Fixed-wing unmanned aerial vehicle rocket separation mechanism

Abstract

The invention discloses a fixed-wing unmanned aerial vehicle rocket separation mechanism which comprises a boosting limiting device arranged on a boosting rocket, the boosting limiting device comprises a boosting limiting block fixedly connected with the bottom of an unmanned aerial vehicle and provided with a through hole, and a boosting limiting taper pin fixed in the through hole, and one end of the boosting limiting taper pin forms a conical end face; the boosting limiting device further comprises a conical groove which is formed in the boosting rocket and matched with the conical end face. In the boosting process, the conical end face and the conical groove form surface contact and abut against and are attached, it is guaranteed that thrust is evenly transmitted, the stress concentration risk of the fuselage is reduced, meanwhile, interference of non-directional airflow in the boosting process is counteracted, and the situation that the attitude of the unmanned aerial vehicle is out of control is avoided. And after boosting is completed, unpowered natural separation of the unmanned aerial vehicle and the boosting limiting device is achieved through the resistance difference of air to the unmanned aerial vehicle and the boosting limiting device, the conical groove guides the conical end face, additional driving parts are not needed, the structure is simplified, and the flight safety of the separated unmanned aerial vehicle is improved.

Description

Technical Field

[0001] This disclosure relates to the field of fixed-wing unmanned aerial vehicle (UAV) booster technology, specifically to a fixed-wing UAV rocket separation mechanism. Background Technology

[0002] Gravity separation is a typical passive separation method in the rocket booster mechanism of fixed-wing UAVs. Its core is that after the booster rocket shuts down and the thrust disappears, it automatically detaches from the UAV's simple connection mechanism and falls off by relying on its own gravity and aerodynamic drag.

[0003] Current gravity separation methods include hook-type connection structures, slot-type connection structures, and push-rod-type connection structures. Hook-type connection structures transmit thrust through the engagement of a hook and a pin / shaft. After rocket shutdown, disengagement relies on relative displacement. Hooks are often cantilevered or single-point contact designs. During launch, rocket thrust is concentrated at the contact point between the hook and the shaft. If the UAV has a large takeoff weight and the rocket's peak thrust is high, the hook is prone to elastic deformation or even plastic bending, causing the hook to fail to disengage properly and resulting in separation jamming. Slot-type connection structures transmit thrust through a convex-concave fit, relying on the relative movement during separation to disengage the convex part. The sliding out of the slot requires a small clearance design (usually 0.1–0.3 mm) for the slot and the protrusion to fit together. If the machining error exceeds the standard, or if the protrusion is not fully engaged in the bottom of the slot during assembly, the vibration during launch will cause the protrusion to jam against the side wall of the slot. After the rocket is shut down, it will not be able to slide out along the guide chamfer, resulting in separation failure. The push rod type connection structure transmits thrust through the end face of the push rod. After the rocket is shut down, the rocket sinks and the push rod separates from the contact surface. The push rod relies on the end face to transmit thrust. The peak thrust during launch will cause local crushing and denting of the contact surface. The push rod will be stuck in the dented area and unable to separate, causing separation jamming. Summary of the Invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide a rocket separation mechanism for fixed-wing unmanned aerial vehicles.

[0005] In a first aspect, this application provides a fixed-wing unmanned aerial vehicle (UAV) rocket separation mechanism, including a booster limiting device disposed on the booster rocket for supporting the UAV, the booster limiting device comprising: A booster limiting block is fixedly connected to the bottom of the UAV, and a through hole is provided on the booster limiting block; A booster limiting cone pin is fixedly disposed inside the through hole, and one end of the cone pin extends through the through hole to the side of the booster limiting block near the booster rocket, forming a cone-shaped end face. The booster limiting device also includes a conical groove disposed on the booster rocket and adapted to the conical end face. During the boosting process, the conical end face and the conical groove abut against each other and fit together. After the boosting is completed, the conical end face disengages from the conical groove.

[0006] According to the technical solution provided in the embodiments of this application, the booster limiting block has a triangular cross-section and a first sidewall that is fixedly connected to the bottom of the UAV. The axes of the booster limiting block, the booster limiting cone pin, the booster rocket, and the UAV are coplanar.

[0007] According to the technical solution provided in the embodiments of this application, the booster rocket includes: The booster rocket body has a booster connection seat fixedly installed at its front end. A booster push rod is fixedly connected to the side wall of the booster connection seat away from the booster rocket body, and the booster push rod and the booster rocket body are coaxially arranged. A booster U-shaped ring is fixedly connected to the end of the booster push rod away from the booster connection seat, and is used to support the bottom of the drone.

[0008] According to the technical solution provided in the embodiments of this application, the bottom of the drone is provided with a support groove that is adapted to the booster U-shaped ring, and the booster U-shaped ring has a second side wall that abuts against the inner wall of the support groove, and the second side wall is a U-shaped structure.

[0009] According to the technical solution provided in the embodiments of this application, a connecting groove is provided at one end of the booster push rod near the UAV, and the connecting groove and the booster U-shaped ring are respectively provided with connecting holes and are fixedly connected by a connector. The connecting groove abuts against the inner wall of the booster rocket body and the booster U-shaped ring abuts against the side wall of the booster rocket body.

[0010] According to the technical solution provided in the embodiments of this application, the center of gravity of the UAV is on the axis of the booster rod.

[0011] According to the technical solution provided in the embodiments of this application, the boosting and limiting device further includes: A booster limiting guide cone block is fixedly disposed on the side wall of the booster connecting seat away from the booster rocket body and located on the side of the booster push rod close to the UAV. The booster limiting guide cone block has a conical groove on the side wall away from the booster rocket body.

[0012] According to the technical solution provided in the embodiments of this application, the push-limiting guide cone block is provided with a clearance groove on the side near the push-pull rod. The clearance groove is adapted to the push-pull rod, and the inner wall of the clearance groove abuts against the side wall of the push-pull rod.

[0013] According to the technical solution provided in the embodiments of this application, the inner wall of the through hole is provided with threads, the outer wall of the boosting and limiting cone pin is provided with threads, and the boosting and limiting cone pin is screwed into the through hole.

[0014] In summary, this technical solution specifically discloses a fixed-wing UAV rocket separation mechanism, including a booster limiting device mounted on the booster rocket to support the UAV. The booster limiting device includes a booster limiting block, which is fixedly connected to the bottom of the UAV, and a through hole is provided through the booster limiting block. A booster limiting cone pin is fixedly mounted inside the through hole, and one end of the booster limiting cone pin extends through the through hole to the side of the booster limiting block near the booster rocket, forming a conical end face. The booster limiting device also includes a conical groove mounted on the booster rocket and adapted to the conical end face. During the boost, the conical end face and the conical groove abut against each other and fit together. After the boost is completed, the conical end face disengages from the conical groove. Therefore, the conical end face and the conical groove form a surface contact fit, which can apply bidirectional limiting constraints to the UAV in the left-right and up-down directions. This structure can effectively counteract the interference of unpredictable airflow during the boost process, avoid attitude control problems such as deflection and rollover of the UAV, and ensure the stability of the boost process; The booster limiting block is fixedly connected to the bottom of the drone to form a stable force transmission carrier; the surface contact design of the conical end face and the conical groove can evenly transfer the thrust of the booster rocket to the drone fuselage, avoid local stress concentration caused by point contact or line contact, and reduce the risk of overload damage to the drone fuselage structure during the boost phase. The conical end face and the conical groove are matched in a conical structure. By utilizing the guiding effect of the two and the resistance difference between the UAV and the boost limit device after the boost is completed, the conical end face can be naturally detached along the inner wall of the conical groove. There is no need to set up an additional pyrotechnic separation device or drive component, which simplifies the overall structure of the separation mechanism. At the same time, it avoids the impact of forced separation on the sudden change of UAV attitude and improves flight safety after separation. Attached Figure Description

[0015] 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 This is a schematic diagram of a fixed-wing unmanned aerial vehicle rocket separation mechanism connected to a booster rocket.

[0016] Figure 2 This is a schematic diagram of a rocket separation mechanism for a fixed-wing unmanned aerial vehicle.

[0017] Figure 3 This is a cross-sectional view of a rocket separation mechanism for a fixed-wing unmanned aerial vehicle.

[0018] Figure 4 This is a schematic diagram of a fixed-wing UAV rocket separation mechanism supporting the UAV.

[0019] The following are the labels in the diagram: 1. Boost rocket; 2. Boost limiting block; 3. Boost limiting cone pin; 4. Boost connecting seat; 5. Boost push rod; 6. Boost U-shaped ring; 7. Boost limiting guide cone block; 8. UAV. Detailed Implementation

[0020] 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.

[0021] 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.

[0022] Example 1 Please refer to Figure 1 and Figure 3 A fixed-wing unmanned aerial vehicle (UAV) rocket separation mechanism includes a booster limiting device mounted on the booster rocket to support the UAV 8. The booster limiting device limits the UAV 8, ensuring that the thrust of the booster rocket is smoothly transmitted to the UAV 8. It also prevents the UAV 8 from deflecting or flipping due to airflow during boosting, thus improving the boosting success rate and enhancing its anti-interference capability. The end of the booster rocket furthest from the UAV 8 is the ejector end, which ejects high-speed airflow after the booster rocket is ignited to provide thrust to the UAV 8.

[0023] like Figures 1 to 3 As shown, the booster limiting device includes: The booster limit block 2 is fixedly connected to the bottom of the drone 8, and a through hole is provided on the booster limit block 2. The booster limiting cone pin 3 is fixedly installed inside the through hole, and one end of it extends through the through hole to the side of the booster limiting block 2 near the booster rocket, forming a cone-shaped end face. The booster limiting device also includes a conical groove that is installed on the booster rocket and is adapted to the conical end face. During the boosting process, the conical end face and the conical groove abut against each other and fit together. After the boosting is completed, the conical end face disengages from the conical groove.

[0024] Specifically, the bottom of the booster limiting block 2 and the drone 8 are fixedly connected. The bottom of the drone 8 is provided with a booster limiting groove corresponding to the booster limiting block 2. The booster limiting block 2 is set in the booster limiting groove, so that the booster limiting block 2 and the drone 8 form a surface contact, effectively transmitting the thrust of the booster rocket. A through hole is provided on the boosting limit block 2, and a boosting limit cone pin 3 is fixedly installed in the through hole; optionally, the boosting limit cone pin 3 and the boosting limit block 2 are threadedly connected, specifically: the inner wall of the through hole is provided with threads, and the boosting limit cone pin 3 has a first section and a second section that are integrally formed and fixedly connected. The outer wall of the first section is provided with threads, and the first section is screwed into the through hole to form a tight fit.

[0025] The second section extends through a through hole and protrudes from the side of the booster limiting block 2 near the booster rocket, forming a conical end face. The diameter of the conical end face near the booster rocket is smaller than the diameter of the end away from the booster rocket, and the diameter of the conical end face away from the booster rocket is larger than the diameter of the first section. Optionally, the side wall of the conical end face away from the booster rocket abuts against the side wall of the booster limiting block 2 near the booster rocket.

[0026] The booster limiting device also includes a conical groove that is fitted to the conical end face on the booster rocket. The conical end face and the conical groove are movably connected. The axis of the booster limiting cone pin 3 and the axis of the UAV 8 form a preset angle. Thus, the conical end face and the conical groove form a surface contact. The matching design of the conical structure can achieve limiting in the left and right and up and down directions of the UAV 8. During the boost, the conical end face and the conical groove abut against each other, which can effectively avoid the influence of airflow, improve the stability of the boost, and ensure that the thrust of the booster rocket can be smoothly transmitted to the UAV 8. Meanwhile, due to the design of the conical structure, the diameter of the conical end face near the booster rocket is smaller than the diameter of the end away from the booster rocket. After the booster rocket completes its boost to the UAV 8, due to air resistance, the resistance experienced by the booster limiting device is greater than that experienced by the UAV 8. Therefore, the booster limiting device will decelerate. Guided by the outer wall of the conical end face and the inner wall of the conical groove, the conical end face will disengage from the conical groove, and the booster limiting device will slide naturally to the rear of the UAV 8, thus achieving a smooth separation between the booster limiting device and the UAV 8 without affecting the normal flight of the UAV 8.

[0027] Furthermore, the booster limiting block 2 has a triangular cross-section and a first sidewall that is fixedly connected to the bottom of the UAV 8. The axes of the booster limiting block 2, the booster limiting cone pin 3, the booster rocket, and the UAV 8 are coplanar.

[0028] Specifically, the booster limiting block 2 has a triangular cross section, that is, the booster limiting block 2 is a triangular prism structure, which is fixedly connected to the bottom of the drone 8. The side wall of the booster limiting block 2 connected to the drone 8 is the first side wall. Optionally, the first side wall and the drone 8 are connected by bolts. Boost limit block 2, boost limit cone pin 3, and the 8 axes of the booster rocket and the drone are coplanar.

[0029] Therefore, by using a coplanar design, the thrust direction of the booster rocket can be effectively guaranteed, avoiding thrust deviation that could lead to booster failure.

[0030] Since the booster limiting block 2, the booster limiting cone pin 3 and the UAV 8 are coplanar, that is, the centerline of the first side wall and the axis of the UAV 8 are coplanar, and the two ends of the first side wall are symmetrically distributed on both sides of the axis of the UAV 8, and since the first side wall and the UAV 8 are connected by bolts, and the design of the conical end face and the conical groove are well matched, the booster limiting block 2 can limit the left and right and up and down directions of the UAV 8, so as to avoid the attitude deflection of the UAV 8 caused by external influences such as unpredictable airflow during the boost, thus improving the success rate of the boost.

[0031] Furthermore, the booster limiting device also includes: The booster rocket body 1 has a booster connection seat 4 fixedly installed at its front end. The booster rod 5 is fixedly connected to the side wall of the booster connection seat 4 away from the booster rocket body 1, and the booster rod 5 and the booster rocket body 1 are coaxially arranged. The booster U-shaped ring 6 is fixedly connected to the end of the booster push rod 5 away from the booster connection seat 4, and is used to support the bottom of the drone 8.

[0032] Specifically, the booster connection seat 4 is fixedly installed at the front end of the booster rocket body 1. Its front end is the end of the booster rocket body 1 away from the ejection end, that is, the end of the booster rocket body 1 close to the UAV 8. The booster connection seat 4 can be connected to the booster rocket body 1 by bolts, such as by connecting the front circumferential side wall of the booster rocket body 1 and the circumferential side wall of the booster connection seat 4 with multiple bolts evenly distributed in the circumference. A booster push rod 5 is fixedly installed on the side wall of the booster connection seat 4 away from the booster rocket body 1. Preferably, the booster rod 5 and the booster rocket body 1 are coaxially arranged. This can be achieved by creating a groove on the side wall of the booster connecting seat 4 away from the booster rocket body 1, and fitting or interfering with the end of the booster rod 5 near the booster rocket body 1 into the groove. Then, a screw is passed through the booster connecting seat 4 and screwed into the booster rod 5 to achieve a stable connection.

[0033] A booster U-shaped ring 6 is fixedly connected to the end of the booster rod 5 away from the booster rocket body 1. The booster U-shaped ring 6 has an opening facing the UAV 8. Preferably, the axis of the booster U-shaped ring 6 is perpendicular to the axis of the booster rod 5. The booster U-shaped ring 6 can support the UAV 8, and the axes of the booster U-shaped ring 6, the booster rod 5, the booster rocket body 1, and the UAV 8 are coplanar. Thus, the two ends of the booster U-shaped ring 6 are symmetrically distributed on both sides of the axis of the UAV 8, achieving a stable support function.

[0034] Furthermore, the bottom of the UAV 8 is provided with a support groove that is compatible with the booster U-shaped ring 6. The booster U-shaped ring 6 has a second side wall that abuts against the inner wall of the support groove. The second side wall has a U-shaped structure.

[0035] Specifically, the bottom of the UAV 8 is provided with a support groove that matches the booster U-shaped ring 6. The booster U-shaped ring 6 is located in the support groove, and the booster U-shaped ring 6 has a second side wall away from the booster push rod 5. The second side wall abuts against the inner wall of the support groove. Thus, a surface contact is formed between the booster U-shaped ring 6 and the UAV 8. The two ends of the booster U-shaped ring 6 are symmetrically distributed on both sides of the axis of the UAV 8, which can effectively support the UAV 8 and maintain its balance, while limiting the forward and backward movement of the UAV 8. Since the booster U-shaped ring 6 and the UAV 8 are in surface contact, the thrust of the booster rocket body 1 can be effectively transmitted during the boost process, ensuring the stable flight attitude of the UAV 8 and stably propelling the UAV 8 to take off.

[0036] Furthermore, the booster rod 5 is provided with a connecting groove at one end near the UAV 8. The connecting groove and the booster U-shaped ring 6 are respectively provided with connecting holes and are fixedly connected by a connector. The connecting groove abuts against the inner wall of the booster rocket body 1 and the booster U-shaped ring 6 abuts against the side wall of the booster rocket body 1.

[0037] Specifically, the booster rod 5 has a connecting groove at the end near the drone 8 for connecting with the booster U-shaped ring 6. Optionally, the connecting groove is located at the end of the booster rod 5 near the drone 8, on the side away from the drone 8, that is, the lower side of the booster rod 5. A connecting hole is provided through the connecting groove, and a corresponding connecting hole is provided on the booster U-shaped ring 6. The booster U-shaped ring 6 and the connecting groove are fixedly connected by a connector. Optionally, the connecting hole is a screw hole, and the connector is a bolt.

[0038] By setting a connecting groove on the booster push rod 5 and connecting it to the booster U-shaped ring 6 through a connector, the inner wall of the connecting groove can abut against the side wall of the booster U-shaped ring 6 to form a surface contact. The thrust of the booster rocket body 1 can be stably transmitted to the booster U-shaped ring 6, and then transmitted from the booster U-shaped ring 6 to the UAV 8. At the same time, the connecting groove is located on the lower side of the booster push rod 5, realizing the structure of the booster push rod 5 pressing the booster U-shaped ring 6. The connection with the booster U-shaped ring 6 is strengthened in conjunction with the connector, which can prevent the booster U-shaped ring 6 from flipping due to the sudden action of thrust during the boost process and the UAV 8's tendency to block the booster U-shaped ring 6, which would cause the booster U-shaped ring 6 to fail.

[0039] Furthermore, the center of gravity of the drone 8 is on the axis of the booster rod 5.

[0040] Specifically, the center of gravity of the UAV 8 is on the axis of the booster rod 5. At the same time, the booster rod 5 and the booster rocket body 1 are coaxially set. Therefore, the thrust line of the booster rocket body 1 can pass through the center of gravity of the UAV 8. In other words, the thrust of the booster rocket body 1 acts on the center of gravity of the UAV 8, which can ensure the stability of the fuselage attitude during the boost and prevent pitching, pitching or rolling. At the same time, at the moment of separation between the booster limiting device and the UAV 8, the UAV 8 will not experience a sudden change in attitude due to residual torque and can smoothly transition to autonomous flight, thus improving the safety when the booster limiting device and the UAV 8 separate.

[0041] Furthermore, the booster limiting device also includes: The booster limiting guide cone 7 is fixedly installed on the side wall of the booster connecting seat 4 away from the booster rocket body 1, and located on the side of the booster push rod 5 close to the UAV 8. A conical groove is provided on the side wall of the booster limiting guide cone 7 away from the booster rocket body 1.

[0042] The boosting limit guide cone block 7 is provided with a clearance groove on the side near the boosting push rod 5. The clearance groove is adapted to the boosting push rod 5, and the inner wall of the clearance groove abuts against the side wall of the boosting push rod 5.

[0043] Specifically, the booster limiting guide cone 7 is fixedly installed on the side wall of the booster connecting seat 4 away from the booster rocket body 1, and the conical groove is installed on the side wall of the booster limiting guide cone 7 away from the booster rocket body 1. At the same time, the booster limiting guide cone 7 is located on the side of the booster push rod 5 close to the UAV 8, and the side of the booster limiting guide cone 7 close to the booster push rod 5 is provided with a clearance groove that is compatible with the booster push rod 5. The inner wall of the clearance groove abuts against the side wall of the booster push rod 5. Therefore, the boost limiting guide cone block 7 not only provides a accommodating space that can be adapted to the conical end face of the boost limiting cone pin 3 to limit the left and right and up and down directions of the UAV 8 and ensure the stable transmission of thrust, but also limits and fixes the boost push rod 5, ensuring the stability of the boost push rod 5 and avoiding the situation where the boost push rod 5 deflects due to the sudden increase in thrust during the boost, thus improving the success rate of the boost.

[0044] Working principle: This fixed-wing UAV rocket separation mechanism achieves stable transmission of thrust of the booster rocket body 1 and smooth separation of the booster limiting device through the coordinated cooperation of the first booster limiting component, the second booster limiting component and the booster limiting guide cone block 7. The booster connection seat 4 is fixed to the front end of the booster rocket body 1, and the booster push rod 5 is fixedly set on the side wall of the booster connection seat 4 away from the booster rocket body 1. The booster U-shaped ring 6 set at the end away from the booster rocket body 1 cooperates with the support groove at the bottom of the UAV 8, and the second side wall of the booster U-shaped ring 6 contacts the inner wall of the support groove. At the same time, due to the design of the UAV 8's center of gravity on the axis of the booster push rod 5, the thrust is directly applied to the center of gravity of the UAV 8 without additional deflection torque, thus avoiding the generation of pitch, yaw, and roll torques caused by thrust eccentricity. The boost limiting block 2 is set in the boost limiting groove. The tapered end face of the boost limiting cone pin 3 in the through hole of the boost limiting block 2 is movably adapted to the tapered groove on the boost limiting guide cone block 7. The tapered end face and the tapered groove are in surface contact to realize the rigid limitation of the UAV 8 in the left and right and up and down directions, ensuring uniform transmission of thrust and reducing the risk of local stress concentration in the fuselage. At the same time, the clearance groove of the boost limiting guide cone block 7 abuts against the side wall of the boost push rod 5 to radially fix the boost push rod 5 and prevent the boost push rod 5 from deflecting due to a sudden increase in thrust. The conical limiter of the first booster limiter constrains the UAV 8 in the up-down and left-right directions, while the booster U-shaped ring 6 of the second booster limiter constrains the UAV 8 in the front-back direction. This effectively resists the interference of unpredictable airflow during the boost and prevents the UAV 8 from deviating in attitude.

[0045] After the booster rocket body 1 completes its boost, the air resistance has a greater effect on the booster limiting device than on the UAV 8 body, and the booster limiting device decelerates later than the UAV 8. Under the conical guidance of the conical end face and the conical groove, the conical end face naturally slides off along the inner wall of the conical groove, while the booster U-shaped ring 6 disengages from the bottom support groove of the UAV 8, ultimately achieving a smooth and impact-free separation between the booster limiting device and the UAV 8 without the need for an additional separation drive mechanism.

[0046] Natural separation is achieved by utilizing air resistance difference and a conical guide structure, eliminating the need for additional pyrotechnics or drive components. This simplifies the system structure and avoids the abrupt changes in the attitude of UAV 8 caused by forced separation, ensuring that UAV 8 smoothly transitions to autonomous flight after separation.

[0047] 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 rocket separation mechanism for a fixed-wing unmanned aerial vehicle, characterized in that, Includes a booster limiting device mounted on the booster rocket for supporting the unmanned aerial vehicle (8), the booster limiting device comprising: A booster limiting block (2) is fixedly connected to the bottom of the UAV (8), and a through hole is provided on the booster limiting block (2); The booster limiting cone pin (3) is fixedly disposed inside the through hole, and one end of it extends through the through hole to the side of the booster limiting block (2) near the booster rocket and forms a cone-shaped end face. The booster limiting device also includes a conical groove disposed on the booster rocket and adapted to the conical end face. During the boosting process, the conical end face and the conical groove abut against each other and fit together. After the boosting is completed, the conical end face disengages from the conical groove.

2. The fixed-wing UAV rocket separation mechanism according to claim 1, characterized in that, The booster limiting block (2) has a triangular cross section and a first sidewall that is fixedly connected to the bottom of the UAV (8). The axes of the booster limiting block (2), the booster limiting cone pin (3), the booster rocket, and the UAV (8) are coplanar.

3. The fixed-wing UAV rocket separation mechanism according to claim 1, characterized in that, The booster rocket includes: The booster rocket body (1) has a booster connection seat (4) fixedly installed at the front end of the booster rocket body (1); The booster push rod (5) is fixedly connected to the side wall of the booster connection seat (4) away from the booster rocket body (1), and the booster push rod (5) and the booster rocket body (1) are coaxially arranged. A booster U-shaped ring (6) is fixedly connected to one end of the booster push rod (5) away from the booster connecting seat (4) and is used to support the bottom of the UAV (8).

4. A fixed-wing unmanned aerial vehicle rocket separation mechanism according to claim 3, characterized in that, The bottom of the drone (8) is provided with a support groove that is compatible with the booster U-shaped ring (6). The booster U-shaped ring (6) has a second side wall that abuts against the inner wall of the support groove. The second side wall is a U-shaped structure.

5. A fixed-wing unmanned aerial vehicle rocket separation mechanism according to claim 3, characterized in that, The booster push rod (5) is provided with a connecting groove at one end near the UAV (8). The connecting groove and the booster U-shaped ring (6) are provided with corresponding connecting holes and are fixedly connected by a connector. The connecting groove abuts against the inner wall of the booster rocket body (1) and the booster U-shaped ring (6) abuts against the side wall of the booster rocket body (1).

6. A fixed-wing unmanned aerial vehicle rocket separation mechanism according to claim 3, characterized in that, The center of gravity of the drone (8) is on the axis of the booster rod (5).

7. A fixed-wing unmanned aerial vehicle rocket separation mechanism according to claim 3, characterized in that, The booster limiting device also includes: The boost limiting guide cone (7) is fixedly disposed on the side wall of the booster connecting seat (4) away from the booster rocket body (1) and located on the side of the booster push rod (5) close to the UAV (8). The boost limiting guide cone (7) is provided with the conical groove on the side wall away from the booster rocket body (1).

8. A fixed-wing unmanned aerial vehicle rocket separation mechanism according to claim 7, characterized in that, The boosting limit guide cone block (7) is provided with a clearance groove on the side near the boosting push rod (5). The clearance groove is adapted to the boosting push rod (5), and the inner wall of the clearance groove abuts against the side wall of the boosting push rod (5).

9. A fixed-wing unmanned aerial vehicle rocket separation mechanism according to claim 1, characterized in that, The inner wall of the through hole is provided with threads, and the outer wall of the boosting limit cone pin (3) is provided with threads. The boosting limit cone pin (3) is screwed into the through hole.

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