Unmanned aerial vehicle rocket boosting takeoff force bearing device with abdomen air inlet channel

Abstract

The invention relates to the field of aerospace, in particular to an unmanned aerial vehicle rocket boosting takeoff force bearing device with a belly air inlet channel, which comprises an adapter bracket, a separation device, a fuselage longitudinal stringer, a rear air bag box, a boosting reinforcing frame, a thrust seat, an engine left thrust beam, an engine right thrust beam, a boosting reinforcing beam and a rear hanging point frame. The reliability of the unmanned aerial vehicle in the boosting flight process can be improved, the force bearing structure of the unmanned aerial vehicle body is simplified, the body structure is simple, force transmission is direct, the booster rocket installation process is simplified, the reliability of separation of the booster rocket and the unmanned aerial vehicle is improved, and the cost of each flight of the unmanned aerial vehicle is reduced.

Description

Technical Field

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

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

[0003] However, both the first boosting scheme and the second boosting scheme 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 may result in inconsistent ignition times of the booster rockets on both sides, thus affecting the attitude of the UAV during takeoff.

[0005] The main drawback of the second boost scheme is that the thrust line of a UAV with a ventral air intake usually passes near the air intake, but the air intake is not a 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 UAV rocket-assisted takeoff device with a ventral air intake, thereby improving the reliability of the UAV during boosted flight, simplifying the UAV body load-bearing structure, 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] In order to solve the above technical problems, this application provides the following technical solutions:

[0009] A rocket-assisted takeoff bearing device for a drone with a ventral air intake comprises: an adapter bracket, a separation device, a longitudinal long stringer of a fuselage, a rear airbag box, a booster reinforcement frame, a thrust seat, a left thrust beam of an engine, a right thrust beam of an 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 drone; 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, 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, 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 opened 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 opens toward the rear; the thrust seat has an installation cavity inside, 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 joint is fixed to the upper part of the adapter bracket body near its front end, the upper end of the front joint extends into the installation cavity, and the front part of the upper end of the front joint 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 UAV 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 inlet, 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] In the UAV rocket-assisted takeoff load-bearing device with a ventral air inlet as described above, 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, in the rocket-assisted takeoff load-bearing device for unmanned aerial vehicles with a ventral air intake, preferably, the longitudinal long stringers of the fuselage and the rear airbag box are made of carbon fiber composite materials; 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 materials, 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 inlet, preferably, a hook is formed at the upper end of the hanging ear, and the hook is hung in the hook hole of the supporting ear.

[0014] In the UAV rocket-assisted takeoff load-bearing device with a ventral air inlet as described above, 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 supporting ear, and the first fixing hole is opposite to the second fixing hole; after the hanging ear and the supporting 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 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.

[0015] In the UAV rocket-assisted takeoff load-bearing device with a ventral air inlet as described above, 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] The UAV rocket-assisted takeoff load-bearing device with a ventral air intake as described above, 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 contacts the upper part of the adapter bracket body, and the upper end of the separation bracket contacts 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-mentioned background technology, the present 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 transmitting force; simplifies the installation process of the booster rocket, increases the reliability of the separation of the booster rocket from the UAV; and reduces the cost of each flight of the UAV. 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 drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

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

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

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

[0024] Embodiments of the present invention are described in detail below, 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 only used to explain the present invention, and cannot be interpreted as limiting the present invention.

[0025] like Figure 1 and Figure 2 As shown, the present application provides a rocket-assisted takeoff load-bearing device for a UAV 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, 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 left thrust beam 350 and the engine right thrust beam 360; the air intake of the UAV engine is located in front of the boost reinforcement frame 330 and above the longitudinal long stringer 310 of the fuselage, which is used to provide air for the UAV engine; the external rectifying of the air intake is located below the longitudinal long stringer 310 of the fuselage and around the rear airbag box 320, which is used to organize and optimize the airflow around the air intake.

[0028] The booster reinforcement frame 330, the longitudinal long stringer 310 of the fuselage, and the rear airbag box 320 constitute the forward bearing structure of the booster rocket, which is used to bear the thrust load of the booster rocket when it is working, and disperse the concentrated load of the booster rocket on the body structure of the drone; the left thrust beam 350 of the engine, the right thrust beam 360 of the engine, the booster reinforcement beam 370, the booster reinforcement frame 330, and the rear hanging point frame 380 constitute the rear bearing structure of the booster rocket, and disperse the concentrated load of the booster rocket on the body structure of the drone. Among them, the booster reinforcement frame 330 is the main bearing frame that bears the thrust load of the booster rocket, and bears most of the thrust load of the booster rocket. The rear hanging point frame 380 is the secondary bearing frame that bears the thrust load of the booster rocket. Its main function is to maintain the posture stability of the booster rocket when it is working, and to bear the eccentric force caused by the misalignment of the thrust of the booster rocket and the thrust application point.

[0029] The lower surface of the rear hanging point frame 380 has a downwardly extending ear 381, and a hook hole is provided near the lower end of the ear 381. The hook hole passes through the left and right sides of the ear 381, that is, the penetration direction of the hook hole is perpendicular to the axis direction of the drone, and the hook hole is open to the rear, so that the ear 130 of the adapter bracket 100 can be hung in the hook hole and fall off from the hook hole. Optionally, 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 tilts downward from front to back, so as to facilitate the ear 130 of the adapter bracket 100 to fall off from the hook hole of the ear 381, and then facilitate the fall-off 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 penetrates the lower surface of the thrust seat 340, and the front part of the installation cavity does not penetrate 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 drone. Also optionally, the thrust seat 340 is fixedly connected to the boost reinforcement frame 330 by screws. Also 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 a plurality of through holes extending from top to bottom, and all the through holes surround the outside of the safety cavity, and a threaded hole is provided at a corresponding position in the fixing groove. The screw passes through the through hole of the thrust seat 340 and is screwed into the threaded hole in the fixing groove, thereby realizing a fixed connection between the thrust seat 340 and the boost reinforcement frame 330.

[0031] On the basis of the above, the materials of the longitudinal long stringer 310 of the fuselage and the rear airbag box 320 can be selected as carbon fiber composite materials, the materials of the booster reinforcement frame 330, the left thrust beam 350 of the engine, the right thrust beam 360 of the engine, the booster reinforcement beam 370, and the rear hanging point frame 380 can be selected as metal aluminum alloy materials, and the material of the thrust seat 340 can be selected as high-strength alloy steel materials. Optionally, the rear end of the longitudinal long stringer 310 of the fuselage and the front end of the booster reinforcement frame 330 are fixedly connected by screw connection + riveting; the upper surface of the rear airbag box 320 and the lower surface of the longitudinal long stringer 310 of the fuselage, as well as the rear end of the rear airbag box 320 and the front end of the booster reinforcement frame 330, are fixedly connected by screw connection.

[0032] The adapter bracket 100 includes: an adapter bracket body 110, a front joint 120 and a hanging ear 130; the lower end of the front joint 120 is fixed to the upper part of the adapter bracket body 110 near its front end, the upper end of the front joint 120 extends into the installation cavity of the thrust seat 340, and the front part of the upper end of the front joint 120 is inserted into the front part of the installation cavity from back to front, so as to realize the clamping of the front joint 120 and the thrust seat 340; the lower end of the hanging ear 130 is fixed to the upper part of the adapter bracket body 110 near its rear end, and the upper end of the hanging ear 130 is hung in the hook hole of the supporting ear 381 of the rear hanging point frame 380; the adapter bracket body 110 is used to be fixedly connected with 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 hanging point frame 380 through the adapter bracket 100, so that the concentrated load of the booster rocket is dispersed on the body structure of the drone.

[0033] Optionally, a hook is formed at the upper end of the hanging ear 130, so that the hanging ear 130 can be easily hung in the hook hole of the support ear 381 through the hook. Optionally, a first fixing hole is opened near the upper end of the hanging ear 130, and a second fixing hole is opened near the lower end of the support ear 381. The first fixing hole is opposite to the second fixing hole, so that after the hanging ear 130 and the support ear 381 are hung, the fixing rod is inserted into the first fixing hole and the second fixing hole to achieve temporary fixation of the hanging ear 130 and the support ear 381. After the UAV and the booster rocket are hoisted onto the launcher as a whole, the fixing rod is pulled out from the first fixing hole and the second fixing hole, so as to release the temporary fixation of the hanging ear 130 and the support ear 381. Optionally, both the first fixing hole and the second fixing hole are threaded holes, and the fixing rod is a screw, and the temporary fixation of the hanging ear 130 and the support ear 381 is achieved through 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, 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 two fixing hoops, one of which is detachably connected to the upper frame near its front end, and the other fixing hoop 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 UAV body, and the separation device 200 is close to the rear end of the adapter bracket body 110, so that when the hook 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 UAV body, thereby avoiding the adapter bracket 100 and the booster rocket from colliding with the UAV 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 part of the adapter bracket body, and the upper end of the separation bracket 210 contacts the UAV body. Optionally, the upper end of the separation bracket 210 has a downward auxiliary groove, and the auxiliary groove runs through both sides, so that after the front joint 120 of the adapter bracket 100 is clamped with the thrust seat 340 and the hanging ear 130 is hooked with the supporting ear 381, the installation rope can be clamped into the auxiliary groove, and then the installation rope is used to compress the separation spring 220, so as to facilitate the separation device 200 to be placed between the upper part of the adapter bracket body 110 and the UAV body, and after the connection, the installation rope can be pulled out, so that the separation device 200 is pressed tightly between the upper part of the adapter bracket body 110 and the UAV body.

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

[0038] 1. The booster rocket is connected and fixed to the adapter bracket 100 to form a whole, and the lower end of the separation device 200 is installed on the adapter bracket 100;

[0039] 2. The front joint 120 of the adapter bracket 100 is docked with the thrust seat 340, and the hanging ear 130 of the adapter bracket 100 is docked with the supporting ear 381 of the rear hanging point frame 380. After docking, the hanging ear 130 of the adapter bracket 100 is connected with the supporting ear 381 of the rear hanging point frame 380 using screws, and the front joint 120 of the adapter bracket 100 is bound to the UAV body using a rope tightener. Finally, the separation device 200 is compressed and the upper end of the separation device 200 is pushed to the UAV body.

[0040] 3. Hoist the UAV and booster rocket onto the launch pad as a whole. After they are installed in place on the launch pad, remove the screws connecting the mounting ears 130 of the adapter bracket 100 and the mounting ears 381 of the rear hanging point frame 380, and remove the rope tightener that binds the front joint 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, under the action of aerodynamic force and its own gravity, it moves in the direction opposite to the movement direction of the UAV. Under the action of the separation device 200, the booster rocket moves away from the UAV body to avoid collision with the UAV during the separation process, which affects flight safety.

[0043] In this application, the booster rocket acts on the drone body through the adapter bracket, so that when the booster rocket is working, the thrust is transmitted to the drone body structure through the adapter bracket. After the booster rocket is finished working, it is safely separated from the drone under the joint action of the aerodynamic force and the separation device. This application improves the reliability of the drone during boosted flight, simplifies the load-bearing structure of the drone 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 drone; and reduces the cost of each drone flight.

[0044] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0045] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description 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 may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A rocket-assisted takeoff bearing device for a UAV with a ventral air inlet, characterized in that: include: Adapter bracket, separation device, longitudinal long stringer of fuselage, rear airbag box, booster reinforcement frame, thrust seat, engine left thrust beam, engine right thrust beam, booster reinforcement beam and rear hanging point frame; The boost reinforcement frame and the rear hanging point frame are both annular, and the axes of the boost 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 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 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 and the right thrust beam of the engine are fixedly connected to the rear end of the booster reinforcement frame, the rear ends of the left thrust beam 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 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, 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 and the right thrust beam of the engine are located above the booster reinforcement beam; The lower surface of the rear hanging point frame has a support ear extending downward, and a hook hole is opened 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 opens toward the rear; The thrust seat has an installation cavity inside, the rear portion of the installation cavity penetrates the lower surface of the thrust seat, and the front portion of the installation cavity does not penetrate 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 hanging ear; the lower end of the front joint is fixed to the upper part of the adapter bracket body near the front end thereof, the upper end of the front joint extends into the installation cavity, and the front part of the upper end of the front joint 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 the rear end thereof, and the upper end of the hanging ear is hung in the hook hole of the supporting 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 front to 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 materials; 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 materials, and the thrust seat is made of high-strength alloy steel material.

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

6. The UAV rocket-assisted takeoff bearing device with a ventral air intake 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, and the first fixing hole is 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 fixing 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 rocket-assisted takeoff bearing device for unmanned aerial vehicle with a ventral air intake 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 rocket-assisted takeoff bearing device for unmanned aerial vehicle 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 rocket-assisted takeoff bearing device for unmanned aerial vehicle 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 runs through both sides.

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