A method for determining the bending moment resistance of satellite waveguide switches

Abstract

The present invention relates to a method for determining the bending moment resistance of a satellite waveguide switch, and belongs to the field of mechanical engineering technology. The method superimposes the maximum radial deformation of the switch radio frequency housing caused by the assembly deviation source, the thermal mismatch deviation source, the gravity prestress deviation source, and the vibration stress deviation source, and the shaft coaxiality deviation caused by the actual process defects of the waveguide switch, to obtain the maximum deformation of the radio frequency housing under the worst working condition; based on the bending moment analysis benchmark, the maximum deformation of the radio frequency housing under the worst working condition is equivalent to the broadside bending moment M acting at the free port of the standard straight waveguide, and the bending moment resistance of the waveguide switch is quantitatively determined, which can be used as the test magnitude basis for the acceptance of the bending moment test of the waveguide switch.

Description

Technical Field

[0001] The present invention relates to a method for determining the bending moment resistance of a satellite waveguide switch under the combined effects of complex layout, diverse connections, assembly deviation, gravity deformation, mechanical environment of the launch stage and ground test, high and low temperature environment on orbit, etc., which can provide reasonable bending moment resistance design indicators for the development of satellite waveguide switch products. The present invention belongs to the field of mechanical engineering technology. Background Art

[0002] Waveguide switches are key components of satellite payloads, and are mainly used for loop backup of amplifiers in satellite transponder subsystems to improve satellite reliability. A typical waveguide switch includes a drive motor and an RF shaft. The drive motor rotor is fixedly connected to the RF shaft. The drive motor is installed in the drive housing, and the RF shaft is installed in the RF housing. A switch flange is provided on the outside of the RF housing for connecting the waveguide. The working principle of a typical waveguide switch is as follows: after receiving the command signal, the drive motor provides a torque to drive the motor rotor and the RF shaft to rotate toward the target state. After reaching the position, the locking magnet provides a locking torque to keep the switch in the working state and complete the RF channel switching.

[0003] To ensure good RF performance of the switch, the gap between the inner cavity of the RF housing and the rotor needs to be controlled at tens of microns. At the same time, under the pressure of reducing the weight of the spacecraft, the miniaturization and lightweight design of waveguide switches continue to advance. The switch faces a complex mechanical environment in actual use on the satellite. Due to the combined effects of factors such as complex waveguide layout, diverse switch connections, mechanical and thermal coupling, assembly deviation, and process deviation, there is a potential risk of switch rotation jamming due to excessive deformation of the RF housing.

[0004] At present, there is no systematic and effective method for designing the bending moment resistance of waveguide switches at home and abroad. Product designers carry out relevant designs based on their own experience, which is prone to over-design or under-design of structures. At the least, it will cause redundant and heavy structures and increase launch costs. At the worst, it will cause product jamming and failure, repeated designs, and affect the progress of spacecraft models and missions.

[0005] At present, the waveguide switch product design based on the designer's experience does not pay enough attention to the actual use environment of the product on the satellite, and it is impossible to accurately propose reasonable anti-bending moment design indicators in the early stage of product development. Driven by the design requirements of lightweight and miniaturized aerospace products, it is easy to cause the switch's anti-bending moment design to be insufficient, and even lead to repeated product design, which greatly delays the progress of model development and generates huge direct or indirect economic losses. The current waveguide switch product anti-bending moment design has the following shortcomings:

[0006] (1) There is a lack of quantitative budget for the installation stress caused by the onboard waveguide assembly deviation;

[0007] (2) There is a lack of quantitative budget for the prestress caused by the gravity of the cabin during the ground test phase of the whole satellite;

[0008] (3) There is a lack of quantitative budget for the worst stress scenarios of waveguide switch port connection forms and multi-switch component connection forms;

[0009] (4) There is a lack of quantitative budget for the worst stress scenario caused by thermal mismatch between the cabin and waveguide and waveguide switch components during satellite ground thermal testing and on-orbit environment;

[0010] (5) There is a lack of quantitative budget for the worst stress scenarios caused by satellite component-level, star-level ground mechanical tests, and launch phase vibration environment. Summary of the invention

[0011] The technical problem solved by the present invention is: to overcome the above-mentioned shortcomings and provide a method for determining the bending moment resistance of a satellite waveguide switch, which is used for system bending moment budget analysis under the comprehensive effects of complex layout, diverse connections, assembly deviation, gravity deformation, mechanical environment of the launch segment and ground test, high and low temperature environment on orbit, etc., so as to provide reasonable bending moment resistance design indicators for the development of waveguide switch products.

[0012] The technical solution of the present invention is: a method for determining the bending moment resistance of a satellite waveguide switch, the method comprising the following steps:

[0013] Establish a first component-level finite element physical model of a waveguide switch connected to a single standard straight waveguide, a second component-level finite element physical model of a waveguide switch connected to four standard straight waveguides, and a star-level finite element physical model including the on-board waveguide and the secondary structure of the waveguide switch;

[0014] A unit broadside bending moment is applied to the standard straight waveguide free port in the first component level finite element physical model to obtain a bending moment analysis benchmark;

[0015] The maximum allowable deviation of the final assembly is introduced into the second-component-level finite element physical model to calculate the maximum radial deformation of the waveguide switch RF housing caused by the final assembly deviation source;

[0016] The maximum temperature difference between the waveguide switch and the cabin is introduced into the second component level finite element physical model to calculate the maximum radial deformation T of the switch RF housing caused by the thermal mismatch deviation source;

[0017] Apply gravity field to the finite element physical model of the whole star, and calculate the radial deformation of the switch RF housing caused by gravity prestress deviation sources under different gravity conditions;

[0018] Apply ground test carrier sinusoidal excitation to the whole star finite element model and calculate the maximum radial deformation F of the switch RF housing caused by the vibration stress deviation source;

[0019] The maximum radial deformation of the switch RF housing caused by the assembly deviation source, thermal mismatch deviation source, gravity prestress deviation source and vibration stress deviation source and the shaft coaxiality deviation caused by the actual process defects of the waveguide switch are superimposed to obtain the maximum deformation of the RF housing under the worst working condition;

[0020] According to the bending moment analysis benchmark, the maximum deformation of the RF housing under the worst working condition is equivalent to the broadside bending moment M acting at the free port of the standard straight waveguide. The broadside bending moment M is used to characterize the bending moment resistance of the satellite waveguide switch.

[0021] Preferably, the waveguide switch model in the first component-level finite element model and the second component-level finite element model includes at least three parts: a switch base, a RF housing, and a drive housing. The material properties of the finite element physical model are the same as the actual material properties of each component, and the boundary condition is that the switch base is fixed with screw holes.

[0022] Preferably, the boundary condition of the entire star-level finite element physical model of the waveguide switch is the fixed support of the satellite-rocket docking frame.

[0023] Preferably, the bending moment analysis benchmark includes the free end displacement d0 of the standard straight waveguide, the strain value ε0 of the connection root between the straight waveguide and the wave switch, and the maximum radial deformation μ0 of the RF housing.

[0024] Preferably, the maximum allowable deviation of the final assembly includes three types of deviations, namely: waveguide port misalignment, waveguide port non-parallelism, and switch installation bottom surface unevenness; the specific steps of introducing the maximum allowable deviation of the final assembly into the second component-level finite element physical model are:

[0025] The waveguide port misalignment is introduced at the four standard straight waveguide free ports to obtain the maximum radial deformation D of the switch RF housing;

[0026] The non-parallelism of the waveguide ports is introduced at the four standard straight waveguide free ports to obtain the maximum radial deformation P of the switch RF housing;

[0027] The bottom surface unevenness is introduced into the switch base, and the four waveguide free ports are fixed to obtain the maximum radial deformation B of the switch RF housing.

[0028] Preferably, the specific method for calculating the maximum radial deformation T of the switch RF housing caused by the thermal mismatch deviation source is:

[0029] The mechanical-thermal coupling analysis method is used to fix the four straight waveguide free ports and introduce temperature rise to obtain the maximum radial deformation T of the switch RF housing, which is the maximum radial deformation of the switch RF housing caused by the thermal mismatch deviation source. The temperature rise is the maximum temperature difference between the waveguide switch and the cabin.

[0030] Preferably, the specific steps of calculating the radial deformation of the switch RF housing caused by the gravity prestress deviation source under different gravity conditions are as follows:

[0031] The whole satellite coordinate system is defined as follows: the X direction is parallel to the theoretical normal direction of the satellite east plate, and the Z direction is parallel to the axis of the load-bearing cylinder;

[0032] Constrain the displacement of the satellite-rocket docking frame, apply the gravity load in the X-axis direction, and obtain the gravity deformation d of the cabin G ;

[0033] The gravity deformation of the cabin plate is equivalent to the reference value of radial deformation of the switch RF housing caused by the gravity prestress deviation source;

[0034] According to the reference value of radial deformation of the switch RF housing caused by the gravity prestress deviation source, the radial deformation of the switch RF housing caused by the gravity prestress deviation source under different working conditions is calculated;

[0035] Gravity conditions include ground assembly test conditions, ground thermal test conditions, on-orbit operation conditions, and ground force test conditions;

[0036] Under the ground assembly test condition, the whole satellite is rotated from +X downward 180° to -X downward, and the radial deformation of the switch RF housing caused by gravity prestress is equal to the reference value of the radial deformation of the switch RF housing caused by the gravity prestress deviation source;

[0037] Under the ground thermal test conditions and on-orbit conditions, the radial deformation of the switch RF housing caused by gravity prestress is 0.5 times the reference value of the radial deformation of the switch RF housing caused by the gravity prestress deviation source;

[0038] Under the ground force test condition, the radial deformation of the switch RF housing caused by gravity prestress is 0.

[0039] Preferably, the gravity deformation of the deck is G The calculation formula of the radial deformation G of the switch RF housing caused by the gravity prestress deviation source is equivalent to:

[0040] G=(d G ·μ0) / d0.

[0041] Preferably, the calculation formula for the maximum radial deformation F of the switch RF housing caused by the vibration stress deviation source is:

[0042] F=(ε F ·μ0) / ε0

[0043] Among them, ε F is the peak strain at the root of the connection between the waveguide and the waveguide switch during vibration.

[0044] Preferably, the broadside bending moment M acting on the free port of the standard straight waveguide is:

[0045] M=(N0-N min ) / μ0

[0046] Where N0 is the waveguide switch design gap, N0-N min It is the maximum deformation of the RF housing under the worst working condition.

[0047] The beneficial effects of the present invention compared with the prior art are:

[0048] (1) The present invention determines the external stress environment that the waveguide switch will withstand during its entire life cycle by quantitatively analyzing factors such as complex layout, diverse connections, assembly deviation, gravity deformation, mechanical environment of the launch stage and ground test, and high and low temperature environment on orbit, thereby solving the difficult problem of designing the waveguide switch's anti-bending moment capability.

[0049] (2) The method for determining the bending moment resistance of a waveguide switch proposed in the present invention can be used as a basis for the acceptance of a bending moment test for a waveguide switch, thereby avoiding repeated product design and greatly saving manpower and material resources. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 It is a flow chart of a method for determining the bending moment resistance capability of a satellite waveguide switch according to an embodiment of the present invention.

[0051] Figure 2 Schematic diagram of a waveguide switch according to an embodiment of the present invention and a single 100 mm standard straight waveguide (bending moment analysis benchmark).

[0052] Figure 3 Schematic diagram of the waveguide switch and four 100 mm standard straight waveguides according to an embodiment of the present invention (the stress is the worst stress condition).

[0053] Figure 4 Schematic diagram of the misalignment of the waveguide port according to an embodiment of the present invention.

[0054] Figure 5 Schematic diagram of the non-parallelism of the waveguide port according to an embodiment of the present invention.

[0055] Figure 6 It is a schematic diagram of the unevenness of the bottom surface of the installation of an embodiment of the present invention. DETAILED DESCRIPTION

[0056] The present invention will be further described below in conjunction with the embodiments.

[0057] The present invention provides a method for determining the bending moment resistance capacity of a satellite waveguide switch, the method comprising the following steps:

[0058] S1. Establish a first component-level finite element physical model of a waveguide switch connected to a single standard straight waveguide, a second component-level finite element physical model of a waveguide switch connected to four standard straight waveguides, and a star-level finite element physical model including the on-board waveguide and the secondary structure of the waveguide switch;

[0059] The waveguide switch model in the first component-level finite element model and the second component-level finite element model includes at least three parts: a switch base, a RF housing, and a driver housing. The material properties of the finite element physical model are the same as the actual material properties of each component, and the boundary condition is that the switch base is fixed with screw holes.

[0060] The boundary condition of the finite element physical model of the entire waveguide switch star is the fixed support of the satellite-rocket docking frame.

[0061] S2. Using the structural statics analysis method, a unit width bending moment is applied to the free port of the standard straight waveguide in the first component-level finite element physical model to obtain a bending moment analysis benchmark, wherein the bending moment analysis benchmark includes the free end displacement d0 of the standard straight waveguide, the strain value ε0 at the root of the connection between the straight waveguide and the wave switch, and the maximum radial deformation μ0 of the RF housing; the unit width bending moment is 1 Nm; and the length of the standard straight waveguide is 100 mm.

[0062] S3. Using the structural statics analysis method, the maximum allowable deviation of the final assembly is introduced into the second component-level finite element physical model, and the maximum radial deformation of the waveguide switch RF housing corresponding to a single type of deviation is calculated respectively. The maximum radial deformation of the waveguide switch RF housing caused by all types of deviations is superimposed as the maximum radial deformation of the waveguide switch RF housing caused by the final assembly deviation source;

[0063] The maximum allowable deviation of the final assembly includes three types of deviations, namely: waveguide port misalignment, waveguide port non-parallelism, and switch installation bottom surface unevenness. The worst stress condition is applied to the straight waveguide free port in the second component level finite element physical model. The worst stress condition is that the radial deformation direction of the RF housing caused by the installation deviation of adjacent waveguide ports is the same.

[0064] The specific steps are:

[0065] The waveguide port misalignment is introduced at the four standard straight waveguide free ports to obtain the maximum radial deformation D of the switch RF housing;

[0066] The non-parallelism of the waveguide ports is introduced at the four standard straight waveguide free ports to obtain the maximum radial deformation P of the switch RF housing;

[0067] The bottom surface unevenness is introduced into the switch base, and the four waveguide free ports are fixed to obtain the maximum radial deformation B of the switch RF housing.

[0068] S4. Using the mechanical-thermal coupling analysis method, the maximum temperature difference between the waveguide switch and the cabin is introduced into the second component-level finite element physical model to calculate the maximum radial deformation T of the switch RF housing caused by the thermal mismatch deviation source;

[0069] The specific method is:

[0070] The mechanical-thermal coupling analysis method is used to fix the four straight waveguide free ports and introduce temperature rise to obtain the maximum radial deformation T of the switch RF housing, which is the maximum radial deformation of the switch RF housing caused by the thermal mismatch deviation source. The temperature rise is the maximum temperature difference between the waveguide switch and the cabin.

[0071] S6. Using the structural statics analysis method, a gravity field is applied to the finite element physical model of the entire star, and the gravity deformation of the cabin plate under the gravity load is calculated. Based on the bending moment analysis benchmark, the gravity deformation of the cabin plate is equivalent to the radial deformation of the switch RF housing; and then the radial deformation of the switch RF housing is used as a benchmark to calculate the radial deformation of the switch RF housing caused by the gravity prestress deviation source under different gravity conditions;

[0072] The specific steps are as follows:

[0073] S6.1. The whole satellite coordinate system is defined as follows: the X direction is parallel to the theoretical normal direction of the satellite east plate, and the Z direction is parallel to the axis of the load-bearing cylinder;

[0074] S6.2. Constrain the displacement of the satellite-rocket docking frame and apply gravity load in the X-axis direction to obtain the gravity deformation of the cabin plate d G (Deformation per 100mm G , unit: mm);

[0075] S6.3. Equivalent the gravity deformation of the cabin plate to the reference value of radial deformation of the switch RF housing caused by the gravity prestress deviation source;

[0076] The gravity deformation of the deck is d G The calculation formula of the radial deformation G (unit: μm) of the switch RF housing caused by the gravity prestress deviation source is equivalent to:

[0077] G=(d G ·μ0) / d0.

[0078] S6.4. Calculate the radial deformation of the switch RF housing caused by the gravity prestress deviation source under different working conditions based on the reference value of the radial deformation of the switch RF housing caused by the gravity prestress deviation source;

[0079] Gravity conditions include ground assembly test conditions, ground thermal test conditions, on-orbit operation conditions, and ground force test conditions;

[0080] Under the ground assembly test condition, the whole satellite is rotated from +X downward 180° to -X downward, and the radial deformation of the switch RF housing caused by gravity prestress is equal to the reference value of the radial deformation of the switch RF housing caused by the gravity prestress deviation source;

[0081] Under the ground thermal test conditions and on-orbit conditions, the radial deformation of the switch RF housing caused by gravity prestress is 0.5 times the reference value of the radial deformation of the switch RF housing caused by the gravity prestress deviation source;

[0082] Under the ground force test condition, the radial deformation of the switch RF housing caused by gravity prestress is 0.

[0083] S7. Using the structural dynamics analysis method, the ground test carrier sinusoidal excitation is applied to the whole star finite element model to calculate the strain peak value ε at the root of the waveguide and the waveguide switch connection during the vibration process. F According to the bending moment analysis standard, the strain peak value ε F Equivalent to the maximum radial deformation F of the switch RF housing caused by the vibration stress deviation source;

[0084] The peak strain ε F The calculation formula for the maximum radial deformation F of the switch RF housing caused by the vibration stress deviation source is:

[0085] F=(ε F ·μ0) / ε0.

[0086] S8. Superimpose the maximum radial deformation of the switch RF housing caused by the assembly deviation source, thermal mismatch deviation source, gravity prestress deviation source and vibration stress deviation source, and the shaft coaxiality deviation caused by the actual process defects of the waveguide switch to obtain the maximum deformation of the RF housing under the worst working condition;

[0087] S9. Based on the bending moment analysis benchmark, the maximum deformation of the RF housing under the worst working condition is equivalent to the broadside bending moment M acting at the free port of the standard straight waveguide. The broadside bending moment M is used to characterize the bending moment resistance of the satellite waveguide switch. The unit broadside bending moment is 1 Nm.

[0088] The broadside bending moment M acting on the free port of a standard straight waveguide is:

[0089] M=(N0-N min ) / μ0

[0090] Where N0 is the waveguide switch design gap, N0-N min It is the maximum deformation of the RF housing under the worst working condition.

[0091] In summary, the present invention quantitatively determines the bending moment resistance of the waveguide switch by conducting statics, dynamics, and mechanical-thermal coupling analysis on factors such as complex layout, diverse connections, assembly deviation, gravity deformation, the mechanical environment of the launch stage and ground tests, and the high and low temperature environment on orbit, and establishing an equivalent relationship between multiple factors.

[0092] Example:

[0093] Some details of the technical solution of the present invention are further described below in conjunction with the accompanying drawings.

[0094] A method for determining the bending moment resistance of a satellite waveguide switch, the process is as follows: Figure 1 As shown, the following steps are included:

[0095] Step 1: Use commercial modeling software to establish a geometric model of a waveguide switch and a 100 mm standard straight waveguide. The geometric model of the waveguide switch must at least include a switch base 4, a radio frequency housing 3, and a driver housing. Figure 2 As shown, the waveguide switch in this embodiment includes a driving housing 1, a driving motor, a RF housing 3, a RF shaft and a switch flange 2. The driving motor rotor is fixedly connected to the RF shaft. The driving motor is installed in the driving housing. The RF shaft is installed in the RF housing. A switch flange is provided outside the RF housing for connecting the waveguide. There is a gap between the RF housing and the switch flange.

[0096] The geometric model was imported into the commercial finite element software to obtain the first component-level finite element physical model of the waveguide switch connected to a single standard straight waveguide 5 and the second component-level finite element physical model of the waveguide switch connected to four standard straight waveguides. The material properties of the finite element physical model are the same as the actual material properties of each component, and the boundary condition is the switch base installation screw hole fixation.

[0097] Step 2: Use commercial finite element software to create a finite element physical model of the entire satellite including the onboard waveguide and waveguide switch secondary structure, with the boundary condition being the fixed support of the satellite-rocket docking frame;

[0098] Step 3: Use the structural statics analysis method to perform a bending moment benchmark analysis on the first component level finite element physical model. Figure 2 As shown, a 1Nm unit wide side bending moment is applied to the waveguide free port, and the bending moment analysis benchmarks are obtained: waveguide free end displacement d0 (unit: mm), strain value ε0 at the root of the connection between the waveguide and the switch, and maximum radial deformation μ0 (unit: μm) of the RF housing;

[0099] Step 4: Use the structural statics analysis method to introduce the maximum allowable deviation of the assembly into the second component level finite element physical model. The deviation introduction should meet the following requirements: Figure 3The worst stress case is shown in Figure 1. The worst stress case is that the radial deformation direction of the RF housing caused by the installation deviation of adjacent waveguide ports is the same. The maximum radial deformation of the waveguide switch RF housing corresponding to a single type of deviation is calculated respectively:

[0100] A. Introduce waveguide port misalignment (e.g. 0.2 mm, see Figure 4 ), and obtain the maximum radial deformation D (unit: μm) of the switch RF housing;

[0101] B. Introduce waveguide port non-parallelism (e.g. 0.1 mm, see Figure 5 ), and obtain the maximum radial deformation P (unit: μm) of the switch RF housing;

[0102] C. Introduce bottom surface unevenness (such as 0.1mm, see Figure 6 , number 6 in the figure is the installation cabin), the four waveguide free ports are fixed, and the maximum radial deformation B (unit: μm) of the switch RF housing is obtained.

[0103] Step 5: Use the mechanical-thermal coupling analysis method to introduce the maximum temperature difference between the waveguide component and the cabin in the second component level finite element physical model (based on the ground whole-satellite thermal test and on-orbit telemetry data, the maximum temperature difference is 30°C). The linear expansion coefficient of the carbon fiber skin cabin is 1.5×10 -6 / ℃, the expansion coefficient of aluminum alloy waveguide is 22.7×10 -6 / ℃. When the temperature changes, the cabin plate hardly deforms, but the waveguide deforms and generates thermal stress. The four straight waveguide free ports are fixed, and a temperature rise of 30℃ is introduced to obtain the maximum radial deformation T (unit: μm) of the switch RF housing;

[0104] Step 6: Using the structural statics method, a gravity field is applied to the finite element physical model of the entire star in the east-west direction of the satellite to constrain the displacement of the satellite-rocket docking frame and calculate the gravity deformation of the cabin under gravity load (deformation d per 100 mm). G , unit: mm). Since gravity prestress is directional, according to the bending moment analysis benchmark in step 3, the gravity deformation of the cabin is equivalent to the corresponding radial deformation of the switch RF housing G = (d G ·μ0) / d0(μm). Then, taking the radial deformation of the switch RF housing as a benchmark, the radial deformation of the switch RF housing caused by the gravity prestress deviation source under different gravity conditions is calculated:

[0105] A. During the ground AIT (final assembly test) phase, the entire satellite rotates 180° from +X downward to -X downward, and the radial deformation of the switch RF housing caused by gravity prestress is G;

[0106] B. During the ground thermal test and on-orbit phase, the payload cabin was in a horizontal state during the thermal test, flipped 90° compared to the final assembly, and the entire satellite was in a weightless state during the on-orbit phase. It can be considered that the radial deformation of the switch RF housing caused by gravity prestress was 0.5G;

[0107] C. During the ground force test phase, the entire satellite is placed vertically along the Z direction, and the main load-bearing component is the central load-bearing cylinder. Due to its high stiffness, it is considered that the influence of gravity prestress at this stage can be ignored and is regarded as 0.

[0108] Step 7: Use structural dynamics analysis. Input the ground test carrier sinusoidal excitation into the star-rocket docking frame of the whole star finite element physical model, and calculate the strain peak value ε at the root of the connection between the waveguide and the switch during the vibration process. F Since the vibration stress is directional, the vibration strain peak is equivalent to the corresponding maximum radial deformation of the switch RF housing F = (ε F ·μ0) / ε0(μm).

[0109] Step 8. Consider the shaft coaxiality deviation Z (usually controlled by the process to be less than 6μm) caused by the actual process defects of the switch. This item needs to be deducted from the gap between the RF housing and the rotor. For different working conditions of the switch on the satellite, calculate the switch gap margin N under each working condition:

[0110]

[0111] Step 9: Based on the maximum deformation of the RF housing under the worst working condition in step 9, N0-N min , combined with the bending moment analysis benchmark in step 3, the equivalent broadside bending moment M acting at the 100 mm straight waveguide port is (N0-N min ) / μ0(Nm), which is used as the test magnitude basis for the bending moment test acceptance of waveguide switches.

[0112] The present invention can be specifically implemented according to the above steps 1-9 by performing structural statics, dynamics and mechanical-thermal coupling analysis on commercial finite element software such as MSC.Patran / Nastran and Ansys.

[0113] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A method for determining the bending moment resistance of a satellite waveguide switch, characterized in that The steps include: Establish a first component-level finite element physical model of a waveguide switch connected to a single standard straight waveguide, a second component-level finite element physical model of a waveguide switch connected to four standard straight waveguides, and a star-level finite element physical model including the on-board waveguide and the secondary structure of the waveguide switch; A unit broadside bending moment is applied to the standard straight waveguide free port in the first component level finite element physical model to obtain a bending moment analysis benchmark; The maximum allowable deviation of the final assembly is introduced into the second-component-level finite element physical model to calculate the maximum radial deformation of the waveguide switch RF housing caused by the final assembly deviation source; The maximum temperature difference between the waveguide switch and the cabin is introduced into the second component level finite element physical model to calculate the maximum radial deformation T of the switch RF housing caused by the thermal mismatch deviation source; Apply gravity field to the finite element physical model of the whole star, and calculate the radial deformation of the switch RF housing caused by gravity prestress deviation sources under different gravity conditions; Apply ground test carrier sinusoidal excitation to the whole star finite element model to calculate the maximum radial deformation of the switch RF housing caused by the vibration stress deviation source ; The maximum radial deformation of the switch RF housing caused by the assembly deviation source, thermal mismatch deviation source, gravity prestress deviation source and vibration stress deviation source and the shaft coaxiality deviation caused by the actual process defects of the waveguide switch are superimposed to obtain the maximum deformation of the RF housing under the worst working condition; According to the bending moment analysis benchmark, the maximum deformation of the RF housing under the worst working condition is equivalent to the broadside bending moment acting at the free port of the standard straight waveguide. , the broadside bending moment Used to characterize the bending moment resistance of satellite waveguide switches; The bending moment analysis benchmark includes the standard straight waveguide free end displacement , the strain value at the connection root between the straight waveguide and the wave switch , Maximum radial deformation of RF housing ; The maximum allowable deviation of the final assembly includes three types of deviations, namely: waveguide port misalignment, waveguide port non-parallelism, and switch installation bottom surface unevenness; the specific steps of introducing the maximum allowable deviation of the final assembly into the second component level finite element physical model are: The waveguide port misalignment is introduced at the four standard straight waveguide free ports to obtain the maximum radial deformation D of the switch RF housing; The non-parallelism of the waveguide ports is introduced at the four standard straight waveguide free ports to obtain the maximum radial deformation P of the switch RF housing; The bottom surface unevenness is introduced into the switch base, and the four waveguide free ports are fixed to obtain the maximum radial deformation B of the switch RF housing; The specific steps for calculating the radial deformation of the switch RF housing caused by the gravity prestress deviation source under different gravity conditions are as follows: The whole satellite coordinate system is defined as follows: the X direction is parallel to the theoretical normal direction of the satellite east plate, and the Z direction is parallel to the axis of the load-bearing cylinder; Constrain the displacement of the satellite-rocket docking frame, apply the gravity load in the X-axis direction, and obtain the gravity deformation of the cabin plate ; The gravity deformation of the cabin plate is equivalent to the reference value of radial deformation of the switch RF housing caused by the gravity prestress deviation source; According to the reference value of radial deformation of the switch RF housing caused by the gravity prestress deviation source, the radial deformation of the switch RF housing caused by the gravity prestress deviation source under different working conditions is calculated; Gravity conditions include ground assembly test conditions, ground thermal test conditions, on-orbit operation conditions, and ground force test conditions; Under the ground assembly test condition, the whole satellite is rotated from +X downward 180° to -X downward, and the radial deformation of the switch RF housing caused by gravity prestress is equal to the reference value of the radial deformation of the switch RF housing caused by the gravity prestress deviation source; Under the ground thermal test conditions and on-orbit conditions, the radial deformation of the switch RF housing caused by gravity prestress is 0.5 times the reference value of the radial deformation of the switch RF housing caused by the gravity prestress deviation source; Under the ground force test condition, the radial deformation of the switch RF housing caused by gravity prestress is 0.

2. A method for determining the bending moment resistance of a satellite waveguide switch according to claim 1, characterized in that The waveguide switch model in the first component-level finite element model and the second component-level finite element model includes at least three parts: a switch base, a RF housing, and a drive housing. The material properties of the finite element physical model are the same as the actual material properties of each component, and the boundary condition is that the switch base is fixed with screw holes.

3. A method for determining the bending moment resistance of a satellite waveguide switch according to claim 1, characterized in that The boundary condition of the whole-star finite element physical model of the waveguide switch is that the satellite-rocket docking frame is fixed.

4. A method for determining the bending moment resistance of a satellite waveguide switch according to claim 1, characterized in that The specific method for calculating the maximum radial deformation T of the switch RF housing caused by the thermal mismatch deviation source is: The mechanical-thermal coupling analysis method is used to fix the four straight waveguide free ports and introduce temperature rise to obtain the maximum radial deformation T of the switch RF housing, which is the maximum radial deformation of the switch RF housing caused by the thermal mismatch deviation source. The temperature rise is the maximum temperature difference between the waveguide switch and the cabin.

5. A method for determining the bending moment resistance of a satellite waveguide switch according to claim 1, characterized in that The gravity deformation of the deck Equivalent to the radial deformation of the switch RF housing caused by the gravity prestress deviation source The calculation formula is: 。 6. A method for determining the bending moment resistance of a satellite waveguide switch according to claim 1, characterized in that Maximum radial deformation of the switch RF housing caused by vibration stress deviation sources The calculation formula is: in, is the peak strain at the root of the connection between the waveguide and the waveguide switch during vibration.

7. A method for determining the bending moment resistance of a satellite waveguide switch according to claim 1, characterized in that The broadside bending moment acting on the free port of a standard straight waveguide is for: in, Designing gaps for waveguide switches, It is the maximum deformation of the RF housing under the worst working condition.

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