Satellite preload force applying device and precise measurement method thereof

Abstract

The present invention provides a satellite preload force application device and a precision measurement method thereof, wherein the satellite preload force application device is suitable for locking and releasing a satellite assembly formed by stacking multiple satellite bodies. Each separation strut of the satellite bodies is superimposed and connected; the top of the connected separation struts is provided with an end cap, and the bottom of the connected separation struts is provided with a base. The base connects the satellite assembly to a carrier via fasteners. Two tension rods are provided between the base and the end caps. The two tension rods are respectively provided on both sides of the connected separation struts and apply pressure along the axis of the satellite assembly to lock the satellite assembly. Each tension rod is provided with a preload force monitoring system; and a locking and releasing mechanism is provided on the top of the end cap. The present invention provides multiple strain gauges on the cross section of the tension rods, and monitors the strain gauges through the preload force monitoring system, thereby accurately measuring the preload force on the tension rods, ensuring that the tension rods have good consistency.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft precision measurement, and in particular to a satellite preload applying device and a precision measurement method thereof. Background Art

[0002] With the successful launch of Starlink satellites, stacked satellite launches have become the preferred method for launching multiple satellites with a single rocket, thanks to their simple structure, high space utilization, and low launch costs compared to traditional launch methods. Preload is a key element of satellite stacking design, ensuring the stability of the satellite baseband frequency during launch. Therefore, the preload application process is crucial to the success of satellite stacking.

[0003] The preload force of the satellite stacking assembly determines the fundamental frequency of the assembly. Traditional preload force application mainly relies on controlling the tightening torque of the screws. This method makes it difficult to accurately measure the preload force, has poor consistency, and easily causes the tension rod to twist and deform, which cannot meet the preload force application requirements of the satellite stacking assembly.

[0004] At the same time, during the application of preload force to the satellite stack assembly, the following issues need to be addressed:

[0005] 1) Preload force measurement standard: that is, the method for determining the size of the preload force applied;

[0006] 2) Preload force consistency: that is, the sizes of different preload force carriers are basically the same;

[0007] 3) Preload application operating space: that is, the preload application requires sufficient operating space to avoid interference;

[0008] 4) Gap treatment caused by preload: The load-bearing carrier undergoes elastic deformation before and after the preload is applied, so the gap change needs to be treated;

[0009] 5) Torque application: The application of preload will increase the tightening torque of the load-bearing carrier connecting screws or pyrotechnics, so the torque needs to be applied reasonably to prevent excessive torque. Summary of the Invention

[0010] The purpose of the present invention is to provide a preload application device and its precision measurement solution that can solve the above problems, including a monitoring system, an application system, a load-bearing beam, a load-bearing rod, an adjustment gasket, and an adjustment nut, to improve the precision measurement efficiency and accuracy.

[0011] In order to achieve the above object, the present invention adopts the following technical solutions:

[0012] A method for accurately measuring a satellite preload force application device comprises the following steps:

[0013] S1: Installation: Install the satellite assembly on the carrier through the base, and install the end cap on the top of the separation pillar. Install a load-bearing beam above the end cap, and install an application system between the load-bearing beam and the end cap. The application system includes a jack, a data acquisition system, and a control system. The jack is installed between the load-bearing beam and the end cap. The load-bearing beam and the end cap are connected and fixed at both ends through a load-bearing rod and an adjustment nut. The bottom of the end cap is connected to the tension rod through a flange, and the bottom of the tension rod is connected to the base through a falling mechanism; install several strain gauges at the corresponding positions of the cross section of the tension rod. The strain gauges are connected to the preload monitoring system through cables and data acquisition devices, and the preload monitoring system and the application system are connected and conducted respectively;

[0014] S2: As described in step S1, the base and the carrier are connected by fasteners. The fasteners are initially tightened. The initial tightening torque is less than the difference between the standard tightening torque of the fastener and the torque generated by the pre-tightening force, so as to prevent the fastener torque from exceeding the standard tightening torque of the fastener after the pre-tightening force is applied.

[0015] S3: Pre-application of preload: The strain of the preload monitoring system is reset to zero and data collection begins. The system initially applies preload, records the data of each strain gauge on the tension rod, and evaluates the consistency of the tension on the tension rod.

[0016] If the tension is inconsistent, adjust the installation position of the load-bearing beam: Unload the system, and adjust the installation position of the load-bearing beam by adjusting the nut according to the data of the strain gauge in the previous step: make the preload force of the two inconsistent tension rods consistent; tighten the adjustment nut;

[0017] S4: Preload: Apply the preload input by the system, control the jack to slowly press down to complete the preload application, and after the preload reaches the standard, the application system starts the voltage stabilization mode and maintains it. At this time, the data of each strain gauge on the tension rod is recorded;

[0018] S5: Measure the gap between the tension rod and the end cap with a feeler gauge and fill the gap with an adjusting shim;

[0019] S6: Unload the system and remove the jack. Record the data changes of each strain gauge on the tension rod. The change is required to be less than 3%;

[0020] S7: Tighten the fasteners connecting the base at the lower end of the tension rod and the carrier again. The tightening torque is the standard tightening torque of the fasteners.

[0021] S8: Record the data changes of each strain gauge on the tension rod again, and finally make the error between the strain magnitude and the calibration value less than 5%;

[0022] S9: disconnect the preload monitoring system and the preload application is completed;

[0023] S10: The adjustment gasket that fills the gap is fixed with screws to prevent the adjustment gasket from falling off during the separation process of the satellite assembly.

[0024] Furthermore, before step S2, strain gauge detection and calibration are performed: after the strain gauge is pasted on the corresponding cross section of the tension rod, a tensile test is performed on the tension rod through the application system, and the applied preload force is loaded in equal parts, each time by tons, and the strain data after each loading is recorded; the above loading test process is carried out at least three times to verify the effectiveness of the strain gauge, so that the obtained strain data can be used as one of the standards for measuring the size of the preload force on the tension rod.

[0025] The present invention also provides a satellite preload force applying device, which is suitable for locking and releasing a satellite assembly formed by stacking a number of satellite bodies, wherein each separation pillar of the satellite bodies on the satellite assembly is stacked and connected; the top of the connected separation pillar is provided with an end cap, and the bottom end of the connected separation pillar is provided with a base, and the base is connected to the carrier through a fastener, and two tensioning rods are provided between the base and the end cap, and the bottoms of the two tensioning rods are connected to the base through a falling mechanism, and the two tensioning rods are respectively provided on both sides of the connected separation pillar and apply pressure along the axis direction of the satellite assembly to lock the satellite assembly, and each tensioning rod is provided with a preload force monitoring system; the top of the end cap is provided with a locking and releasing mechanism.

[0026] Preferably, the locking and releasing mechanism comprises a load-bearing beam and an application system, wherein the application system is arranged between the load-bearing beam and the center of the end cap, and the application system is conductively connected to the preload force detection system.

[0027] Preferably, the preload monitoring system includes several strain gauges, cables and a data collector, and its function is to measure the preload of each tension rod and the consistency of the preload of different tension rods through the data of the strain gauges.

[0028] Preferably, the tension rod is provided with at least two sections, and each section is pasted with at least two strain gauges along the cylindrical surface, so as to reduce the data error transmitted by the strain gauges.

[0029] Preferably, the application system includes a jack, a data acquisition system and a control system, the top of the jack is in contact with the load-bearing beam, and the bottom of the jack is in contact with the end cap on the satellite assembly; the control system controls the jack according to the input force to slowly lift the load-bearing beam, synchronously applies pre-tightening force to multiple tension rods, and collects the force magnitude through the data acquisition system.

[0030] Preferably, the two ends of the load-bearing beam and the two ends of the end cap are respectively connected through load-bearing rods, the top of the load-bearing rod is connected to the top of the load-bearing beam, the bottom of the load-bearing rod is arranged on the end cap, and the tension rod is passed through a flange in the end cap and connected to the load-bearing rod.

[0031] Preferably, the top of the load-bearing rod is passed through the top of the load-bearing beam and is adjustably connected via an adjusting nut.

[0032] Preferably, at least one set of adjusting gaskets is provided between the flange and the end cap, and the adjusting gaskets are fixed by screws after the pre-tightening force is applied.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] 1. The present invention provides multiple strain gauges on the cross section of the tension rod, and uses a preload monitoring system to monitor the strain on the strain gauges, thereby accurately measuring the preload on the tension rod. After monitoring and adjustment, two tension rods in a group can have good consistency, and can contact satellites at different levels evenly and reliably, with ideal mechanical properties.

[0035] 2. The present invention provides a large operating space during the application process by setting a load-bearing rod. The preload application system can apply multiple sets of preloads simultaneously and synchronously, which is highly efficient and can ensure that the force on the star is balanced.

[0036] 3. In the present invention, the pre-tightening force on the tension rod is generated by the thrust of the application system along the axis of the tension rod through the slow lifting of the jack, thereby avoiding the problem of twisting and deformation of the tension rod during the application process of the traditional method. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 This is a schematic structural diagram of a satellite body in a satellite preload force applying device proposed by the present invention;

[0038] Figure 2 This is a schematic structural diagram of a satellite assembly in a satellite preload force applying device proposed by the present invention;

[0039] Figure 3 This is a structural schematic diagram of a satellite preload force applying device proposed by the present invention installed on a satellite assembly;

[0040] Figure 4 This is a schematic structural diagram of a preload force applying device in a satellite preload force applying device proposed by the present invention;

[0041] Figure 5 This is a structural schematic diagram of a base in a satellite preload force applying device proposed by the present invention.

[0042] The serial numbers in the figure are as follows:

[0043] 1. Satellite assembly; 2. Preload application device; 3. Load-bearing beam; 4. End cap; 5. Jack; 6. Load-bearing rod; 7. Adjustment nut; 8. Explosive bolt; 9. Tension rod; 10. Flange; 11. Adjustment gasket; 12. Base; 13. Separation pillar; 14. Falling mechanism. DETAILED DESCRIPTION

[0044] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0045] like Figure 3 As shown, the present invention discloses a precise measurement method for a satellite preload force applying device, and the steps are as follows:

[0046] S1: Installation: Install the bottom of the separation pillar 13 on the satellite assembly on the carrier through the base, and install the end cap 4 on the top of the separation pillar 13, install the load-bearing beam 3 above the end cap 4, and install the application system between the load-bearing beam 3 and the end cap 4. The application system includes a jack 5, a data acquisition system and a control system. The jack 5 is installed between the load-bearing beam 3 and the end cap 4. The two ends of the load-bearing beam 3 and the end cap 4 are connected and fixed by a load-bearing rod 6 and an adjusting nut 7. The bottom of the end cap 4 is connected to the tension rod 9 through a flange, and the tension rod 9 is also provided with a blasting bolt 8 for blasting. The bottom of the tension rod 9 is connected to the base 12 through a falling mechanism 14; several strain gauges are installed at the corresponding positions of the cross section of the tension rod 9. The strain gauges are connected to the preload monitoring system through cables and data collectors, and the preload monitoring system and the application system are connected and conducted respectively;

[0047] S2: As described in step S1, the base 12 is connected to the carrier through fasteners, and the fasteners are initially tightened. The initial tightening torque is less than the difference between the standard tightening torque of the fastener and the torque generated by the pre-tightening force, so as to prevent the fastener torque from exceeding the standard tightening torque of the fastener after the pre-tightening force is applied;

[0048] S3: Pre-application of preload: The strain of the preload monitoring system is reset to zero and data collection begins. The preload is initially applied through the application system, and the data of each strain gauge on the tension rod 9 is recorded to evaluate the consistency of the tension of the tension rod 9.

[0049] If the tension is inconsistent, adjust the installation position of the load-bearing beam 3: unload the system, and adjust the installation position of the load-bearing beam 3 by adjusting the nut 7 according to the data of the strain gauge in the previous step: make the preload forces of the two inconsistent tension rods 9 tend to be consistent; tighten the adjusting nut 7;

[0050] S4: Preload: The preload applied by the system input is controlled to slowly press down the jack 5 to complete the preload application. After the preload reaches the target, the system starts the voltage stabilization mode and maintains it. At this time, the data of each strain gauge on the tension rod 9 is recorded.

[0051] S5: Measure the gap between the tension rod 9 and the end cap 4 with a feeler gauge and fill the gap with the adjusting gasket 11;

[0052] S6: Unload the application system and remove the jack 5. Record the data changes of each strain gauge on the tension rod 9. The change is required to be less than 3%;

[0053] S7: Tighten the base 12 at the lower end of the tension rod 9 and the fasteners connected to the carrier again, and the tightening torque is the standard tightening torque of the fasteners;

[0054] S8: Record the data changes of each strain gauge on the tension rod 9 again, and finally make the error between the strain magnitude and the calibration value less than 5%;

[0055] S9: disconnect the preload monitoring system and the preload application is completed;

[0056] S10: The adjustment gasket 11 filling the gap is fixed by screws to prevent the adjustment gasket 11 from falling off during the separation process of the satellite assembly.

[0057] Furthermore, before step S2, strain gauge detection and calibration are performed: after the strain gauge is pasted on the corresponding cross section of the tension rod 9, a tensile test is performed on the tension rod 9 through the application system, and the applied preload force is evenly divided into 3 loadings, and the strain data after each loading is recorded; the above loading test process is performed at least three times to verify the effectiveness of the strain gauge, so that the obtained strain data is used as one of the standards for measuring the size of the preload force on the tension rod 9.

[0058] like Figures 1 to 5As shown, the satellite preload force applying device provided by the present invention is suitable for locking and releasing a satellite assembly formed by stacking a plurality of satellite bodies, wherein each separation pillar 13 of a satellite body on the satellite assembly is superimposed and connected; the top of the separation pillar 13 after connection is provided with an end cap 4, and the bottom end of the separation pillar 13 after connection is provided with a base 12, and the base 12 is connected to the carrier through a fastener, and two tension rods 9 are provided between the base 12 and the end cap 4, and the bottoms of the two tension rods 9 are connected to the base 12 through a falling mechanism 14, and the two tension rods 9 are respectively provided at the separation pillars 13 after connection. Pressure is applied on both sides of the pillar 13 and along the axis of the satellite assembly to lock the satellite assembly. Each tensioning rod 9 is provided with a preload monitoring system, which includes several strain gauges, cables and data collectors. Its function is to measure the preload size of each tensioning rod 9 and the consistency of the preload of different tensioning rods 9 through the data of the strain gauges; the top of the end cap 4 is provided with a locking release mechanism 2, which includes a load-bearing beam 3 and an application system. The application system is arranged between the load-bearing beam 3 and the center of the end cap 4, and the application system is conductively connected to the preload detection system.

[0059] Furthermore, to reduce strain gauge errors, the tension rod 9 provided by the present invention is provided with at least two cross-sections. Multiple (≥2) strain gauges must be attached to each cross-section of the tension rod at equal angles along the cylindrical surface. After attachment, the strain gauges must be inspected and calibrated to verify their effectiveness.

[0060] The application system provided by the present invention includes a jack 5, a data acquisition system and a control system. The top of the jack 5 contacts the load-bearing beam 3, and the bottom of the jack 5 contacts the end cap 4 on the satellite assembly; the control system controls the jack 5 according to the input force to slowly push up the load-bearing beam 3. The load-bearing beam 3 is the main force carrier of the jack 5, and its function is to transfer the preload force to the tensioning rod through the load-bearing rod to complete the application of the preload force; the preload force is applied to multiple tensioning rods 9 synchronously, and the force size is collected through the data acquisition system.

[0061] Furthermore, the two ends of the load-bearing beam 3 and the two ends of the end cap 4 are respectively connected by a load-bearing rod 6. The top of the load-bearing rod 6 is connected to the top of the load-bearing beam 3. The top of the load-bearing rod 6 is inserted into the top of the load-bearing beam 3 and is adjustably connected via an adjustment nut 7. The tension rod 9 is inserted into the end cap 4 via a flange and connected to the load-bearing rod 6. Due to the shape and position errors and installation errors of the tension rod 9, when the preload is applied, it is necessary to adjust the installation position of the load-bearing beam, that is, the angular relationship between the lower end face of the load-bearing beam 3 and the upper end face of the satellite assembly 1, to ensure that the tension rods 9 on both sides of each separation pillar 13 are evenly stressed. The adjustment nut 7 adjusts the position of the load-bearing beam 3 and the load-bearing rod 3 by adjusting the height on both sides to meet the requirement of even stress on the tension rod. At the same time, after adjustment, the positional relationship between the two can be fixed to ensure reuse. The distance between the load-bearing rod 6 and the end cap 4 is used to create space for applying preload and ensure the installation space requirements of various tooling equipment.

[0062] Furthermore, after the preload is applied, a gap exists between the flange on the tension rod and the end cap. Therefore, an adjustment gasket is required to fill this gap and ensure the assembled contact between the tension rod and the end cap after the preload is applied. Therefore, the present invention connects the gap between the flange and the end cap 4 by filling it with an adjustment gasket 11. The adjustment gasket 11 is a semi-circular thin sheet of varying thickness, and has holes for fasteners. After the preload is applied, the adjustment gasket 11 is secured with screws to prevent the gasket from falling off after orbital separation, creating debris and the risk of collision with the satellite.

[0063] The following is a detailed description using specific examples and data:

[0064] Example

[0065] This embodiment takes a 20-satellite stacking assembly as an example, and the preload force is 3 tons.

[0066] S1: Install the load-bearing rods 6, 3 and the adjusting nuts 7 on the satellite stacking assembly, and connect the preload monitoring system and the application system respectively;

[0067] S2: As described in step S1, the base 12 and the adapter connecting fasteners are initially tightened, and the tightening torque is less than the torque generated by the fastener tightening torque and the pre-tightening force to prevent the fastener torque from being too large after the pre-tightening force;

[0068] S3: Preload: The preload monitoring system is reset to zero strain and data collection begins. A preliminary preload of approximately 0.5 tons (which can be appropriately selected based on the actual total preload) is applied through the system. Data from each strain gauge on the tension rod 9 is recorded to assess the consistency of the tension on the tension rod 9.

[0069] If the tension is inconsistent, adjust the installation position of the load-bearing beam 3 of the group of satellites with inconsistent tension: apply system unloading, and adjust the installation position of the load-bearing beam 3 according to the strain size in the previous step so that the pre-tightening force of the two tension rods 9 in the group of satellites tends to be consistent; until the pre-tightening force of the two tension rods 9 in the group is within 50kg, tighten the adjustment nut 7;

[0070] S4: Preload: Apply the preload applied by the system input, control the jack 5 to slowly complete the preload application, and after the preload application reaches the standard, the application system starts the voltage stabilization mode and maintains it, and records the data of each strain gauge on the tension rod;

[0071] S5: Use a feeler gauge to measure the gap between the flange on the tension rod and the end cap 4, fill it with an adjusting shim 11, and install the shim connecting screws; the thickness of the adjusting shim 11 should be larger than the gap measured by the feeler gauge (generally required to be 0.03mm larger, which can be appropriately increased or decreased according to the deformation of the tension rod);

[0072] S6: Unload the applied system and remove the jack 5. The data change of each strain gauge on the tension rod 9 is required to be less than 3%. Otherwise, it is necessary to detect whether the gap is reduced due to the compression of the gasket, and the gasket thickness should be increased.

[0073] S7: The lower end of the tension rod 9 is connected to the fastener and tightened again. The tightening torque is the standard tightening torque of the fastener;

[0074] S8: Record the data changes of each strain gauge on the tension rod 9 again, and finally make the error between the strain magnitude and the calibration value less than 5%;

[0075] S9: disconnect the preload monitoring system and the preload application is completed;

[0076] S10: Install the fixing screws of the adjustment gasket 11 to prevent the gasket from falling off during the separation process.

[0077] Through the above devices and precise measurement methods, the preload force of each tension rod in the 20-star stacking assembly is within the range of 30,000N±1,000N, meeting the index requirements and verified by mechanical tests.

[0078] Compared with conventional inventions, the preload force applying device and its precise measurement method in the present invention have the following advantages:

[0079] 1. The present invention provides multiple strain gauges on the cross section of the tension rod, and uses a preload monitoring system to monitor the strain on the strain gauges, thereby accurately measuring the preload on the tension rod. After monitoring and adjustment, two tension rods in a group can have good consistency, and can contact satellites at different levels evenly and reliably, with ideal mechanical properties.

[0080] 2. The present invention provides a large operating space during the application process by setting a load-bearing rod. The preload application system can apply multiple sets of preloads simultaneously and synchronously, which is highly efficient and can ensure that the force on the star is balanced.

[0081] 3. In the present invention, the pre-tightening force on the tension rod is generated by the thrust of the application system along the axis of the tension rod through the slow lifting of the jack, thereby avoiding the problem of twisting and deformation of the tension rod during the application process of the traditional method.

[0082] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0083] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature identified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0084] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A method for accurately measuring a satellite preload force application device, characterized in that: Here are the steps: S1: Installation: A preload force applying device is installed on the satellite assembly (1). Specifically, the satellite bodies are stacked on the base (12) to form the satellite assembly (1), and the base (12) is installed on the carrier. An end cap (4) is installed on the upper end of the separation support (13) on the top of the satellite assembly (1). A load-bearing beam (3) is installed above the end cap (4). An application system is installed between the load-bearing beam (3) and the end cap (4). The application system includes a jack (5), a data acquisition system and a control system. The jack (5) is installed. Installed between the load-bearing beam (3) and the end cap (4), the two ends of the load-bearing beam (3) and the end cap (4) are connected and fixed by a load-bearing rod (6) and an adjusting nut (7), the bottom of the end cap (4) is connected to the tension rod (9) through a flange, and the bottom of the tension rod (9) is connected to the base (12) through a falling mechanism (14); a plurality of strain gauges are installed at corresponding positions of the cross section of the tension rod (9), the strain gauges are connected to the preload monitoring system through cables and a data acquisition device, and the preload monitoring system and the application system are connected and conducted respectively; S2: As described in step S1, the base (12) is connected to the carrier through a fastener, and the fastener is initially tightened. The initial tightening torque is less than the difference between the standard tightening torque of the fastener and the torque generated by the pre-tightening force, so as to prevent the fastener torque from exceeding the standard tightening torque of the fastener after the pre-tightening force is applied; S3: Pre-applying pre-tightening force: the strain of the pre-tightening force monitoring system is cleared and the collection is started; the pre-tightening force is initially applied by the application system, the data of each strain gauge on the tension rod (9) is recorded, and the consistency of the tension of the tension rod (9) is evaluated; If the tension is inconsistent, adjust the installation position of the load-bearing beam (3): apply system unloading, and adjust the installation position of the load-bearing beam (3) by adjusting the nut (7) according to the data of the strain gauge in the previous step: make the preload forces of the two inconsistent tension rods (9) tend to be consistent; lock the adjusting nut 7; S4: Preload: Apply the preload applied by the system input, control the jack (5) to slowly press down to complete the preload application, and after the preload application reaches the standard, the application system starts the voltage stabilization mode and maintains it. At this time, record the data of each strain gauge on the tension rod (9); S5: Measure the gap between the tension rod (9) and the end cap (4) using a feeler gauge, and fill the gap by adjusting the gasket (11); S6: Unload the application system and remove the jack (5), record the data changes of each strain gauge on the tension rod (9), and the change is required to be less than 3%; S7: Tighten the base (12) at the lower end of the tension rod (9) and the fasteners connected to the carrier again, and the tightening torque is the standard tightening torque of the fasteners; S8: Record the data changes of each strain gauge on the tension rod (9) again, and finally make the error between the strain magnitude and the calibration value less than 5%; S9: disconnect the preload monitoring system and the preload application is completed; S10: The adjusting gasket (11) for filling the gap is fixed by screws to prevent the adjusting gasket (11) from falling off during the separation process of the satellite assembly (1).

2. The precise measurement method of a satellite preload force applying device according to claim 1, characterized in that: Before step S2, the strain gauge detection and calibration is performed: after the strain gauge is pasted on the corresponding cross section of the tension rod (9), the tension rod (9) is subjected to a tension test through the application system, the applied preload force is evenly divided into 3 loadings, and the strain data after each loading is recorded; the above loading test process is performed at least three times to verify the effectiveness of the strain gauge, so that the obtained strain data is used as one of the standards for measuring the size of the preload force on the tension rod (9).

3. A satellite preload force applying device, applied to the precision measurement method of the satellite preload force applying device according to claim 1, wherein the satellite preload force applying device is suitable for locking and releasing a satellite assembly (1) formed by stacking a plurality of satellite bodies, wherein each separation support (13) of the satellite bodies on the satellite assembly (1) is superimposed and connected; characterized in that: The top end of the connected separation pillar (13) is provided with an end cap (4), and the bottom end of the connected separation pillar (13) is provided with a base (12). The base (12) connects the satellite assembly (1) to the carrier through a fastener. Two tension rods (9) are provided between the base (12) and the end cap (4). The bottoms of the two tension rods (9) are connected to the base (12) through a falling mechanism (14). The two tension rods (9) are respectively provided on both sides of the connected separation pillar (13) and apply pressure along the axis direction of the satellite assembly (1) to lock the satellite assembly (1). Each tension rod (9) is provided with a preload monitoring system; and a locking release mechanism (2) is provided on the top of the end cap (4).

4. A satellite preload force applying device according to claim 3, characterized in that: The locking and releasing mechanism (2) comprises a load-bearing beam (3) and an application system, wherein the application system is arranged between the load-bearing beam (3) and the center of the end cap (4), and the application system is conductively connected to a preload detection system.

5. The satellite preload force applying device according to claim 3, characterized in that: The preload monitoring system comprises a number of strain gauges, cables and a data collector, and its function is to measure the preload size of each tensioning rod (9) and the consistency of the preload of different tensioning rods (9) through the data of the strain gauges.

6. The satellite preload force applying device according to claim 5, characterized in that: The tension rod (9) is provided with at least two cross sections, and each cross section has at least two strain gauges attached along a cylindrical surface, so as to reduce the data error transmitted by the strain gauges.

7. The satellite preload force applying device according to claim 4, characterized in that: The application system includes a jack (5), a data acquisition system and a control system. The top of the jack (5) contacts the load-bearing beam (3), and the bottom of the jack (5) contacts the end cap (4) on the satellite assembly (1). The control system controls the jack (5) according to the input force to slowly push up the load-bearing beam (3), synchronously applies pre-tightening force to multiple tension rods (9), and collects the magnitude of the force through the data acquisition system.

8. The satellite preload force applying device according to claim 4, characterized in that: The two ends of the load-bearing beam (3) and the two ends of the end cap (4) are respectively connected through a load-bearing rod (6), the top of the load-bearing rod (6) is connected to the top of the load-bearing beam (3), the bottom of the load-bearing rod (6) is arranged on the end cap (4), and the tension rod (9) is passed through the end cap (4) through a flange and connected to the load-bearing rod (6).

9. The satellite preload force applying device according to claim 8, characterized in that: The top of the load-bearing rod (6) is passed through the top of the load-bearing beam (3) and is adjustably connected via an adjusting nut (7).

10. The satellite preload force applying device according to claim 8, characterized in that: At least one set of adjustment gaskets (11) is filled and connected between the flange and the end cap (4), and the adjustment gaskets (11) are fixed by screws after the pre-tightening force is applied.

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