Pop-up booster mounting and separating mechanism

Abstract

The utility model provides a pop-up booster installation and separation mechanism. The pop-up booster installation and separation mechanism comprises a booster body and a push rod, the front support is arranged at the front end outside the booster body; the rear support is arranged at the rear end outside the booster body; the front connecting seat is arranged on the front support, and the front connecting seat is used for being mounted on an aircraft; the rear connecting seat is arranged on the rear support, and the rear connecting seat is used for being installed on the aircraft; the separation bolt penetrates through the front connecting seat and the front support to connect the front connecting seat with the front support, and the separation bolt is used for connecting the aircraft to separate the front connecting seat from the front support; the elastic piece is arranged on the rear support and installed between the rear support and the rear connecting base in a compressed mode, so that the rear support is subjected to acting force facing the tail end of the booster body. The problem that separation power of the booster is insufficient when gravity and aerodynamic force are insufficient can be solved, after the separation bolt is opened, the elastic piece releases energy, separation of the booster and the aircraft is assisted, the pressing plate structure is easy to install, and extra driving force is not needed.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft boosters, and in particular relates to an installation and separation mechanism of a pop-up booster. Background Art

[0002] This application is a technical improvement of the application number "202421117523X" and the name "A booster installation and separation mechanism". In the prior art, when the booster is separated, the aircraft is in a high-speed flight state, and coupled with the influence of the external environment, the attitude of the aircraft deviates from the ideal state. Therefore, there is a probability that the rear connection seat and the rear support are not separated smoothly, which will seriously affect the flight trajectory of the aircraft, causing deviations or even crashing the aircraft. Summary of the invention

[0003] In view of this, an object of the present invention is to provide a mounting and separation mechanism for a pop-up booster, so as to solve the technical problem that the booster may not separate smoothly when leaving the aircraft.

[0004] The present application proposes a pop-up booster installation and separation mechanism, comprising:

[0005] Booster body;

[0006] A front support, which is arranged at the front end of the booster body;

[0007] A rear support, which is arranged at the rear end of the booster body;

[0008] A front connecting seat, which is arranged on the front support, and the front connecting seat is used to be installed on the aircraft;

[0009] A rear connecting seat, which is arranged on the rear support, and the rear connecting seat is used to be installed on the aircraft;

[0010] a separation bolt, which passes through the front connecting seat and the front support to connect the front connecting seat and the front support, and the separation bolt is used to connect the aircraft and can separate the front connecting seat and the front support;

[0011] An elastic member is arranged on the rear support, and the elastic member is compressed and installed between the rear support and the rear connecting seat, so that the rear support is subjected to a force acting toward the rear end of the booster body.

[0012] Furthermore, the front support comprises:

[0013] A first mounting portion connected to the booster body;

[0014] The first docking portion is vertically arranged with respect to the first mounting portion, and the first mounting portion is provided with a first through hole coaxial with the booster body.

[0015] Furthermore, the front connecting seat comprises:

[0016] a second mounting portion, which is used to be connected to the aircraft;

[0017] The second docking portion is provided with a guide cavity for accommodating the first docking portion of the front support, and the second docking portion is provided with a second through hole coaxial with the booster body.

[0018] Furthermore, the rear support comprises:

[0019] a third mounting portion connected to the booster body;

[0020] A third docking portion, which is disposed on the third mounting portion, is cylindrical, is parallel to the axis of the booster body, and is used for slidably mounting the rear connecting seat;

[0021] A pressure plate is arranged on one end of the third docking portion facing the rear end of the booster body, and the pressure plate is connected to the elastic member.

[0022] Furthermore, a limiting rod is vertically connected to the pressing plate to be used for installing the elastic member and limiting the position of the elastic member.

[0023] Furthermore, the elastic member is a spring, a first end of which is connected to the pressure plate and is coaxially sleeved on the limiting rod.

[0024] Furthermore, the rear support further comprises:

[0025] A screw passes through the pressing plate and is connected to the third docking portion.

[0026] Furthermore, the rear connecting seat comprises:

[0027] a fourth mounting portion, which is used to be connected to the aircraft;

[0028] The fourth docking portion is provided with a guide hole for slidably mounting the third docking portion.

[0029] Furthermore, the separation bolt is fixed to the front connection seat via a bolt card;

[0030] The bolt card is provided with a groove matching the appearance of the separation bolt, and the bolt card is fixed on the front connecting seat.

[0031] Furthermore, an elastic member is provided between the front support and the front connecting seat.

[0032] The beneficial effects of this application are:

[0033] The present application provides a pop-up booster installation and separation mechanism, which can solve the problem of insufficient booster separation power when gravity and aerodynamic force are insufficient by disposing an elastic member between the booster body and the connecting seat. After the separation bolt is opened, the elastic member releases energy to assist in the separation of the booster from the connecting seat, i.e., the aircraft. The pressure plate structure is easy to install and does not require additional driving force. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The above and other objects, features and advantages of the present invention will become more apparent through the following description of the embodiments of the present invention with reference to the accompanying drawings.

[0035] Figure 1 It is a schematic diagram of the structure of the booster after installation according to the embodiment of the utility model;

[0036] Figure 2 This is a schematic diagram of the front structure of the booster after installation according to an embodiment of the utility model;

[0037] Figure 3 It is a schematic diagram of the front support structure provided according to an embodiment of the utility model;

[0038] Figure 4 It is a schematic diagram of the structure of the front connecting seat provided according to an embodiment of the utility model;

[0039] Figure 5 It is a schematic diagram of the bolt card structure provided according to an embodiment of the utility model;

[0040] Figure 6 It is a schematic diagram of the rear support structure provided according to an embodiment of the utility model;

[0041] Figure 7 It is a schematic diagram of the structure of the rear connecting seat provided according to an embodiment of the utility model;

[0042] Figure 8 It is a schematic diagram of the pressing plate structure provided according to an embodiment of the utility model;

[0043] Fig. 9 It is a partial cross-sectional view of the rear support and the rear connecting seat in the installed state according to the embodiment of the utility model.

[0044] Among them, 1-separation bolt, 2-front connecting seat, 3-bolt card, 4-front support, 5-rear connecting seat, 6-rear support, 7-booster body, 8-pressure plate, 9-spring;

[0045] 21 - second mounting portion, 22 - second docking portion, 23 - guide cavity, 24 - second through hole;

[0046] 31-groove;

[0047] 41-first mounting portion, 42-first docking portion, 43-first through hole;

[0048] 51-fourth mounting portion, 52-fourth docking portion, 53-guide hole;

[0049] 61-third mounting portion, 62-third docking portion, 63-screw;

[0050] 81 - limiting rod, 82 - third through hole. DETAILED DESCRIPTION

[0051] Various embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. In each of the accompanying drawings, the same elements are represented by the same or similar reference numerals. For the sake of clarity, the various parts in the accompanying drawings are not drawn to scale.

[0052] refer to Figures 1 to 9 The present application provides a booster installation and separation mechanism, comprising: a booster body 7; a front support 4, which is arranged at the front end outside the booster body 7; a rear support 6, which is arranged at the rear end outside the booster body 7 and is parallel to the axis of the front support 4; a front connecting seat 2, which is arranged on the front support 4, and the front connecting seat 2 is used to be installed on an aircraft; a rear connecting seat 5, which is arranged on the rear support 6, and the rear connecting seat 5 is used to be installed on an aircraft; a separation bolt 1, which passes through the front connecting seat 2 and the front support 4 to connect the front connecting seat 2 and the front support 4, and the separation bolt 1 is used to connect the aircraft and can separate the front connecting seat 2 and the front support 4.

[0053] The front support 4 is fixedly connected to the front connecting seat 2 via the separation bolt 1, and the rear support 6 is slidably connected to the rear connecting seat 5. The separation bolt 1 is an explosive bolt, which explodes and separates under command, thereby separating the front support 4 from the front connecting seat 2, and the rear support 6 from the rear connecting seat 5 by sliding, so as to realize the automatic separation of the booster and the aircraft. The elastic member is arranged on the rear support 6, and the elastic member is compressed and installed between the rear support 6 and the rear connecting seat 5, so that the rear support 6 is subjected to a force toward the rear end of the booster body 7. In the installed state, the elastic member is compressed to store energy. After the separation bolt 1 is opened, the elastic member releases energy and acts on the rear support 6 and the rear connecting seat 5 respectively, that is, the booster is separated from the aircraft.

[0054] refer to Figures 1 to 5 In this embodiment, the front support 4 includes: a first mounting portion 41, which is connected to the booster body 7; a first docking portion 42, which is vertically arranged with the first mounting portion 41, and a first through hole 43 coaxial with the booster body 7 is opened on the first mounting portion 41.

[0055] The front connecting seat 2 includes: a second mounting portion 21, which is used to connect to the aircraft; a second docking portion 22, which is provided with a guide cavity 23 for accommodating the first docking portion 42 of the front support 4, and a second through hole 24 coaxial with the booster body 7 is opened on the second docking portion 22.

[0056] The front support 4 is fixed to the booster body 7, and the guide cavity 23 of the front connecting seat 2 can slidably install the first docking portion 42 of the front support 4. The first through hole 43 is coaxial with the second through hole 24, and the hole diameters are consistent. The separation bolt 1 penetrates the first through hole 43 and the second through hole 24 at the same time, fixing the front support 4 and the front connecting seat 2 together, that is, the booster is installed on the aircraft.

[0057] In this embodiment, the separation bolt 1 is fixed to the front connection seat 2 via a bolt card 3; a groove 31 matching the shape of the separation bolt 1 is provided on the bolt card 3, and the bolt card 3 is fixed to the front connection seat 2. It can be understood that the bolt card 3 is fixed to the front connection seat 2, and the groove 31 matching the shape of the separation bolt 1 on the bolt card 3 can realize the circumferential fixation of the bolt, so that the separation bolt 1 is firmly fixed to the front connection seat 2.

[0058] In this embodiment, reference Figure 1 , Figure 6 , Figure 7 , Figure 8 and Fig. 9 The rear support 6 includes: a third mounting portion 61, which is connected to the booster body 7; a third docking portion 62, which is arranged on the third mounting portion 61, the third docking portion 62 is cylindrical, the third docking portion 62 is parallel to the axis of the booster body 7, and is used for slidingly mounting the rear connection seat 5; a pressure plate 8, which is arranged on one end of the third docking portion 62 facing the tail end of the booster body 7, and the pressure plate 8 is connected to the elastic member. It should be understood that when the booster is separated during the flight of the aircraft, the elastic member is elastic. When releasing energy, in order to prevent the elastic member from damaging the aircraft, the elastic member is fixedly connected to the pressure plate 8, that is, the elastic member is fixedly connected to the booster body 7.

[0059] A limit rod 81 is arranged perpendicularly to the pressure plate 8, which is used to install and limit the elastic member. In this embodiment, the elastic member is a spring 9. After the spring 9 is compressed, it will deform radially. The spring 9 is coaxially sleeved on the limit rod 81. The limit rod 81 can limit the radial direction of the spring 9, so that the spring 9 completes the compression energy storage and smoothly completes the energy release. It can be understood that the length of the limit rod 81 is less than the length of the spring 9 in the natural state.

[0060] The rear support 8 further includes a screw 63 , which can fix the pressure plate to the third docking portion 62 . It should be understood that a threaded hole is provided at one end of the third docking portion 62 for installing the screw 63 .

[0061] During installation, first install the booster body 7 onto the aircraft, install the separation bolt 1, and then install the spring 9 and the pressure plate 8. By screwing the screw 63, the pressure plate 8 compresses the spring 9 to achieve energy storage of the spring 9, which is easy to install and more convenient and labor-saving.

[0062] The pressing plate 8 is provided with a third through hole 82 for the screw 63 to pass through.

[0063] As an optional embodiment, a limiting hole can be opened on the third mounting portion 61 for one end of the limiting rod 81 to pass through the third mounting portion 61. The advantage is that it can not only relatively fix the pressure plate 8 and the third docking portion 61, but also adjust the compression energy storage of the spring 9.

[0064] The rear connection seat 5 includes: a fourth mounting portion 51, which is used to be connected to the aircraft; a fourth docking portion 52, which is provided with a guide hole 53 for slidably mounting the third docking portion 62, and the guide hole 53 is used to limit the radial direction of the booster. In this embodiment, the lower end of the guide hole 53 is open to avoid the connection between the third docking portion 62 and the third mounting portion 61.

[0065] It should be understood that the rear support 6 and the front support 4 are both fixed on the booster body 7, and the guide hole 53 of the fourth docking portion 52 can slidably mount the third docking portion 62, so that the booster body 7 can move in its axial direction.

[0066] When the separation command is issued, the separation bolt 1 is damaged and the front connecting seat 2 is separated from the front support 4. However, under the action of the guide cavity 23 of the front support 4 and the guide hole 53 of the rear support 6, the aircraft and the booster make relative divergent movement to achieve the separation of the booster.

[0067] In this embodiment, the guide lengths of the guide cavity 23 and the guide hole 53 are consistent, ensuring the synchronous separation of the front and rear connection points when the booster is separated. The cross section of the guide cavity 32 is square, and the cross section of the guide hole 53 is arc-shaped, that is, the front is round and the back is round. The square guide of the front section can limit the circumference of the booster, and the circular guide of the rear end facilitates the separation of the booster. It should be understood by those skilled in the art that the guide cavity 32 at the front end is not limited to a structure with a cross section in a direction, but can also be polygonal or circular. When the cross section is circular, the directions other than the axial direction of the booster can be limited by various mounting parts.

[0068] In this embodiment, the first mounting portion 41 and the third mounting portion 61 are connected to the booster body 7 via bolt assemblies. The second mounting portion 21 and the fourth mounting portion 51 are both connected to the aircraft via bolt assemblies.

[0069] In an optional embodiment, the rear support 6 is located closer to the tail end of the booster, the third docking portion 62 extends toward the front end of the booster, the elastic member is arranged on the third docking portion 62, and can be compressed and abutted on the rear support connection seat 5, the guide hole 53 provided on the rear connection seat 5 can be a round hole, when the elastic member is selected as a spring, the spring can be sleeved on the third docking portion 62. When installing the booster, first compress the spring, correspond each connection seat to the corresponding support, continue to compress the spring, install each support to the connection seat, and finally fix the booster with the separation bolt. The solution of this embodiment saves more parts and reduces the take-off weight of the aircraft, but requires a greater force to compress the elastic member during installation.

[0070] The elastic member in the above embodiments includes but is not limited to a spring, and various spring sheets suitable for installation.

[0071] In an optional embodiment, an elastic member is provided between the front support 4 and the front connecting seat 2, the elastic member is fixedly connected to the front support 4, and the elastic member is compressed and installed between the front support 4 and the front connecting seat 2. When the separation bolt 1 is opened, it contacts the fixed constraint of the front support 4 and the front connecting seat 2, and the elastic member releases the stored energy to help the booster separate from the aircraft. Optimally, it should be understood that when the elastic member is installed at both the front and rear, the energy storage of the elastic member remains consistent, so that the energy released by the front and rear elastic members is the same.

[0072] The present application provides a pop-up booster installation and separation mechanism, which can solve the problem of insufficient booster separation power when gravity and aerodynamic force are insufficient by setting an elastic member between the support and the connection seat of the booster body 7. After the separation bolt 1 is opened, the elastic member releases energy to assist the booster and the connection seat, i.e., the aircraft to separate, without the need for additional driving force. The structure of the pressure plate 8 is simple to install and easy to operate, and the elastic force of the spring 9 is adjustable.

[0073] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0074] Finally, it should be noted that: Obviously, the above embodiments are only examples for clearly explaining the present invention, and are not intended to limit the implementation methods. For ordinary technicians in the relevant field, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived from this are still within the scope of protection of the present invention.

Claims

1. A pop-up booster installation and separation mechanism, characterized in that: include: Booster body; A front support, which is arranged at the front end of the booster body; A rear support, which is arranged at the rear end of the booster body; A front connecting seat, which is arranged on the front support, and the front connecting seat is used to be installed on the aircraft; A rear connecting seat, which is arranged on the rear support, and the rear connecting seat is used to be installed on the aircraft; a separation bolt, which passes through the front connecting seat and the front support to connect the front connecting seat and the front support, and the separation bolt is used to connect the aircraft and can separate the front connecting seat and the front support; An elastic member is arranged on the rear support, and the elastic member is compressed and installed between the rear support and the rear connecting seat, so that the rear support is subjected to a force acting toward the rear end of the booster body.

2. The pop-up booster installation and separation mechanism according to claim 1, characterized in that: The front support comprises: A first mounting portion connected to the booster body; The first docking portion is vertically arranged with respect to the first mounting portion, and the first mounting portion is provided with a first through hole coaxial with the booster body.

3. A pop-up booster installation and separation mechanism according to claim 1, characterized in that: The front connecting seat comprises: a second mounting portion, which is used to be connected to the aircraft; The second docking portion is provided with a guide cavity for accommodating the first docking portion of the front support, and the second docking portion is provided with a second through hole coaxial with the booster body.

4. A pop-up booster installation and separation mechanism according to claim 1, characterized in that: The rear support comprises: a third mounting portion connected to the booster body; A third docking portion, which is disposed on the third mounting portion, is cylindrical, is parallel to the axis of the booster body, and is used for slidably mounting the rear connecting seat; A pressure plate is arranged on one end of the third docking portion facing the rear end of the booster body, and the pressure plate is connected to the elastic member.

5. A pop-up booster installation and separation mechanism according to claim 4, characterized in that: The pressing plate is vertically connected with a limiting rod for installing the elastic member and limiting the position of the elastic member.

6. A pop-up booster installation and separation mechanism according to claim 5, characterized in that: The elastic member is a spring, a first end of which is connected to the pressing plate and is coaxially sleeved on the limiting rod.

7. A pop-up booster installation and separation mechanism according to claim 4, characterized in that: The rear support also includes: A screw passes through the pressing plate and is connected to the third docking portion.

8. A pop-up booster installation and separation mechanism according to claim 4, characterized in that: The rear connecting seat comprises: a fourth mounting portion, which is used to be connected to the aircraft; The fourth docking portion is provided with a guide hole for slidably mounting the third docking portion.

9. The pop-up booster installation and separation mechanism according to claim 1, characterized in that: The separation bolt is fixed to the front connection seat via a bolt clip; The bolt card is provided with a groove matching the appearance of the separation bolt, and the bolt card is fixed on the front connecting seat.

10. A pop-up booster installation and separation mechanism according to claim 1, characterized in that: An elastic member is arranged between the front support and the front connecting seat.

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