted takeoff bearing device with a ventral air inlet according to claim 1 or 2, characterized in that: The upper end of the hanging ear is formed with a hook, which is hung in the hook hole of the supporting ear.

6. The UAV rocket-assisted takeoff bearing device with a ventral air inlet according to claim 5 is characterized in that: A first fixing hole is provided near the upper end of the hanging ear, and a second fixing hole is provided near the lower end of the supporting ear, the first fixing hole being opposite to the second fixing hole; After the hanging ear is hooked to the supporting ear, the fixing rod is inserted into the first fixing hole and the second fixing hole to achieve temporary fixation of the hanging ear and the supporting ear; After the UAV and the booster rocket are hoisted onto the launch pad as a whole, the fixing rod is pulled out from the first fixing hole and the second fixing hole to release the temporary fixation of the hanging ear and the supporting ear.

7. The UAV rocket-assisted takeoff bearing device with a ventral air inlet according to claim 6 is characterized in that: The first fixing hole and the second fixing hole are both threaded holes, and the fixing rod is a screw.

8. The UAV rocket-assisted takeoff bearing device with a ventral air inlet according to claim 1 or 2, characterized in that: The adapter bracket body includes: an upper frame, a front frame and a fixing hoop; The upper part of the front frame is fixed to the lower surface of the front end of the upper frame; the booster rocket is located below the upper frame and behind the front frame, the fixing hoop is used to hold the booster rocket, and the two ends of the fixing hoop are detachably connected to the upper frame; the lower end of the front joint is fixed to the upper part of the upper frame near its front end, and the lower end of the hanging ear is fixed to the upper part of the upper frame near its rear end.

9. The UAV rocket-assisted takeoff bearing device with a ventral air inlet according to claim 1 or 2, characterized in that: The separation device includes: a separation bracket and a separation spring; the upper end of the separation spring is connected to the lower end of the separation bracket, the lower end of the separation spring contacts the upper part of the adapter bracket body, and the upper end of the separation bracket contacts the drone body.

10. The UAV rocket-assisted takeoff bearing device with a ventral air inlet according to claim 9, characterized in that: The upper end of the separation bracket is provided with a downward auxiliary groove, and the auxiliary groove passes through both sides.

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