A separation limit device and method for a rocket booster

Abstract

An off - limit device and method for a rocket booster, belonging to the technical field of UAV launching; the off - limit device includes a rocket booster, a guiding device, a detachment device and a rocket booster adapter ring. One end of the guiding device is fixed to the abdomen of the UAV fuselage. The crossbar of the T - shaped joint of the guiding device is hinged to the connecting hole with a notch at the front end of the detachment device. The rear end of the detachment device is connected to two radial lugs of the rocket booster adapter ring through a limiting component. The rocket booster adapter ring is sleeved on the front end of the rocket booster. When the rocket booster finishes working, it automatically separates from the fuselage under its own gravity and falls downward. Driven by the detachment device, it rotates around the crossbar of the T - shaped joint to a certain angle. After the crossbar of the T - shaped joint slides out from the front notch, the rocket booster, together with the detachment device, is completely separated from the UAV. The present invention can reliably fix the rocket booster, keep the angle between it and the airframe unchanged, avoid the upward warping of the booster nozzle, and ensure that the UAV is not damaged.

Description

Technical Field

[0001] The present invention belongs to the technical field of UAV launch, and particularly relates to a separation limiting device and method for a rocket booster. Background Art

[0002] For a UAV using a rocket-boosted launch method, before takeoff, the docking structure of the rocket booster is attached to the airframe. During the takeoff process of the UAV, the two are tightly connected together under the thrust of the booster. After the rocket booster finishes working, it can be discarded from the airframe or not. If not discarded, the rocket booster is fixedly connected to the aircraft and continues to perform the flight mission with the UAV after the work is completed; if discarded, it is necessary to control the separation route of the rocket booster from the airframe to prevent the booster from colliding with the airframe or the rotating propeller, causing the propeller to break or the airframe to be damaged, affecting the flight safety of the UAV, or even causing it to lose power and be damaged, and unable to complete the predetermined task.

[0003] Currently, the common methods for controlling the separation route of the rocket booster are generally wire fixing or using a separation frame for guidance. In the patent application "A Rocket Separation Mechanism for a UAV with a Rear Power Layout" (application publication number CN109703772 A), a rocket booster separation mechanism used for a UAV with a rear power layout is introduced. This separation mechanism can control the rocket to rotate around a control point and separate at a predetermined position. This solution has poor adaptability. Due to the different docking states between the rocket booster and different UAVs, there may be an interference situation between the separation mechanism and the rocket structure after installation (in this case, the separation mechanism needs to be repaired), or there may be a situation where the gap between the separation mechanism and the rocket is too large. At this time, the separation route of the rocket cannot be effectively controlled, and the gap cannot be adjusted by repairing the separation mechanism.

[0004] The technical solutions adopted by current control devices generally have problems such as many components, high cost, the need for tools during the disassembly and assembly process, poor installation adaptability, the need for on-site adjustment or filing and repair, and cumbersome operation. Summary of the Invention

[0005] Technical Problems to be Solved

[0006] In order to avoid the deficiencies of the prior art, the present invention provides a separation limiting device and method for a rocket booster. By adjusting the nuts of the universal adjusting feet and the star nuts, the gap between the universal adjusting feet and the rocket booster can be maintained at a reasonable value, and it can adapt to different UAVs.

[0007] The technical solution of the present invention is: a separation limiting device for a rocket booster, including a rocket booster, characterized in that: it further includes a guiding device, a separation device and a rocket booster adapter ring. One end of the guiding device is fixed to the abdomen of the UAV fuselage, and the other end is hinged to one end of the separation device. The other end of the separation device is connected to the rocket booster through the rocket booster adapter ring;

[0008] The guiding device includes a base, a torsion spring and a T-shaped joint. The base is connected to the abdomen of the fuselage; the bottom end of the vertical rod of the T-shaped joint is hinged to the base through a pin, and the axial direction of the crossbar at its head is perpendicular to the central axis of the vertical rod; two torsion springs are respectively sleeved at both ends of the pin, and the T-shaped joint is controlled to bounce back upward after the rocket booster separates through the resilience;

[0009] The separation device includes a separation frame assembly, a star nut and a universal adjusting foot. Two lugs are arranged in parallel at both ends of the separation frame assembly. A connecting hole with a notch is coaxially arranged on the two lugs at one end. The crossbar of the T-shaped joint is hinged to the lug at one end through the connecting hole with a notch, and the separation of the two is realized through the notch; a limiting component is arranged on the two lugs at the other end of the separation frame assembly and is connected to the rocket booster adapter ring; the threaded rod of the universal adjusting foot passes through the through hole on the separation frame assembly and is tightened and fixed through the star nut; the foot seat of the universal adjusting foot is located above the separation frame assembly and is pressed and fitted with the peripheral surface at the front end of the rocket booster and rotates with the change of the position of the rocket booster;

[0010] The rocket booster adapter ring is a circular ring structure and is sleeved on the front end of the rocket booster; two radial lugs are symmetrically arranged on the outer peripheral surface of the rocket booster adapter ring and are connected to the limiting components on the two lugs at the other end of the separation frame assembly.

[0011] A further technical solution of the present invention is: the guiding device further includes a rubber pad fixed to the abdomen of the fuselage, which is opposite to the position of the vertical rod of the T-shaped joint. When the T-shaped joint bounces back, the rubber pad can prevent the body from being damaged.

[0012] A further technical solution of the present invention is: the cross-sectional shape of the crossbar of the T-shaped joint is circular, and parallel axial cutting surfaces are arranged at both ends of the crossbar to facilitate sliding out from the notch.

[0013] A further technical solution of the present invention is: the separation frame assembly includes a front joint, a rear joint and a plate member; the plate member is a rectangular structure, and the front joint and the rear joint are respectively fixed to both ends of the plate member, and lugs are arranged at their outer ends as connecting components for the crossbar of the T-shaped joint and the rocket booster adapter ring.

[0014] A further technical solution of the present invention is: the limiting assembly of the falling frame assembly includes a limiting block, a spring sheet, a limiting block screw and a fastening screw; a rectangular notch is opened at the two lug ends at the other end of the falling frame assembly, and one end of the limiting block is hinged to the bottom of the rectangular notch by the limiting block screw; the upper end of the spring sheet is fixed to the upper end of the rectangular notch by the fastening screw, and the lower end has a bending structure; after the free end of the limiting block is rotated to the lower end of the spring sheet, it is positioned by the bending structure of the spring sheet, and a closed connecting hole is formed, which is used to connect with the radial ear sheets at both ends of the rocket booster adapter ring.

[0015] A further technical solution of the present invention is that the foot seat of the universal adjustment foot can be universally rotated around the ball head at the end of its threaded rod, and the axial position of the universal adjustment foot can be adjusted by adjusting the nut on the threaded rod.

[0016] A further technical solution of the present invention is: the universal adjustment foot is located on the plate near one end of the rear joint.

[0017] A further technical solution of the present invention is that the front joint, the rear joint and the plate are fixedly connected by screws.

[0018] A method for installing a drop-off limiter for a rocket booster, characterized in that the specific steps are as follows:

[0019] Step 1: dock the rocket booster with the fuselage and secure the rocket booster;

[0020] Step 2: manually pry open the spring sheet of the shedding frame assembly and place the limit block in the open position;

[0021] Step 3: Press down the T-shaped joint of the guide device, and at the same time, the connection holes with notches on both sides of the front end of the shedding device are fitted on both ends of the crossbar of the T-shaped joint and can rotate;

[0022] Step 4: Put the limiting components on both sides of the rear end of the shedding device onto the radial ear pieces of the rocket booster adapter ring, and then rotate the limiting block upward and close it with the spring sheet to connect the shedding device to the rocket booster adapter ring;

[0023] Step 5: Rotate the nut and star nut on the threaded rod of the universal adjustment foot to make the base of the universal adjustment foot contact the front end surface of the rocket booster, and then fix the universal adjustment foot.

[0024] A separation method for a separation limiting device of a rocket booster, characterized in that: first, the rocket booster is docked with the fuselage. When the rocket booster finishes working, it automatically separates from the fuselage under its own gravity and falls downward; then it is pulled by the separation device and rotates around the crossbar of the T-shaped joint, gradually falling away from the fuselage; finally, when it rotates until the front notch of the separation device is located above and the two ends of the crossbar of the T-shaped joint slide out from the front notch, the rocket booster is completely separated from the unmanned aerial vehicle along with the separation device.

[0025] Beneficial effects

[0026] The beneficial effects of the present invention are as follows: The separation limiting device disclosed in the present invention can reliably fix the rocket booster, keep the included angle between it and the airframe unchanged, avoid the upward warping of the tail nozzle of the booster, ensure the structural integrity of the propeller and the unmanned aerial vehicle airframe, and ensure flight safety. By adjusting the nuts of the universal adjusting feet and the star nuts, the gap between the universal adjusting feet and the rocket booster can be kept at a reasonable value, which can adapt to different unmanned aerial vehicles. The components are made of commonly used industrial materials, with a simple structure, and can be quickly mass-produced through processes such as wire cutting and sheet metal working. Standard parts are selected as national standard parts or aviation standard parts. Some parts are selected as off-the-shelf products, with low procurement costs. Therefore, the overall processing and use cost of the separation limiting device is low. The separation limiting device disclosed in the present invention adopts a manual installation and adjustment method during operation, without the need for any tools, with convenient operation and can be quickly disassembled and assembled. By adjusting the thread, the included angle between the separation limiting device and the rocket booster can be adjusted to adapt to the individual differences of unmanned aerial vehicles caused by manufacturing deviations. Description of the drawings

[0027] Figure 1 is the left view of the system composition of this embodiment;

[0028] Figure 2 is the connection schematic diagram of the guiding device and the separation device of this embodiment;

[0029] Figure 3 is the connection schematic diagram of the separation device and the rocket booster adapter ring of this embodiment;

[0030] Figure 4 is the system working principle diagram of this embodiment;

[0031] Figure 5 is the left view of the separation device of this embodiment;

[0032] Figure 6 is the top view of the separation device of this embodiment;

[0033] Figure 7 is the left view of the rocket booster adapter ring of this embodiment;

[0034] Figure 8 is the top view of the rocket booster adapter ring of this embodiment;

[0035] Figure 9 is the left view of the guiding device of this embodiment;

[0036] Figure 10 is the top view of the guiding device of this embodiment;

[0037] Explanation of reference numerals: 1, separation device; 2, rocket booster adapter ring; 3, guiding device; 4, fuselage; 5, rocket booster; 6, center of gravity; 7, propeller; 8, propeller axis; 11, separation frame assembly; 12, star nut; 13, universal adjusting foot; 31, base; 32, torsion spring; 33, T-shaped joint; 34, pin; 35, rubber pad; 111, front joint; 112, rear joint; 113, plate; 114, limit block; 115, spring piece; 116, limit block screw; 117, fastening screw; 131, foot seat; 132, nut; 133, threaded rod. Detailed implementation manners

[0038] The embodiments described below by referring to the accompanying drawings are exemplary and are intended to explain the present invention, and should not be construed as limiting the present invention.

[0039] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

[0040] Referring to Figure 1 As shown, a separation limiting device for a rocket booster of the present invention includes a rocket booster, a guiding device, a separation device, and a rocket booster adapter ring. One end of the guiding device is fixed to the abdomen of the UAV fuselage, and the other end is hinged to one end of the separation device. The other end of the separation device is connected to the rocket booster through the rocket booster adapter ring; the rocket booster can be limited to prevent the tail from moving upward.

[0041] The guide device includes a base, a torsion spring, a T-shaped joint, and a rubber pad. The base is connected to the belly of the fuselage. The bottom end of the vertical rod of the T-shaped joint is hinged to the base through a pin, and the cross bar at the head is axially perpendicular to the central axis of the vertical rod. Two torsion springs are respectively mounted on the two ends of the pin, and the T-shaped joint is controlled by the rebound force to bounce back upward after the rocket booster falls off. The rubber pad is fixed to the belly of the fuselage, opposite to the vertical rod of the T-shaped joint. When the T-shaped joint bounces back, the rubber pad can avoid damaging the fuselage.

[0042] The falling device includes a falling frame assembly, a star nut and a universal adjustment foot, and the falling frame assembly includes a front joint, a rear joint and a plate; the plate is a rectangular structure, and the front joint and the rear joint are respectively fixed at the two ends of the plate, and lugs are provided at the outer ends thereof, which serve as components hinged with the cross bar of the T-joint and the rocket booster adapter ring. Connecting holes with notches are coaxially arranged on the two lugs of the front joint, and the cross bar of the T-joint is hinged to the lug at one end through the connecting hole with the notch, and the separation of the two is achieved through the notch; a limiting assembly is provided on the two lugs of the rear joint, which is hinged to the rocket booster adapter ring; the threaded rod of the universal adjustment foot passes through the through hole on the falling frame assembly, and is tightened and fixed by a star nut; the base of the universal adjustment foot is located above the falling frame assembly, close to one end of the rear joint, and is pressed and fitted with the circumference of the front end of the rocket booster, and rotates with the position change of the rocket booster;

[0043] The limiting assembly of the falling frame assembly includes a limiting block, a spring sheet, a limiting block screw and a fastening screw; a rectangular notch is opened at the two lug ends at the other end of the falling frame assembly, and one end of the limiting block is hinged to the bottom of the rectangular notch by the limiting block screw; the upper end of the spring sheet is fixed to the upper end of the rectangular notch by the fastening screw, and the lower end has a bending structure; after the free end of the limiting block is rotated to the lower end of the spring sheet, it is positioned by the bending structure of the spring sheet, and a closed connecting hole is formed, which is used to be hinged with the radial ears at both ends of the rocket booster adapter ring.

[0044] The rocket booster adapter ring is a circular ring structure, which is mounted on the front end of the rocket booster; two radial ears are symmetrically arranged on the outer peripheral surface of the rocket booster adapter ring, which are hinged to the limit assemblies on the two lugs at the other end of the shedding frame assembly.

[0045] The method for disengaging the rocket booster's disengagement limiter is as follows: first, the rocket booster is docked with the fuselage, and when the rocket booster finishes working, it automatically separates from the fuselage under the action of its own gravity and falls downward; then, it is pulled by the disengagement device and rotates around the cross bar of the T-joint, gradually falling away from the fuselage; finally, when the disengagement device rotates until the front end notch is located at the top and the two ends of the cross bar of the T-joint slide out of the front end notch, the rocket booster is completely separated from the UAV along with the disengagement device.

[0046] After the rocket booster falls off, the T-shaped joint of the guide device rebounds upward under the action of the torsion spring, close to the belly of the fuselage, and reduces the impact on the aerodynamic characteristics of the aircraft. When the T-shaped joint rebounds, the rubber pad can prevent the fuselage from being damaged.

[0047] The working principle of the present invention is: Figure 1 As shown, the rocket booster 5 is docked with the fuselage 4. After the booster finishes working, it will automatically separate from the fuselage under its own gravity and fall downward. At this time, under the influence of the airflow, the booster may move upward at the tail end, or the fuselage may change its posture under the influence of the gust, causing the distance between the fuselage and the booster to narrow, and eventually causing the booster to collide with the propeller and damage the propeller. This failure has occurred during the actual flight of the drone. The technical solution of the present invention fixes the front end of the rocket booster 5 to prevent its tail from tilting up, so that it rotates downward around a set point and a fixed axis together with the shedding device 1, gradually falls away from the fuselage, and completely separates from the drone after rotating to a predetermined angle, thereby preventing the rocket booster 5 from hitting the propeller 7 and ensuring the safe launch of the drone.

[0048] The present invention shows Figure 1 and 4 The left direction is the heading.

[0049] The shedding device 1 of the embodiment of the present invention is composed of a shedding frame assembly 11, a star nut 12, and a universal adjustment foot 13. The foot seat 131 of the universal adjustment foot 13 can be universally rotated around the ball head at the end of the threaded rod 133. After the threaded rod 133 passes through the hole of the shedding frame assembly 11, it can be screwed into the star nut 12, and the nut 132 can rotate around the threaded rod 133 and move up and down. The nut 132 and the star nut 12 are used together to fix the universal adjustment foot 13 and the shedding device 1.

[0050] The limit block screw 116 of the embodiment of the present invention fixes the limit block 114 on the shedding frame assembly 11, and the limit block 114 can rotate around the axis of the screw 116. The top of the spring sheet 115 has a curved edge, and after the limit block 114 is rotated upward and closed, the spring sheet 115 can fix its position. The spring sheet 115 is manually opened, and the limit block 114 can be rotated downward. The fastening screw 117 fixes the spring sheet 115 to the end of the rear joint 112 of the shedding frame assembly 11.

[0051] The structure of the rocket booster adapter ring 2 of the embodiment of the present invention is as follows Figure 7 and 8 As shown, it is sleeved on the rocket booster 5 and is a part thereof. The adapter ring and the rocket booster 5 adopt clearance fit and can rotate around the axis of the rocket booster.

[0052] The rocket booster 5 of the embodiment of the present invention is connected to the body by a planar docking method. In other embodiments, different schemes may also be adopted, such as a guide cone seat.

[0053] The base 31 of the guide device 3 of the embodiment of the present invention is fixed to the machine body by screws. The pin 34 connects the base 31, the torsion spring 32 and the T-shaped joint 33 as a whole. The T-shaped joint 33 can rotate downward around the pin 34 and twist the torsion spring 32, such as Figure 9 In other embodiments, the function of the guide device 3 may be realized in other ways.

[0054] In the embodiment of the present invention, the rubber pad 35 is bonded to the belly of the fuselage to prevent the rebounding T-shaped connector 33 from damaging the belly of the drone. In other embodiments, other elastic materials may be used to replace the rubber pad.

[0055] The shedding device 1 and the rocket booster adapter ring 2 in the embodiment of the present invention are consumables, and one piece is consumed for each sortie.

[0056] The cross-sections of both ends of the T-shaped joint 33 of the guide device 3 of the embodiment of the present invention are circular and cut into sections. Figure 9 As shown, the front connector 111 of the corresponding shedding device 1 is a circular hole and is partially grooved, such as Figure 5 shown.

[0057] The center of gravity 6 of the assembly (including the rocket booster 5, the adapter ring 2 and the shedding device 1) of the embodiment of the present invention and the hinge points between the shedding device 1 and the guide device 3 are as follows: Figure 4 As shown. After the rocket booster 5 finishes working, it moves downward under its own gravity, and at the same time drives the adapter ring 2 and the shedding device 1 to rotate around the hinge point. Figure 4 When in the position shown, it is separated from the body.

[0058] The embodiment of the present invention does not require any tools to be used during operation, adopts a manual adjustment method, is easy to operate, and has the convenience of tool-free quick disassembly and assembly.

[0059] The key to the safe launch of the rocket booster of the UAV is that the thrust line of the booster 5 should pass through the center of gravity of the aircraft, or the deviation between the thrust line and the center of gravity is within the required range. Due to manufacturing deviations, the center of gravity of each UAV is different, and the thrust line angle of the booster 5 is also different. Therefore, the angle between the rocket booster 5 and each body 4 is different, resulting in different angles between the shedding device 1 and the rocket booster 5.

[0060] The embodiment of the present invention has the characteristic of strong adaptability. Figure 3 It can be seen that the universal adjustment foot 13 can adjust the relative position with the shedding frame assembly 11 through the nut, so that the bottom of the adjustment foot can firmly support the side of the rocket booster 5, ensuring that the angle between the shedding device 1 and the rocket booster 5 remains unchanged, preventing the booster tail nozzle from tilting up.

[0061] The installation process of the technical solution of the embodiment of the present invention is:

[0062] ① docking the rocket booster 5 with the fuselage 4 and fixing the rocket booster 5;

[0063] ② Manually break open the spring sheet 115 of the shedding frame assembly 11 and place the limit block 114 in the open position;

[0064] ③ Press down the T-shaped joint 33 of the guide device 3, put the front end of the shedding device 1 on the T-shaped joint and rotate it;

[0065] ④ Put the ear piece on the rocket booster adapter ring 2 on the rear end of the shedding device 2, and turn the closing limit block 114 upward to connect the shedding device 2 with the adapter ring 2;

[0066] ⑤ Rotate the nut 132 and the star nut 12 to make the foot seat 131 of the universal adjustment foot 13 contact the side of the rocket booster, and fix the universal adjustment foot 12.

[0067] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and intent of the present invention.

Claims

1. A separation limit device for a rocket booster, comprising a rocket booster, characterized in that: It also includes a guide device, a shedding device and a rocket booster adapter ring, wherein one end of the guide device is fixed to the belly of the UAV fuselage, and the other end is hinged to one end of the shedding device, and the other end of the shedding device is connected to the rocket booster through the rocket booster adapter ring; The guide device includes a base, a torsion spring and a T-shaped joint, wherein the base is connected to the belly of the fuselage; the bottom end of the vertical rod of the T-shaped joint is hinged to the base through a pin, and the axial direction of the cross bar at the head thereof is perpendicular to the central axis of the vertical rod; two torsion springs are respectively mounted on both ends of the pin, and the T-shaped joint is controlled to rebound upwards through the rebound force after the rocket booster falls off; The shedding device comprises a shedding frame assembly, a star nut and a universal adjustment foot, two lugs are arranged in parallel at both ends of the shedding frame assembly, connecting holes with notches are coaxially arranged on the two lugs at one end, the cross bar of the T-joint is hinged to the lug at one end through the connecting hole with the notch, and the two are separated by the notch; a limit assembly is arranged on the two lugs at the other end of the shedding frame assembly, which is connected to the rocket booster adapter ring; the threaded rod of the universal adjustment foot passes through the through hole on the shedding frame assembly, and is tightened and fixed by the star nut; the foot seat of the universal adjustment foot is located above the shedding frame assembly, is pressed and fitted with the circumference of the front end of the rocket booster, and rotates with the position change of the rocket booster; The rocket booster adapter ring is a circular ring structure, which is mounted on the front end of the rocket booster; two radial ears are symmetrically arranged on the outer circumference of the rocket booster adapter ring, which are connected to the limit assemblies on the two lugs at the other end of the shedding frame assembly; The shedding frame assembly includes a front joint, a rear joint and a plate; the plate is a rectangular structure, the front joint and the rear joint are respectively fixed at both ends of the plate, and lugs are provided at the outer ends thereof as connecting parts with the cross bar of the T-joint and the rocket booster adapter ring; The limiting assembly of the falling frame assembly includes a limiting block, a spring sheet, a limiting block screw and a fastening screw; a rectangular notch is opened at the two lug ends at the other end of the falling frame assembly, and one end of the limiting block is hinged to the bottom of the rectangular notch by the limiting block screw; the upper end of the spring sheet is fixed to the upper end of the rectangular notch by the fastening screw, and the lower end has a bending structure; after the free end of the limiting block is rotated to the lower end of the spring sheet, it is positioned by the bending structure of the spring sheet, and a closed connecting hole is formed for connecting with the radial ear pieces at both ends of the rocket booster adapter ring.

2. The separation limit device for a rocket booster according to claim 1, wherein: The guide device also includes a rubber pad fixed to the belly of the fuselage, which is opposite to the vertical rod of the T-shaped joint. When the T-shaped joint rebounds, the rubber pad can avoid damaging the fuselage.

3. The separation limit device for a rocket booster according to claim 1, wherein: The radial cross section of the cross bar of the T-shaped joint is circular, and sections parallel to the axial direction are arranged at both ends of the cross bar.

4. The separation limit device for a rocket booster according to claim 1, characterized in that: The foot seat of the universal adjustment foot can be universally rotated around the ball head at the end of the threaded rod, and the axial position of the universal adjustment foot can be adjusted by adjusting the nut on the threaded rod.

5. The separation limit device for a rocket booster according to claim 1, wherein: The universal adjustment foot is located on one end of the plate close to the rear joint.

6. The separation limit device for a rocket booster according to claim 1, characterized in that: The front joint, the rear joint and the plate are all fixedly connected by screws.

7. An installation method of the separation limiting device for a rocket booster according to any one of claims 1-6, characterized in that The specific steps are as follows: Step 1: dock the rocket booster with the fuselage and secure the rocket booster; Step 2: manually pry open the spring sheet of the shedding frame assembly and place the limit block in the open position; Step 3: Press down the T-shaped joint of the guiding device. At the same time, the connecting holes with notches on both sides at the front end of the detachment device are sleeved on both ends of the cross bar of the T-shaped joint and can rotate; Step 4: Sleeve the limiting components on both sides at the rear end of the detachment device on the radial lugs of the rocket booster adapter ring. Then rotate the limiting blocks upward and close them with the spring plates to connect the detachment device with the rocket booster adapter ring; Step 5: Rotate the nuts and star nuts on the screw rod of the universal adjusting foot so that the footrest of the universal adjusting foot contacts the peripheral surface of the front end of the rocket booster, and then fix the universal adjusting foot.

8. A separation method of the separation limiting device for a rocket booster as described in any one of claims 1-6, characterized in that: First, the rocket booster is docked with the fuselage. When the rocket booster finishes working, it automatically separates from the fuselage under its own gravity and falls downward; then it is pulled by the detachment device and rotates around the cross bar of the T-shaped joint at the same time, gradually falling away from the fuselage; finally, when it rotates until the front end notch of the detachment device is located above and the two ends of the cross bar of the T-shaped joint slide out from the front end notch, the rocket booster separates from the UAV completely together with the detachment device.

Images