Module-based static testing method for large multi-module spacecraft structure

Abstract

A module-based static testing method for a large multi-module spacecraft structure. The method comprises: decomposing a large multi-module spacecraft into a plurality of modules according to connection interfaces, and performing load testing and envelope analysis on each individual module to determine a load condition for the module; superimposing an acceleration load of test conditions with the mass of a loaded part of the module to determine the stress of a loading point, and establishing a finite element model for analysis, wherein the stress of a root part under an actual load is less than or equal to the actual load on the module, and a local loading stress envelopes an actual state stress; performing finite element analysis on a tooling design to confirm that tooling transmits the actual load; and performing a static load test, and completing the test.

Description

A static test method for compartmentalized structure of large multi-compartment spacecraft Technical Field

[0001] The present invention relates to the field of spacecraft testing technology, and in particular provides a static test method for compartmentalization of a large multi-compartment combined spacecraft structure. Background Art

[0002] Large spacecraft structures are characterized by large size, multiple modules, and complex operating conditions. For example, a space station system assembly consists of nearly 20 modules, with a module length of approximately 15 meters and a weight of 22.7 tons. Independently launched spacecraft involve at least four modules, with large structures such as robotic arms and solar panels mounted externally. Conducting full-module static testing is challenging and difficult to design. Existing satellites, such as those for communications and remote sensing, often consist solely of a propulsion module and a payload module, suffice for assessing structural stress under quasi-static loads. Multi-module structure assessments for rockets and other launch vehicles, lacking internal load-bearing equipment such as cargo containers and instrument panels, or the loads of external robotic arms and solar panels, often equate the combined lateral and longitudinal loads to equivalent axial compression and apply longitudinal loading. Large multi-module spacecraft, such as space stations, undergo not only maximum dynamic pressure, maximum overload, quasi-static loads with booster and core stage shutdown, sinusoidal vibration, random vibration, and noise loading during launch into orbit, but also ground vibration testing and transit overloads. Technical issues

[0003] The static test design not only considers the loads on each cabin interface, but also the amplification effect of the ground vibration test caused by the high height of the combined cabin sections. If the load distribution and operating condition selection in the static test are too large, it will result in excessive strength design of the product, resulting in a heavy spacecraft structure. If the design is too small, it is easy to cause the product to not be fully verified on the ground, posing risks to the launch and on-orbit operation of future spacecraft such as space stations. To this end, it is further necessary to solve the problem of the inability to directly verify the structure of large multi-cabin combined spacecraft, improve test efficiency and reduce test costs. Technical Solutions

[0004] In order to solve the problem that large multi-cabin combined spacecraft cannot be directly subjected to static loading test verification, effectively improve test efficiency and reduce test costs, the present invention provides a large multi-cabin combined spacecraft structural compartment static test method, the specific technical solution is as follows.

[0005] A method for static testing of a large multi-cabin structure of a spacecraft, comprising the following steps:

[0006] S1. Decompose a large multi-cabin spacecraft into multiple cabins based on their connection interfaces. Perform load tests and envelope analysis on each cabin to determine the load conditions for each cabin.

[0007] S2. Superimpose the acceleration load of the test condition with the mass of the loaded portion of the cabin to determine the force at the loading point. Build a finite element model and perform analysis. Under the actual load, the root force is less than or equal to the actual cabin load, and the local loading stress envelopes the actual state stress.

[0008] S3. Conduct finite element analysis on the tooling design to confirm the actual loads transmitted by the tooling;

[0009] S4. Perform static loading test and complete the test.

[0010] Preferably, the load conditions include the load at the moment of launch stage booster shutdown, maximum dynamic pressure, maximum overload, core stage shutdown, in-orbit pressure and indexing load, and ground transportation and testing load.

[0011] Preferably, the tooling includes an instrument panel and equipment interface inside the main structure, an equipment interface outside the main structure, and a tooling hole reserved in the cabin.

[0012] Preferably, the static loading conditions include: quasi-static loading conditions, spacecraft pre-launch conditions and spacecraft on-orbit conditions; in the static loading conditions, the static test load coefficient of the spacecraft is represented by a quasi-static load, which is a combination of dynamic and static accelerations, giving the overload of the quasi-static acceleration under the spacecraft transonic speed, maximum dynamic pressure, maximum overload and boost shutdown state, with the lateral acceleration a perpendicular to the launch direction of the cabin at the center of mass. h and the acceleration a at the center of mass parallel to the launch direction of the capsule z Indicates that before the launch of the spacecraft, it is necessary to pass the sinusoidal vibration and noise test on the ground. The top cabin is dynamically amplified under the lateral sinusoidal vibration load, and the cabin is subjected to the lateral acceleration a s overload; the spacecraft on-orbit working condition, including the effect of the movement of the external robotic arm and solar wing secondary structure on the main structure, and the combined loading of internal pressure load and concentrated load during the assessment.

[0013] It is also preferred that the load conditions are simplified before the static test, specifically including:

[0014] Under the non-internal pressure state, calculate the longitudinal and transverse axial compressive loads at the root of the main structure under different working conditions:

[0015] Peq=P+4M / D

[0016] Where Peq is the axial compressive load at the root of the main structure, P is the section axial load, M is the section bending moment, and D is the section diameter;

[0017] The conditions at the moment of maximum lateral overload and maximum longitudinal overload were selected as the test conditions, as well as the condition with the maximum equivalent axial pressure;

[0018] A finite element model was established to confirm whether the local stresses of the two test conditions encompassed all load conditions.

[0019] It is further preferred that the external load of the cabin includes the load of the top cabin and the bulkhead structure. In the static loading test, the load is multiplied by the center of mass of each part of the upper cabin and the acceleration overload to constitute the loading magnitude and loading position of the lateral load and longitudinal load loaded on the outside of the cabin.

[0020] It is further preferred that the internal load of the cabin includes the load of the cabinet and the instrument panel, and a part of the longitudinal load generated by the horizontal instrument panel equipment inside the cabin is transferred to the vertical beam on the bulkhead side through the in-plane shear of the side vertical panels and the middle vertical panels, and then transferred to the frame in the form of a concentrated load through the interface between the vertical beam and the frame; the other part of the load is transferred to the frame through the interface between the horizontal instrument panel and the frame, and the two parts of the load are transferred to the root of the cabin through external loads such as the column section wall panels and the frame; a part of the transverse load generated by the horizontal instrument panel equipment inside the cabin is transferred to the column section connecting frame and the middle frame through the in-plane shear of the horizontal instrument, and a part is transferred to the frame through the vertical beam on the bulkhead side of the side vertical panels and the middle vertical panels, and the two parts of the load are finally transferred to the root through the column section wall panels and the frame; the cabinet inside the cabin is installed through the angle grid beam. The angle beams form a stable triangular structure through vertical bars and diagonal braces, which transfer the cabinet load to the frame and wall panels through the angle beams, braces and diagonal braces. The vertical plate equipment load is mainly transferred to the vertical beams through the vertical plate in-plane shear, and then transferred to the frame in the form of concentrated load through the interface between the vertical beam and the frame, and then through the root of the sealed cabin bulkhead. The other part of the vertical plate load is transferred to the horizontal plate, which is then transferred to the root through the frame, column segment wall panels, etc.

[0021] The internal load and external load of the cabin are summarized to calculate the equivalent axial pressure at the root, and the equivalent axial pressure under the envelope working condition is used to avoid local overload.

[0022] It is further preferred that the loading fixture for the external load is installed above the cabin using a steel solid fixture and connected to the cabin by screws; the internal load is divided into four areas: quadrant I, quadrant II, quadrant III, and quadrant IV. The actual instrument panels and angle grid beam systems are installed in quadrants I and II, and the loading of quadrants III and IV is applied to the connecting frame through the fixture.

[0023] It is further preferred that, in the static loading test, pre-test loading and unloading are carried out first; for the assessment of local air pressure and load combined loading, a pressure monitoring line and an air charging line are respectively connected to the water inlet flange of the lower cover of the cabin, and a pressure monitoring line is connected to a process port flange in the middle of the cabin. Each pressure monitoring line is connected to a pressure gauge for monitoring the internal pressure of the cabin, and the air charging line is connected to the outlet of the high-purity nitrogen bottle for injecting pressure into the cabin. High-purity nitrogen is used to pressurize the cabin in a manually controlled manner and the displacement and strain data are tested; after the cabin is pressurized to 1 atm pressure, a load test is carried out; the load test obtains linear load-displacement and load-strain loading and unloading curves, the test data is consistent with the actual stress state of the test piece, the return to zero state after unloading is good, and there is no obvious load drop phenomenon during the test, indicating that the single cabin structure design meets the requirements. Beneficial effects

[0024] The present invention provides a method for static testing of compartmented structures of large, multi-compartment spacecraft. This method addresses the issue of inaccurate compartment test load distribution through compartment test load distribution and operating condition selection. Furthermore, by simultaneously loading the internal and external structures, the method ensures that both the primary structure and the secondary structure are fully verified, improving verification efficiency. This method employs a rational loading method to verify the spacecraft's structural design and manufacturing process, examining its ability to withstand certification-level testing while also avoiding local damage due to excessive local loads. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is a schematic diagram of the compartment connection relationship;

[0026] FIG2 is a schematic diagram of the transmission path of the external load;

[0027] FIG3 is a schematic diagram of the transfer path of the internal load;

[0028] Figure 4 is a schematic diagram of the combination of loading points in the longitudinal layer;

[0029] Figure 5 is a schematic diagram of the combination of loading points in the transverse layer;

[0030] FIG6 is a schematic diagram of the distribution of loading points within the transverse layer;

[0031] In the figure: 1-loading point, 2-end frame, 3-middle frame, 4-connecting frame, 5-cabin, 6-interface, 7-root interface, 8-loading tooling, 9-internal tooling, 10-layering, 11-point of action of resultant force. Modes for Carrying Out the Invention

[0032] 1 to 6 , a specific implementation of a static test method for a large multi-cabin combined spacecraft structure provided by the present invention will be described.

[0033] The static test of spacecraft structure verifies the spacecraft structure design and manufacturing process by rationally selecting the axial force, shear force, torque and bending moment that the structure is subjected to and designing a reasonable loading method, and tests the spacecraft's ability to withstand the certification test while avoiding local damage caused by excessive local loads. A static test method for the compartment of a large multi-compartment spacecraft structure is provided, which includes the following steps:

[0034] S1. Decompose a large multi-cabin spacecraft into multiple cabins based on their connection interfaces. Perform load tests and envelope analysis on each cabin to determine the load conditions for each cabin.

[0035] The load conditions include the load at the moment of booster shutdown in the launch phase, maximum dynamic pressure, maximum overload, core stage shutdown, in-orbit pressure and transfer load, and ground transportation and testing load.

[0036] Static loading conditions include: quasi-static loading conditions, pre-launch conditions, and on-orbit conditions. In static loading conditions, the static test load coefficient for the spacecraft is represented by a quasi-static load, a combination of dynamic and static accelerations. This overload is expressed as the lateral acceleration ah at the center of mass perpendicular to the launch direction of the capsule, and the acceleration az at the center of mass parallel to the launch direction of the capsule, given the spacecraft's transonic speed, maximum dynamic pressure, maximum overload, and booster shutdown state. Pre-launch conditions require verification on the ground through sinusoidal vibration and noise tests. The top capsule undergoes dynamic amplification under transverse sinusoidal vibration loads, and the capsule is subjected to an overload of lateral acceleration as. In on-orbit conditions, the effects of the movement of secondary structures such as the robotic arm and solar panels outside the capsule on the primary structure are assessed through a combination of internal pressure and concentrated loads.

[0037] Since the height of the connection structure of multiple sealed cabins in a space station is as high as 15 meters, the quasi-static load is generally not enough to encompass the impact of all working conditions on the structure, and a multi-load evaluation is required. The load conditions need to be simplified before the static test. First, under the non-internal pressure state, the axial pressure load Peq at the root of the main structure is calculated longitudinally and transversely under various working conditions, except for the local test conditions. Generally, the working conditions of the maximum transverse overload and the maximum longitudinal overload in several states are selected as the test conditions, and the working condition with the maximum equivalent axial pressure is selected at the same time. If the maximum equivalent axial pressure condition is in the maximum transverse and longitudinal conditions, it is not selected separately. At the same time, a finite element model is established to confirm whether the local stress of the two test conditions can envelop all working condition loads, including vibration tests and ground tests.

[0038] Before the static test, the load conditions are simplified, specifically including: calculating the longitudinal and transverse axial compressive loads at the root of the main structure under different conditions without internal pressure:

[0039] Peq=P+4M / D

[0040] Where Peq is the axial compressive load at the root of the main structure, P is the section axial load, M is the section bending moment, and D is the section diameter;

[0041] The working conditions at the moments of maximum lateral overload and maximum longitudinal overload were selected as the test conditions, as well as the working condition with the maximum equivalent axial pressure. A finite element model was established to confirm whether the local stresses of the two test conditions envelop all the loads of the working conditions.

[0042] Through test envelope analysis, determine whether it is necessary to add certain local loading and pressurization tests, such as air pressurization of the robot arm adaptation structure, tensile load and air pressurization, etc.

[0043] S2. Superimpose the acceleration load of the test condition with the mass of the loaded part of the cabin to determine the force at the loading point. Build a finite element model and perform analysis. Under the actual load, the root force is less than or equal to the actual cabin load, and the local loading stress envelopes the actual state stress.

[0044] The external load of the cabin includes the load of the top cabin and bulkhead structure. In the static loading test, the load is multiplied by the center of mass of each part of the upper cabin and the acceleration overload to form the loading magnitude and loading position of the lateral load and longitudinal load loaded on the outside of the cabin.

[0045] The loads inside the cabin include those from the cabinet units and instrument panels. The instrument panels consist of horizontal and vertical panels, all of which are aluminum panel honeycomb structures. Part of the longitudinal load generated by the horizontal instrument panel equipment inside the cabin is transferred to the vertical beams near the bulkhead through the in-plane shear of the side and middle vertical panels, and then transferred to the frame as a concentrated load through the interface between the vertical beams and the frame. Another part of the load is transferred to the frame through the interface between the horizontal instrument panel and the frame. Both loads are transferred to the base of the cabin through external loads such as the column wall panels and the frame. Part of the transverse load generated by the horizontal instrument panel equipment inside the cabin is transferred to the column connection frame and the middle frame through the in-plane shear of the horizontal instruments, and part is transferred to the frame through the vertical beams near the bulkhead of the side and middle vertical panels. Both loads are finally transferred to the base through the column wall panels and the frame. The cabinet units inside the cabin are installed using angle grid beams. The angle beams form a stable triangular structure through vertical poles and diagonal braces, which transfer the load of the cabinet to the frame and wall panels through the angle beams, braces and diagonal braces; the load of the vertical plate equipment is mainly transferred to the vertical beams through the in-plane shear of the vertical plate, and then transferred to the frame in the form of concentrated load through the interface between the vertical beam and the frame, and then through the root of the sealed cabin bulkhead; another part of the load of the vertical plate is transferred to the horizontal plate, and the horizontal plate is transferred to the root through the frame, column section wall panel, etc.; the internal load and the external load of the cabin are summarized to calculate the equivalent axial pressure at the root, and the equivalent axial pressure under the envelope working condition is avoided to avoid local overload.

[0046] The loading fixture for external loads is installed on the top of the cabin using a steel solid fixture and connected to the cabin by screws; the internal load is divided into four areas: Quadrant I, Quadrant II, Quadrant III, and Quadrant IV. The actual instrument panels and angle grid beam systems are installed in Quadrant I and Quadrant II, and the loading of Quadrant III and Quadrant IV is applied to the connection frame through the fixture.

[0047] Specifically, the main structure load loading is divided into internal and external loads. For the external load, the loading fixture is simulated by a steel solid fixture ring with strong rigidity, which is directly installed on the cabin. The mounting ring is connected to the cabin through 144-M16 screws, and a 200t loading cylinder is installed in the center of the top loading fixture.

[0048] To verify the cabin's internal structure, actual instrument panels and grid beams are installed in Quadrants I and II. For loading in Quadrants III and IV, the load is applied to the connection frame via fixtures. For longitudinal loading, two aluminum loading plates are installed on each layer of the horizontal instrument panels in Quadrants I and II, with 2-3 loading points set up on each layer of the horizontal instrument panels based on the area. For transverse loading, the loads in Quadrants I and II are applied to the vertical panels via a loading fixture. Each vertical panel is loaded using one loading fixture plate. The horizontal and vertical panels in Quadrants III and IV are replaced with fixtures, which are internal fixtures connected to the cabin frame via screws.

[0049] During longitudinal loading, longitudinal loads are applied simultaneously to the horizontal and vertical plates in all four quadrants according to load distribution. Loading holes are pre-reserved on the bottom and sides of the cabin. For test loading, a loading actuator of no less than 300t is installed directly below, connected to the sensor, loading rod, and loading lever. Transverse loads are applied through the loading rod lead-out holes in each zone, leading to the layer load rod. Outside the cabin, the six forces are combined into a total force through levers. Load distribution and combination are then combined, and a loading actuator of no less than 100t is installed on the side.

[0050] S3. Conduct finite element analysis on the tooling design to confirm the actual load transmitted by the tooling; the tooling includes instrument panels and equipment interfaces inside the main structure, equipment interfaces outside the main structure, and holes reserved for tooling penetration in the cabin.

[0051] S4. Perform static loading test and complete the test.

[0052] Each working condition of the main structure static test is divided into acceptance level and appraisal level. The appraisal level load is 1.5 times that of the acceptance level. Before the formal test of each working condition, a pre-test loading and unloading is carried out. The pre-test load level is 40% of the acceptance level of each working condition.

[0053] In the static loading test, pre-test loading and unloading are carried out first; for the assessment of local air pressure and load combined loading, a pressure monitoring pipeline and an air charging pipeline are connected to the water inlet flange of the lower cover of the cabin respectively, and a pressure monitoring pipeline is connected to a process port flange in the middle of the cabin. Each pressure monitoring pipeline is connected to a pressure gauge for monitoring the internal pressure of the cabin, and the air charging pipeline is connected to the outlet of the high-purity nitrogen bottle for injecting pressure into the cabin. High-purity nitrogen is used to pressurize the cabin in a manually controlled manner and the displacement and strain data are tested; after the cabin is pressurized to 1atm pressure, a load test is carried out; the load-displacement and load-strain loading and unloading curves obtained from the load test are linear, the test data is consistent with the actual stress state of the test piece, the return to zero state after unloading is good, and there is no obvious load drop phenomenon during the test, indicating that the single cabin structure design meets the requirements.

[0054] Specifically, the cabin was pressurized to 1.0 atm using high-purity nitrogen gas under manual control. Displacement and strain data were measured at 0.2 atm, 0.4 atm, 0.6 atm, 0.8 atm, and 1 atm. After the cabin reached 1 atm pressure, a load test was conducted.

[0055] This method provides a basis for selecting load conditions for static testing of large multi-compartment spacecraft structures. Specifically for the design of tooling and cabin design for static testing of large multi-compartment spacecraft, it addresses the issue of inaccurate load distribution in compartment tests through load distribution and load condition selection. Furthermore, by simultaneously loading the internal and external structures, it ensures that both the primary structure and the secondary structure are fully verified, improving verification efficiency. This method designs a rational loading method to verify the spacecraft's structural design and manufacturing process, examining the spacecraft's ability to withstand certification-level testing, while also avoiding local damage due to excessive local loads.

[0056] Of course, the above description is not a limitation of the present invention, and the present invention is not limited to the above examples. Changes, modifications, additions or substitutions made by technicians in this technical field within the essential scope of the present invention should also fall within the scope of protection of the present invention.

Claims

1. A method for static testing of a large multi-cabin structure of a spacecraft, characterized by the following steps: include: S1. Decompose a large multi-cabin spacecraft into multiple cabins based on their connection interfaces. Perform load tests and envelope analysis on each cabin to determine the load conditions for each cabin. S2. Superimpose the acceleration load of the test condition with the mass of the loaded portion of the cabin to determine the force at the loading point. Build a finite element model and perform analysis. Under the actual load, the root force is less than or equal to the actual cabin load, and the local loading stress envelopes the actual state stress. S3. Conduct finite element analysis on the tooling design to confirm the actual loads transmitted by the tooling; S4. Perform static loading test and complete the test.

2. A static test method for compartmentalization of a large multi-compartment spacecraft structure according to claim 1, characterized in that: The load conditions include the load at the moment of launch stage booster shutdown, maximum dynamic pressure, maximum overload, core stage shutdown, in-orbit pressure and indexing load, and ground transportation and testing load.

3. A static test method for compartmentalization of a large multi-compartment spacecraft structure according to claim 1, characterized in that: The tooling includes an instrument panel and equipment interface inside the main structure, an equipment interface outside the main structure, and a tooling hole reserved in the cabin.

4. A static test method for compartmentalization of a large multi-compartment spacecraft structure according to claim 1, characterized in that: The static loading conditions include: quasi-static loading conditions, spacecraft pre-launch conditions, and spacecraft on-orbit conditions; The static test load coefficient of the spacecraft in the static loading condition is represented by the quasi-static load, which is a combination of dynamic and static accelerations. It gives the overload of the quasi-static acceleration under the spacecraft transonic speed, maximum dynamic pressure, maximum overload and boost shutdown state, and the lateral acceleration a at the center of mass perpendicular to the launch direction of the cabin. h and the acceleration a at the center of mass parallel to the launch direction of the capsule z express; In the pre-launch working condition of the spacecraft, it is necessary to pass the sinusoidal vibration and noise test on the ground. The top cabin is dynamically amplified under the lateral sinusoidal vibration load, and the cabin is subjected to the lateral acceleration a s Overload; The spacecraft is in orbit, and the effects of the movement of the robotic arm outside the cabin and the secondary structure of the solar wing on the main structure are assessed by combining internal pressure loads and concentrated loads.

5. The method for static testing of a large multi-cabin structure of a spacecraft according to claim 1, characterized in that: The load conditions are simplified before the static test, specifically including: Under the non-internal pressure state, calculate the longitudinal and transverse axial compressive loads at the root of the main structure under different working conditions: Peq=P+4M / D Where Peq is the axial compressive load at the root of the main structure, P is the section axial load, M is the section bending moment, and D is the section diameter; The conditions at the moment of maximum lateral overload and maximum longitudinal overload were selected as the test conditions, as well as the condition with the maximum equivalent axial pressure; A finite element model was established to confirm whether the local stresses of the two test conditions encompassed all load conditions.

6. A static test method for compartmentalization of a large multi-compartment spacecraft structure according to claim 1, characterized in that: The external load of the cabin includes the load of the top cabin and the bulkhead structure. In the static loading test, the load is multiplied by the center of mass of each part of the upper cabin and the acceleration overload to form the loading magnitude and loading position of the lateral load and longitudinal load loaded on the outside of the cabin.

7. A static test method for compartmentalization of a large multi-compartment spacecraft structure according to claim 1 or 6, characterized in that: The internal load of the cabin includes the load of the cabinet and instrument panel. A part of the longitudinal load generated by the horizontal instrument panel equipment inside the cabin is transferred to the vertical beam on the side of the bulkhead through the in-plane shear of the side vertical panel and the middle vertical panel, and then transferred to the frame in the form of a concentrated load through the interface between the vertical beam and the frame; the other part of the load is transferred to the frame through the interface between the horizontal instrument panel and the frame, and the two parts of the load are transferred to the root of the cabin through external loads such as the column section wall panel and the frame; a part of the transverse load generated by the horizontal instrument panel equipment in the cabin is transferred to the column section connection frame and the middle frame through the in-plane shear of the horizontal instrument, and a part is transferred to the frame through the vertical beam on the side of the side vertical panel and the middle vertical panel close to the bulkhead, and the two parts of the load are finally transferred to the root through the column section wall panel and the frame; the cabinet inside the cabin is installed through the angle grid beam. The angle beams form a stable triangular structure through vertical bars and diagonal braces, which transfer the cabinet load to the frame and wall panels through the angle beams, braces and diagonal braces. The vertical plate equipment load is mainly transferred to the vertical beams through the vertical plate in-plane shear, and then transferred to the frame in the form of concentrated load through the interface between the vertical beam and the frame, and then through the root of the sealed cabin bulkhead. The other part of the vertical plate load is transferred to the horizontal plate, which is then transferred to the root through the frame, column segment wall panels, etc. The internal load and external load of the cabin are summarized to calculate the equivalent axial pressure at the root, and the equivalent axial pressure under the envelope working condition is used to avoid local overload.

8. The method for static testing of a large multi-cabin structure of a spacecraft according to claim 1, characterized in that: The loading fixture for the external load is installed above the cabin using a steel solid fixture and connected to the cabin by screws; the internal load is divided into four areas: Quadrant I, Quadrant II, Quadrant III, and Quadrant IV. The actual instrument panels and angle grid beam systems are installed in Quadrant I and Quadrant II, and the loading of Quadrant III and Quadrant IV is applied to the connecting frame through the fixture.

9. The method for static testing of a large multi-cabin structure of a spacecraft according to claim 1, characterized in that: In the static loading test, pre-test loading and unloading are carried out first; for the assessment of local air pressure and load combined loading, a pressure monitoring pipeline and an air charging pipeline are respectively connected to the water inlet flange of the lower cover of the cabin, and a pressure monitoring pipeline is connected to a process port flange in the middle of the cabin. Each pressure monitoring pipeline is connected to a pressure gauge for monitoring the internal pressure of the cabin, and the air charging pipeline is connected to the outlet of the high-purity nitrogen bottle for injecting pressure into the cabin. High-purity nitrogen is used to pressurize the cabin in a manually controlled manner and the displacement and strain data are tested; after the cabin is pressurized to 1atm pressure, a load test is carried out; the load-displacement and load-strain loading and unloading curves obtained from the load test are linear, the test data is consistent with the actual stress state of the test piece, the return to zero state after unloading is good, and there is no obvious load drop phenomenon during the test, indicating that the single-cabin structure design meets the requirements.

Images