A dual-engine booster rocket shedding device for unmanned aerial vehicles

Abstract

The present invention discloses a dual-launch booster rocket shedding device for an unmanned aerial vehicle, which belongs to the field of unmanned aerial vehicle body structure. Two sets of shedding devices are symmetrically arranged on both sides of the unmanned aerial vehicle fuselage, connecting the fuselage and the booster rockets on both sides. The shedding device includes a main mounting interface and a secondary mounting interface. The front mounting seat assembly of the main mounting interface is fixed to the unmanned aerial vehicle fuselage, and is used to be detachably connected to the front joint fixed to the front end of the booster rocket through a ball joint docking form. The rear support assembly of the secondary mounting interface is fixed to the unmanned aerial vehicle fuselage, and is fixedly connected to the rear joint fixed to the rear end of the booster rocket. An explosive bolt is installed in the rear support assembly, which is used to disconnect the connection between the rear support assembly and the rear joint after the booster rocket is completed. The device can ensure the consistency of the left and right installation of the dual-launch rocket, and is convenient to replace, and the connection is stable and reliable. It can effectively avoid the problem of shaking or premature falling off during the operation of the rocket, as well as the difficulty of falling off after the work is completed.

Description

Technical Field

[0001] The invention belongs to the field of unmanned aerial vehicle body structure, and in particular relates to a dual-engine booster rocket shedding device for an unmanned aerial vehicle. Background Art

[0002] For small and medium-sized drones that use landing gear for takeoff and landing, booster rockets are generally installed under the fuselage or on the side to ensure short-distance takeoff and landing requirements. During takeoff and taxiing, the rocket generally works for a few seconds, and the combustion of its internal fuel will generate a large forward thrust. The combustion will produce a cone flame behind the rocket, and it will quickly fall off after completing the work, generating a large forward thrust to enable the drone to quickly taxi forward and take off. The booster rocket shell is large in size and heavy in weight. If the booster rocket shell does not fall off, it will increase aerodynamic resistance on the one hand, and increase the takeoff weight of the drone on the other hand, with a low cost-effectiveness. Therefore, most drones use a rocket shedding design.

[0003] At present, most booster rockets use single-shot rockets, which are installed under the fuselage in a conical mounting port. There are few cases of using double-shot rockets for reference. Double-shot booster rockets are required to be installed symmetrically on the left and right sides or the lower side of the fuselage. Each booster rocket has two installation interfaces with the fuselage, the main and the auxiliary installation interfaces. The forward thrust generated by the rocket is mainly transmitted to the fuselage through the main installation interface. The main and auxiliary installation interfaces together bear the overload generated by the rocket's inertial load, which is much smaller than the thrust. The installation structure must have a reliable connection and good rigidity to prevent the rocket from shaking or falling off during operation, affecting work efficiency, and it must fall off quickly after completing the work so as not to affect the safety of the UAV's taxiing and takeoff.

[0004] In order to ensure the smooth fall of the rocket, the main installation interface of the existing twin-launch rocket drone draws on the installation form of the single-launch rocket. The rocket uses a conical sleeve to fit over the conical end of the fuselage support. The secondary installation interface uses a circular axis arranged along the Y direction of the rocket, and a Y-shaped joint arranged along the X direction of the fuselage to clamp it. In order to ensure that the rocket can fall off smoothly under the action of gravity after the work is completed, the two fork-shaped ears of the Y-shaped joint are in the form of a long upper part and a short lower part. In the test flight, it was found that the lower part of the fork-shaped ear was designed too long, which would make it difficult to fall off. If it was designed too short, it would cause the rocket to shake during work and there would be a risk of falling off. In addition, the rounded corner design of the fork-shaped ear would also affect the falling off (here the X and Y directions use the right-handed coordinate system, the reverse heading is the positive X direction, and the Z axis is vertically upward). And because the booster rocket is a consumable, it needs to be replaced after each use. This structural form also has the problem of being difficult to disassemble and inconvenient to replace.

[0005] In addition, the consistency requirements of the twin-launch rockets are high, otherwise it will have an adverse effect on the attitude of the UAV during taxiing. In order to ensure consistency, in addition to the consistency requirements of the rockets themselves, the installation consistency requirements are also high. The installation design needs to consider the impact of the rocket combustion tail flame and cannot affect the body structure. However, the existing twin-launch rocket main and auxiliary installation interface structures are difficult to ensure consistency requirements. The rocket is prone to shaking when working, affecting the safety of taxiing and takeoff. Summary of the invention

[0006] Technical issues to be solved:

[0007] In order to avoid the shortcomings of the prior art, the present invention provides a twin-engine booster rocket detachment device for unmanned aerial vehicles. The device provides another structure of the main and auxiliary mounting interfaces of the twin-engine rockets that is different from the existing structure, so as to solve the problems of insufficient consistency of the existing twin-engine booster rocket mounting structure, inconvenience in rocket replacement, shaking or premature detachment during operation, and difficulty in detachment after the work is completed.

[0008] The technical solution of the present invention is: a dual-engine booster rocket shedding device for a UAV, which is provided with two groups, symmetrically arranged on both sides of the UAV fuselage, and is used to connect the fuselage and the booster rockets on both sides of the fuselage;

[0009] Each group of the detaching devices includes a main mounting interface and a secondary mounting interface, which are connected to the front end and rear end of the booster rocket respectively, and the front end of the booster rocket faces the nose of the UAV; the main mounting interface includes a front mounting seat assembly and a front joint, and the front mounting seat assembly is fixed to the UAV fuselage, and is used to be detachably connected to the front joint fixed to the front end of the booster rocket through a ball joint docking form; the secondary mounting interface includes a rear support assembly and a rear joint, and the rear support assembly is fixed to the UAV fuselage, located at the rear side of the front mounting seat assembly, and is fixedly connected to the rear joint fixed to the rear end of the booster rocket; an explosive bolt is installed in the rear support assembly, which is used to disconnect the connection between the rear support assembly and the rear joint after the booster rocket is completed.

[0010] A further technical solution of the present invention is: the front mounting seat assembly includes a front mounting seat, a ejector pin, a first spring and a front baffle; the front mounting seat includes a mounting base plate and a vertical plate perpendicular to the mounting base plate, the mounting base plate is fixedly connected to the fuselage of the UAV, and a variable-section through hole is provided on the vertical plate along the axial direction of the UAV, one end of the through hole is a hemispherical hole structure, the middle part is a small hole section, and the other end is a large hole section; the large hole section faces the nose end, and the hemispherical hole is used to cooperate with the spherical surface of the front joint; the ejector pin is coaxially installed in the through hole, one end of which is located in the large hole section, and the other end extends into the hemispherical hole; the first spring is coaxially installed in the large hole section, one end of which contacts with the ejector pin, and the other end contacts with the front baffle; the front baffle is fixedly connected to the vertical plate for limiting the first spring.

[0011] A further technical solution of the present invention is: the side of the vertical plate facing away from the machine head is a conical joint structure, with multiple recessed parts evenly distributed around the circumference to reduce the weight of the vertical plate; reinforcing ribs are provided between the vertical plate and the mounting base to increase the strength of the front mounting seat.

[0012] A further technical solution of the present invention is: the ejector pin is a stepped columnar rotating body, including a rod and a head, the diameter of the head is larger than the diameter of the rod, the head of the ejector pin is located in the large hole section, the rod of the ejector pin passes through the small hole section and extends into the hemispherical hole, the steps of the large hole section and the small hole section face the head of the ejector pin to form an axial limit; the head of the ejector pin is against the first spring on the side facing away from the rod.

[0013] A further technical solution of the present invention is: the front joint body is an L-shaped structure, a side plate at one end thereof is welded and fixed to the front end outer diameter wall of the booster rocket, and a ball head with a spherical structure is provided at the end of the side plate at the other end thereof, the ball head faces the nose of the UAV, contacts the inner wall surface of the hemispherical hole of the front mounting seat, and abuts against the end of the ejector pin located in the hemispherical hole; when the booster rocket is in the installation state, the ball head of the front joint squeezes the ejector pin, and the first spring is in a compressed state.

[0014] A further technical solution of the present invention is: the rear support assembly includes a rear support, an explosive bolt, a sleeve, a second spring and a screw; the rear support is fixed to the fuselage, one end of the explosive bolt is fixedly connected to the rear support, the other end of the explosive bolt is provided with an external thread, and a fracture surface is provided near the external thread; the sleeve passes through the mounting plate of the rear joint, one end of the sleeve is screwed with the external thread of the explosive bolt, and the other end is coaxially installed with a screw; the second spring is sleeved on the outer diameter of the sleeve, one end of which is against the mounting plate of the rear joint, and the other end is against the head of the screw, and the second spring is in a compressed state.

[0015] A further technical solution of the present invention is: the two ends of the rear support are sunken for fixed connection with the fuselage, the middle part of the rear support is convex, forming a mounting plate of the rear support for installing explosion-proof bolts; an inner groove is provided on the outer side of the mounting plate of the rear support, and a mounting through hole is provided in the middle of the inner groove; the end of the explosive bolt and the fixed end of the rear support is its signal access end, the signal access end penetrates into the mounting through hole of the rear support, and the bottom plate of the explosive bolt is embedded in the inner groove; the outer baffle is coaxially sleeved on the explosive bolt, located on the outer side of the bottom plate of the explosive bolt, and the outer baffle and the mounting plate of the rear support are fixedly connected by screws, which is used to fix the explosion bolt and the rear support.

[0016] A further technical solution of the present invention is: the signal access end of the explosive bolt is electrically connected to the explosive bolt electric control box located in the fuselage through a control cable, and the explosive bolt electric control box is used to control the explosive bolt to break at the fracture surface.

[0017] A further technical solution of the present invention is: the rear joint body is an L-shaped structure, one end side plate of which is welded and fixed to the rear end outer diameter wall of the booster rocket, and the other end side plate of which is a mounting plate of the rear joint for cooperating and connecting with the rear support assembly.

[0018] A further technical solution of the present invention is: the main mounting interface and the auxiliary mounting interface maintain the heading angle between the booster rocket and the UAV at 5°, so that the distance between the rear end of the booster rocket and the UAV is greater than the distance between the front end of the booster rocket and the UAV, which is used to prevent the booster rocket tail flame area from affecting the fuselage structure.

[0019] Beneficial Effects

[0020] The beneficial effects of the present invention are as follows: the present invention is a dual-engine booster rocket shedding device for unmanned aerial vehicles, which is used for small and medium-sized unmanned aerial vehicles that take off and land with landing gear. By matching the mounting structures on both sides of the unmanned aerial vehicle fuselage and the mounting structures of the booster rocket, a main mounting interface and a secondary mounting interface symmetrical on both sides of the unmanned aerial vehicle are formed. The secondary mounting interface of the booster rocket is fixed by mechanical connection, and the front mounting interface is fixed by concave-convex contact spherical surface matching. The connection is reliable and has good rigidity. The rocket cannot fall naturally in the taxiing state before the shutdown and the booster rocket work. The adopted structural form can quickly transfer the forward thrust generated by the booster rocket when working to the fuselage structure, and can prevent the rocket from shaking or falling off prematurely when working, affecting the work efficiency.

[0021] When the booster rocket falls off after completing its work, the explosive bolt breaks off from the fracture surface, the first spring of the front mounting interface pushes the booster rocket backwards, and the second spring of the rear mounting interface pushes the booster rocket outwards. The rocket will fall downward again under the action of gravity, ensuring that it falls off smoothly. The outward push will prevent it from hitting the fuselage structure when it falls off, further improving the reliability of the fall-off.

[0022] The structure of the present invention has high installation accuracy, can ensure the consistency of the left and right of the double rockets, and is convenient and quick to disassemble and replace. The booster rocket can be quickly replaced and reset by removing the remaining explosive bolts, and has good interchangeability. By installing the booster rocket with a small tilt angle, the influence of the rocket combustion tail flame on the fuselage structure is avoided, and the safety is good. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a schematic diagram of the overall installation of a dual-engine booster rocket shedding device for a UAV;

[0024] Figure 2 This is a schematic diagram of the installation of the front and rear joints on the booster rocket;

[0025] Figure 3 This is an exploded view of the front mounting assembly;

[0026] Figure 4 for Figure 1 AA section view in;

[0027] Figure 5 This is the three-view drawing of the front mounting seat structure;

[0028] Figure 6 for Figure 5 CC section view in;

[0029] Figure 7 This is an exploded view of the rear support assembly;

[0030] Figure 8 for Figure 1 BB section view in;

[0031] Fig. 9 is a schematic diagram of the rear support structure;

[0032] Fig.10 It is the three-view drawing of the explosive bolt structure;

[0033] Fig.11 It is a schematic diagram of the installation position relationship of the sleeve, the second spring and the screw;

[0034] Fig.12 It is a schematic diagram of the sleeve structure.

[0035] Explanation of the reference numerals: 1. fuselage, 2. booster rocket, 3. front mounting seat assembly, 31. front mounting seat, 311. mounting base plate, 312. vertical plate, 313. through hole, 314. reinforcing rib, 315. baffle mounting groove, 32. ejector pin, 321. rod, 322. head, 33. first spring, 34. front baffle, 4. front joint, 41. ball head, 5. rear support assembly, 51. rear support, 511 mounting plate of support, 512. inner groove, 513. mounting through hole, 514. edge strip, 52. explosive bolt, 521. external thread, 522. fracture surface, 523. signal access terminal, 524. bottom plate, 53. sleeve, 54. second spring, 55. screw, 56. external baffle, 6. rear joint, 61. mounting plate of rear joint, 7. fuselage skin. DETAILED DESCRIPTION

[0036] The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, but should not be construed as limiting the present invention.

[0037] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0038] See also Figure 1 , using a right-hand coordinate system, the reverse heading is the positive X direction, and the Z axis is vertically upward. This embodiment provides a dual-engine booster rocket shedding device for a drone. The device is provided with two groups, which are symmetrically arranged on both sides of the drone fuselage 1, and are used to symmetrically install dual-engine booster rockets 2 on both sides of the drone fuselage. Each group of devices is corresponding to a booster rocket 2. Each group of booster rocket shedding devices includes a main installation interface and a secondary installation interface. The main installation interface is connected to the front end of the booster rocket 2, and the secondary installation interface is connected to the rear end of the booster rocket 2. The front end of the booster rocket 2 faces the nose of the drone, and its rear end faces the tail. Some components in the main installation interface and the secondary installation interface are fixed to the fuselage 1, and some components are fixed to the booster rocket 2. They cooperate with each other to realize the detachable fixed connection between the drone fuselage 1 and the booster rocket 2.

[0039] The main installation interface includes a front mounting seat assembly 3 and a front joint 4. The front mounting seat assembly 3 is fixed to the UAV 1, and the front joint 4 is fixed to the front end of the booster rocket 2. The mounting seat assembly 3 and the front joint 4 are detachably connected through a ball joint.

[0040] For details, see Figure 3 The front mounting seat assembly 3 includes a front mounting seat 31 , a ejector pin 32 , a first spring 33 and a front baffle 34 .

[0041] See also Figure 3-6The front mounting seat 31 is a frame plate structure, including a mounting base plate 311 and a vertical plate 312 perpendicular to the mounting base plate 311, and two reinforcing ribs 314 located on both sides of the mounting base plate 311, connecting the mounting base plate 311 and the vertical plate 312. The reinforcing ribs 314 are used to strengthen the supporting rigidity of the mounting seat 31. The mounting base plate 311 of the front mounting seat 31 is fixedly connected to the UAV fuselage 1. The vertical plate 312 is a conical head structure, and the side facing the UAV nose is a straight surface perpendicular to the mounting base plate 311, and the side facing away from the nose is a conical joint. A plurality of recessed parts are evenly distributed around the conical joint to reduce the weight of the vertical plate 312, and a rib plate is formed between two adjacent recessed parts to strengthen the strength of the conical joint. A variable-section through hole 313 is provided in the center of the vertical plate 312 along the axial direction of the UAV through its conical head to form a docking hole with the front joint 4. The axis of the variable cross-section through hole 313 is coaxial with the heading. The through hole 313 is a hemispherical hole structure at one end facing the tail, with a small hole section in the middle and a large hole section at the other end. The diameter of the large hole section is larger than that of the small hole section, and the large hole section faces the nose end of the drone. The hemispherical hole is used to cooperate with the spherical surface of the front joint 4.

[0042] The ejector pin 32 is a stepped columnar rotating body installed in the through hole 313. The ejector pin 32 includes a rod portion 321 and a head portion 322. The diameter of the head portion 322 is larger than the diameter of the rod portion 321. The head portion 322 of the ejector pin 32 is located in the large hole section. The rod portion 321 of the ejector pin 32 passes through the small hole section of the through hole 313 and extends into the hemispherical hole. The steps between the large hole section and the small hole section face the head portion 322 of the ejector pin 32 to form an axial limit.

[0043] The first spring 33 is coaxially installed in the large hole section, one end of which contacts the ejector pin 32, and the other end is limited by the front baffle 34. Specifically, the head 322 of the ejector pin 32 contacts the first spring 33 on the side facing away from the rod 321, and a concave baffle installation groove 315 is provided at the end of the large hole section facing the machine head end. The front baffle 34 is fixedly installed in the installation groove 315 by three screws evenly distributed around the circumference, and the end surface of the front baffle 34 facing the large hole section contacts the first spring 33 to form an axial limit for it.

[0044] See also Figure 2 , 4 The main body of the front joint 4 is an L-shaped structure, and the side plate at one end of the L-shape is welded and fixed to the front outer diameter wall of the booster rocket 2 through a base fixed at its end, and the side plate at the other end faces the front end of the booster rocket 2, and a ball head 41 with a spherical structure is provided at the end, and the ball head 41 faces the nose of the drone 1. During installation, the ball head 41 contacts the inner wall surface of the hemispherical hole of the front mounting seat 31, and abuts against the end of the ejector pin 32 located in the hemispherical hole, thereby squeezing the ejector pin 32 and putting the first spring 33 in a compressed state. Since the matching part of the variable-section through hole 313 and the ball head 41 is an open structure of the hemispherical hole, the size matches the ball head 41, which facilitates the installation and separation of the ball head 41.

[0045] See also Figure 1 , 7 8. The secondary mounting interface includes a rear support assembly 5 and a rear joint 6. The rear support assembly 5 is fixed to the UAV fuselage 1, located at the rear side of the front mounting assembly 3, and fixedly connected to the rear joint 6 fixed to the rear end of the booster rocket 2.

[0046] Specifically, the rear support assembly 5 includes a rear support 51, an explosion-proof bolt 52, a sleeve 53, a second spring 54, a screw 55 and an outer baffle 56. The rear support 51 is fixed to the fuselage 1, and is used to support and install other components of the rear support assembly 5. The two ends of the rear support 51 are sunken, and the middle part is convex, forming a π-shaped structure. The two ends are sunken to form an outer edge strip 514, and the outer edge strip 514 is evenly distributed with mounting screw holes, which are used to pass fasteners to fix the outer edge strip 514 to the fuselage skin 7; the middle convex part of the rear support 51 is the mounting plate 511 of the rear support, which is used to install the explosion-proof bolt 52. An inner groove 512 is provided on the outer side of the mounting plate 511 of the rear support, and a mounting through hole 513 is provided in the middle of the inner groove 512. The mounting through hole 513 passes through the mounting plate 511 of the rear support, and is used to penetrate the signal access end of the explosion bolt 52. A through hole corresponding to the mounting through hole 513 is provided on the fuselage skin 7 and is used for passing the control cable of the explosive bolt 52 .

[0047] See also Figure 8 , 10 One end of the explosive bolt 52 is fixedly connected to the rear support 51, and the other end is provided with an external thread 521, and an annular fracture surface 522 is provided near the external thread 521. The end of the explosive bolt 52 fixedly connected to the rear support 51 is its signal access end 523, and the bottom plate 524 of the explosive bolt 52 is close to the signal access end 523. The signal access end 523 penetrates into the mounting through hole 513 of the rear support 51, and the bottom plate 524 of the explosive bolt 52 is embedded in the inner groove 512. The axial thickness of the bottom plate 524 is the same as the inner concave depth of the inner groove 512. The outer baffle 56 is coaxially sleeved on the explosive bolt 52 and is located on the outside of the bottom plate 524 of the explosive bolt. The outer baffle 56 is fixedly connected to the mounting plate 511 of the rear support by four screws evenly distributed around the circumference, so that the explosive bolt 52 and the rear support 51 are fixedly connected, and the outer baffle 56 and the bottom surface of the inner groove 512 form an axial limit for the explosive bolt 52. The signal access terminal 523 of the explosive bolt 52 is electrically connected to the explosive bolt electronic control box located in the fuselage through a control cable. The explosive bolt electronic control box is used to control the explosive bolt 52 to break at the fracture surface 522, so as to disconnect the connection between the rear support assembly 5 and the rear joint 6 after the booster rocket 2 is completed.

[0048] See also Figure 8 , 11The sleeve 53 is threadedly connected with the external thread end of the explosive bolt 52, and cooperates with the second spring 54 and the screw 55 to realize the fixed connection between the explosive bolt 52 and the rear joint 6. Specifically, the main body of the sleeve 53 is a cylindrical structure, and a threaded blind hole is provided at both ends along its axis, which is used to connect the explosive bolt 52 and the screw 55 respectively. The sleeve 53 passes through the mounting plate 61 of the rear joint 6, one end of which is coaxially screwed with the external thread 521 of the explosive bolt 52, and the other end is coaxially installed with the screw 55. The second spring sleeve 54 is installed on the outer diameter of the sleeve 53, one end of the second spring sleeve 54 is against the mounting plate 61 of the rear joint, and the other end is against the head of the screw 55, and the second spring 54 is in a compressed state. The screw 55 is a special screw, including a screw rod and a screw head. The screw rod is threaded with the sleeve 53, and the screw head is an external hexagonal structure for easy operation. The end face of the screw head facing the screw rod is provided with an axial boss along the end face, which is convenient for the installation of the second spring 54 and prevents the second spring 54 from sliding and deflecting in the radial direction. Correspondingly, an outer wall of the sleeve 53 facing the mounting end of the screw 55 is provided with an outer hexagonal structure to facilitate the installation of the sleeve 53 .

[0049] See also Figure 2 , 7 The main body of the rear joint 6 is an L-shaped structure, one end side plate of which is welded and fixed to the rear end outer diameter wall of the booster rocket 2 through its bottom welding seat, and the other end side plate is the mounting plate 61 of the rear joint, and the mounting plate 61 faces the front end of the booster rocket 2. A through hole is provided on the mounting plate 61 perpendicular to the mounting plate, which is used to pass the sleeve 53, and the sleeve 53 is in clearance with the through hole on the mounting plate 61. When the sleeve 53 is installed, it passes through the through hole of the mounting plate 61 close to the side of the booster rocket 2 and is connected to the explosive bolt 52.

[0050] See also Figure 1 , 2 , the installation height of the rear joint 6 is higher than the installation height of the front joint 4. When the booster rocket 2 and the fuselage 1 are installed, the main installation interface and the auxiliary installation interface jointly maintain the heading angle between the booster rocket 2 and the UAV 1 at 5°, so that the distance between the rear end of the booster rocket 2 and the UAV 1 is greater than the distance between the front end of the booster rocket 2 and the UAV 1, thereby preventing the tail flame area of ​​the booster rocket 2 from affecting the fuselage structure.

[0051] When the booster rocket 2 is working, it generates a forward thrust, and the ball head 41 of the front joint 4 on the booster rocket 2 squeezes the ejector pin 32 forward, causing the first spring 33 to be in a compressed state. The forward thrust generated by the rocket causes the ball head 41 to contact the arc-shaped concave surface of the hemispherical hole in the conical joint of the front mounting seat 31, and is in a forward pressed state. The thrust is transmitted to the front mounting seat 31 through the contact surface, and is transmitted to the UAV fuselage structure through its mounting base plate 311. The forward overload generated by the gravity of the booster rocket 2 is much smaller than the thrust, and is borne by the front mounting seat assembly 3 and the rear support assembly 5 at the same time. When the booster rocket 2 stops working, the first spring 33 generates a backward reaction force and returns to a free state, pushing the ball head 41 of the front joint 4 on the booster rocket 2 backward. When the booster rocket 2 stops working, the UAV control end sends a command to control the explosive bolt electronic control box, and the embedded explosive in the explosive bolt 52 will detonate, causing it to explode from the bottom. Figure 8 The second spring 54 on the sleeve 53 generates an outward reaction force (away from the fuselage 1) to return to a free state, as shown in FIG. Figure 8 As shown, the structure outside the fracture surface 522 of the explosive bolt 52 at the entire secondary mounting interface moves outward with the booster rocket 2, and then falls downward under the action of gravity. At this time, the portion inside the fracture surface 522 of the explosive bolt 52 (i.e., the portion close to the fuselage 1 and fixed to the rear support 51) together with the outer baffle 56 and the rear support 51 still remains on the fuselage 1.

[0052] The booster rocket 2 and the explosive bolt 52 are both consumables and must be replaced for each takeoff and landing. After the booster rocket 2 falls off, the part within the cross section of the explosive bolt 52 will remain on the fuselage. When replacing it with a new one, first remove the remaining part, unplug the connection plug on the explosive bolt electric control box, disconnect the control cable of the explosive bolt 52 from the wiring cable, remove the four screws connecting the outer baffle 56 and the mounting plate 511 of the support, take out the explosive bolt 52, replace it with a new one, connect the control cable, and plug in the plug; then install the new booster rocket 2, align the ball head 41 of the front joint 4 with the hemispherical hole of the front mounting seat 31, insert the sleeve 53 equipped with the second spring 54 and the screw 55 from the booster rocket side into the through hole of the mounting plate 61 of the rear joint, and then screw the internal thread at the inner end of the sleeve 53 with the external thread 521 end of the explosive bolt 52, and the replacement of the booster rocket 2 is completed.

[0053] The front mounting seat assembly 3 and the rear support assembly 5 on the left and right sides of the fuselage 1 of the present invention are convenient for controlling the relative position accuracy of the front mounting seats 31 and the rear support 51 on the left and right sides during installation. The distance tolerance between the front mounting seats 31 and the rear support 51 on the left and right sides is consistent and has high precision, and is consistent with the distance tolerance of the front and rear joints of the booster rocket 2. After installation, the consistency of the main and auxiliary mounting interfaces on the left and right sides is high, which effectively ensures the installation consistency of the twin-launch booster rocket.

[0054] 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 purpose of the present invention.

Claims

1. A dual-engine booster rocket shedding device for a UAV, with two sets, symmetrically arranged on both sides of the UAV fuselage, used to connect the fuselage and the booster rockets on both sides of the fuselage; It is characterized in that Each group of the detaching devices includes a main mounting interface and a secondary mounting interface, which are connected to the front end and rear end of the booster rocket respectively, and the front end of the booster rocket faces the nose of the UAV; the main mounting interface includes a front mounting seat assembly and a front joint, and the front mounting seat assembly is fixed to the UAV, and is used to be detachably connected to the front joint fixed to the front end of the booster rocket through a ball joint docking form; the secondary mounting interface includes a rear support assembly and a rear joint, and the rear support assembly is fixed to the fuselage, located at the rear side of the front mounting seat assembly, and is fixedly connected to the rear joint fixed to the rear end of the booster rocket; an explosive bolt is installed in the rear support assembly, which is used to disconnect the connection between the rear support assembly and the rear joint after the booster rocket is completed.

2. The UAV dual-engine booster rocket shedding device according to claim 1 is characterized in that: The front mounting seat assembly includes a front mounting seat, an ejector pin, a first spring and a front baffle; the front mounting seat includes a mounting base plate and a vertical plate perpendicular to the mounting base plate, the mounting base plate is fixedly connected to the fuselage of the UAV, and a variable-section through hole is provided on the vertical plate along the axial direction of the UAV, one end of the through hole is a hemispherical hole structure, the middle part is a small hole section, and the other end is a large hole section, the large hole section faces the nose end, and the hemispherical hole is used to cooperate with the spherical surface of the front joint; the ejector pin is coaxially installed in the through hole, one end of which is located in the large hole section, and the other end extends into the hemispherical hole; the first spring is coaxially installed in the large hole section, one end of which contacts with the ejector pin, and the other end contacts with the front baffle; the front baffle is fixedly connected to the vertical plate and used to limit the first spring.

3. The UAV dual-engine booster rocket shedding device according to claim 2 is characterized in that: The side of the vertical plate facing away from the machine head is a conical joint structure with multiple recessed parts evenly distributed around the circumference to reduce the weight of the vertical plate; reinforcing ribs are provided between the vertical plate and the mounting base to increase the strength of the front mounting seat.

4. The UAV dual-engine booster rocket shedding device according to claim 2 is characterized in that: The ejector pin is a stepped columnar rotating body, including a rod and a head, wherein the diameter of the head is larger than the diameter of the rod, the head of the ejector pin is located in the large hole section, the rod of the ejector pin passes through the small hole section and extends into the hemispherical hole, and the steps of the large hole section and the small hole section face the head of the ejector pin to form an axial limit; the head of the ejector pin is against the first spring on the side facing away from the rod.

5. The UAV dual-engine booster rocket shedding device according to claim 2 is characterized in that: The front joint body is an L-shaped structure, with a side plate at one end welded and fixed to the front end outer diameter wall of the booster rocket, and a ball head with a spherical structure is provided at the end of the side plate at the other end. The ball head faces the nose of the UAV, contacts the inner wall surface of the hemispherical hole of the front mounting seat, and abuts against the end of the ejector pin located in the hemispherical hole; when the booster rocket is in the installation state, the ball head of the front joint squeezes the ejector pin, and the first spring is in a compressed state.

6. The UAV dual-engine booster rocket shedding device according to claim 1 is characterized in that: The rear support assembly includes a rear support, an explosive bolt, a sleeve, a second spring and a screw; the rear support is fixed to the fuselage, one end of the explosive bolt is fixedly connected to the rear support, the other end of the explosive bolt is provided with an external thread, and a fracture surface is provided near the external thread; the sleeve passes through the mounting plate of the rear joint, one end of the sleeve is screwed with the external thread of the explosive bolt, and the other end is coaxially installed with a screw; the second spring is sleeved on the outer diameter of the sleeve, one end of which is abutted against the mounting plate of the rear joint, and the other end is abutted against the head of the screw, and the second spring is in a compressed state.

7. The UAV dual-engine booster rocket shedding device according to claim 6 is characterized in that: The two ends of the rear support are sunken for fixed connection with the fuselage, and the middle part of the rear support is convex to form a mounting plate of the rear support for installing explosion-proof bolts; an inner groove is provided on the outer side of the mounting plate of the rear support, and a mounting through hole is provided in the middle of the inner groove; the end of the explosive bolt and the fixed end of the rear support is its signal access end, the signal access end penetrates into the mounting through hole of the rear support, and the bottom plate of the explosive bolt is embedded in the inner groove; the outer baffle is coaxially sleeved on the explosive bolt, located on the outer side of the bottom plate of the explosive bolt, and is fixedly connected to the outer baffle and the mounting plate of the rear support by screws, which is used to fix the explosion bolt and the rear support.

8. The UAV dual-engine booster rocket shedding device according to claim 7 is characterized in that: The signal access end of the explosive bolt is electrically connected to an explosive bolt electric control box located in the fuselage through a control cable, and the explosive bolt electric control box is used to control the explosive bolt to break at the fracture surface.

9. The UAV dual-engine booster rocket shedding device according to claim 6 is characterized in that: The rear joint body is an L-shaped structure, one end side plate of which is welded and fixed to the rear end outer diameter wall of the booster rocket, and the other end side plate of which is the mounting plate of the rear joint for connecting with the rear support assembly.

10. The UAV dual-engine booster rocket shedding device according to claim 1, characterized in that: The main mounting interface and the auxiliary mounting interface maintain the heading angle between the booster rocket and the UAV at 5°, so that the distance between the rear end of the booster rocket and the UAV is greater than the distance between the front end of the booster rocket and the UAV, which is used to prevent the tail flame area of ​​the booster rocket from affecting the fuselage structure.

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