A slow pressure balance device for spacecraft

Abstract

The present invention belongs to the field of spacecraft technology, and in particular relates to a slow pressure balancing device for spacecraft, comprising: a support seat fixedly connected to a spacecraft mounting interface, a first sealing assembly provided between the support seat and the spacecraft mounting interface, a protective cap detachably connected to the support seat, a second sealing assembly provided between the support seat and the protective cap, an air pressure balancing mechanism provided between the support seat and the protective cap, anti-blocking mechanisms provided on both sides of the air pressure balancing mechanism, and a gap left between the air pressure balancing mechanism and the anti-blocking mechanism. The present invention adjusts the air flow through the air pressure balancing mechanism according to different use environments and working conditions by providing an air pressure balancing mechanism between the support seat and the protective cap, thereby achieving steady-state and slow balance of internal and external pressure differences and effectively ensuring the safety of pressure-sensitive devices; at the same time, anti-blocking mechanisms are provided on both sides of the air pressure balancing mechanism to effectively ensure that the air pressure balancing mechanism will not be blocked.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft, and in particular relates to a slow pressure balancing device for spacecraft. Background Art

[0002] During the launch phase of a spacecraft, the pressure inside and outside the spacecraft changes rapidly, resulting in a pressure difference. After the spacecraft enters the predetermined orbit, the outside is in a vacuum state, resulting in a large pressure difference, which affects the safety of the spacecraft. It is necessary to balance the pressure difference between the inside and outside of the spacecraft. The existing pressure relief valve is mainly used for the rapid drop in ambient air pressure during the launch phase of a spacecraft, and is used to quickly release the pressure in the spacecraft's sealed cabin to prevent the pressure difference from exceeding the bearing capacity of the spacecraft's sealed cabin structure and causing structural damage. However, the existing pressure relief valve is not suitable for aircraft in orbit. When the existing pressure relief valve releases pressure, it will generate airflow disturbances in the sealed cabin, and in severe cases, it may even cause damage to pressure-sensitive devices. In view of this, it is necessary to achieve a steady-state, slow balance of internal and external pressures when the spacecraft is in orbit. Therefore, a slow pressure balancing device for spacecraft is urgently needed. Summary of the Invention

[0003] The purpose of the present invention is to provide a spacecraft slow pressure balancing device to solve the above problems and achieve the purpose of steady-state and slow balancing of the pressure difference between the inside and outside of the spacecraft.

[0004] To achieve the above object, the present invention provides the following solutions:

[0005] A spacecraft slow pressure balancing device comprises: a support seat fixedly connected to a spacecraft mounting interface, a first sealing assembly arranged between the support seat and the spacecraft mounting interface, a protective cap detachably connected to the support seat, a second sealing assembly arranged between the support seat and the protective cap, the lower end portion of the protective cap extending into the support seat, an air pressure balancing mechanism arranged between the bottom end of the protective cap extending into the interior of the support seat and the support seat, anti-blocking mechanisms arranged on both sides of the air pressure balancing mechanism, and a gap left between the air pressure balancing mechanism and the anti-blocking mechanism.

[0006] Preferably, a through step hole is provided on the support seat, the step hole is coaxially arranged with the spacecraft mounting interface, the protective cap is threadedly connected to the large end of the step hole, a through second air hole is provided on the protective cap, the second air hole is coaxially arranged with the protective cap, the air pressure balancing mechanism and the two anti-blocking mechanisms are both arranged at the large end of the step hole.

[0007] Preferably, the air pressure balancing mechanism includes a balancing plate, which is arranged in the large end of the step hole, the balancing plate and the step hole are coaxially arranged, and at least one conical microhole is opened on the balancing plate, and the angle of the conical microhole is 50°.

[0008] Preferably, the anti-blocking mechanism includes metal filters arranged on both sides of the balance plate, and rectangular rubber rings are arranged between the two metal filters and the balance plate. The inner diameter of the rectangular rubber ring is equal to the inner diameter of the small end of the step hole. Any one of the metal filters abuts against the step of the step hole, and the other metal filter abuts against one end of the protective cap located in the step hole.

[0009] Preferably, one end of the protective cap extending out of the step hole is coaxially fixed with a nut, the nut is provided with a first air hole, the first air hole is communicated with the second air hole, and the first air hole and the second air hole are coaxially arranged.

[0010] Preferably, the first sealing assembly includes a sealing gasket sleeved on the outside of the protective cap, the sealing gasket and the protective cap are coaxially arranged, the sealing gasket is located between the nut and the support seat, the top surface of the sealing gasket abuts against the nut, the bottom surface of the sealing gasket abuts against the support seat, and the top end of the support seat is provided with a V-shaped groove adapted to the sealing gasket.

[0011] Preferably, the second sealing assembly includes an annular mounting groove provided on the bottom surface of the support seat, the annular mounting groove is coaxially arranged with the support seat, a sealing ring is placed in the annular mounting groove, and the sealing ring abuts against the outer wall of the spacecraft mounting interface.

[0012] Preferably, a flange structure is provided at the bottom end of the support seat, and a plurality of stepped through holes are circumferentially and evenly spaced on the outer wall of the flange structure. Screws are passed through the stepped through holes, and the screws are threadedly connected to the spacecraft mounting interface.

[0013] Compared with the prior art, the present invention has the following advantages and technical effects:

[0014] In the present invention, an air pressure balancing mechanism is provided between the support seat and the protective cap, and the air pressure balancing mechanism is used as the only channel connecting the inside and outside of the spacecraft. According to different usage environments and working conditions, the air flow rate passing through the air pressure balancing mechanism is adjusted to achieve a steady-state and slow balance of the internal and external pressure difference, thereby effectively ensuring the safety of pressure-sensitive devices. At the same time, anti-blocking mechanisms are provided on both sides of the air pressure balancing mechanism to effectively ensure that the air pressure balancing mechanism will not be blocked. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. Those skilled in the art can also derive other drawings based on these drawings without inventive work.

[0016] Figure 1 It is a structural schematic diagram of the present invention;

[0017] Figure 2 Schematic diagram of the structure of the balancing sheet in the present invention;

[0018] Among them, 1. Protective cap; 2. Rectangular rubber ring; 3. Metal filter; 4. Sealing ring; 5. Spacecraft installation interface; 6. Support seat; 7. Balance plate; 8. Sealing gasket. DETAILED DESCRIPTION

[0019] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0020] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0021] Reference Figures 1 to 2 The present invention provides a spacecraft slow pressure balancing device, which is characterized in that it includes: a support seat 6 fixedly connected to the spacecraft mounting interface 5, a first sealing component is arranged between the support seat 6 and the spacecraft mounting interface 5, a protective cap 1 is detachably connected to the support seat 6, a second sealing component is arranged between the support seat 6 and the protective cap 1, the lower end portion of the protective cap 1 extends into the support seat 6, and an air pressure balancing mechanism is arranged between the bottom end of the protective cap 1 extending into the interior of the support seat 6 and the support seat 6, anti-blocking mechanisms are arranged on both sides of the air pressure balancing mechanism, and a gap is left between the air pressure balancing mechanism and the anti-blocking mechanism.

[0022] In the present invention, an air pressure balancing mechanism is provided between the support seat 6 and the protective cap 1, and the air pressure balancing mechanism is used as the only channel connecting the inside and outside of the spacecraft. According to different use environments and working conditions, the air flow rate passing through the air pressure balancing mechanism is adjusted to achieve a steady-state and slow balance of the internal and external pressure difference, thereby effectively ensuring the safety of pressure-sensitive devices. At the same time, anti-blocking mechanisms are provided on both sides of the air pressure balancing mechanism to effectively ensure that the air pressure balancing mechanism will not be blocked, and a gap is left between the air pressure balancing mechanism and the anti-blocking mechanism to prevent the air pressure balancing mechanism from being affected by the anti-blocking mechanism.

[0023] To further optimize the solution, a through step hole is provided on the support seat 6, the step hole is coaxially arranged with the spacecraft mounting interface 5, the protective cap 1 is threadedly connected to the large end of the step hole, a through second air hole is provided on the protective cap 1, the second air hole is coaxially arranged with the protective cap 1, and the air pressure balancing mechanism and the two anti-blocking mechanisms are both arranged at the large end of the step hole.

[0024] A further optimized solution includes a pressure balancing mechanism comprising a balancing plate 7, which is positioned within the large end of the stepped hole, coaxially with the stepped hole. The plate is provided with at least one tapered microhole with a 50° angle. The number of tapered microholes is consistent with the volume inside and outside the sealed cabin to be balanced and the balancing rate. If multiple tapered microholes are provided, they are evenly distributed along the center of the plate, with the center-to-center distance between adjacent tapered microholes being greater than or equal to five times the thickness of the plate.

[0025] To further optimize the solution, the anti-blocking mechanism includes metal filter screens 3 arranged on both sides of the balance plate 7, and rectangular rubber rings 2 are arranged between the two metal filter screens 3 and the balance plate 7. The inner diameter of the rectangular rubber ring 2 is equal to the inner diameter of the small end of the step hole. Any metal filter screen 3 abuts against the step of the step hole, and the other metal filter screen 3 abuts against one end of the protective cap 1 located in the step hole.

[0026] To further optimize the solution, one end of the protective cap 1 extending out of the step hole is coaxially fixed with a nut, a first air hole is opened on the nut, the first air hole is connected to the second air hole, and the first air hole and the second air hole are coaxially arranged.

[0027] To further optimize the solution, the first sealing component includes a sealing gasket 8 that is sleeved on the outside of the protective cap 1. The sealing gasket 8 is coaxially arranged with the protective cap 1. The sealing gasket 8 is located between the nut and the support seat 6. The top surface of the sealing gasket 8 abuts against the nut, and the bottom surface of the sealing gasket 8 abuts against the support seat 6. The top of the support seat 6 is provided with a V-shaped groove that is compatible with the sealing gasket 8.

[0028] To further optimize the solution, the second sealing component includes an annular mounting groove opened on the bottom surface of the support seat 6, the annular mounting groove is coaxially arranged with the support seat 6, a sealing ring 4 is placed in the annular mounting groove, and the sealing ring 4 abuts against the outer wall of the spacecraft mounting interface 5.

[0029] To further optimize the solution, a flange structure is provided at the bottom end of the support seat 6, and a plurality of stepped through holes are circumferentially and evenly spaced on the outer wall of the flange structure. Screws are passed through the stepped through holes, and the screws are threadedly connected to the spacecraft mounting interface 5.

[0030] The upper part of the protective cap 1 is a hexagonal nut structure, and the lower part is a cylindrical structure with a second air hole. The hexagonal nut structure and the cylindrical structure are integrally formed. The second air hole, the cylindrical structure and the hexagonal nut structure are all coaxially arranged.

[0031] The rectangular rubber ring 2 is made of rubber. Its outer diameter is smaller than the inner diameter of the large end of the stepped hole, while its inner diameter is larger than the inner diameter of the small end of the stepped hole. The rectangular rubber ring 2 separates the balancing plate 7 from the metal filter 3, creating a gap between them so they do not contact each other. This prevents contact between the balancing plate 7 and the metal filter 3, which could affect the ventilation efficiency of the tapered micropores. The metal filter 3 is a thin, circular, densely woven metal mesh. Its diameter is smaller than the inner diameter of the large end of the stepped hole and larger than the inner diameter of the small end of the stepped hole, ensuring that the tapered micropores on the balancing plate 7 are not clogged.

[0032] The balance sheet 7 is a thin sheet structure, with a conical micropore in the middle of the balance sheet 7. The opening angle of the conical micropore is 50°. The thickness h of the balance sheet 7 can be adjusted according to different usage environments, and the aperture d of the conical micropore is adjusted accordingly according to the volume size of the spacecraft and the pressure relief rate; the material of the balance sheet 7 is preferably oxygen-free copper or pure nickel to prevent the balance sheet 7 from oxidizing in the atmospheric environment and the oxide film from clogging the conical micropore.

[0033] The V-shaped groove at the top of the support seat 6 is arranged circumferentially and coaxially with the support seat 6. The surface roughness of the V-shaped groove and the sealing gasket is good. The sealing gasket 8 is made of a softer aluminum alloy, preferably 1060 aluminum alloy or 3A21 aluminum alloy.

[0034] The spacecraft installation interface 5 is connected to the support seat 6 by screws. A sealing ring 4 is installed between the support seat 6 and the spacecraft installation interface 5, and the compression rate of the sealing ring 4 meets the sealing requirements.

[0035] The filter screen 3, the rectangular rubber ring 2, the balance piece 7, the rectangular rubber ring 2 and the filter screen 3 are installed in sequence in the large end of the step hole of the support seat 6. The above parts are installed to ensure that they are installed flat.

[0036] The sealing gasket 8 is placed on the top of the support seat 6, just above the V-groove of the support seat 6. The protective cap 1 passes through the inner hole of the sealing gasket 8, and the lower external thread section is screwed together with the internal thread section of the support seat 6.

[0037] Use a wrench to tighten the hexagonal nut structure of the protective cap 1 so that the threaded section of the protective cap 1 is screwed together with the threaded section of the support seat 6. During the screwing process, the rectangular rubber ring 2 has a certain amount of deformation due to being an elastic material, which can ensure that the sealing gasket 8 is squeezed and deformed by the protective cap 1 and filled into the V-groove on the top of the support seat 6 to ensure good sealing. The above installation constitutes a unique airflow channel with conical micropores on the balance plate 7.

[0038] In the description of the present invention, it should be understood that the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0039] The embodiments described above are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by persons skilled in the art should fall within the scope of protection defined by the claims of the present invention.

Claims

1. A spacecraft slow pressure balance device, characterized in that: include: A support seat (6) is fixedly connected to the spacecraft mounting interface (5), a first sealing component is provided between the support seat (6) and the spacecraft mounting interface (5), a protective cap (1) is detachably connected to the support seat (6), a second sealing component is provided between the support seat (6) and the protective cap (1), a lower end portion of the protective cap (1) extends into the support seat (6), an air pressure balancing mechanism is provided between the bottom end of the protective cap (1) extending into the interior of the support seat (6) and the support seat (6), anti-blocking mechanisms are provided on both sides of the air pressure balancing mechanism, and a gap is left between the air pressure balancing mechanism and the anti-blocking mechanism; The support seat (6) is provided with a through-step hole, the through-step hole is coaxially arranged with the spacecraft mounting interface (5), the protective cap (1) is threadedly connected to the large end of the through-step hole, the protective cap (1) is provided with a through-second air hole, the second air hole is coaxially arranged with the protective cap (1), and the air pressure balancing mechanism and the two anti-blocking mechanisms are both arranged at the large end of the through-step hole; The air pressure balancing mechanism comprises a balancing plate (7), the balancing plate (7) being arranged in the large end of the step hole, the balancing plate (7) being coaxially arranged with the step hole, and at least one tapered micro-hole being formed on the balancing plate (7), the angle of the tapered micro-hole being 50°; The anti-blocking mechanism comprises metal filter screens (3) arranged on both sides of the balance plate (7), and rectangular rubber rings (2) are arranged between the two metal filter screens (3) and the balance plate (7), and the inner diameter of the rectangular rubber ring (2) is equal to the inner diameter of the small end of the step hole. Any one of the metal filter screens (3) abuts against the step of the step hole, and the other metal filter screen (3) abuts against one end of the protective cap (1) located in the step hole.

2. A spacecraft slow pressure balance device according to claim 1, characterized in that: One end of the protective cap (1) extending out of the step hole is coaxially fixed with a nut, and the nut is provided with a first air hole, the first air hole is communicated with the second air hole, and the first air hole and the second air hole are coaxially arranged.

3. A spacecraft slow pressure balance device according to claim 2, characterized in that: The first sealing assembly includes a sealing gasket (8) sleeved on the outside of the protective cap (1), the sealing gasket (8) and the protective cap (1) are coaxially arranged, the sealing gasket (8) is located between the nut and the support seat (6), the top surface of the sealing gasket (8) abuts against the nut, the bottom surface of the sealing gasket (8) abuts against the support seat (6), and the top end of the support seat (6) is provided with a V-shaped groove adapted to the sealing gasket (8).

4. The slow pressure balance device for spacecraft according to claim 1, characterized in that: The second sealing assembly includes an annular mounting groove provided on the bottom surface of the support seat (6), the annular mounting groove being coaxially arranged with the support seat (6), a sealing ring (4) being placed in the annular mounting groove, and the sealing ring (4) being in contact with the outer side wall of the spacecraft mounting interface (5).

5. The slow pressure balance device for spacecraft according to claim 1, characterized in that: The bottom end of the support seat (6) is provided with a flange structure, and the outer wall of the flange structure is provided with a plurality of stepped through holes at equal intervals in the circumferential direction, and screws are passed through the stepped through holes, and the screws are threadedly connected to the spacecraft mounting interface (5).

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