Spacecraft shading and gas releasing device

Abstract

A multifunctional light-shading and air-releasing device for a spacecraft comprises a tubular structure with an air-releasing hole and a flange structure, a light-shading cover is of a flanging cover plate structure, a cover plate is a plane, a flanging is of a side-standing short-edge structure formed by machining along the outer edge curve of the cover plate, and the light-shading cover covers the end, provided with the air-releasing hole, of the tubular structure; the flange structure is located at the other end of the tubular structure, is matched with the radian of the bearing cylinder and is used for tightly attaching the device to the outer wall of the bearing cylinder; the light-shading and air-releasing device adopts an integrally-formed processing mode, has the advantages of integration, multiple functions, simple structure, light weight, convenience in installation and the like, and is well applied to spacecrafts.

Description

Technical Field

[0001] The invention relates to a spacecraft light-shielding and air-releasing device, and belongs to the field of spacecraft design. Background Art

[0002] The payload of a spacecraft is installed in the platform bearing cylinder. To ensure its normal operation, the vacuum degree in the bearing cylinder needs to be quickly reduced to a certain condition. Therefore, it is necessary to set a release hole on the platform bearing cylinder so that the air in the bearing cylinder can be quickly released after the payload enters space. If the release hole is directly set on the bearing cylinder, the purpose of air release can be achieved, but because the payload has thermal control requirements, the sunlight will enter the platform bearing cylinder through the release hole, which may cause the local temperature of the load to rise. Therefore, it is necessary to design a device that can meet the need for air release and prevent light from entering the bearing cylinder.

[0003] Traditional light-shielding and air-release devices usually use a mechanism to open and block the air outlet to achieve the purpose of air release and light-shielding: the mechanism opens when releasing air, and blocks the air outlet again after the air release is completed to prevent light from entering. The mechanism system is relatively complex, and its reliability is not easy to guarantee, and it is not lightweight enough. Therefore, it is necessary to design a light-shielding and air-release device that can not only meet the functions of light-shielding and rapid air release, but also be easy to operate, highly reliable, and meet the requirements of lightweight and mechanics, so as to minimize the impact on the overall layout and center of mass of the spacecraft and adapt to the use environment. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and to provide a spacecraft shading and air release device, which takes into account both shading and air release requirements, has reliable rigidity and stability, and can meet mechanical requirements and lightweight requirements.

[0005] The technical solution of the present invention is: a spacecraft light-shielding and air-releasing device, comprising: a light-shielding cover, a tubular structure with air-releasing holes, and a flange structure, wherein:

[0006] The sunshade is a flanged cover plate structure, wherein the cover plate is a plane, the flange is a side-standing short side structure formed by processing along the outer edge curve of the cover plate, and the sunshade covers one end of the tubular structure with a gas release hole;

[0007] The flange structure is located at the other end of the tubular structure, which fits the curvature of the bearing cylinder and is used to fit the shading and air release device tightly onto the side wall of the bearing cylinder;

[0008] The sunshade, the tubular structure with air release holes and the flange structure are integrally formed.

[0009] Preferably, the material of the light shield, the tubular structure with air release holes and the flange structure is T700S.

[0010] Preferably, the air release holes of the tubular structure are waist-shaped holes.

[0011] Preferably, the size of the air release holes on the tubular structure is determined based on the light reflection path and the minimum cross-sectional area required for rapid air release.

[0012] Preferably, the cross-sectional area of ​​the tubular structure is ≥ 11300 mm 2 .

[0013] Preferably, the size of the air release hole is based on the light reflection path requirements as follows:

[0014] In the most severe case where the light is not blocked by the sunshade, after entering the tubular structure, it will be unable to enter the aircraft platform bearing cylinder after a mirror reflection;

[0015] The light in the most stringent case is the light on the line connecting the edge of the lens hood flange and the edge of the air release hole away from the bottom point of the lens hood.

[0016] Preferably, the size of the upper flange of the sunshade is designed based on the path of the light reflected once on the inner wall of the sunshade tubular structure under the most stringent conditions so as not to enter the bearing cylinder of the aircraft platform.

[0017] Preferably, the air release area of ​​the space between the flange and the tubular structure, the sum of the areas of all the air release holes on the tubular structure, and the cross-sectional area of ​​the tubular structure are the same.

[0018] Compared with the prior art, the present invention has the following advantages:

[0019] (1) The present invention is a spacecraft light-shielding and air-releasing device, wherein the sizes of the light-shielding cover, the tubular structure and the air-releasing hole can meet the requirements of rapid air release; the light-shielding cover can prevent most light from entering the bearing cylinder of the aircraft platform, and the tubular structure ensures that the light that cannot be completely blocked by the light-shielding cover cannot reach the bearing cylinder after entering the light-shielding and air-releasing device after a mirror reflection, thereby meeting the requirements of both light-shielding and air-releasing;

[0020] (2) The present invention is manufactured by an integrated molding method, which reduces the difficulty of processing and improves the rigidity, stability and reliability of the overall structure; the light shield is designed as a flanged cover structure, which can effectively reduce the diameter and height of the light shielding and gas release device, making the overall structure of the device compact and occupying less space when installed on the spacecraft;

[0021] (3) The material of the device of the present invention is preferably T700S, which has the advantages of high strength, high rigidity and low density, can meet the mechanical requirements and lightweight requirements, and can ensure that the structure will not be damaged in the harsh launch environment and space environment, and has strong reliability;

[0022] (4) The device of the present invention is installed in a manner that fits closely to the wall of the load-bearing cylinder, which can prevent stray light from leaking into the load-bearing cylinder;

[0023] (5) The structural form and installation method of the device of the present invention can prevent excess objects from falling directly into the load-bearing cylinder. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 The overall schematic diagram of the spacecraft light-shielding and gas-releasing device provided by the present invention and the schematic diagram of component decomposition;

[0025] Figure 2 This is a schematic diagram of the reflection path of light after entering the device of the present invention;

[0026] Figure 3 Schematic diagram of the exhaust path of the device of the present invention. DETAILED DESCRIPTION

[0027] A spacecraft light-shielding and air-releasing device can realize the rapid release of air in the bearing cylinder of the aircraft platform and prevent light from entering the bearing cylinder. It has the advantages of simple structure, light weight, high rigidity, small size, and easy installation. The specific structure is as follows:

[0028] The light shielding and air release device designed in the present invention comprises a light shielding cover, a tubular structure with air release holes, and a flange structure at the bottom. The light shielding cover is a flanged cover plate structure, the cover plate structure is a plane, and the flanged structure is a side-standing short-side structure formed by processing along the outer edge curve of the cover plate. The light shielding cover covers one end of the tubular structure and can block part of the light that is intended to enter the device. The design of the flanged cover plate also effectively reduces the diameter and height of the entire device to meet the needs of small and light weight.

[0029] An air release hole is provided on one end where the tubular structure is connected to the sunshade cover structure, and the air in the load-bearing cylinder can be discharged from the air release hole through the tubular channel; the design of the size of the air release hole can not only meet the demand for rapid air release, so that the air in the load-bearing cylinder of the aircraft platform can be quickly discharged from the air release hole through the channel in the tubular structure, but also ensure that the light entering the device cannot enter the load-bearing cylinder after one mirror reflection; the flange structure of the sunshade blocks the upper half of the air release hole, which can block part of the light that wants to enter the device, and at the same time, the light entering the air release hole cannot enter the load-bearing cylinder after one mirror reflection, thereby avoiding local heating of the load installed inside the load-bearing cylinder.

[0030] The flange structure at the bottom of the device is a flange structure that fits the curvature of the bearing cylinder, which can ensure that the device fits tightly on the side wall of the bearing cylinder. The flange flange structure is a structure that adapts to the installation surface. It is located at the bottom of the tubular structure and has a through hole for installation. The device can be fixed to the bearing cylinder of the aircraft platform through fasteners. Considering the mechanical requirements of the use environment, T700S is preferred as the material of the device; this material has the characteristics of high rigidity and low density, which can meet the mechanical requirements and lightweight requirements while ensuring the reliability of the device. Considering the difficulty of processing, the entire device is manufactured using an integrated molding method, which can improve the rigidity and stability of the entire device.

[0031] The light shield on the top of the light shielding and air releasing device is designed as a flanged cover structure, which can effectively reduce the diameter and height of the light shielding and air releasing device;

[0032] The tubular structure is provided with four waist-shaped holes as air release holes. The air release area of ​​the space between the flange cover plate and the tubular structure, the sum of the areas of all the air release holes on the tubular structure, and the cross-sectional area of ​​the tubular structure are respectively the same as the minimum diameter cross-sectional area that meets the requirements of rapid air release. The diameter size of the tubular structure is designed based on the minimum cross-sectional area that meets the requirements of rapid air release, and the size of the air release holes on the tubular structure is determined based on the light reflection path and the air release caliber.

[0033] The minimum cross-sectional area required for rapid gas release is ≥11300mm 2 .

[0034] The size of the upper flange of the sunshade (the short side of the cover plate) is designed based on the path of the light reflected once on the inner wall of the sunshade tubular structure under the most stringent conditions so that it will not enter the bearing tube of the aircraft platform.

[0035] The mounting flange at the bottom of the device is provided with mounting through holes, and is mounted on the outer wall of the bearing cylinder of the aircraft platform by means of screws.

[0036] The following is further described based on specific embodiments:

[0037] like Figure 1 As shown, the main components of the device include a light shield 1, a tubular structure 2 and a flange structure 3, with the light shield 1 and the tubular structure 2 being the main functional structures, and the flange structure 3 being the connecting structure;

[0038] The installation method of the shading and air release device is that after the bottom surface of the mounting flange is attached to the outer wall of the aircraft platform bearing cylinder, it is fixed and installed by screw fastening and a pre-tightening force is applied.

[0039] like Figure 2The figure shows the reflection path of the light entering the device. It can be seen that the size of the designed air release hole can ensure that the light in the most severe case that is not blocked by the sunshade cannot enter the aircraft platform bearing cylinder after a mirror reflection after entering the tubular structure of the device, thereby effectively avoiding the local heating of the load installed inside the bearing cylinder. The light in the most severe case is the light on the line connecting the edge of the sunshade flange and the edge of the air release hole away from the bottom point of the sunshade. The carbon fiber material used has good wave absorption performance and can effectively reduce stray light. The stray light after a mirror reflection entering the bearing cylinder will hardly cause the equipment in the bearing cylinder to heat up.

[0040] like Figure 3 The figure shows the air release path. When releasing air, it is ensured that the air release area 4 of the space between the flange cover and the tubular structure, the total area 5 of all the air release holes on the tubular structure and the cross-sectional area 6 of the tubular structure are respectively the same as the minimum diameter cross-sectional area that meets the requirements of rapid air release. If the cross-sectional areas are different, it is easy to cause eddies and vortices inside the air release channel or the air flow rate to slow down, increase resistance, and fail to achieve the purpose of rapid air release. Therefore, the same area of ​​the three can ensure a smooth air release process, which is used as the basis for the size design of the flange cover and the air release holes.

[0041] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in this field.

Claims

1. A spacecraft light-shielding and gas-releasing device, characterized in that include: A sunshade, a tubular structure with air release holes, and a flange structure, wherein: The sunshade is a flanged cover plate structure, wherein the cover plate is a plane, the flange is a side-standing short side structure formed by processing along the outer edge curve of the cover plate, and the sunshade covers one end of the tubular structure with a gas release hole; The flange structure is located at the other end of the tubular structure, which fits the curvature of the bearing cylinder and is used to fit the shading and air release device tightly onto the side wall of the bearing cylinder; The sunshade, the tubular structure with air release holes and the flange structure are integrally formed.

2. A spacecraft light-shielding and air-releasing device according to claim 1, characterized in that: The material of the sunshade, the tubular structure with air release holes and the flange structure is T700S.

3. A spacecraft light-shielding and air-releasing device according to claim 1, characterized in that: The air release holes of the tubular structure are waist-shaped holes.

4. The spacecraft light-shielding and air-releasing device according to claim 1, characterized in that: The size of the air release holes on the tubular structure is determined based on the light reflection path and the minimum cross-sectional area required for rapid air release.

5. A spacecraft light-shielding and air-releasing device according to claim 4, characterized in that: Cross-sectional area of ​​tubular structure ≥11300mm 2 .

6. The spacecraft light-shielding and air-releasing device according to claim 4, characterized in that: The size of the air release hole is based on the light reflection path requirements: In the most severe case where the light is not blocked by the sunshade, after entering the tubular structure, it will be unable to enter the aircraft platform bearing cylinder after a mirror reflection; The light in the most stringent case is the light on the line connecting the edge of the lens hood flange and the edge of the air release hole away from the bottom point of the lens hood.

7. A spacecraft light-shielding and air-releasing device according to claim 6, characterized in that: The size of the upper flange of the sunshade is designed based on the path of the light reflected once on the inner wall of the tubular structure of the sunshade under the most stringent conditions so that the light will not enter the bearing tube of the aircraft platform.

8. The spacecraft light-shielding and air-releasing device according to claim 5, characterized in that: The air release area of ​​the space between the flange and the tubular structure, the sum of the areas of all the air release holes on the tubular structure, and the cross-sectional area of ​​the tubular structure are the same.

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