A deployable space thermal isolation assembly for satellite optical remote sensing systems

Abstract

The application relates to a deployable space thermal isolation assembly specially designed for a satellite optical remote sensing system, and aims to solve the thermal isolation problem of a two-dimensional single pendulum mirror rotating table in a space environment. The assembly comprises the following key components: an aluminum alloy framework A which is composed of at least three independently rotatable and deployable framework units, each unit is equipped with an L-shaped hole structure which is accurately matched with a locking shaft to ensure the smooth locking and unlocking process; an aluminum alloy framework B which is a fixed supporting part of the assembly and is stably connected with a combined base; and the combined base is responsible for stably installing the whole thermal isolation assembly on the two-dimensional rotating table shaft system of the satellite to ensure the stability and range control during work. The application realizes the functions of efficient folding and locking before launching, autonomous unlocking and deploying after entering an orbit and self-locking after deploying, and significantly improves the flexibility and reliability of space application.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of thermal isolation, and particularly relates to a deployable space thermal isolation assembly for a satellite optical remote sensing system, which is mainly used for space thermal isolation of a single pendulum mirror type two-dimensional rotary table to reduce the influence of space external heat flow on the optical performance of a lens. BACKGROUND

[0002] A thermal isolation cover is an important component of a satellite optical remote sensing system, and is mainly used for shielding the lens from the lens deformation caused by the large thermal variation difference of the outside world, so as to improve the imaging quality or detection performance. A conventional isolation cover is usually designed to be fixed in size and is processed into a shape by using metal or composite materials. However, in order to meet the use standard of the optical system, the size of the isolation cover is large, which not only leads to excessive occupation of space resources, but also increases the launch cost of the satellite. In particular, for a large-aperture isolation cover, its size is also limited by the rocket fairing.

[0003] In order to solve this challenge in space utilization, a deployable thermal isolation assembly emerges as the times require and becomes a key technology, which can be tightly folded before launch and reliably deployed after entering the orbit. At present, the deployable isolation covers on the market are mainly divided into three types: mechanism deployment type, inflation deployment type and self-deployment type. Among them, the mechanism deployment type isolation cover has many hinged units, a complex structure and needs an additional driving system to support the deployment process; the inflation deployment type isolation cover has light weight and large compression ratio, but its precision after deployment is often lacking, and at the same time, its system is also complex and needs an additional drive to assist the inflation process; the self-deployment type isolation cover does not need external driving force, has excellent compression ratio and can ensure high-precision positioning after deployment, which provides a strong guarantee for the performance of the optical system.

[0004] However, the existing deployable isolation covers still have the problems of complex structure system and large resource consumption in common, which to a great extent limit their wide application in optical systems, especially in small optical systems such as star sensors, and their application is greatly restricted. Therefore, it is of great significance to further optimize the design and improve the performance and efficiency of the deployable thermal isolation cover for promoting its wide application in the satellite optical remote sensing system. SUMMARY

[0005] In order to overcome the technical problems of complex structure, high resource consumption of the existing deployable heat shield and few heat isolation components for two-dimensional rotary tables, the application provides a deployable space heat isolation component for a satellite optical remote sensing system, which can realize functions such as folding and locking before launch into orbit, unlocking and self-deployment after launch into orbit, self-locking after deployment, and the like, has the characteristics of simple structure, light weight, small occupied launch space, high folding efficiency, no need for external driving in the deployment process, self-locking after deployment, and the like, and solves the space heat isolation problem of a two-dimensional single pendulum mirror rotary table.

[0006] The technical solution of the application is as follows:

[0007] A deployable space heat isolation component for a satellite optical remote sensing system, characterized in that it comprises:

[0008] An aluminum alloy framework A comprises at least three independently deployable framework units, each of which is provided with an L-shaped hole structure for cooperating with a locking shaft to realize locking and unlocking;

[0009] An aluminum alloy framework B is fixedly connected with a combined base and serves as a fixed part of the heat isolation component;

[0010] The combined base is used to be connected with both ends of the shaft system of a two-dimensional rotary table on the satellite, so as to ensure the installation stability and working range of the heat isolation component are not affected;

[0011] A bearing is installed in the aluminum alloy framework to support the rotation thereof;

[0012] A torsional spring is connected with at least one framework unit of the aluminum alloy framework A and serves as a deployment power source;

[0013] A framework shaft is connected with the combined base and serves as a limiting shaft during deployment of the aluminum alloy framework A;

[0014] A locking shaft cooperates with the tensile spring to realize folding and locking before launch into orbit and self-deployment and unlocking in orbit;

[0015] The tensile spring is connected at one end with the locking shaft and at the other end with a fixing mechanism and is used to assist locking and resetting;

[0016] The fixing mechanism cooperates with the tensile spring and is used for locking;

[0017] A steel wire rope is used to connect and pull the aluminum alloy framework A and the aluminum alloy framework B and realize self-deployment after unlocking;

[0018] A multilayer heat insulation component is laid between each of the framework units and between the aluminum alloy framework A and the aluminum alloy framework B and is used to reduce the influence of space external heat flow on the performance of optical lenses and to block light;

[0019] Limiting shafts for limiting the range of the heat isolation assembly after unfolding, penetrating through both ends of the combined base and fixed with the combined base.

[0020] Further, small holes are regularly arranged on the framework units, and the multi-layer heat insulation assembly is connected with the framework units through binding wires.

[0021] Further, the multi-layer heat insulation assembly is a four-layer heat covering, wherein the bottom film is polyimide, the first intermediate layer is polyester film, the second intermediate layer is nylon net, and the outer layer is a protective film and a surface film of double-sided aluminum-coated polyimide.

[0022] Further, the relative positions of the framework units are fixed through the cooperation of the steel wire ropes and the torsional springs, and the absolute positions of the framework units and the aluminum alloy framework B are fixed through the limiting shafts.

[0023] Further, the self-unfolding of the drive structure of the two-dimensional rotary table shaft system is realized through the tensile spring at one end, without additional power.

[0024] Further, the fixing mechanism is a long bolt.

[0025] Compared with the prior art, the beneficial effects of the present application are as follows:

[0026] 1) The present application proposes a new self-unfolding and locking mechanism, which realizes the automatic unfolding of the assembly after unlocking on the orbit and the compact folding before locking through the ingenious cooperation of elements such as steel wire ropes, locking shafts, tensile springs and torsional springs, thereby improving the space utilization and reducing the launch cost.

[0027] 2) The multi-layer heat insulation assembly and the light shielding function are integrated, which not only improves the heat insulation effect, but also avoids the interference of stray light on the optical system, realizes the maximum utilization of function and optimization of performance.

[0028] 3) Through the use of high-vacuum perfluoropolyether lubricating grease and special material selection, the adaptability and stability of the assembly in extreme harsh environment conditions are improved, which provides a strong guarantee for the long-term stable operation of the space optical system.

[0029] 4) It is ensured that the heat isolation assembly will not affect the working range of the optical mirror after unfolding, and the integrity and accuracy of the optical system are maintained, which provides a new idea and method for the design and application of the space optical system. BRIEF DESCRIPTION OF DRAWINGS

[0030] Fig. 1 It is a folding and locking state diagram of the present application for the deployable space heat isolation assembly of the satellite optical remote sensing system.

[0031] Fig. 2The figure is a schematic diagram of the unfolding process of the satellite optical remote sensing system deployable space thermal isolation assembly of the present application;

[0032] Fig. 3 The figure is a schematic diagram of the unfolded state of the satellite optical remote sensing system deployable space thermal isolation assembly of the present application;

[0033] Fig. 4 The figure is a three-view diagram of the satellite optical remote sensing system deployable space thermal isolation assembly of the present application;

[0034] Fig. 5 The figure is a partial enlarged view of the satellite optical remote sensing system deployable space thermal isolation assembly of the present application;

[0035] In the figure: 1 - aluminum alloy skeleton A; 2 - aluminum alloy skeleton B; 3 - combined base; 4 - bearing; 5 - torsion spring; 6 - skeleton shaft; 7 - locking shaft; 8 - tension spring; 9 - bolt; 10 - steel wire rope; 11 - multilayer thermal insulation assembly; 12 - limiting shaft. DETAILED DESCRIPTION

[0036] The present application will be further described below in conjunction with the embodiments and the accompanying drawings, but the protection scope of the present application should not be limited thereby.

[0037] Reference Figs. 1-4 The figure is a schematic diagram of the structure of the satellite optical remote sensing system deployable space thermal isolation assembly of the present application. As can be seen from the figure, it comprises: aluminum alloy skeleton A1, aluminum alloy skeleton B2, combined base 3, bearing 4, torsion spring 5, skeleton shaft 6, locking shaft 7, tension spring 8, long bolt 9, steel wire rope 10, multilayer thermal insulation assembly 11 and limiting shaft 12. The multilayer thermal insulation assembly is connected with the aluminum alloy skeleton A1 and the aluminum alloy skeleton B2 in a threading manner, and the aluminum alloy skeleton A1 and the aluminum alloy skeleton B2 are connected with each other by the steel wire rope passing through the small holes at the middle positions of the two. The bearing 4 is embedded in the aluminum alloy skeleton A1 and the aluminum alloy skeleton B2, and the torsion spring is combined with the outermost aluminum alloy skeleton A1. The long bolt penetrates through one end of the combined base, the aluminum alloy skeleton A1, the torsion spring and the aluminum alloy skeleton B2 in sequence, and is screwed into the other end of the combined base, thereby ensuring the stability of the whole structure. One end of the tension spring is connected with the combined base by a screw, and the other end passes through the small hole on the locking shaft, thereby realizing the functions of stretching and locking. At the same time, the limiting shaft passes through both ends of the combined base, and is firmly fixed with the combined base by the threads at the bottom of the limiting shaft, thereby further enhancing the stability and reliability of the whole assembly.

[0038] When zero-seeking is performed at one end of the pitch axis system, the locking shafts on both sides are simultaneously pushed out, the skeletons are unfolded by the steel wire rope and the torsion spring, and the absolute position of the No. 1 aluminum alloy skeleton A and the relative positions of the No. 2 and No. 3 aluminum alloy skeletons A are ensured by the limiting shaft.

[0039] The embodiment realizes position limitation and unfolding of the framework through the L-shaped groove structure.

[0040] The combined base connects the deployable space thermal isolation assembly and the pitch axis system of the two-dimensional turntable, and ensures that the two-dimensional working range is not affected by the thermal isolation assembly.

[0041] The movable end support rod pushes out the locking shaft through the support rod at one end of the pitch axis system, realizes self-unfolding of the structure, and does not need additional power.

[0042] The working principle of the present application is as follows:

[0043] The combined base is used as the foundation, the multi-layer thermal isolation assembly 11 is connected with the three aluminum alloy frameworks A1 and one aluminum alloy framework B2 through wires, the three aluminum alloy frameworks A1 and the aluminum alloy framework B2 are connected through the steel wire rope 10 to realize unlocking and self-unfolding after entering the track, the multi-layer thermal isolation assembly reduces the influence of the space heat flow on the performance of the optical lens, and can also play a certain light shielding role to prevent the entry of stray light, the framework is assembled into the framework through the bearing 4 and is lubricated with high vacuum perfluoropolyether grease, so that the bearing jamming in the extremely harsh environment condition is prevented, the framework shaft 6 is sequentially assembled, the No. 1 aluminum alloy framework A1 needs to be assembled with the torsional spring 5 before being assembled, and the torsional spring 5 is used as the unfolding power after unlocking, the three aluminum alloy frameworks A1 are restored to the folded state, the locking shaft passes through the L-shaped hole structure, one end of the tension spring 8 is connected with the locking shaft 7, and the other end is connected with the long bolt 9, the locking of the assembly before entering the track is realized, finally, the limiting shaft 12 is assembled to realize the limitation of the thermal isolation range after unfolding, the thermal isolation assembly and the pitch axis system of the two-dimensional turntable are fixed, so that the thermal isolation assembly does not affect the working range of the mirror.

[0044] The present application has the characteristics of simple structure, light weight, small occupied launch area, high folding efficiency, no need for external driving in the unfolding process, self-locking after unfolding, shielding stray light and reducing space heat convection, etc.

Claims

1. A deployable space thermal isolation assembly for a satellite optical remote sensing system, characterized in that, The application relates to a heat isolation assembly for a satellite, which comprises the following components: an aluminum alloy frame A, which comprises at least three independently expandable frame units, each of which is provided with an L-shaped hole structure for cooperating with a locking shaft to realize locking and unlocking; an aluminum alloy frame B, which is fixedly connected with a combined base and serves as a fixed part of the heat isolation assembly; the combined base, which is used for connecting with both ends of an elevation shaft system of a two-dimensional turntable on the satellite to ensure the installation stability of the heat isolation assembly and the working range of the heat isolation assembly; bearings, which are installed in the aluminum alloy frame A and the aluminum alloy frame B to support the rotation thereof; a torsional spring, which is connected with at least one frame unit of the aluminum alloy frame A and serves as an expansion power source; a frame shaft, which is connected with the combined base and serves as a limiting shaft during expansion of the aluminum alloy frame A; a locking shaft, which cooperates with a tension spring to realize folding locking before launching into orbit and self-expansion unlocking in orbit; the tension spring, one end of which is connected with the locking shaft and the other end of which is connected with a fixing mechanism, and which is used for assisting locking and resetting; the fixing mechanism, which cooperates with the tension spring and is used for locking; a steel wire rope, which is used for connecting and pulling the aluminum alloy frame A and the aluminum alloy frame B to realize self-expansion after unlocking; a multilayer heat insulation assembly, which is laid between the frame units and between the aluminum alloy frame A and the aluminum alloy frame B and is used for reducing the influence of space external heat flow on the performance of optical lenses and shielding light; a limiting shaft, which is used for limiting the range of the heat isolation assembly after expansion and passes through both ends of the combined base and is fixed with the combined base; the aluminum alloy frame A is restored to a folded state, the locking shaft is inserted through the L-shaped hole structure to realize locking before launching into orbit, and the locking shaft is pushed out of the L-shaped hole structure through a supporting rod at one end of the elevation shaft system to realize self-expansion; the relative positions between the frame units are fixed through mutual cooperation of the steel wire rope and the torsional spring; and the absolute positions of the frame units and the aluminum alloy frame B are fixed through the limiting shaft. Small holes are equidistantly arranged on the frame units, and the multilayer heat insulation assembly is connected with the frame units through binding wires. The multilayer heat insulation assembly is a four-layer heat covering, wherein a bottom film is polyimide, a first intermediate layer is a polyester film, a second intermediate layer is a nylon net stack, and an outer layer is a protective film and a surface film of double-sided aluminum-plated polyimide. The fixing mechanism is a long bolt. ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ 2. The deployable thermal space isolation assembly of claim 1, wherein, ​ 3. The deployable thermal space isolation assembly of claim 2, wherein, ​ 4. The deployable thermal space isolation assembly of any of claims 1-3, wherein, ​

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