Satellite initiating explosive device heat conduction buffer structure

Abstract

The invention provides a heat conduction buffer structure of a satellite initiating explosive device. The heat conduction buffer structure comprises mounting screws, mounting feet, an upper buffer heat conduction pad, a middle buffer heat conduction pad and a lower buffer heat conduction pad. The middle buffering heat conduction pad and the upper buffering heat conduction pad are sequentially arranged on the top of the initiating explosive device unlocking and separating device from bottom to top, and the lower buffering heat conduction pad is arranged between the bottom of the initiating explosive device unlocking and separating device and a satellite. The satellite is arranged at the top of the mounting foot, and the mounting screws are used for sequentially fixing the upper buffering heat conduction pad, the middle buffering heat conduction pad, the initiating explosive device unlocking and separating device, the lower buffering heat conduction pad and the satellite to the mounting foot and providing pre-tightening force. The heat conduction buffer structure adopts an upper-layer, middle-layer and lower-layer heat conduction pad structure, heat generated during explosion of the initiating explosive device is better dissipated through superposition of multiple layers of materials, and the thermal shock of explosion of the initiating explosive device on a satellite structure and equipment is effectively reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite unlocking and separation, and in particular to a thermally conductive buffer structure of a satellite pyrotechnic device, and in particular to a thermally conductive buffer structure of a pyrotechnic device unlocking and separation device on a satellite. Background Art

[0002] Satellite unlocking and separation technology refers to the technology of unlocking and separating various components of a satellite during the launch, operation or return of the satellite, such as unlocking and deploying the satellite's solar panels, antennas, payloads, etc., or separating the satellite's upper stage, recovery cabin, etc. Satellite unlocking and separation technology usually uses pyrotechnics as a power source, using the explosive energy of pyrotechnics to drive the unlocking and separation mechanism to achieve satellite unlocking and separation.

[0003] However, the explosion of pyrotechnics will produce high-temperature and high-pressure gas and debris, causing thermal and mechanical shock to the satellite's structure and equipment, affecting the satellite's performance and reliability. In order to mitigate the adverse effects of pyrotechnic explosions, it is usually necessary to set a heat-conducting buffer structure at the installation location of the pyrotechnic unlocking and separation device to dissipate the heat generated by the pyrotechnic explosion and buffer the impact force generated by the pyrotechnic explosion to protect the satellite's structure and equipment.

[0004] The existing thermal buffer structure usually uses a single or double-layer thermal pad, such as a metal pad, graphite pad, ceramic pad, etc., to isolate the pyrotechnic unlocking and separation device and the satellite mounting feet. The disadvantages of this thermal buffer structure are that the material selection of the thermal pad is limited, the thickness and hardness of the thermal pad are difficult to balance, the contact area of ​​the thermal pad is small, and the heat dissipation and buffering effects of the thermal pad are not ideal. Summary of the invention

[0005] In view of the defects in the prior art, the purpose of the present invention is to provide a thermal conductive buffer structure for satellite pyrotechnics.

[0006] The satellite pyrotechnic thermal conductive buffer structure provided by the present invention comprises mounting screws, mounting feet, an upper thermal conductive buffer pad, a middle thermal conductive buffer pad and a lower thermal conductive buffer pad;

[0007] The middle buffer thermal pad and the upper buffer thermal pad are arranged on the top of the pyrotechnic unlocking and separating device in sequence from bottom to top, and the lower buffer thermal pad is arranged between the bottom of the pyrotechnic unlocking and separating device and the satellite;

[0008] The satellite is arranged on the top of the mounting foot, and the mounting screws are used to sequentially fix the upper buffer thermal pad, the middle buffer thermal pad, the pyrotechnic unlocking and separation device, the lower buffer thermal pad and the satellite on the mounting foot and provide a pre-tightening force.

[0009] Preferably, the upper buffer thermal conductive pad, the middle buffer thermal conductive pad and the lower buffer thermal conductive pad are made of different materials.

[0010] Preferably, the thermal conductivity of the upper buffer thermal pad material is in the range of 100 W / mK or more, and the thermal expansion coefficient of the upper buffer thermal pad material is in the range of no more than 23.1×10 -6 / ℃.

[0011] Preferably, the thermal conductivity of the medium buffer thermal pad material is less than 100 W / mK, but the specific heat capacity of the medium buffer thermal pad material is not greater than 2×10 3 J / (kg·℃).

[0012] Preferably, the elastic modulus of the lower buffer thermal pad material is in the range of no more than 1 GPa, and the Poisson's ratio of the lower buffer thermal pad material is in the range of 0-0.5.

[0013] Preferably, the upper buffer thermal pad is made of aluminum alloy.

[0014] Preferably, the material of the middle buffer thermal pad is silica gel.

[0015] Preferably, the lower buffer thermal pad is made of rubber.

[0016] Preferably, the ends of the upper thermally conductive buffer pad, the middle thermally conductive buffer pad and the lower thermally conductive buffer pad are interfaces for cooperating with mounting screws or adjacent thermally conductive buffer pads, and the interfaces are round holes, square holes or elliptical holes.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The thermal conductive buffer structure of the present invention adopts a three-layer thermal conductive pad structure of upper, middle and lower layers. The stacking of multiple layers of materials can better dissipate the heat generated by the explosion of pyrotechnics, effectively reducing the thermal shock of the explosion of pyrotechnics on satellite structures and equipment.

[0019] 2. The thermal conductive buffering method of the present invention increases the contact surface of the buffer by means of three-layer contact of the thermal conductive pad. When impacted, the multi-layer structure can effectively disperse the impact force, thereby effectively reducing the mechanical impact of the explosion of pyrotechnics on the satellite structure and equipment.

[0020] 3. The thermal buffer method of the present invention uses installation screws to fix the thermal pad, which has a simple structure and is easy to install. At the same time, the number and position of the thermal pads can be flexibly adjusted according to the different specifications of pyrotechnics and the different needs of satellites, thereby improving the adaptability and reliability of the thermal buffer structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0022] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0023] Figure 2 It is a cross-sectional structural schematic diagram of the present invention;

[0024] Figure 3 It is a schematic diagram of the structure of the present invention from a top view.

[0025] The figure shows:

[0026] Explosive device unlocking and separation device 1 Upper buffer thermal pad 5

[0027] Satellite 2 Medium Buffer Thermal Pad 6

[0028] Mounting foot 3 Buffer thermal pad 7

[0029] Mounting screw 4 DETAILED DESCRIPTION

[0030] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0031] The present invention discloses a satellite pyrotechnic thermal conductive buffer structure, which adopts an upper, middle and lower three-layer thermal conductive pad structure, and can better dissipate the heat generated by the explosion of the pyrotechnic by stacking multiple layers of materials, thereby effectively reducing the thermal impact of the pyrotechnic explosion on the satellite structure and equipment.

[0032] The satellite pyrotechnic thermal conductive buffer structure provided by the present invention includes mounting screws 4, mounting feet 3, upper buffer thermal conductive pads 5, middle buffer thermal conductive pads 6 and lower buffer thermal conductive pads 7; the middle buffer thermal conductive pads 6 and upper buffer thermal conductive pads 5 are sequentially arranged on the top of the pyrotechnic unlocking and separation device 1 from bottom to top, and the lower buffer thermal conductive pad 7 is arranged between the bottom of the pyrotechnic unlocking and separation device 1 and the satellite 2; the satellite 2 is arranged on the top of the mounting feet 3, and the mounting screws 4 are used to sequentially fix the upper buffer thermal conductive pad 5, the middle buffer thermal conductive pad 6, the pyrotechnic unlocking and separation device 1, the lower buffer thermal conductive pad 7 and the satellite 2 on the mounting feet 3 and provide pre-tightening force.

[0033] The upper buffer thermal pad 5, the middle buffer thermal pad 6 and the lower buffer thermal pad 7 are made of different materials. The thermal conductivity of the upper buffer thermal pad 5 is above 100 W / mK, and the thermal expansion coefficient of the upper buffer thermal pad 5 is not higher than 23.1×10 -6 / ℃.

[0034] The middle thermal buffer pad 6 is mainly used to absorb the heat transferred by the upper thermal pad. The thermal conductivity of the material of the middle thermal buffer pad 6 can be less than that of the upper thermal buffer pad, that is, less than 100 W / mK. The specific heat capacity range of the material of the middle thermal buffer pad 6 is not more than 2×10 3 The lower buffer thermal pad 7 mainly plays a buffering role, and should be made of a material with low rigidity, and the elastic modulus of the material should not exceed 1 GPa, and the Poisson's ratio of the material of the lower buffer thermal pad 7 should be in the range of 0-0.5.

[0035] Preferably, the upper buffer thermal pad 5 is made of aluminum alloy, the middle buffer thermal pad 6 is made of silica gel, and the lower buffer thermal pad 7 is made of rubber.

[0036] like Figure 3 As shown, the ends of the upper thermal buffer pad 5, the middle thermal buffer pad 6 and the lower thermal buffer pad 7 are interfaces for cooperating with mounting screws or adjacent thermal buffer pads, and the interfaces are round holes, square holes or elliptical holes.

[0037] Example 1

[0038] This embodiment discloses a thermally conductive buffer structure of a satellite explosive device, such as Figure 1 As shown, in the figure, 1 is the unlocking and separating device of the pyrotechnics, 2 is the satellite, 3 is the mounting foot, 4 is the mounting screw, 5 is the upper buffer thermal pad, 6 is the middle buffer thermal pad, and 7 is the lower buffer thermal pad.

[0039] The specific installation steps are as follows:

[0040] Step 1. Connect the explosive unlocking and separating device 1 to the mounting foot 3 of the satellite 2, fix it with the mounting screws 4 and provide a pre-tightening force, so that the explosive unlocking and separating device 1 and the satellite 2 fit tightly to form a heat-conducting buffer structure;

[0041] Step 2. Place the upper buffer thermal pad 5, the middle buffer thermal pad 6 and the lower buffer thermal pad 7 on the upper and lower sides of the mounting foot 3 respectively, so that they cooperate with the mounting screws 4 or the adjacent thermal buffer pads to form an interface. The shape of the interface can be a round hole, a square hole, an elliptical hole or other different shapes to adapt to different installation methods;

[0042] Step 3. The upper buffer thermal pad 5, the middle buffer thermal pad 6 and the lower buffer thermal pad 7 are respectively made of different materials to achieve different heat conduction and buffering effects. For example, the material of the upper buffer thermal pad 5 can be aluminum alloy, the material of the middle buffer thermal pad 6 can be silica gel, and the material of the lower buffer thermal pad 7 can be rubber;

[0043] Step 4. When the pyrotechnic unlocking separation device 1 receives the separation signal, the pyrotechnic is triggered to explode, generating high-temperature and high-pressure gas and fragments, posing a threat to the structure and function of the satellite 2;

[0044] Among them, the material of the upper buffer thermal pad 5 has a high thermal conductivity and a low thermal expansion coefficient, which can quickly conduct the heat generated by the explosion of the pyrotechnics and prevent structural deformation caused by thermal expansion; the material of the middle buffer thermal pad 6 has a high specific heat capacity and a low thermal conductivity, which can absorb and store the heat generated by the explosion of the pyrotechnics and slow down the heat conduction speed, thereby reducing the temperature impact on the satellite 2; the material of the lower buffer thermal pad 7 has a low elastic modulus and a high Poisson's ratio, which can withstand and disperse the impact force generated by the explosion of the pyrotechnics and prevent structural damage caused by the impact;

[0045] Through the above-mentioned heat conduction buffering method, the structure and function of the satellite 2 can be effectively protected from being affected by the pyrotechnic unlocking and separation device 1, thereby achieving safe separation of the satellite 2.

[0046] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply 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 a limitation on the present application.

[0047] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A thermally conductive buffer structure for satellite explosives, characterized in that: It comprises a mounting screw (4), a mounting foot (3), an upper buffer thermal conductive pad (5), a middle buffer thermal conductive pad (6) and a lower buffer thermal conductive pad (7); The middle buffer thermal pad (6) and the upper buffer thermal pad (5) are arranged in sequence from bottom to top on the top of the explosive device unlocking and separating device (1), and the lower buffer thermal pad (7) is arranged between the bottom of the explosive device unlocking and separating device (1) and the satellite (2); The satellite (2) is arranged on the top of the mounting foot (3), and the mounting screw (4) is used to sequentially fix the upper buffer thermal pad (5), the middle buffer thermal pad (6), the pyrotechnic unlocking and separation device (1), the lower buffer thermal pad (7) and the satellite (2) on the mounting foot (3) and provide a pre-tightening force.

2. The satellite pyrotechnic thermal conductive buffer structure according to claim 1, characterized in that: The upper buffer thermal conductive pad (5), the middle buffer thermal conductive pad (6) and the lower buffer thermal conductive pad (7) are made of different materials.

3. The satellite pyrotechnic thermal conductive buffer structure according to claim 2, characterized in that: The thermal conductivity of the material of the upper buffer thermal pad (5) is in the range of above 100 W / mK, and the thermal expansion coefficient of the material of the upper buffer thermal pad (5) is not higher than 23.1×10 -6 / ℃.

4. The satellite pyrotechnic thermal conductive buffer structure according to claim 2, characterized in that: The thermal conductivity of the material of the middle buffer thermal pad (6) is less than 100 W / mK, and the specific heat capacity of the material of the middle buffer thermal pad (6) is not more than 2×10 3 J / (kg·℃).

5. The satellite pyrotechnic thermal conductive buffer structure according to claim 2, characterized in that: The elastic modulus of the material of the lower buffer thermal pad (7) is within a range of no more than 1 GPa, and the Poisson's ratio of the material of the lower buffer thermal pad (7) is within a range of 0-0.

5.

6. The satellite pyrotechnic thermal conductive buffer structure according to claim 3, characterized in that: The upper buffer thermal pad (5) is made of aluminum alloy.

7. The satellite pyrotechnic thermal conductive buffer structure according to claim 4, characterized in that: The material of the middle buffer thermal conductive pad (6) is silica gel.

8. The satellite pyrotechnic thermal conductive buffer structure according to claim 5, characterized in that: The lower buffer heat-conducting pad (7) is made of rubber.

9. The satellite pyrotechnic thermal conductive buffer structure according to claim 1, characterized in that: The ends of the upper thermal buffer pad (5), the middle thermal buffer pad (6) and the lower thermal buffer pad (7) are interfaces for cooperating with mounting screws or adjacent thermal buffer pads, and the interfaces are round holes, square holes or elliptical holes.

Images