Large equipment cross-structure installation precision control and final assembly method

Abstract

The invention discloses a large-scale equipment cross-structure installation precision control and final assembly method, which comprises the following steps: investigating spacecraft configuration and equipment layout design, and determining a precision index; in the structure assembling stage, position errors and form and position errors of upper and lower mounting surfaces of each structure and an equipment mounting surface are controlled; in the bracket assembling stage, the mounting precision of the bracket on the structure and the position error and the form and position error of the equipment mounting interface on the bracket are controlled; in the whole device final assembly stage, the position and angle errors between the structure 1 and the structure 2 are controlled in a positioning pin adaptation mode, the structure 3 is adjusted according to the relative positions and form and position error measurement results of the equipment installation interfaces on different structures, and the equipment installation interfaces on the different structures are controlled to be matched; and an equipment installation stage. According to the method, multiple precision control measures are implemented in each stage of spacecraft development, high-efficiency, high-reliability and stress-free installation of the large-scale equipment under multi-connection-point and cross-structure layout is ensured, and the method has a great application prospect in cross-structure installation of the large-scale equipment.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a large-scale equipment cross-structure installation precision control and assembly method. Background Art

[0002] In the aerospace field, spacecraft are generally divided into multiple compartments according to their missions or functional positioning, and equipment is usually installed on the main cabin structure or a single box panel of a certain compartment. However, due to the coupling of multiple factors such as the available space of the carrier fairing, equipment layout, equipment dimensions, and main structure dimensions, some equipment still has the need for cross-structure installation. In particular, some large equipment, such as large antennas, solar wings, robotic arms and other deployable mechanisms, are generally in a retracted state before launch, and have the characteristics of large dimensions and a large number of connection points. The cross-structure installation of large equipment involves the main structure, equipment, brackets and other products themselves, as well as all installation links and multiple error types. How to ensure the precision matching and coordination between the installation interfaces on different compartments or structures, and realize the efficient, reliable, and stress-free installation of large equipment across structures is an extremely complex precision assurance problem faced during the assembly of spacecraft. Summary of the invention

[0003] The purpose of the present invention is to provide a large-scale equipment cross-structure installation precision control and assembly method to meet the needs of high-efficiency, high-reliability and stress-free installation of large-scale equipment across the structure.

[0004] In order to solve the above technical problems, the technical solution of the present invention is to provide a large-scale equipment cross-structure installation precision control and assembly method, comprising the following steps:

[0005] Step S1: Investigate the spacecraft configuration and equipment layout design, clarify the distribution of solar wing 6 connection points, assembly links and assembly constraints, and determine the accuracy index based on the error transmission link;

[0006] Step S2: In the structural assembly stage, the flatness of the mounting surfaces of the first structure 1, the second structure 2, and the third structure 3, the parallelism, coaxiality, and distance tolerance between the upper and lower mounting surfaces, and the position and posture errors of the equipment mounting surfaces relative to the structural reference of this level are controlled by combined processing;

[0007] Step S3: During the bracket assembly stage, the bracket mounting holes are adapted to the positioning pins to achieve precision control of the equipment mounting bracket 4 being installed on the first structure 1; the structure and the bracket are combined and processed as a whole to form an equipment mounting interface on the bracket, and the mounting hole position error, the distance error between multiple mounting surfaces, the flatness and parallelism of the assembly are controlled;

[0008] Step S4: In the overall assembly stage, the pin holes on the lower mounting surface of the second structure 2 are matched with the positioning pins on the upper mounting surface of the first structure 1 to control the lateral position error and the in-plane torsion error between the two docking structures; when the driving mechanism 5 is installed on the third structure 3, the center position of the solar wing mounting surface is measured and adjusted to meet the requirements; when the driving mechanism 5 is docked with the third structure 3, the position and posture of the device mounting interface on the third structure 3 relative to the device mounting interface on the first structure 1 are measured by a laser tracker, and the third structure 3 is adjusted in the form of gaskets and waist-shaped holes to control the relative error between the target mounting interfaces on different structures;

[0009] Step S5: During the equipment installation phase, the spacecraft attitude is adjusted using tooling until the horizontality of the equipment installation surface is better than 0.1°; the equipment is installed in a hanging and falling manner, and during the connection and tightening process, precision adjustments are made by adding adjustment gaskets and using the gap between screws and installation through holes to ensure stress-free installation of multiple connection points of the equipment.

[0010] Furthermore, in step S1, the spacecraft is a first structure 1, a second structure 2, and a third structure 3 configured in series, and the solar wing 6 is arranged on the side wall of the spacecraft across the structure. One end of the solar wing 6 is connected to the driving mechanism 5 installed on the third structure 3, and the other end is connected to the equipment mounting bracket 4 on the first structure 1 through multiple connection points, and the distance between the connection point 1-1 and the connection point 5-1 is greater than 3m.

[0011] Furthermore, in the step S2, during the structural assembly stage, the flatness of the upper docking surface of the first structure 1, the upper docking surface and the lower docking surface of the second structure 2 are controlled to be no more than 0.2 mm through combined processing; the distance tolerance of the upper and lower docking surfaces of the second structure 2 is no more than 0.5 mm, the coaxiality is no more than 0.3 mm, and the parallelism is no more than 0.5 mm; the flatness of the lower docking surface of the third structure 3 is no more than 0.2 mm, and the flatness of the driving mechanism mounting surface is no more than 0.02 mm; the flatness of the cabin mounting surface of the driving mechanism 5 is no more than 0.02 mm, and the distance error between the cabin mounting surface and the solar wing mounting surface is no more than 0.2 mm, and the parallelism is no more than 0.2 mm.

[0012] Furthermore, the equipment installation bracket adopts a truss-type integral bracket, and a machining allowance of not less than 3 mm is reserved on the upper surface of the bracket.

[0013] Furthermore, when the bracket mounting surface is assembled and processed, the upper docking surface of the first structure 1 and its quadrant scale lines are used as references to control the position and attitude accuracy of the mounting interface of the connection point 1-1; the remaining connection points are based on the connection point 1-1, and the flatness of the mounting surfaces of each connection point on the processing control equipment mounting bracket 4 is not greater than 0.02mm, the longitudinal and lateral distance errors of the center of the mounting surface relative to the connection point 1-1 are not greater than 0.1mm, the parallelism of the mounting surface is not greater than 0.12mm, and the mounting hole position error is within the range of ±0.1mm.

[0014] The beneficial effects of the large-scale equipment cross-structure installation precision control and assembly method provided by the present invention are:

[0015] 1) The present invention provides an effective, efficient, and reliable precision control and assembly solution for the cross-structure layout of large equipment, reducing the constraint coupling between the layout of large equipment and the spacecraft configuration;

[0016] 2) When different structures with equipment installation interfaces are connected, the present invention performs precision adjustment of structure assembly with the goal of ensuring that the relative posture accuracy between the equipment installation interfaces meets the requirements, thereby reducing the precision measurement items and time between structures, improving the assembly efficiency between structures, and effectively reducing the accumulation of precision measurement errors and the risk of insufficient subsequent equipment installation accuracy;

[0017] 3) The horizontal equipment installation surface and the equipment hanging and falling installation method adopted by the present invention are simple and reliable, which effectively reduces the adverse effects of the spacecraft configuration and parking posture on the equipment installation surface accuracy and the safety of assembly operations. At the same time, the horizontal posture of the equipment installation surface facilitates large-scale mechanical equipment to be verified by zero-gravity tooling on the cabin deployment test, ensuring the reliable deployment and operation of large equipment in orbit. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The invention will be further described below in conjunction with the accompanying drawings:

[0019] Figure 1 This is a schematic diagram of the installation of a solar wing span structure for a spacecraft;

[0020] Figure 2 This is a schematic diagram of the distribution of solar wing connection points for a spacecraft;

[0021] Description of Reference Numerals

[0022] 1 is structure 1, 2 is structure 2, 3 is structure 3, 4 is the equipment mounting bracket, 5 is the driving mechanism, and 6 is the solar wing. The X direction refers to the height direction of the structure, and the Y direction refers to the normal direction of the mounting surface of the solar wing 6. The number before the "-" in the solar wing connection point number is the structure number, and the number after the "-" indicates the connection point number on the structure. DETAILED DESCRIPTION

[0023] The following is a further detailed description of the large equipment cross-structure installation precision control and assembly method proposed by the present invention in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become clearer according to the following description and claims. It should be noted that the accompanying drawings are all in a very simplified form and use non-precise ratios, which are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention.

[0024] like Figure 1-2 As shown, the present invention is a large-scale equipment cross-structure installation precision control and assembly method, comprising the following steps:

[0025] Step 1: Investigate the spacecraft configuration and equipment layout design, clarify the distribution of solar wing 6 connection points, assembly links and assembly constraints, and determine the relevant accuracy indicators of structure 1-3, equipment mounting bracket 4, and drive mechanism 5 based on the error transmission link;

[0026] Step 2: During the structural assembly stage, the flatness of the upper docking surface of structure 1, the upper docking surface of structure 2 and the lower docking surface is controlled to be no more than 0.2mm through combined processing; the distance tolerance of the upper and lower docking surfaces of structure 2 is no more than 0.5mm, the coaxiality is no more than 0.3mm, and the parallelism is no more than 0.5mm; the flatness of the lower docking surface of structure 3 is no more than 0.2mm, the flatness of the driving mechanism mounting surface is no more than 0.02mm, and the center distance of the mounting surface is controlled according to the negative tolerance; the flatness of the cabin mounting surface of the driving mechanism 5 is no more than 0.02mm, the distance error between the cabin mounting surface and the solar wing mounting surface is no more than 0.2mm, and the parallelism is no more than 0.2mm.

[0027] Step three: During the bracket assembly stage, the bracket mounting holes are used to adapt the positioning pins to achieve precision control of the equipment mounting bracket 4 installed on the structure 1; when there are many connection points distributed on the structure, the structure and the bracket are combined to form the equipment installation interface, and the upper docking surface of the structure 1 and its quadrant scale are used as the reference to control the position and posture accuracy of the installation interface on the connection point 1-1. With the connection point 1-1 as the reference, the flatness of the mounting surface of each connection point on the equipment mounting bracket 4 is controlled to be no greater than 0.02mm, the longitudinal and lateral distance errors of the center of the mounting surface relative to the connection point 1-1 are no greater than 0.1mm, the parallelism of the mounting surface is no greater than 0.12mm, and the position error of the mounting hole is within the range of ±0.1mm;

[0028] Step 4: During the assembly of the whole device, the pin holes on the lower mounting surface of structure 2 are matched with the positioning pins on the upper mounting surface of structure 1 to control the lateral position error and in-plane torsion error between the two docking structures; when the drive mechanism 5 is installed on the structure 3, the center position of the solar wing mounting surface 5-1 is measured and adjusted to meet the requirements; the drive mechanism 5 is docked with the structure 1-2 as a whole along with the structure 3. Before docking, a gasket of appropriate thickness is added between the two structures according to the measured results of the x-direction distance of the connection point 5-1 on the structure 3 and the distance between the upper and lower docking surfaces of the structure 2. During the docking, the relative position and posture between the device mounting interface on the structure 3 and the structure 1 are measured by a laser tracker, and the installation posture of the structure 3 is adjusted by the waist-shaped hole gap, and the longitudinal and lateral distance errors between the center of the mounting surface of the connection point 1-1 on the structure 1 and the center of the solar wing mounting surface 5-1 on the structure 3 are controlled to be no more than 0.1 mm;

[0029] Step 5: During the equipment installation phase, use tooling to adjust the spacecraft's attitude until the horizontality of the equipment installation surface is better than 0.1°; the equipment is installed in a hanging and falling manner, and during the connection and tightening process, precision adjustments are made by adding adjustment gaskets and using the gap between screws and mounting holes to ensure stress-free installation of multiple connection points of the equipment.

[0030] Specifically, a certain spacecraft has a serial configuration of structure 1, structure 2, and structure 3, and a solar wing 6 is arranged on the side wall of the spacecraft across the structure. One end of the solar wing 6 is connected to a driving mechanism 5 installed on structure 3, and the other end is connected to an equipment mounting bracket 4 on structure 1 through multiple connection points, and the distance between connection point 1-1 and connection point 5-1 is greater than 3m.

[0031] Specifically, the equipment installation bracket adopts a truss-type integral bracket to control the relative deformation between the connection points, and a machining allowance of no less than 3 mm is reserved on the upper surface of the bracket.

[0032] The contents not described in detail in this specification belong to the prior art known to those skilled in the art. It is obvious 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 present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention.

Claims

1. A large-scale equipment cross-structure installation precision control and assembly method, characterized in that: The steps include: Step S1: Investigate the spacecraft configuration and equipment layout design, clarify the solar wing (6) connection point distribution, assembly links and assembly constraints, and determine the accuracy index based on the error transmission link; Step S2: During the structural assembly stage, the flatness of the mounting surfaces of the first structure (1), the second structure (2), and the third structure (3), the parallelism, coaxiality, and distance tolerance between the upper and lower mounting surfaces, and the position and posture errors of the mounting surfaces of the equipment relative to the structural reference of the current level are controlled by combined processing; Step S3: During the bracket assembly stage, the bracket mounting holes are adapted to the positioning pins to achieve precision control of the equipment mounting bracket (4) mounted on the first structure (1); the structure and the bracket are combined and processed as a whole to form an equipment mounting interface on the bracket, and the mounting hole position error, the distance error between multiple mounting surfaces, the flatness and parallelism of the assembly are controlled; Step S4: During the assembly of the whole device, the pin holes on the lower mounting surface of the second structure (2) are matched with the positioning pins on the upper mounting surface of the first structure (1) to control the lateral position error and the in-plane torsion error between the two docking structures; when the driving mechanism (5) is installed on the third structure (3), the center position of the solar wing mounting surface is measured and adjusted to meet the requirements; when the driving mechanism (5) is docked with the third structure (3), the position and posture of the device mounting interface on the third structure (3) relative to the device mounting interface on the first structure (1) are measured by a laser tracker, and the third structure (3) is adjusted in the form of gaskets and waist-shaped holes to control the relative error between the target mounting interfaces on different structures; Step S5: During the equipment installation phase, the spacecraft attitude is adjusted using tooling until the horizontality of the equipment installation surface is better than 0.1°; the equipment is installed in a hanging and falling manner, and during the connection and tightening process, precision adjustments are made by adding adjustment gaskets and using the gap between screws and installation through holes to ensure stress-free installation of multiple connection points of the equipment.

2. The large equipment cross-structure installation precision control and assembly method according to claim 1, characterized in that: In step S1, the spacecraft is a first structure (1), a second structure (2), and a third structure (3) in series, and the solar wing (6) is arranged on the side wall of the spacecraft across the structure. One end of the solar wing (6) is connected to a driving mechanism (5) installed on the third structure (3), and the other end is connected to an equipment mounting bracket (4) on the first structure (1) through multiple connection points, and the distance between the connection point (1-1) and the connection point (5-1) is greater than 3m.

3. The large equipment cross-structure installation precision control and assembly method according to claim 1, characterized in that: In the step S2, during the structural assembly stage, the flatness of the upper docking surface of the first structure (1), the upper docking surface of the second structure (2) and the lower docking surface is controlled by combined processing to be no greater than 0.2 mm; the distance tolerance of the upper and lower docking surfaces of the second structure (2) is no greater than 0.5 mm, the coaxiality is no greater than 0.3 mm, and the parallelism is no greater than 0.5 mm; the flatness of the lower docking surface of the third structure (3) is no greater than 0.2 mm, and the flatness of the drive mechanism mounting surface is no greater than 0.02 mm; the flatness of the cabin mounting surface of the drive mechanism (5) is no greater than 0.02 mm, and the distance error between the cabin mounting surface and the solar wing mounting surface is no greater than 0.2 mm, and the parallelism is no greater than 0.2 mm.

4. The large-scale equipment cross-structure installation precision control and assembly method according to claim 1 is characterized in that: The equipment installation bracket adopts a truss-type integral bracket, and a machining allowance of not less than 3 mm is reserved on the upper surface of the bracket.

5. The large-scale equipment cross-structure installation precision control and assembly method according to claim 1, characterized in that: When the bracket mounting surface is combined and processed, the upper docking surface of the first structure (1) and its quadrant scale lines are used as references to control the position and attitude accuracy of the mounting interface of the connection point (1-1); the remaining connection points are based on the connection point (1-1), and the flatness of the mounting surface of each connection point on the processing control device mounting bracket (4) is not greater than 0.02mm, the longitudinal and lateral distance errors of the center of the mounting surface relative to the connection point (1-1) are not greater than 0.1mm, the parallelism of the mounting surface is not greater than 0.12mm, and the position error of the mounting hole is within the range of ±0.1mm.

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