Booster mounting and separating mechanism

Abstract

The utility model provides a booster mounting and separating mechanism. The booster mounting and separating mechanism comprises a booster body; 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 and is parallel to the axis of the front support; the front connecting base is arranged on the front support, and the front connecting base is used for being installed on an aircraft; the rear connecting base is arranged on the rear support, and the rear connecting base is used for being installed on an aircraft; and 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 an aircraft and can separate the front connecting seat from the front support. The structure is relatively simple, installation is convenient, the two connecting points of the front support and the rear support can be separated at the same time, it is guaranteed that the front connecting point and the rear connecting point of the booster are separated synchronously, and the separation reliability of the booster is improved.

Description

Technical Field

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

[0002] In the prior art, China Invention Patent Publication No. CN111731515A discloses a booster installation and separation mechanism. It includes an aircraft body, a booster, a rear bracket, a hanging beam and a hook. The booster ball joint contacts the ball socket on the body, and the rear bracket on the booster contacts the hanging beam on the body. They are connected by hooks and fixed and unlocked by a bayonet. The structure of this patent application is complex to install, and the unlocking method is not easy to ensure the separation synchronization of the booster, which is not conducive to the realization of the function of the booster. Utility Model Content

[0003] In view of this, the purpose of the utility model is to provide a booster installation and separation mechanism to solve at least one technical problem existing in the prior art: the installation structure is complex, the unlocking method is difficult to ensure the separation synchronization of the booster, and the reliability is poor.

[0004] The present application provides a 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 and is parallel to the axis of the front support;

[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 passes through the front connecting seat and the front support to connect the front connecting seat and the front support. The separation bolt is used to connect the aircraft and can separate the front connecting seat and the front support.

[0011] Furthermore, the front support comprises:

[0012] A first mounting portion connected to the booster body;

[0013] 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.

[0014] Furthermore, the front connecting seat comprises:

[0015] a second mounting portion, which is used to be connected to the aircraft;

[0016] 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.

[0017] Furthermore, the rear support comprises:

[0018] a third mounting portion connected to the booster body;

[0019] The third docking portion is arranged on the third mounting portion and is used for connecting to the rear connecting seat.

[0020] Furthermore, the rear connecting seat comprises:

[0021] a fourth mounting portion, which is used to be connected to the aircraft;

[0022] The fourth docking portion is provided with a guide groove for slidably mounting the third docking portion, and the guide groove is used to limit the radial direction of the booster.

[0023] Furthermore, the separation bolt is fixed to the front connection seat via a bolt card;

[0024] 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.

[0025] Furthermore, the first mounting portion and the third mounting portion are connected to the booster body via a bolt assembly.

[0026] Furthermore, the guiding lengths of the guiding cavity and the guiding groove are consistent.

[0027] The beneficial effects of this application are:

[0028] The booster installation and separation mechanism provided in the present application has a relatively simple structure and is easy to install. The two connection points of the front support and the rear support can be separated at the same time, ensuring the synchronous separation of the front and rear connection points of the booster and improving the reliability of the booster separation. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] 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.

[0030] Figure 1 It is a schematic diagram of the structure of the booster after installation according to the embodiment of the utility model;

[0031] Figure 2This is a schematic diagram of the front structure of the booster after installation according to an embodiment of the utility model;

[0032] Figure 3 It is a schematic diagram of the front support structure provided according to an embodiment of the utility model;

[0033] Figure 4 It is a schematic diagram of the structure of the front connecting seat provided according to an embodiment of the utility model;

[0034] Figure 5 It is a schematic diagram of the rear support structure provided according to an embodiment of the utility model;

[0035] Figure 6 It is a schematic diagram of the structure of the rear connecting seat provided according to an embodiment of the utility model;

[0036] Figure 7 It is a schematic diagram of a bolt card structure provided according to an embodiment of the utility model.

[0037] 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;

[0038] 21 - second mounting portion, 22 - second docking portion, 23 - guide cavity, 24 - second through hole;

[0039] 31-groove;

[0040] 41-first mounting portion, 42-first docking portion, 43-first through hole;

[0041] 51-fourth mounting portion, 52-fourth docking portion, 53-guide groove;

[0042] 61 - third mounting portion, 62 - third docking portion. DETAILED DESCRIPTION

[0043] 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.

[0044] refer to Figures 1 to 7The 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.

[0045] 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 separation, thereby realizing the separation of the booster from the aircraft.

[0046] In this embodiment, reference Figures 2 to 4 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.

[0047] 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.

[0048] 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 ensured to be consistent. The separation bolt 1 simultaneously penetrates the first through hole 43 and the second through hole 24 to fix the front support 4 and the front connecting seat 2 together, thereby realizing the installation of the booster on the aircraft.

[0049] In this embodiment, reference Figure 1 , Figure 2 and Figure 7 , 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.

[0050] In this embodiment, reference Figure 1 , Figure 5 and Figure 6 The rear support 6 includes: a third mounting portion 61, which is connected to the booster body 7; and a third docking portion 62, which is arranged on the third mounting portion 61 and is used to connect to the rear connecting seat 5.

[0051] The rear connecting 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 groove 53 for slidably mounting the third docking portion 62, and the guide groove 53 is used to limit the radial direction of the booster.

[0052] It should be understood that the rear support 6 and the front support 4 are both fixed on the booster body 7 and are located on the same axis. The guide groove 53 of the fourth docking portion 52 can slidably mount the third docking portion 62, allowing the booster body 7 to move in its axial direction.

[0053] 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 groove 53 of the rear support 6, the aircraft and the booster make relative divergent movement to achieve the separation of the booster.

[0054] In this embodiment, the guiding lengths of the guiding cavity 23 and the guiding groove 53 are consistent, which ensures the synchronous separation of the front and rear connection points when the booster is separated.

[0055] 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.

[0056] The booster installation and separation mechanism provided in the present application has a relatively simple structure and is easy to install. The two connection points of the front support 4 and the rear support 6 can be separated at the same time, ensuring the synchronous separation of the front and rear connection points of the booster and improving the reliability of the booster separation.

[0057] 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.

[0058] 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 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 and is parallel to the axis of the front support; 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 passes through the front connecting seat and the front support to connect the front connecting seat and the front support. The separation bolt is used to connect the aircraft and can separate the front connecting seat and the front support.

2. A 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 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 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; The third docking portion is arranged on the third mounting portion and is used for connecting to the rear connecting seat.

5. A 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 groove for slidably mounting the third docking portion, and the guide groove is used to limit the radial direction of the booster.

6. A 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.

7. A booster installation and separation mechanism according to claim 2 or 4, characterized in that: Each of the mounting portions is connected to the booster body via a bolt assembly.

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