CN117268675A - Spacecraft equipment installation precision deviation compensation method - Google Patents

Spacecraft equipment installation precision deviation compensation method Download PDF

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Publication number
CN117268675A
CN117268675A CN202311220583.4A CN202311220583A CN117268675A CN 117268675 A CN117268675 A CN 117268675A CN 202311220583 A CN202311220583 A CN 202311220583A CN 117268675 A CN117268675 A CN 117268675A
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China
Prior art keywords
spacecraft
precision
test
cabin
equipment
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CN202311220583.4A
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Inventor
贾东永
付新卫
刘睿
韩修柱
彭喆
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Beijing Institute of Technology BIT
Beijing Institute of Spacecraft System Engineering
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Beijing Institute of Technology BIT
Beijing Institute of Spacecraft System Engineering
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Priority to CN202311220583.4A priority Critical patent/CN117268675A/en
Publication of CN117268675A publication Critical patent/CN117268675A/en
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
    • G01M7/02—Vibration-testing by means of a shake table
    • G01M7/06—Multidirectional test stands
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
    • G01M7/02—Vibration-testing by means of a shake table
    • G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
    • G01M7/02—Vibration-testing by means of a shake table
    • G01M7/025—Measuring arrangements
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M99/00—Subject matter not provided for in other groups of this subclass
    • G01M99/005—Testing of complete machines, e.g. washing-machines or mobile phones

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Testing Of Balance (AREA)

Abstract

The invention discloses a spacecraft equipment installation precision deviation compensation method, which comprises the following steps: in the initial sample stage, initial sample precision variation before and after initial sample mechanical test of the spacecraft is obtained; rechecking and adjusting the layout position and the secondary structure design of the equipment according to the initial sample precision variation; in the positive sample stage, the positive sample precision variation before and after the spacecraft positive sample mechanical test is obtained; determining a precision compensation value according to the positive sample precision variation; the method comprises the steps that precision measurement is carried out on equipment and a cabin before launching of a spacecraft, so that a precision measurement value before launching is obtained; and calculating to obtain the on-orbit precision according to the precision measurement value before transmission and the precision compensation value. By utilizing the scheme of the invention, the consistency of the installation precision of equipment on the spacecraft cabin body on the ground and on-orbit can be ensured.

Description

Spacecraft equipment installation precision deviation compensation method
Technical Field
The invention relates to the technical field of equipment installation, in particular to a spacecraft equipment installation precision deviation compensation method.
Background
In the on-orbit flight process of the spacecraft, related tasks such as intersection butt joint, orbit attitude control and the like are required to be completed by means of various position and attitude sensors. In order to ensure accurate completion of tasks, various sensors must meet the requirement of installation precision when the spacecraft is assembled, which can be achieved through ground assembly precision measurement, but in the process of launching the spacecraft, the equipment installation support and the cabin body can be caused to locally deform due to severe launching section vibration and noise environment, so that the installation precision of the equipment is changed, and the control precision of the GNC (Guidance Navigation Control ) and the measurement precision of the attitude sensor are affected. The installation accuracy of the equipment meeting the index requirements during ground refinement may cause serious consequences in the case that the installation accuracy exceeds the range of the installation accuracy index under the influence of the transmission section factors.
Disclosure of Invention
The invention provides a spacecraft equipment installation precision deviation compensation method, which aims to solve the problem that the installation precision of equipment on a spacecraft cabin is inconsistent between the ground and the on-orbit.
Therefore, the invention provides the following technical scheme:
a spacecraft equipment installation accuracy deviation compensation method, the method comprising:
in the initial sample stage, initial sample precision variation before and after initial sample mechanical test of the spacecraft is obtained;
rechecking and adjusting the layout position and the secondary structure design of the equipment according to the initial sample precision variation;
in the positive sample stage, the positive sample precision variation before and after the spacecraft positive sample mechanical test is obtained;
determining a precision deviation compensation value according to the positive sample precision variation;
after the spacecraft is just sample and the emission state is set, precision measurement is carried out on the equipment and the cabin body to obtain reference data;
and determining on-orbit data according to the reference data and the precision compensation value.
Optionally, the method further comprises:
in the initial sample stage, setting a state before the mechanical test of the spacecraft, and pasting mechanical sensors on the cabin, equipment and secondary structure;
the method comprises the steps that precision measurement is carried out on equipment and a cabin body before a spacecraft initial sample mechanical test, so that precision before the spacecraft initial sample mechanical test is obtained;
carrying out mechanical test on the spacecraft;
performing precision measurement on equipment and a cabin body after the initial sample mechanical test of the spacecraft to obtain the precision after the initial sample mechanical test of the spacecraft;
the initial sample precision variation before and after the initial sample mechanical test of the spacecraft is obtained comprises the following steps: and determining the initial sample precision variation according to the precision before the initial sample mechanical test of the spacecraft and the precision after the initial sample mechanical test of the spacecraft.
Optionally, the measuring the precision of the equipment and the cabin before the initial sample mechanics test of the spacecraft to obtain the precision before the initial sample mechanics test of the spacecraft includes:
installing a precise measurement cube mirror in a single cabin state of the spacecraft, establishing a structural coordinate system of a cabin body, and establishing a cabin body structure by taking the coordinate system as a reference;
the sensor is measured accurately in a single cabin state;
performing and completing cabin butt joint, and performing inter-cabin precision measurement in a whole machine state;
and integrating the precise measurement parameters of each measuring point into a first table to obtain the precision of the spacecraft before the initial sample mechanical test.
Optionally, the structural rigidity of the position where the precision cube mirror is installed in the single cabin state of the spacecraft is greater than or equal to the structural rigidity of other positions.
Optionally, the measuring the precision of the equipment and the cabin after the initial sample mechanics test of the spacecraft to obtain the precision after the initial sample mechanics test of the spacecraft includes:
after the initial sample mechanical test of the spacecraft, performing inter-cabin precision retesting in the whole spacecraft state;
after the accuracy retest of the whole device is completed, cabin segment decomposition is carried out, and the accuracy retest is carried out on the sensor in a single cabin segment state;
and assembling the precise measurement parameters of each measuring point into a second table to obtain the precision of the spacecraft after the initial sample mechanical test.
Optionally, the method further comprises:
in the sample correction stage, the whole device is modified by vibration environment test so that the quality characteristics of the whole device and equipment are covered in the quality characteristic range of the initial sample test and the emission state or kept consistent, and mechanical sensors are attached to the cabin body, the equipment and the secondary structure;
finishing test preparation work;
the method comprises the steps that precision measurement is carried out on equipment and a cabin body before a spacecraft positive sample mechanical test, so that precision before the spacecraft positive sample mechanical test is obtained;
carrying out a mechanical test on the spacecraft positive sample;
measuring the precision of equipment and a cabin body after the spacecraft positive sample mechanical test to obtain the precision after the spacecraft positive sample mechanical test;
the method for obtaining the positive sample precision variation before and after the spacecraft positive sample mechanical test comprises the following steps: and determining the positive sample precision variation according to the precision before the spacecraft positive sample mechanical test and the precision after the spacecraft positive sample mechanical test.
Optionally, mechanical sensors attached to the nacelle, equipment and substructure during the sample stage remain consistent with the sample stage.
Optionally, the measuring the precision of the equipment and the cabin before the spacecraft positive mechanics test to obtain the precision before the spacecraft positive mechanics test includes:
installing a precise measurement cube mirror in a single cabin section state of the spacecraft, establishing a structural coordinate system of a cabin body, and establishing a cabin body structure by taking the coordinate system as a reference;
the sensor is measured accurately in a single cabin state;
finishing the cabin section butt joint, and carrying out the precision measurement between cabin sections in the whole machine state;
and integrating the accurate measurement parameters of all the measuring points into a third table.
Optionally, the measuring the precision of the device and the cabin after the spacecraft positive mechanics test, and obtaining the precision after the spacecraft positive mechanics test includes:
after the spacecraft positive mechanics test, performing inter-cabin precision retesting in the whole spacecraft state;
after the accuracy retest of the whole device is completed, cabin segment decomposition is carried out, and the accuracy retest is carried out on the sensor in a single cabin segment state;
and assembling the precise measurement parameters of each measuring point into a fourth table to obtain the precision of the spacecraft after the positive mechanical test.
Optionally, the mechanical test comprises any one or more of: sinusoidal vibration test, noise test.
Optionally, the sinusoidal vibration test includes three test conditions: sinusoidal vibration of the whole device in the X direction; sinusoidal vibration of the whole device in Y direction; the whole device vibrates in a Z-direction sinusoidal manner, and the loading sequence of the test working conditions is Y-direction, Z-direction and X-direction in sequence; and each test working condition sequentially completes the noise test of the pre-vibration stage, the characteristic stage, the acceptance stage and the characteristic stage.
Optionally, the noise test comprises: pre-vibration stage, characteristic stage, acceptance stage and characteristic stage noise test.
According to the spacecraft equipment installation precision deviation compensation method provided by the invention, equipment installation precision deviation of a spacecraft caused by a vibration environment is compensated, equipment precision deviation compensation is implemented through two times of mechanical tests and multiple times of fine measurement in a spacecraft initial sample stage and a positive sample stage, equipment layout and installation secondary structure rigidity weak links are specifically identified through the mechanical tests in the initial sample stage, and equipment layout adjustment and secondary structure reinforcement design are carried out to solve the problem of large equipment installation precision change, so that a positive sample design state is determined; acquiring precision deviation of equipment before and after a test through a positive sample stage mechanical test, and acquiring a precision compensation value which is close to the vibration environment of a spacecraft launching section; the final accurate measurement before emission and the precision compensation are adopted, so that the installation precision of the equipment after the spacecraft enters the orbit is effectively ensured to meet the index requirement.
Drawings
FIG. 1 is a schematic block diagram of a spacecraft apparatus installation accuracy deviation compensation method provided by the present invention;
FIG. 2 is a flow chart of a spacecraft equipment installation accuracy deviation compensation method provided by the invention;
FIG. 3 is a flow chart of the process at the initial stage in the spacecraft installation accuracy deviation compensation method of the present invention;
fig. 4 is a flow chart of the process at the sample stage in the spacecraft installation accuracy deviation compensation method of the invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments will be briefly described below. It is apparent that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
In describing embodiments of the present invention, the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in terms of orientation or positional relationship shown in the drawings for convenience of description and simplicity of description only, and do not denote or imply that the devices or elements in question must have a particular orientation, be constructed and operated in a particular orientation, so that the above terms are not to be construed as limiting the invention.
The present invention will be described in detail below with reference to the drawings and the specific embodiments, which are not described in detail herein, but the embodiments of the present invention are not limited to the following embodiments.
The invention provides a spacecraft equipment installation precision deviation compensation method, which aims at compensating equipment installation precision deviation of a spacecraft caused by a vibration environment and implements equipment precision deviation compensation through two times of mechanical tests and multiple times of precise measurement in a spacecraft initial sample stage and a spacecraft positive sample stage.
As shown in fig. 1, the invention provides a schematic block diagram of a spacecraft equipment installation accuracy deviation compensation method.
Referring to fig. 1, in the initial sample stage, the method performs initial sample mechanical test on an initial sample product, namely a spacecraft initial sample, performs fine measurement on the initial sample before and after the initial sample mechanical test, identifies weak links of the spacecraft initial sample according to the fine measurement result of the initial sample, and performs recheck adjustment on equipment layout positions and secondary structure designs. In the positive sample stage, carrying out positive sample mechanical test on a positive sample product, namely a spacecraft positive sample, respectively carrying out accurate measurement on the positive sample before and after the positive sample mechanical test, determining the precision deviation compensation quantity according to the accurate measurement result of the positive sample, and carrying out precision measurement on the spacecraft positive sample before the spacecraft positive sample is transmitted after the transmission state is set, so as to obtain reference data; and finally, determining on-orbit data according to the reference data and the precision compensation value.
The specific process of the spacecraft equipment installation accuracy deviation compensation method provided by the invention is further described in detail below with reference to fig. 2.
Referring to fig. 2, fig. 2 is a flowchart of a spacecraft equipment installation accuracy deviation compensation method provided by the invention, which includes the following steps:
step 201, in the initial sample stage, initial sample precision variation before and after initial sample mechanical test of the spacecraft is obtained.
And 202, rechecking and adjusting the layout position and the secondary structure design of the equipment according to the initial sample precision variation.
In the embodiment of the invention, equipment with large precision variation can be subjected to layout adjustment or design reinforcement of the support substructure according to the initial sample precision variation.
Specifically, the accurate measurement data before and after the mechanical test is compared and analyzed, the layout position and the secondary structure design analysis and rechecking are carried out on the equipment with large precision variation, and the layout adjustment scheme and the secondary structure reinforcement scheme are determined.
And 203, in the positive sample stage, obtaining the positive sample precision variation quantity before and after the spacecraft positive sample mechanical test.
And 204, determining a precision deviation compensation value according to the positive sample precision variation.
Specifically, the precision measurement data before and after the mechanical test are subjected to comparative analysis to obtain the precision variation before and after the positive sample mechanical test, and the precision compensation value is obtained.
And 205, performing precision measurement on equipment and the cabin after the spacecraft is just in a sample state and the emission state is set, and obtaining reference data.
The accuracy measurement at this time mainly includes:
(1) The method mainly comprises the steps of measuring the precision of a sensor in a single cabin state of a launching field spacecraft, wherein the precision measurement of the sensor mainly comprises the control of the precision of the sensor and the precision of an attitude measurement sensor, and the installation precision of the sensor can be represented by measuring the relation between the sensor and a cabin;
(2) After the docking of the cabin sections is completed, the precision measurement between the cabin sections is carried out in the whole machine state, and the precision measurement is mainly carried out on the relation between the precision measurement cubic mirrors of the cabin sections.
The last fine measurement before the spacecraft launching is the adjustment measurement, the equipment precision is required to be adjusted to be within the precision index requirement range, and the tolerance between the equipment precision and the index is required to be larger than the precision deviation compensation value acquired before and after the positive mechanical test.
In a specific application, the device position and angle data measured by the last adjustment before transmission can be used as spacecraft control parameters to be input into a software system.
And 206, determining on-orbit data according to the reference data and the precision compensation value.
Specifically, the on-orbit equipment precision value after the transmission of the spacecraft can be calculated according to the last precision measurement data before the transmission of the transmission field and by combining the precision compensation values acquired before and after the positive mechanical test. In addition, the calculated on-orbit precision value of the spacecraft is checked again, and the on-orbit precision value is confirmed to be within the technical index requirement.
The mechanical test is needed for both the initial sample and the positive sample of the spacecraft, and the precise test is needed for the spacecraft before and after the mechanical test.
The detailed procedures of the preliminary stage and the positive stage are described in detail below, respectively.
As shown in fig. 3, the process flow chart of the initial sample stage in the spacecraft equipment installation accuracy deviation compensation method of the invention comprises the following steps:
step 301, in the initial sample stage, setting a state before the mechanical test of the spacecraft integral unit, and pasting mechanical sensors on the cabin body, equipment and secondary structure. The secondary structure refers to a bracket structure connecting the device and the spacecraft body. The device refers to an electronic stand-alone unit mounted on an aerospace vehicle.
In general, after the spacecraft assembly and comprehensive test are completed in the initial sample stage, the mechanical test modification of the spacecraft whole device is carried out to ensure that the quality characteristics of the whole device and equipment cover the quality characteristic range of the positive sample and the emission state or keep the quality characteristics consistent. In the preliminary stage, the apparatus may be replaced with a structural member in conformity with the state of the sample.
In the embodiment of the invention, mechanical sensors can be stuck to the spacecraft cabin, equipment and support substructure according to the requirements of the mechanical test outline and the mechanical test point; the mechanical test measuring points should be considered to cover comprehensively, and especially the backup measuring points should be considered for the areas with weaker rigidity.
Before the precision measurement is performed, test equipment debugging, test site safety state confirmation, comprehensive test preparation and other test preparation works are also required to be completed, so that the test process is ensured not to be interrupted due to test problems.
And 302, measuring the precision of equipment and a cabin body before the initial sample mechanical test of the spacecraft to obtain the precision before the initial sample mechanical test of the spacecraft.
Specifically, in one non-limiting embodiment, the accuracy measurement may be made as follows:
firstly, installing a precision measurement cube mirror in a single cabin section state of an aircraft, establishing a structural coordinate system of a cabin body, and establishing a cabin body structure by taking the structural coordinate system as a reference;
then, the precision measurement is carried out on the sensor in a single cabin state, wherein the precision measurement mainly comprises the precision of measuring and controlling the measuring sensor and the attitude measuring sensor, the specific measurement mode is required to be determined according to the precision measurement technical requirement and the flow, and the embodiment of the invention is not limited;
then, docking of cabin sections is carried out and completed, and precision measurement among the cabin sections is carried out in a whole machine state, wherein the precision measurement is mainly carried out on the relation among the precision measurement cubic mirrors among the cabin sections;
and finally, integrating the precise measurement parameters of each measuring point into a first table to obtain the precision of the spacecraft before the initial sample mechanical test.
The structural rigidity of the position where the precise measurement cube mirror is installed in the single cabin of the spacecraft is larger than or equal to the structural rigidity of other positions, so that the problem that the accuracy of the cube mirror is poor due to the fact that the cabin rigidity of the installation position of the cube mirror is weak is solved, and the cube mirror cannot be used as a precise measurement reference. In addition, in the actual development process, the work of installing the precision cube mirror and establishing the structural coordinate system of the cabin body can be implemented in the final assembly stage, and the embodiment of the invention is not limited.
The states of equipment, a support substructure, a mechanical sensor and the like are also required to be checked in the state of a single cabin section, and the fact that no looseness phenomenon exists is confirmed;
in addition, for the accurate measurement of the sealed cabin, the accurate measurement state is a state of no inflation.
And 303, performing mechanical test on the whole spacecraft.
In one non-limiting embodiment, the mechanical test may include, but is not limited to, any one or more of the following: sinusoidal vibration test, noise test, etc. Wherein the noise test comprises: pre-vibration stage, characteristic stage, acceptance stage and characteristic stage noise test.
The specific process of the mechanical test is as follows:
first, a sinusoidal vibration test was performed on the spacecraft whole. The sinusoidal vibration test of the whole device comprises three working conditions: sinusoidal vibration of the whole device in the X direction; sinusoidal vibration of the whole device in Y direction; the whole device vibrates sinusoidally in the Z direction. The loading sequence of the test working conditions is Y-direction, Z-direction and X-direction in sequence, and the loading sequence can be changed according to the characteristics of the spacecraft. Each test condition (loading direction) is completed in sequence: and performing noise tests on the pre-vibration stage, the characteristic stage, the acceptance stage and the characteristic stage once respectively. Wherein the number of pre-vibration stages can be increased as appropriate according to the sensor conduction conditions in the test.
After each working condition of each direction test is completed, the test data needs to be interpreted and compared. After confirming that the data are correct and the requirements of the sinusoidal vibration test are met, the appearance of the cabin body is checked to be abnormal, and then the noise test of the whole cabin body is implemented.
And secondly, carrying out noise test on the whole spacecraft. And the noise test of the pre-vibration stage, the characteristic stage, the acceptance stage and the characteristic stage is sequentially completed during the noise test of the whole device, and the pre-vibration stage, the characteristic stage, the acceptance stage and the characteristic stage are respectively performed once. Wherein the number of pre-vibration stages can be increased as appropriate according to the sensor conduction conditions in the test.
After each working condition of each direction test is completed, judging and comparing test data; after data analysis, the test is ended after the noise test requirement is confirmed to be met.
After the test is completed, the spacecraft cabin, the equipment and the like are also required to be checked so as to ensure that the spacecraft cabin, the equipment and the like are not damaged by the mechanical test.
And 304, measuring the precision of the equipment and the cabin after the initial sample mechanical test of the spacecraft to obtain the precision after the initial sample mechanical test of the spacecraft.
Specifically, in one non-limiting embodiment, the accuracy measurement may be made as follows:
firstly, after a spacecraft initial sample mechanical test, performing inter-cabin precision retesting in a whole spacecraft state, mainly measuring the relation between precision testing cubic mirrors among all cabin sections;
after the accuracy retesting of the whole device is completed, cabin segment decomposition is carried out, accuracy retesting is carried out on the sensor in a single cabin segment state, the accuracy retesting mainly comprises the steps of measuring, controlling and measuring the accuracy of the sensor and the attitude measuring sensor, and the installation accuracy of the sensor can be represented by measuring the relation between the sensor and a cabin body;
and finally, integrating the precise measurement parameters of each measuring point into a second table to obtain the precision of the spacecraft after the initial sample mechanical test.
And 305, determining the initial sample precision change amount according to the precision before the initial sample mechanical test of the spacecraft and the precision after the initial sample mechanical test of the spacecraft.
After the initial sample precision variation is obtained, the layout position and the secondary structure design analysis and review can be carried out on the equipment with large precision variation (such as the precision variation is larger than a set threshold value), and the layout adjustment scheme and the secondary structure reinforcement scheme are determined.
In the positive sample stage, the equipment layout is required to be adjusted and the secondary structure is required to be strengthened and designed according to the accurate measurement result in the initial sample stage. After the spacecraft is subjected to positive sample assembly and comprehensive test, the vibration environment test modification of the whole device in the spacecraft positive sample stage is carried out, so that the quality characteristics of the whole device and equipment are ensured to be covered in the quality characteristic range of the initial sample test and the emission state or kept consistent.
As shown in fig. 4, the process flow chart of the initial sample stage in the spacecraft equipment installation accuracy deviation compensation method of the invention comprises the following steps:
in the sample correction stage, the whole device is modified in a vibration environment test so that the mass characteristics of the whole device and equipment are covered in the mass characteristic range of the initial sample test and the emission state or kept consistent, and mechanical sensors are attached to the cabin body, the equipment and the secondary structure.
Specifically, mechanical sensors can be stuck to the spacecraft cabin, the equipment and the support substructure according to the positive mechanical test outline and the mechanical test point requirements. The pasting position of the mechanical sensor on the secondary structure of the spacecraft cabin body, the equipment and the bracket is consistent with the initial state, or the coverage range of the measuring point is enlarged.
Step 402, the test preparation is completed.
Specifically, test equipment debugging, test site safety state confirmation, comprehensive test preparation and other test preparation works need to be completed.
And step 403, measuring the precision of the equipment and the cabin body before the spacecraft positive mechanics test to obtain the precision before the spacecraft positive mechanics test.
Specifically, in one non-limiting embodiment, the accuracy measurement may be made as follows:
firstly, installing a precision measurement cube mirror in a single cabin section state of an aircraft, and establishing a cabin body structure coordinate system of a cabin body to establish a cabin body structure reference. The structural rigidity of the position of the cabin body, where the precise measurement cube mirror is installed, is larger than or equal to that of other positions, and the position of the cabin body is consistent with that of the initial sample state. It should be noted that, according to the actual development process, the work may also be implemented in the positive assembly stage, and the embodiment of the present invention is not limited thereto.
Then, the precision measurement is carried out on the sensor in a single cabin section state, and the precision measurement can be carried out according to the precision measurement technical requirements and the flow, and mainly comprises the steps of controlling the precision of the measurement sensor and the precision of the attitude measurement sensor, and the installation precision of the sensor can be represented by measuring the relation between the sensor and the cabin body. It should be noted that, in the single-cabin state, the states of the equipment, the support substructure, the mechanical sensor, etc. are also required to be checked, and no loosening phenomenon is confirmed.
In addition, the precise measurement state of the sealed cabin is a non-inflated state.
Then, the docking of the cabin sections is completed, and precision measurement among the cabin sections is carried out in a whole machine state, wherein the precision measurement is mainly carried out on the relation among the precision measurement cubic mirrors among the cabin sections;
and finally, integrating the accurate measurement parameters of all the measuring points into a third table.
Step 404, performing mechanical test on the spacecraft positive sample.
In one non-limiting embodiment, the mechanical test may include, but is not limited to, any one or more of the following: sinusoidal vibration test, noise test, etc. Wherein the noise test comprises: pre-vibration stage, characteristic stage, acceptance stage and characteristic stage noise test.
The specific process of the mechanical test is as follows:
first, a sinusoidal vibration test was performed on the spacecraft whole. The sinusoidal vibration test of the whole device comprises three working conditions: sinusoidal vibration of the whole device in the X direction; sinusoidal vibration of the whole device in Y direction; the whole device vibrates sinusoidally in the Z direction. The loading sequence of the test working conditions is Y-direction, Z-direction and X-direction in sequence, and the loading sequence can be changed according to the characteristics of the spacecraft. Each test condition (loading direction) is completed in sequence: and performing noise tests on the pre-vibration stage, the characteristic stage, the acceptance stage and the characteristic stage once respectively. Wherein the number of pre-vibration stages can be increased as appropriate according to the sensor conduction conditions in the test.
After each working condition of each direction test is completed, the test data needs to be interpreted and compared. After confirming that the data are correct and the requirements of the sinusoidal vibration test are met, the appearance of the cabin body is checked to be abnormal, and then the noise test of the whole cabin body is implemented.
And secondly, carrying out noise test on the whole spacecraft. And the noise test of the pre-vibration stage, the characteristic stage, the acceptance stage and the characteristic stage is sequentially completed during the noise test of the whole device, and the pre-vibration stage, the characteristic stage, the acceptance stage and the characteristic stage are respectively performed once. Wherein the number of pre-vibration stages can be increased as appropriate according to the sensor conduction conditions in the test.
After each working condition of each direction test is completed, judging and comparing test data; after data analysis, the test is ended after the noise test requirement is confirmed to be met.
After the test is completed, the spacecraft cabin, the equipment and the like are also required to be checked so as to ensure that the spacecraft cabin, the equipment and the like are not damaged by the mechanical test.
And step 405, measuring the precision of the equipment and the cabin body after the spacecraft positive mechanics test to obtain the precision after the spacecraft positive mechanics test.
Specifically, in one non-limiting embodiment, the accuracy measurement may be made as follows:
firstly, after a spacecraft positive mechanical test, performing inter-cabin precision retesting in a whole spacecraft state, mainly measuring the relation between precision testing cubic mirrors among all cabin sections;
after the accuracy retesting of the whole device is completed, cabin segment decomposition is carried out, accuracy retesting is carried out on the sensor in a single cabin segment state, the accuracy retesting mainly comprises the steps of measuring, controlling and measuring the accuracy of the sensor and the attitude measuring sensor, and the installation accuracy of the sensor can be represented by measuring the relation between the sensor and a cabin body;
and finally, integrating the precise measurement parameters of each measuring point into a fourth table to obtain the precision of the spacecraft after the positive mechanical test.
And step 406, determining the positive sample precision change amount according to the precision before the spacecraft positive sample mechanical test and the precision after the spacecraft positive sample mechanical test.
In the above embodiments, the sinusoidal scanning vibration test condition and the noise test condition of the spacecraft are test conditions specified by the carrier rocket interface file, and the recession control can be performed according to the mechanical response characteristic of the device during the actual test.
In addition, the states of the cabin body and equipment before and after the mechanical test are consistent, the states of parking, loading, equipment installation and the like of the cabin body are consistent during precision measurement, precision measurement deviation caused by inconsistent states is avoided, and the contrast of precision measurement data before and after the mechanical test is further ensured.
Furthermore, for batch production models with the same state, the same effect can be achieved only by implementing relevant projects in the positive sample stage except for the batch production model of the first spacecraft.
According to the spacecraft equipment installation precision deviation compensation method provided by the invention, equipment installation precision deviation of a spacecraft caused by a vibration environment is compensated, equipment precision deviation compensation is implemented through two times of mechanical tests and multiple times of fine measurement in a spacecraft initial sample stage and a positive sample stage, equipment layout and installation secondary structure rigidity weak links are specifically identified through the mechanical tests in the initial sample stage, and equipment layout adjustment and secondary structure reinforcement design are carried out to solve the problem of large equipment installation precision change, so that a positive sample design state is determined; acquiring precision deviation of equipment before and after a test through a positive sample stage mechanical test, and acquiring a precision compensation value which is close to the vibration environment of a spacecraft launching section; the final accurate measurement before emission and the precision compensation are adopted, so that the installation precision of the equipment after the spacecraft enters the orbit is effectively ensured to meet the index requirement.
In the scheme of the invention, the primary sample mechanical test level is subjected to a grade identification and the positive sample mechanical test level is subjected to a grade acceptance; through the primary sample identification level test, the strength of the installation structure of each installation device on the cabin body of the spacecraft can be found in time, so that the installation structure with low structural strength is correspondingly reinforced according to a comparison result, the problem that the installation precision of the device after the spacecraft enters the orbit is not up to standard due to deformation of the installation structure is avoided, and the consistency of the ground measurement result and the actual installation precision of the device after the spacecraft enters the orbit is further ensured.
The foregoing is merely exemplary of embodiments of the invention and, as regards devices and arrangements not explicitly described in this disclosure, it should be understood that this can be done by general purpose devices and methods known in the art.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (12)

1. A spacecraft equipment installation accuracy deviation compensation method, the method comprising: in the initial sample stage, initial sample precision variation before and after initial sample mechanical test of the spacecraft is obtained;
rechecking and adjusting the layout position and the secondary structure design of the equipment according to the initial sample precision variation;
in the positive sample stage, the positive sample precision variation before and after the spacecraft positive sample mechanical test is obtained;
determining a precision deviation compensation value according to the positive sample precision variation;
after the spacecraft is just sample and the emission state is set, precision measurement is carried out on the equipment and the cabin body to obtain reference data;
and determining on-orbit data according to the reference data and the precision compensation value.
2. The spacecraft equipment installation accuracy deviation compensation method of claim 1, further comprising:
in the initial sample stage, setting a state before the mechanical test of the spacecraft, and pasting mechanical sensors on the cabin, equipment and secondary structure;
the method comprises the steps that precision measurement is carried out on equipment and a cabin body before a spacecraft initial sample mechanical test, so that precision before the spacecraft initial sample mechanical test is obtained;
carrying out mechanical test on the spacecraft;
performing precision measurement on equipment and a cabin body after the initial sample mechanical test of the spacecraft to obtain the precision after the initial sample mechanical test of the spacecraft;
the initial sample precision variation before and after the initial sample mechanical test of the spacecraft is obtained comprises the following steps:
and determining the initial sample precision variation according to the precision before the initial sample mechanical test of the spacecraft and the precision after the initial sample mechanical test of the spacecraft.
3. The method for compensating for deviation of installation accuracy of spacecraft equipment according to claim 2, wherein the measuring the accuracy of the equipment and the cabin before the initial sample mechanical test of the spacecraft to obtain the accuracy before the initial sample mechanical test of the spacecraft comprises:
installing a precise measurement cube mirror in a single cabin state of the spacecraft, establishing a structural coordinate system of a cabin body, and establishing a cabin body structure by taking the coordinate system as a reference;
the sensor is measured accurately in a single cabin state;
performing and completing cabin butt joint, and performing inter-cabin precision measurement in a whole machine state;
and integrating the precise measurement parameters of each measuring point into a first table to obtain the precision of the spacecraft before the initial sample mechanical test.
4. A spacecraft installation accuracy deviation compensation method according to claim 3, wherein the structural rigidity of the position where the precision cube is installed in the single-cabin state of the spacecraft is greater than or equal to the structural rigidity of other positions.
5. The method for compensating for deviation of installation accuracy of spacecraft equipment according to claim 2, wherein the measuring of accuracy of equipment and cabin after initial sample mechanics test of spacecraft, obtaining accuracy after initial sample mechanics test of spacecraft, comprises:
after the initial sample mechanical test of the spacecraft, performing inter-cabin precision retesting in the whole spacecraft state;
after the accuracy retest of the whole device is completed, cabin segment decomposition is carried out, and the accuracy retest is carried out on the sensor in a single cabin segment state;
and assembling the precise measurement parameters of each measuring point into a second table to obtain the precision of the spacecraft after the initial sample mechanical test.
6. The spacecraft equipment installation accuracy deviation compensation method of claim 1, further comprising:
in the sample correction stage, the whole device is modified by vibration environment test so that the quality characteristics of the whole device and equipment are covered in the quality characteristic range of the initial sample test and the emission state or kept consistent, and mechanical sensors are attached to the cabin body, the equipment and the secondary structure;
finishing test preparation work;
the method comprises the steps that precision measurement is carried out on equipment and a cabin body before a spacecraft positive sample mechanical test, so that precision before the spacecraft positive sample mechanical test is obtained;
carrying out a mechanical test on the spacecraft positive sample;
measuring the precision of equipment and a cabin body after the spacecraft positive sample mechanical test to obtain the precision after the spacecraft positive sample mechanical test;
the method for obtaining the positive sample precision variation before and after the spacecraft positive sample mechanical test comprises the following steps:
and determining the positive sample precision variation according to the precision before the spacecraft positive sample mechanical test and the precision after the spacecraft positive sample mechanical test.
7. The method for compensating for the deviation in the installation accuracy of a spacecraft apparatus according to claim 6, wherein the mechanical sensors attached to the cabin, the apparatus and the sub-structure in the positive stage are kept identical to those in the initial stage.
8. The method for compensating for the deviation of the installation accuracy of spacecraft equipment according to claim 6, wherein the measuring the accuracy of the equipment and the cabin before the spacecraft positive mechanics test to obtain the accuracy before the spacecraft positive mechanics test comprises:
installing a precise measurement cube mirror in a single cabin section state of the spacecraft, establishing a structural coordinate system of a cabin body, and establishing a cabin body structure by taking the coordinate system as a reference;
the sensor is measured accurately in a single cabin state;
finishing the cabin section butt joint, and carrying out the precision measurement between cabin sections in the whole machine state;
and integrating the accurate measurement parameters of all the measuring points into a third table.
9. The method for compensating for the deviation of the installation accuracy of spacecraft equipment according to claim 6, wherein the measuring the accuracy of the equipment and the cabin after the spacecraft positive mechanics test, and obtaining the accuracy after the spacecraft positive mechanics test, comprises:
after the spacecraft positive mechanics test, performing inter-cabin precision retesting in the whole spacecraft state;
after the accuracy retest of the whole device is completed, cabin segment decomposition is carried out, and the accuracy retest is carried out on the sensor in a single cabin segment state;
and assembling the precise measurement parameters of each measuring point into a fourth table to obtain the precision of the spacecraft after the positive mechanical test.
10. The spacecraft equipment installation accuracy deviation compensation method of claim 2 or 6, wherein the mechanical test comprises any one or more of the following: sinusoidal vibration test, noise test.
11. The spacecraft equipment installation accuracy deviation compensation method of claim 10, wherein said sinusoidal vibration test comprises three test conditions: sinusoidal vibration of the whole device in the X direction; sinusoidal vibration of the whole device in Y direction; the whole device vibrates in a Z-direction sinusoidal manner, and the loading sequence of the test working conditions is Y-direction, Z-direction and X-direction in sequence; and each test working condition sequentially completes the noise test of the pre-vibration stage, the characteristic stage, the acceptance stage and the characteristic stage.
12. The spacecraft equipment installation accuracy deviation compensation method of claim 10, wherein said noise test comprises: pre-vibration stage, characteristic stage, acceptance stage and characteristic stage noise test.
CN202311220583.4A 2023-09-20 2023-09-20 Spacecraft equipment installation precision deviation compensation method Pending CN117268675A (en)

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