Combined gyro support for spacecraft cabin

Abstract

This invention provides a combined gyroscope support for use inside a spacecraft cabin, comprising a gyroscope support body, a support bracket, and a cube mirror adapter bracket. Both the support bracket and the cube mirror adapter bracket are threadedly fastened to the gyroscope support body. The cube mirror adapter bracket transforms the cube mirror matrix relationship of the dual-float gyroscope equipment onto the cube mirror of the mounting bracket, solving the problem of optical path obstruction during precision measurement after the equipment is loaded onto the cabin, thus improving the feasibility of spacecraft precision measurement. The support bracket is installed on both sides of the gyroscope support body, providing adjustment margins during equipment installation and commissioning, and meeting the high-precision installation position relationships between the installed equipment. This invention adopts an integrated installation and integrated precision measurement method, overcoming the problem of optical path obstruction during precision measurement after the equipment is loaded onto the cabin, meeting the high-precision multi-constraint requirements between equipment, improving the feasibility of spacecraft precision measurement, and providing reliable support for the installed equipment. It has broad application prospects in the field of spacecraft and other related fields.

Description

Technical Field

[0001] This invention relates to the field of spacecraft overall design, and in particular to a combined gyroscope support for use inside a spacecraft cabin. Background Technology

[0002] Gyroscopes are the core sensors of the inertial measurement units (IMUs) of modern spacecraft, used to precisely measure the spacecraft's rotation angle around its own axis. In manned space missions, gyroscopes are an important component of the navigation system, precisely controlling the spacecraft's approach attitude and angular velocity.

[0003] According to mission requirements, two devices, a dual-plane gyroscope and a fiber optic gyroscope, need to be installed inside the spacecraft cabin. The dual-plane gyroscope's three-axis alignment requires high installation accuracy relative to the spacecraft cabin structural reference, while the fiber optic gyroscope's three-axis alignment requires high installation accuracy relative to the dual-plane gyroscope. The dual-plane gyroscope is mounted on an equipment mounting plate inside the spacecraft cabin, and its accuracy measurement optical path is constrained by its installation location and equipment layout, necessitating the ensuring rationality and feasibility of the spacecraft's accuracy measurement scheme. Simultaneously, the installation accuracy requirements and installation stability of the two gyroscope devices must be considered.

[0004] Based on the above requirements and current situation, a combined gyroscope support design that can be used inside a spacecraft cabin was proposed.

[0005] This modular support system adopts an overall installation and overall precision measurement design, which provides reliable support for the gyroscope assembly while improving the feasibility of precision measurement inside the spacecraft cabin and meeting the technical requirements of high precision and multiple constraints. Summary of the Invention

[0006] The purpose of this invention is to provide a modular gyroscope support for use inside a spacecraft cabin, which improves the feasibility of accurate spacecraft measurements while ensuring the high-precision constraint installation requirements between gyroscope assembly devices. The technical solution of the present invention is to provide a combined gyroscope bracket for use in a spacecraft cabin, including a gyroscope bracket body, a surface bracket, and a cube mirror adapter bracket.

[0007] Preferably, the combined gyroscope bracket is designed with a cubic mirror adapter bracket, which transforms the cubic mirror matrix relationship of the dual-floating gyroscope equipment onto the cubic mirror of the mounting bracket, solving the problem of optical path obstruction for precision measurement after the equipment is mounted on the upper deck, and improving the feasibility of spacecraft precision measurement.

[0008] Preferably, the combined gyroscope bracket is designed with three support brackets installed on both sides of the gyroscope bracket assembly, providing adjustment margin during equipment installation and commissioning, and meeting the high-precision installation position relationship between the installed equipment.

[0009] Preferably, the gyroscope bracket body has four pre-drilled mounting holes for lifting rings. After the gyroscope assembly is installed on the ground, a special lifting tool is used to install the equipment and the combined gyroscope bracket onto the equipment mounting plate inside the spacecraft cabin. Before installing the two gyroscopes into the cabin, the accuracy relationship between them has been ensured, reducing the difficulty of measuring the accuracy of the equipment on board.

[0010] Preferably, after the equipment and gyroscope bracket assembly are installed in place inside the cabin, the cube mirror on the cube mirror adapter bracket of the combined gyroscope bracket is measured with a theodolite through the precision measurement hole on the spacecraft cabin skin, and compared with the spacecraft structural reference to ensure that the installation accuracy of the two floating gyroscopes relative to the spacecraft cabin structure meets the requirements.

[0011] Compared with the prior art, the beneficial effects of the present invention are as follows: 1) Due to the limitations of its installation position and equipment layout, the optical path for precision measurement is blocked in the cubic mirror of the two-floating gyroscope in this invention. In order to ensure the feasibility of precision measurement, a cubic mirror adapter bracket is designed to realize the transformation of the precision measurement relationship of the reference measurement coordinate system of the two-floating gyroscope cubic mirror.

[0012] 2) Before the combined gyroscope bracket is installed in the upper cabin, the overall precision measurement method is adopted. First, the fiber optic gyroscope and the dual-float gyroscope are installed on the combined gyroscope bracket. The precision measurement of the fiber optic gyroscope and the dual-float gyroscope cubic mirror is carried out on the ground. After meeting the design requirements, the combined gyroscope bracket is then installed as a whole on the spacecraft equipment mounting plate. This reduces the difficulty of precision measurement between equipment after the upper cabin and improves the feasibility of spacecraft precision measurement.

[0013] 3) In this invention, three support brackets are designed. When the ground fiber optic gyroscope and the dual-float gyroscope are installed in the combined gyroscope bracket and the accuracy measurement is performed, the mounting screws on the support brackets are tightened while fine-tuning is performed to provide an adjustable margin to ensure that the installation accuracy between the two devices meets the design requirements.

[0014] 4) In this invention, the combined gyroscope bracket adopts an overall installation method. The bracket body is provided with 4 lifting ring installation interfaces. The bracket is installed in place on the ground, and the combined gyroscope bracket is hoisted onto the spacecraft equipment mounting plate using slings. Attached Figure Description

[0015] The invention will be further described below with reference to the accompanying drawings: Figure 1 This is a schematic diagram illustrating the accuracy measurement principle of the combined gyroscope support according to a preferred embodiment of the present invention. Figure 2 This is a schematic diagram of the combined gyroscope support structure according to a preferred embodiment of the present invention; Figure 3 This is a schematic diagram of the installation of a combined gyroscope bracket according to a preferred embodiment of the present invention; Figure 4This is a schematic diagram illustrating the ground precision measurement principle of the combined gyroscope support according to a preferred embodiment of the present invention. Wherein: 1-Gyroscope support assembly body; 2-Surface support. 3-Hanging ring 4-Cube mirror adapter bracket Detailed Implementation

[0016] The combined gyroscope support for spacecraft cabins proposed in this invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of this invention will become clearer from the following description and claims. It should be noted that the drawings are all in a very simplified form and use non-precise ratios, and are only used to facilitate and clarify the illustration of the embodiments of this invention.

[0017] like Figure 2 and Figure 3 As shown, a modular gyroscope support design for use inside a spacecraft cabin includes a modular gyroscope support body 1, a cubic mirror adapter bracket 4, a hanging ring 3, a support bracket 2, and fasteners for installation.

[0018] The support bracket 2, the hanging ring 3, the cubic mirror adapter bracket 4, and the combined gyroscope bracket body 1 are connected by threads.

[0019] Before installing the combined gyroscope bracket 1 on the upper cabin, the two devices are installed as a whole on the combined gyroscope bracket, and three support brackets 2 are installed. The theodolite is used to measure the cubic mirror of the two gyroscope devices and the cubic mirror of the cubic mirror adapter bracket. During the accuracy measurement, the mounting screws of the three support brackets are finely adjusted until the installation accuracy index of the three axes of the fiber optic gyroscope relative to the two-floating gyroscope is met. Then, the screws of the support brackets are tightened with glue, and the matrix relationship between the cubic mirror of the two-floating gyroscope and the cubic mirror on the cubic mirror bracket is recorded.

[0020] Before the combined gyroscope bracket is installed on the cabin, four lifting rings are installed to attach the two devices and the combined gyroscope bracket as a whole to the spacecraft equipment mounting plate.

[0021] like Figure 1 As shown, to verify the feasibility of overall ship accuracy, precision measurement holes were drilled at the corresponding positions of the cube mirror accuracy measurement optical path on the cube mirror adapter bracket of the spacecraft cabin wall. The accuracy relationship between the cube mirror on the cube mirror adapter bracket and the cube mirror of the spacecraft cabin structure was measured with a theodolite. While measuring, shims were added to the fastening screws of the combined gyroscope bracket and the equipment mounting plate for adjustment until the installation accuracy requirements of the three axes of the two floating gyroscope relative to the spacecraft cabin structure reference were met.

[0022] The contents not described in detail in this specification are prior art known to those skilled in the art. It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

Claims

1. A combined gyroscope support for use inside a spacecraft cabin, characterized in that, Includes the gyroscope support body, the surface support, and the cube mirror adapter bracket; Both the surface support bracket and the cubic mirror adapter bracket are fastened to the gyroscope bracket body by threaded connection. The cubic mirror adapter bracket transforms the cubic mirror matrix relationship of the dual-floating gyroscope equipment onto the cubic mirror of the mounting bracket, solving the problem of optical path obstruction for precision measurement after the equipment is mounted on the upper deck, and improving the feasibility of spacecraft precision measurement. The mounting brackets are installed on both sides of the gyroscope bracket body, providing adjustment margin during equipment installation and testing to meet the high-precision installation position relationship between the installed equipment.

2. The combined gyroscope support for use inside a spacecraft cabin as described in claim 1, characterized in that, The number of the approach supports is three. Before the combined gyroscope bracket is installed in the upper cabin, the fiber optic gyroscope and the dual-float gyroscope are installed as a whole on the combined gyroscope bracket, and three approach supports are installed. The theodolite is used to measure the cubic mirror of the two gyroscope devices and the cubic mirror of the cubic mirror adapter bracket. During the accuracy measurement, the mounting screws of the three approach supports are finely adjusted until the installation accuracy index of the three axes of the fiber optic gyroscope relative to the dual-float gyroscope is met. The screws of the approach supports are then glued and tightened, and the matrix relationship between the cubic mirror of the dual-float gyroscope and the cubic mirror on the cubic mirror bracket is recorded. Then the combined gyroscope bracket is installed as a whole on the spacecraft equipment mounting plate, which reduces the difficulty of accuracy measurement between equipment after the upper cabin.

3. The combined gyroscope support for use inside a spacecraft cabin as described in claim 2, characterized in that, The gyroscope bracket body has four pre-drilled mounting holes for lifting rings. After the gyroscope assembly is installed on the ground, the two gyroscope devices and the combined gyroscope bracket are mounted on the equipment mounting plate inside the spacecraft cabin using a special lifting tool through the lifting rings.

4. The combined gyroscope support for use inside a spacecraft cabin as described in claim 3, characterized in that, After the two gyroscope devices and the combined gyroscope bracket are installed in the cabin, the theodolite is used to measure the cubic mirror on the cubic mirror adapter bracket of the combined gyroscope bracket through the precision measurement hole on the spacecraft cabin skin. The measurement is then compared with the spacecraft structural reference to ensure that the installation accuracy of the two floating gyroscopes relative to the spacecraft cabin structure meets the requirements.

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