CN116242568A - High-reliability operation layout and test method of large-scale double shaking table test system - Google Patents

Abstract

The invention belongs to the field of spacecraft mechanics environment tests, and particularly relates to a large-scale double-vibrating-table test system, which comprises the following components: a vibrating table base which is an integrated base; the horizontal sliding table is positioned right above the vibrating table base; the table body bracket is connected with the vibrating table base through connecting screws at two sides of the bottom; the first vibrating table body is positioned at the left side of the horizontal sliding table; the ox head is used for connecting the vibrating table body and the horizontal sliding table; the moving coil is connected with the ox head; the second vibrating table body is positioned on the right side of the horizontal sliding table and is connected with the expansion table; the expansion table is positioned above the vibration table body; the horizontal slipway both ends all possess the interface of being connected with the ox head. The large-scale double-vibration table test system provided by the invention ensures that any vibration table body fails, the test can still be normally performed, the test progress is not affected at all, a strong technical guarantee is provided for the mechanical test of the spacecraft, and a favorable technical approach is provided for the efficient development of the spacecraft.

Description

High-reliability operation layout and test method of large-scale double shaking table test system

field of invention

The invention belongs to the field of mechanical environment tests of spacecraft, and in particular relates to a high-reliability operation layout and a test method of a large-scale double shaking table test system.

Background technique

Before launch, the spacecraft needs to undergo strict vibration environment test verification to check whether the structural design of the product is reasonable and fully expose the potential defects and hidden dangers of the product. With the continuous development of China's aerospace technology, the research and development activities of ultra-large spacecraft such as the core module of the space station, the space capsule, the dream capsule, and the manned spacecraft are gradually advancing. The key equipment of the test - the large-scale shaking table test system - puts forward high reliability requirements.

The large-scale shaking table test system is mainly divided into multiple parallel excitation and single parallel excitation test types. At present, a set of 40-ton double-stage parallel excitation vibration test system used in Beijing Aerospace City is mainly composed of two 20-ton parallel-connected. This set of equipment mainly includes two sets of vibrating table body, horizontal slide table, expansion table and bull head. For the longitudinal vibration test, the two sets of platforms are connected to the extension table after being in a vertical state to form a longitudinal excitation state; for the transverse vibration test, the two sets of platforms are respectively connected to the horizontal slide table through the bull head to form a transverse excitation state. During the mechanical test of the spacecraft, if there are any faults such as water leakage and oil leakage on the shaking table, the test will be interrupted. Only after the equipment failure is eliminated, the test can continue, and the progress of the test is seriously affected. At the same time, between the lateral and longitudinal vibration tests of the spacecraft, 3 to 4 hours of table body steering operations are required, and the test efficiency is also low.

With the gradual development of China's manufacturing industry, domestic manufacturers of vibrating tables adopted the idea of digestion, absorption and re-innovation, and embarked on a road of independent innovation and development of large-scale vibrating tables. At present, domestic manufacturers have the ability to develop a single set of large-scale vibration table equipment of 20 tons, 35 tons, 40 tons, 50 tons to 70 tons. The shaking table system used in the field of conventional spacecraft mechanical testing generally adopts a 35-ton or 40-ton shaking table test system. In order to improve the execution efficiency of mechanical tests, two sets of large-scale vibration tables are currently configured for a single spacecraft mechanical test station. One set includes the vibration table body and the expansion table, which is arranged on the left side and is mainly used for spacecraft longitudinal vibration tests; The set includes a shaking table body and a horizontal sliding table, which are arranged on the right side and are mainly used for spacecraft lateral vibration tests. The table bodies of two sets of large vibrating tables are close together. Using this method saves the time required for the conventional single set of shaking table to turn, and the test efficiency has been greatly improved.

The vibrating table body is the core body of the test system, and its interior mainly includes the core functional components of the moving coil and the static coil. Due to long-term vibration and long-term circulation of pressurized water inside, these two types of core functional components are the most prone to failure, and they are also the components with long maintenance cycles and difficult maintenance. For the two sets of large-scale shaking table test systems configured above, when one of the shaking table bodies fails, it is still necessary to repair the single shaking table and return to normal before the test can proceed normally, and the progress of spacecraft products is still affected.

In order to realize the high reliability of the operation of the double-set large-scale shaking table system, a high-reliability operation layout and test method of the large-scale double-shaking table test system are proposed. It can be carried out normally, and the test progress is not affected at all, providing a strong technical guarantee for the spacecraft mechanical test, and solving the problem of high reliability of equipment in the field of spacecraft vibration testing.

Contents of the invention

The technical problem to be solved by the present invention is to provide a high-reliability operation layout and test method of a large-scale double shaking table test system, which better solves the technical problem that the progress of the spacecraft vibration test will not be affected in any way when the table body fails, In order to solve the above technical problems, the present invention provides a large-scale double shaking table test system.

The present invention provides a large-scale double-shaking table test system, which includes a shaking table base 8, which is an integrated base to support the shaking table body 1 and the shaking table body 2, the horizontal sliding table 6 and the ground The role of the vibration-damping foundation connection; the horizontal slide table 6, which is located directly above the vibration table base 8; the table body support 3, which is connected to the vibration table base 8 through the connecting screws on both sides of the bottom, and is used to fix the left side of the vibration table body 1; the shaking table body 1, which is located on the left side of the horizontal slide table 6, is used for the lateral vibration test of the spacecraft; the bull head 5, which is used to connect the shaking table body 1 and the horizontal slide table 6; the moving coil 4, which is connected with the horizontal slide table 6 The bull head 5 is connected to provide driving force for the shaking table body 1; the shaking table body 2, which is located on the right side of the horizontal slide table 6, is connected to the extended table 7 for the longitudinal vibration test of the spacecraft; the extended table 7 is located on the shaking table On the top of the table body 2; both ends of the horizontal slide table 6 are equipped with interfaces connected with the bull head 5.

The present invention also provides a high-reliability operation method when a large-scale double shaking table test system detects a spacecraft, including:

i) When the left and right vibration tables are normal, the following steps are included:

1) Spacecraft installation: hoist the fixture to the top of the expansion platform by means of a crane, place it in the center of the expansion platform, fasten it with at least two turns of screws, then lift the spacecraft above the fixture, place the spacecraft in place through the positioning pins, and use The pressure ring and the screw fasten the spacecraft;

2) Spacecraft longitudinal test control and measurement preparation: arrange 4 control sensors on the pressure ring and connect them with the measurement sensors;

3) Spacecraft Longitudinal Vibration Test: Power up the positive spacecraft and conduct a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and the data is valid, and then perform the first characteristic level test and acceptance level test in sequence , The second characteristic level test, after the test, compare the response data of each measuring point at the characteristic level twice, check whether the results of the characteristic level test before and after are consistent, check whether the appearance of the spacecraft is damaged or other abnormal phenomena, and judge whether the spacecraft has passed Assessment of acceptance level tests;

4) Vibration table and reversing under the spacecraft: remove the screws, remove the pressure ring, hoist the spacecraft to the support vehicle with a sling, move the measuring personnel with the wires, remove the fixture from the extended table and hoist it to the horizontal slide table center position, and fasten with screws, horizontally adjust the vibration table system according to the test conditions, then hoist the spacecraft above the fixture, place the spacecraft in the first horizontal direction through positioning pins, use the pressure ring and screws fasten the product;

5) Spacecraft lateral vibration test: power up the positive spacecraft and conduct a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and the data is valid; then conduct the first characteristic level test and acceptance level test in sequence , The second characteristic level test; after the test, compare the response data of each measuring point at the characteristic level twice, check whether the results of the characteristic level test before and after are consistent, check whether the appearance of the spacecraft is damaged or other abnormal phenomena, and judge whether the structure of the spacecraft has passed For the assessment of the acceptance level test, after completing the first horizontal vibration test, rotate the spacecraft 90°, and complete the horizontal two horizontal vibration tests according to the first horizontal horizontal vibration test process;

6) Shaking table under the spacecraft and withdrawing: After the vibration test is completed, remove the connecting wires at the vibration control sensor and the measuring system arm, and arrange them, install the spacecraft spreader, remove the connecting screws, and lift the shaking table under the spacecraft , and placed on the support vehicle, the spacecraft vibration test is all over;

ii) When the left vibrating table is faulty and the right vibrating table is normal, the following steps are included:

1) Spacecraft installation: hoist the fixture to the top of the expansion platform by means of a crane, place it in the center of the expansion platform, fasten it with at least two turns of screws, then lift the spacecraft above the fixture, place the spacecraft in place through the positioning pins, and use The pressure ring and the screw fasten the spacecraft;

2) Spacecraft longitudinal test control and measurement preparation: arrange 4 control sensors on the pressure ring and connect them with the measurement sensors;

3) Spacecraft Longitudinal Vibration Test: Power up the positive spacecraft and conduct a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and the data is valid, and then perform the first characteristic level test and acceptance level test in sequence , The second characteristic level test, after the test, compare the response data of each measuring point at the characteristic level twice, check whether the results of the characteristic level test before and after are consistent, check whether the appearance of the spacecraft is damaged or other abnormal phenomena, and judge whether the spacecraft has passed Assessment of acceptance level tests;

4) The vibrating table under the spacecraft, the table body is turned horizontally, and the spacecraft is reversed in place: remove the screws, remove the pressure ring, and lift the spacecraft to the support vehicle with a sling. Disassemble from the extended table and hang it to the center of the horizontal slide table, and fasten it with screws, remove the extended table, and lift it away from the vibrating table, disassemble the bull head of the left vibrating table, and install it on the right vibrating table Then, turn the vibrating table to the horizontal level, connect the bull head with the horizontal sliding table, check the activity state of the horizontal sliding table, debug the vibrating table system according to the test conditions, and then lift the spacecraft above the fixture, pass Positioning pins put the spacecraft in place in the first horizontal direction, and fasten the product with pressure rings and screws;

5) Spacecraft lateral vibration test: power up the positive spacecraft, conduct a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and the data is valid, and then conduct the first characteristic level test and acceptance level test in sequence , The second characteristic level test, after the test, compare the response data of each measuring point at the characteristic level twice, check whether the results of the characteristic level test before and after are consistent, check whether the appearance of the spacecraft is damaged or other abnormal phenomena, and judge whether the structure of the spacecraft has passed The assessment of the sine acceptance level test is carried out. After the first horizontal vibration test is completed, the spacecraft is rotated 90°, and the horizontal vibration test of the second horizontal direction is completed according to the first horizontal horizontal vibration test process;

6) Shaking table under the spacecraft and withdrawing: After the vibration test is completed, remove the connecting wires at the vibration control sensor and the measuring system arm, and arrange them, install the spacecraft spreader, remove the connecting screws, and lift the shaking table under the spacecraft , and placed on the support vehicle, the spacecraft vibration test is all over; and

iii) When the right vibrating table is faulty and the left vibrating table is normal, the following steps are included:

1) Spacecraft installation: hoist the fixture to the top of the horizontal slide table with the help of a crane, place it in the center of the horizontal slide table, fasten it with at least two turns of screws, then lift the spacecraft above the fixture, and place the spacecraft in place through the positioning pins , fasten the spacecraft with a pressure ring and screws;

2) Spacecraft lateral test control and measurement preparation: Arrange 4 control sensors on the pressure ring and connect them to the measurement sensors;

3) Spacecraft lateral vibration test: power up the positive spacecraft, conduct a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and the data is valid, and then conduct the first characteristic level test and acceptance level test in sequence , The second characteristic level test, after the test, compare the response data of each measuring point at the characteristic level twice, check whether the results of the characteristic level test before and after are consistent, check whether the appearance of the spacecraft is damaged or other abnormal phenomena, and judge whether the spacecraft has passed For the assessment of the sine acceptance level test, after the first horizontal vibration test is completed, the spacecraft is rotated 90°, and the horizontal vibration test of the second horizontal direction is completed referring to the first horizontal horizontal vibration test process;

4) The vibrating table under the spacecraft, the table body is turned vertically, and the spacecraft is in place: disassemble the screws, take off the pressure ring, and lift the spacecraft to the support vehicle with a sling. Disassemble the bull head of the side vibrating table body, turn it vertically, fasten the two sides with trunnion screws, disassemble the extended table from the right vibrating table body, and hoist it above the left vibrating table body, use Fasten the screws, lift the fixture to the top of the extension table with the help of a crane, place it in the center of the extension table, fasten it with at least two turns of screws, and debug the shaking table system according to the test conditions, then lift the spacecraft above the fixture, and pass the positioning The pins put the spacecraft in place, and the spacecraft is fastened with pressure rings and screws;

5) Longitudinal vibration test of spacecraft: power on the positive spacecraft, conduct pre-vibration level conduction test, ensure that all control channels and measurement channels work normally and the data is valid, and then conduct the first characteristic level test and acceptance level test in sequence , The second characteristic level test, after the test, compare the response data of each measuring point at the characteristic level twice, check whether the results of the characteristic level test before and after are consistent, check whether the appearance of the spacecraft is damaged or other abnormal phenomena, and judge whether the spacecraft has passed Assessment of sine acceptance level test;

6) Shaking table under the spacecraft and withdrawing: After the vibration test is completed, remove the connecting wires at the vibration control sensor and the measuring system arm, and arrange them, install the spacecraft spreader, remove the connecting screws, and lift the shaking table under the spacecraft , and placed on the support vehicle, the spacecraft vibration test is all over.

The invention provides a high-reliability operation layout and test method of a large-scale double shaking table test system. The method can ensure that any one of the shaking table bodies fails, and the test can still be carried out normally, and the test progress is not affected at all. The mechanical test of the spacecraft provides a strong technical guarantee and provides a favorable technical approach for the efficient development of the spacecraft.

Description of drawings

Fig. 1 is the high-reliability operation layout and test method of the large-scale double shaking table test system of the present invention; wherein, 1-left shaking table body, 2-right shaking table body, 3-table body support, 4-dynamic circle, 5-bull head, 6-horizontal sliding table, 7-extension table, 8-vibration table base.

Fig. 2 is a layout diagram of the longitudinal vibration test bench body when the left side bench body of the present invention fails.

Fig. 3 is a layout diagram of the lateral vibration test bench body when the left side bench body of the present invention fails.

Fig. 4 is a layout diagram of the lateral vibration test bench body when the right bench body of the present invention fails.

Fig. 5 is a layout diagram of the longitudinal vibration test bench body when the right bench body of the present invention fails.

Detailed ways

The high-reliability operation layout and test method of a large-scale double shaking table test system of the present invention will be further described below in conjunction with the accompanying drawings.

Example 1

The present invention provides a large-scale double-shaking table test system, which includes a shaking table base 8, which is an integrated base to support the shaking table body 1 and the shaking table body 2, the horizontal sliding table 6 and the ground The role of the vibration-damping foundation connection; the horizontal slide table 6, which is located directly above the vibration table base 8; the table body support 3, which is connected to the vibration table base 8 through the connecting screws on both sides of the bottom, and is used to fix the left side of the vibration table body 1; the shaking table body 1, which is located on the left side of the horizontal slide table 6, is used for the lateral vibration test of the spacecraft; the bull head 5, which is used to connect the shaking table body 1 and the horizontal slide table 6; the moving coil 4, which is connected with the horizontal slide table 6 The bull head 5 is connected to provide driving force for the shaking table body 1; the shaking table body 2, which is located on the right side of the horizontal slide table 6, is connected to the extended table 7 for the longitudinal vibration test of the spacecraft; the extended table 7 is located on the shaking table On the top of the table body 2; both ends of the horizontal slide table 6 are equipped with interfaces connected with the bull head 5.

Example 2

For the normal state of the vibration table, the vibration test includes the following steps:

(1) Fixture and product installation. Specifically, the fixture is hoisted to the top of the expansion platform by a crane, positioned in the center of the expansion platform, and fastened by at least two turns of screws. Then the spacecraft product is hoisted above the fixture, the product is placed in place by positioning pins, and the product is fastened by pressing rings and screws.

(2) Spacecraft longitudinal test control and measurement preparation. Specifically, four control sensors are generally evenly distributed on the pressure ring, and the cable connection and conduction of the control sensors and the measurement sensors are performed.

(3) Longitudinal vibration test of spacecraft. Specifically, for the prototype spacecraft, a pre-vibration level conduction test is performed after the spacecraft is powered on to ensure that all control channels and measurement channels work normally and the data is valid. This is followed by a first feature-level test. After the test is over, analyze the response data of all measuring points, and formulate acceptance level test conditions. If there is a response limit point, a conduction test is required to confirm the status of the response limit measuring point to ensure the reliability of the limit measuring point. . After the parameters of the acceptance level are set, the spacecraft is switched to internal power, and when it is confirmed that the vibration can be started, the acceptance level test is started. During the test, the test data is collected, processed, and recorded, while the electrical measurement system monitors the state of the spacecraft, and the spacecraft is switched to external power after the test. This is followed by a second feature-level test. After the test, compare the response data of each measuring point at the characteristic level twice to check whether the test results at the characteristic level before and after are consistent, check whether there is damage or other abnormal phenomena on the appearance of the spacecraft, and judge whether the structure of the spacecraft has withstood the assessment of the sine acceptance level test. For the prototype spacecraft, it is only necessary to conduct the acceptance level vibration test, and the spacecraft is in an internal power state; electricity.

(4) Vibration table and product reversing under the spacecraft. Specifically, install the spacecraft sling, remove the connecting screws, remove the pressure ring, hoist the spacecraft onto the support vehicle, and the surveyor moves with the wires; remove the connecting screws between the fixture and the extended table, and hoist the fixture to the horizontal slide table center position, and fasten with screws; debug the vibration table system according to the test conditions. Then the spacecraft product is hoisted above the fixture, the product is placed in the first horizontal direction through the positioning pin, and the product is fastened with the pressure ring and screws.

(5) Spacecraft lateral vibration test. Specifically, for the prototype spacecraft, after the spacecraft is powered on, conduct the first horizontal pre-vibration level conduction test in the transverse direction to ensure that all control channels and measurement channels work normally and the data is valid. This is followed by a first feature-level test. After the test is over, analyze the response data of all measuring points, and formulate acceptance level test conditions. If there is a response limit point, a conduction test is required to confirm the status of the response limit measuring point to ensure the reliability of the limit measuring point. . After the parameters of the acceptance level are set, the spacecraft is switched to internal power, and when it is confirmed that the vibration can be started, the acceptance level test is started. During the test, the test data is collected, processed, and recorded, while the electrical measurement system monitors the state of the spacecraft, and the spacecraft is switched to external power after the test. This is followed by a second feature-level test. After the test, compare the response data of each measuring point at the characteristic level twice to check whether the test results at the characteristic level before and after are consistent, check whether there is damage or other abnormal phenomena on the appearance of the spacecraft, and judge whether the structure of the spacecraft has withstood the assessment of the sine acceptance level test. For the prototype spacecraft, it is only necessary to conduct the acceptance level vibration test, and the spacecraft is in an internal power state; electricity.

Since the spacecraft needs to carry out vibration tests in two directions horizontally and laterally, after completing the first horizontal direction vibration test, install the spacecraft sling, remove the connecting screws of the pressure ring, lift the spacecraft, and install the pressure ring after turning 90° and falling. And fasten with screws. Refer to the vibration test process of the first horizontal direction in the horizontal direction to complete the vibration test in the second horizontal direction.

(6) Shaking table under the spacecraft and withdrawal. After the vibration test is completed, remove the vibration control sensor and the connection wires at the rotating arm of the measurement system and arrange them. Install the spacecraft sling, remove the connecting screws, lift the vibration table under the spacecraft, and place it on the support vehicle. The spacecraft vibration test is all over.

Example 3

For the failure of the platform body 1 on the left side of the vibration table, in order to prevent the spacecraft vibration test process from being affected and the spacecraft development progress not to be delayed, the following steps are included:

(1) Fixture and product installation. Specifically, the fixture is hoisted to the top of the expansion platform by a crane, positioned in the center of the expansion platform, and fastened by at least two turns of screws. Then the spacecraft product is hoisted above the fixture, the product is placed in place by positioning pins, and the product is fastened by pressing rings and screws.

(2) Spacecraft longitudinal test control and measurement preparation. Specifically, four control sensors are generally evenly distributed on the pressure ring, and the cable connection and conduction of the control sensors and the measurement sensors are performed.

(3) Longitudinal vibration test of spacecraft. Specifically, for the prototype spacecraft, a pre-vibration level conduction test is performed after the spacecraft is powered on to ensure that all control channels and measurement channels work normally and the data is valid. This is followed by a first feature-level test. After the test is over, analyze the response data of all measuring points, and formulate acceptance level test conditions. If there is a response limit point, a conduction test is required to confirm the status of the response limit measuring point to ensure the reliability of the limit measuring point. . After the parameters of the acceptance level are set, the spacecraft is switched to internal power, and when it is confirmed that the vibration can be started, the acceptance level test is started. During the test, the test data is collected, processed, and recorded, while the electrical measurement system monitors the state of the spacecraft, and the spacecraft is switched to external power after the test. This is followed by a second feature-level test. After the test, compare the response data of each measuring point at the characteristic level twice to check whether the test results at the characteristic level before and after are consistent, check whether there is damage or other abnormal phenomena on the appearance of the spacecraft, and judge whether the structure of the spacecraft has withstood the assessment of the sine acceptance level test. For the prototype spacecraft, it is only necessary to conduct the acceptance level vibration test, and the spacecraft is in an internal power state; electricity.

(4) The vibrating table under the spacecraft, the table body is turned horizontally, and the product is in place. Specifically, install the spacecraft sling, remove the connecting screws, remove the pressure ring, hoist the spacecraft onto the support vehicle, and the surveyor moves with the wires; remove the connecting screws between the fixture and the extended table, and hoist the fixture to the horizontal slide table Put it on the center position, and fasten it with screws; remove the connecting screw of the expansion head, and lift the expansion head away from the vibration table; disassemble the bull head of the left table body, install it on the top of the right table body, and fasten it with screws. Then turn the vibrating table to the level, connect the bull head and the horizontal sliding table, and check the activity state of the sliding table; debug the vibrating table system according to the test conditions. Then the spacecraft product is hoisted above the fixture, the product is placed in the first horizontal direction through the positioning pin, and the product is fastened with the pressure ring and screws.

(5) Spacecraft lateral vibration test. Specifically, for the prototype spacecraft, after the spacecraft is powered on, conduct the first horizontal pre-vibration level conduction test in the transverse direction to ensure that all control channels and measurement channels work normally and the data is valid. This is followed by a first feature-level test. After the test is over, analyze the response data of all measuring points, and formulate acceptance level test conditions. If there is a response limit point, a conduction test is required to confirm the status of the response limit measuring point to ensure the reliability of the limit measuring point. . After the parameters of the acceptance level are set, the spacecraft is switched to internal power, and when it is confirmed that the vibration can be started, the acceptance level test is started. During the test, the test data is collected, processed, and recorded, while the electrical measurement system monitors the state of the spacecraft, and the spacecraft is switched to external power after the test. This is followed by a second feature-level test. After the test, compare the response data of each measuring point at the characteristic level twice to check whether the test results at the characteristic level before and after are consistent, check whether there is damage or other abnormal phenomena on the appearance of the spacecraft, and judge whether the structure of the spacecraft has withstood the assessment of the sine acceptance level test. For the prototype spacecraft, it is only necessary to conduct the acceptance level vibration test, and the spacecraft is in an internal power state; electricity.

Since the spacecraft needs to carry out vibration tests in two directions horizontally and laterally, after completing the first horizontal direction vibration test, install the spacecraft sling, remove the connecting screws of the pressure ring, lift the spacecraft, and install the pressure ring after turning 90° and falling. And fasten with screws. Refer to the vibration test process of the first horizontal direction in the horizontal direction to complete the vibration test in the second horizontal direction.

(6) Shaking table under the spacecraft and withdrawal. After the vibration test is completed, remove the vibration control sensor and the connection wires at the rotating arm of the measurement system and arrange them. Install the spacecraft sling, remove the connecting screws, lift the vibration table under the spacecraft, and place it on the support vehicle. The spacecraft vibration test is all over.

Example 4

For the failure of the platform body 2 on the right side of the vibration table, in order to prevent the spacecraft vibration test process from being affected and the spacecraft development progress not to be delayed, the following steps are included:

(1) Fixture and product installation. Specifically, the fixture is hoisted above the horizontal slide table by a crane, positioned in the center of the slide table, and fastened by at least two turns of screws. Then the spacecraft product is hoisted above the fixture, the product is placed in place by positioning pins, and the product is fastened by pressing rings and screws.

(2) Spacecraft transverse test control and measurement preparation. Specifically, four control sensors are generally evenly distributed on the pressure ring, and the cable connection and conduction of the control sensors and the measurement sensors are performed.

(3) Spacecraft lateral vibration test. Specifically, for the prototype spacecraft, after the spacecraft is powered on, conduct the first horizontal pre-vibration level conduction test in the transverse direction to ensure that all control channels and measurement channels work normally and the data is valid. This is followed by a first feature-level test. After the test is over, analyze the response data of all measuring points, and formulate acceptance level test conditions. If there is a response limit point, a conduction test is required to confirm the status of the response limit measuring point to ensure the reliability of the limit measuring point. . After the parameters of the acceptance level are set, the spacecraft is switched to internal power, and when it is confirmed that the vibration can be started, the acceptance level test is started. During the test, the test data is collected, processed, and recorded, while the electrical measurement system monitors the state of the spacecraft, and the spacecraft is switched to external power after the test. This is followed by a second feature-level test. After the test, compare the response data of each measuring point at the characteristic level twice to check whether the test results at the characteristic level before and after are consistent, check whether there is damage or other abnormal phenomena on the appearance of the spacecraft, and judge whether the structure of the spacecraft has withstood the assessment of the sine acceptance level test. For the prototype spacecraft, it is only necessary to conduct the acceptance level vibration test, and the spacecraft is in an internal power state; electricity.

Since the spacecraft needs to carry out vibration tests in two directions horizontally and laterally, after completing the first horizontal direction vibration test, install the spacecraft sling, remove the connecting screws of the pressure ring, lift the spacecraft, and install the pressure ring after turning 90° and falling. And fasten with screws. Refer to the vibration test process of the first horizontal direction in the horizontal direction to complete the vibration test in the second horizontal direction.

(4) The vibrating table under the spacecraft, the table body is turned vertically, and the product is turned in place. Specifically, install the spacecraft sling, remove the connecting screws, remove the pressure ring, hoist the spacecraft onto the support vehicle, and the surveyor moves with the wires; The side platform turns to be vertical, and the trunnion screws on both sides are fastened. Remove the connecting screws between the right extension table and the table body, hoist the extension table above the left table body, and fasten it with screws. Lift the fixture to the top of the extension table by a crane, place it in the center of the extension table, fasten it with at least two turns of screws, and debug the vibration table system according to the test conditions. Then the spacecraft product is hoisted above the fixture, the product is positioned longitudinally through the positioning pins, and the product is fastened with the pressure ring and screws.

(5) Longitudinal vibration test of spacecraft. Specifically, for the prototype spacecraft, a pre-vibration level conduction test is performed after the spacecraft is powered on to ensure that all control channels and measurement channels work normally and the data is valid. This is followed by a first feature-level test. After the test is over, analyze the response data of all measuring points, and formulate acceptance level test conditions. If there is a response limit point, a conduction test is required to confirm the status of the response limit measuring point to ensure the reliability of the limit measuring point. . After the parameters of the acceptance level are set, the spacecraft is switched to internal power, and when it is confirmed that the vibration can be started, the acceptance level test is started. During the test, the test data is collected, processed, and recorded, while the electrical measurement system monitors the state of the spacecraft, and the spacecraft is switched to external power after the test. This is followed by a second feature-level test. After the test, compare the response data of each measuring point at the characteristic level twice to check whether the test results at the characteristic level before and after are consistent, check whether there is damage or other abnormal phenomena on the appearance of the spacecraft, and judge whether the structure of the spacecraft has withstood the assessment of the sine acceptance level test. For the prototype spacecraft, it is only necessary to conduct the acceptance level vibration test, and the spacecraft is in an internal power state; electricity.

(6) Shaking table under the spacecraft and withdrawal. After the vibration test is completed, remove the vibration control sensor and the connection wires at the rotating arm of the measurement system and arrange them. Install the spacecraft sling, remove the connecting screws, lift the vibration table under the spacecraft, and place it on the support vehicle. The spacecraft vibration test is all over.

Although the specific embodiments of the present invention have been described and illustrated in detail above, it should be pointed out that we can make various equivalent changes and modifications to the above-mentioned embodiments according to the concept of the present invention, and the functional effects produced by it are still the same. Anything beyond the spirit contained in the specification and drawings shall fall within the protection scope of the present invention.

Claims (2)

1. A large dual vibrating table test system, comprising:

the vibrating table base is an integrated base and plays a role in supporting the vibrating table body 1, the vibrating table body 2, the horizontal sliding table 6 and connecting with a ground vibration reduction foundation;

a horizontal slipway 6, which is positioned right above the base of the vibrating table;

the table body bracket 3 is connected with the vibrating table base 8 through connecting screws at two sides of the bottom and is used for fixing the left vibrating table body 1; the vibration table body 1 is positioned at the left side of the horizontal sliding table 6 and is used for a transverse vibration test of the spacecraft;

a ox head 5 for connecting the vibrating table body 1 and the horizontal sliding table 6;

a moving coil 4 connected to the ox head 5 and providing driving force to the vibrating table body 1;

the vibration table body 2 is positioned on the right side of the horizontal sliding table 6, is connected with the expansion table 7 and is used for a longitudinal vibration test of the spacecraft; and an expansion table 7 positioned above the vibration table body 2;

the two ends of the horizontal sliding table 6 are respectively provided with an interface connected with the ox head 5.

2. The high reliability operating layout of a large dual vibrating table test system of claim 1, the test method comprising:

i) When the left and right vibration tables are normal, the method comprises the following steps:

1) And (3) spacecraft installation: hoisting the clamp to the top of the expansion table by means of a crane, positioning the clamp in the center of the expansion table, fastening the clamp by at least two circles of screws, hoisting the spacecraft above the clamp, positioning the spacecraft by means of positioning pins, and fastening the spacecraft by means of a compression ring and screws;

2) Longitudinal test control and measurement preparation of a spacecraft: 4 control sensors are arranged on the compression ring and connected with the measuring sensors;

3) Longitudinal vibration test of spacecraft: powering up a positive spacecraft, performing a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and data are valid, then sequentially performing a first characteristic level test, an acceptance level test and a second characteristic level test, performing two characteristic level test point response data comparison after the test is finished, checking whether the front and rear characteristic level test results are consistent, checking whether the appearance of the spacecraft is damaged or abnormal, and judging whether the spacecraft is checked by the acceptance level test;

4) Lower vibrating table of spacecraft and reversing: disassembling a screw, taking down a compression ring, hanging the spacecraft to a bracket vehicle by using a hanger, holding a wire for movement by a measurer, disassembling a clamp from an expansion table top, hanging the clamp to the central position of a horizontal sliding table, fastening the clamp by using the screw, transversely debugging a vibrating table system according to test conditions, then hanging the spacecraft above the clamp, positioning the spacecraft in a first horizontal direction by using a positioning pin, and fastening a product by using the compression ring and the screw;

5) Transverse vibration test of spacecraft: energizing the positive spacecraft, and performing a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and data are valid; then sequentially performing a first characteristic level test, an acceptance level test and a second characteristic level test; after the test is finished, comparing response data of each measuring point of the characteristic level twice, checking whether the test results of the characteristic level before and after are consistent, checking whether the appearance of the spacecraft is damaged or abnormal, judging whether the spacecraft structure is checked by the acceptance level test, rotating the spacecraft by 90 degrees after the first horizontal direction vibration test is finished, and finishing the two horizontal direction vibration tests by referring to the first horizontal direction vibration test flow;

6) Vibrating table and withdrawal under spacecraft: after the vibration test is finished, connecting wires at the vibration control sensor and the rotating arm of the measuring system are removed, the arrangement is carried out, a spacecraft lifting appliance is installed, connecting screws are removed, a lower vibration table of the spacecraft is lifted and placed on a bracket vehicle, and the vibration test of the spacecraft is finished;

ii) left side shaking table trouble, when right side shaking table is normal, include the following steps:

1) And (3) spacecraft installation: hoisting the clamp to the top of the expansion table by means of a crane, positioning the clamp in the center of the expansion table, fastening the clamp by at least two circles of screws, hoisting the spacecraft above the clamp, positioning the spacecraft by means of positioning pins, and fastening the spacecraft by means of a compression ring and screws;

2) Longitudinal test control and measurement preparation of a spacecraft: 4 control sensors are arranged on the compression ring and connected with the measuring sensors;

3) Longitudinal vibration test of spacecraft: powering up a positive spacecraft, performing a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and data are valid, then sequentially performing a first characteristic level test, an acceptance level test and a second characteristic level test, performing two characteristic level test point response data comparison after the test is finished, checking whether the front and rear characteristic level test results are consistent, checking whether the appearance of the spacecraft is damaged or abnormal, and judging whether the spacecraft is checked by the acceptance level test;

4) Lower vibration table of spacecraft, horizontal steering of table body and reversing of spacecraft are put in place: removing screws, removing a compression ring, hanging a spacecraft to a bracket vehicle by using a lifting tool, holding a wire for movement by a measurer, removing a clamp from an expansion table top and hanging the clamp to the center position of a horizontal sliding table, fastening the clamp by using the screws, removing the expansion table top, hanging the clamp away from a vibrating table, removing the ox head of a left vibrating table body, installing the clamp on a right vibrating table body, fastening the clamp by using the screws, rotating the vibrating table to be horizontal, connecting the ox head with the horizontal sliding table, checking the movable state of the horizontal sliding table, debugging a vibrating table system according to test conditions, hanging the spacecraft above the clamp, positioning the spacecraft in a first horizontal direction by using a positioning pin, and fastening a product by using the compression ring and the screws;

5) Transverse vibration test of spacecraft: powering up a positive spacecraft, performing a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and data are effective, then sequentially performing a first characteristic level test, an acceptance level test and a second characteristic level test, performing response data comparison of each measuring point of the characteristic level twice after the test is finished, checking whether the results of the front and rear characteristic level tests are consistent, checking whether the appearance of the spacecraft is damaged or abnormal, judging whether the structure of the spacecraft is checked by a sine acceptance level test, rotating the spacecraft by 90 degrees after the first horizontal direction vibration test is finished, and completing the two horizontal direction vibration tests by referring to a horizontal first horizontal direction vibration test flow;

6) Vibrating table and withdrawal under spacecraft: after the vibration test is finished, connecting wires at the vibration control sensor and the rotating arm of the measuring system are removed, the arrangement is carried out, a spacecraft lifting appliance is installed, connecting screws are removed, a lower vibration table of the spacecraft is lifted and placed on a bracket vehicle, and the vibration test of the spacecraft is finished;

iii) The right vibration table fails, and when the left vibration table is normal, the method comprises the following steps:

1) And (3) spacecraft installation: hoisting the clamp to the top of the horizontal sliding table by means of a crane, positioning the clamp at the center of the horizontal sliding table, fastening the clamp by at least two circles of screws, hoisting the spacecraft above the clamp, positioning the spacecraft by means of positioning pins, and fastening the spacecraft by means of a compression ring and the screws;

2) Spacecraft lateral test control and measurement preparation: 4 control sensors are arranged on the compression ring and connected with the measuring sensors;

3) Transverse vibration test of spacecraft: powering up a positive spacecraft, performing a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and data are effective, then sequentially performing a first characteristic level test, an acceptance level test and a second characteristic level test, performing response data comparison of each measuring point of the characteristic level twice after the test is finished, checking whether the results of the front and rear characteristic level tests are consistent, checking whether the appearance of the spacecraft is damaged or abnormal, judging whether the spacecraft is subjected to the examination of a sine acceptance level test, rotating the spacecraft by 90 degrees after the first horizontal direction vibration test is finished, and finishing the two horizontal direction vibration tests by referring to a horizontal first horizontal direction vibration test flow;

4) Vibrating table, table body turn vertical direction and spacecraft turn to take place under the spacecraft: removing screws, taking down a compression ring, hanging a spacecraft to a bracket vehicle by using a lifting tool, holding a wire for movement by a measurer, disassembling a cow head of a left vibration table body, turning the cow head to be vertical, fastening two sides of the cow head by using trunnion screws, disassembling an expansion table surface from a right vibration table body, hanging the cow head above the left vibration table body, fastening the cow head by using screws, hanging a clamp to the top of the expansion table by using a crane, positioning the center of the expansion table, fastening the screw by using at least two circles of screws, debugging the vibration table system according to test conditions, hanging the spacecraft above the clamp, positioning the spacecraft by using positioning pins, and fastening the spacecraft by using the compression ring and the screw;

5) Longitudinal vibration test of spacecraft: powering up a positive spacecraft, performing a pre-vibration level conduction test to ensure that all control channels and measurement channels work normally and data are valid, then sequentially performing a first characteristic level test, an acceptance level test and a second characteristic level test, performing response data comparison of each measuring point of the characteristic level twice after the test is finished, checking whether the results of the characteristic level tests are consistent, checking whether the appearance of the spacecraft is damaged or abnormal, and judging whether the spacecraft is checked by a sine acceptance level test;

6) Vibrating table and withdrawal under spacecraft: after the vibration test is finished, connecting wires at the vibration control sensor and the rotating arm of the measuring system are removed, the connecting wires are tidied, a spacecraft lifting appliance is installed, connecting screws are removed, a lower vibration table of the spacecraft is lifted, the lower vibration table is placed on a bracket vehicle, and the vibration test of the spacecraft is finished.

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