Structural-load-carrying-associated method for design of time-phased qα clearance value of rocket and for implementation

Abstract

Disclosed in the present invention is a structural-load-carrying-associated method for design of a time-phased Qα clearance value of a rocket and for implementation. The method comprises: performing statistical analysis on measured high-altitude wind data for the location of a rocket launch site, so as to form a high-altitude wind statistical result; designing a standard flight trajectory of a rocket, so as to form a standard trajectory data result; calculating an angle of attack and a sideslip angle under the standard trajectory of the rocket, so as to obtain a preliminary Qα design result that varies with flight time; calculating a rocket flight load, and performing structural design and optimization of the rocket, such that the structure of the rocket satisfies a payload capacity; formulating a time-phased Qα clearance value of the rocket launch site, which comprises obtaining a plurality of incremental Qα values on the basis of the preliminary Qα design result, and on the basis of lateral bending moment loads corresponding to the Qα value, outputting, as the time-phased Qα clearance value, the maximum Qα clearance value that corresponds to meeting the requirement for the maximum load-carrying bending moment; and prior to launch, performing a launch clearance assessment on the basis of the time-phased Qα clearance value. Therefore, the problem of relatively low clearance probability in conventional methods is solved.

Description

A method for designing and implementing rocket time-segmented release values ​​based on structural load-bearing characteristics.

[0001] This application claims priority to Chinese Patent Application No. 2024114391644, filed on October 15, 2024, entitled "A Design Implementation Method for Rocket Time-Segmented Release Value Based on Structural Bearing Correlation", the entire contents of which are incorporated herein by reference. Technical Field

[0002] This application relates to the technical field of overall launch vehicle design, and in particular to a method for designing and implementing time-segmented Qα release values ​​for rockets based on structural load-bearing characteristics. Background Technology

[0003] The amount of crosswind interference that a launch vehicle can withstand during flight is limited. Therefore, high-altitude wind measurements and forecasts are necessary before launch to assess whether the rocket structure can withstand the crosswinds during actual flight, and thus determine whether launch can proceed.

[0004] The US Delta rocket limits the engine control swashplate angle, or flight Qα, based on actual measurements and forecasts of high-altitude wind speeds on the flight day. The engine control swashplate angle is statistically calculated and limited to change over flight time. The specific design of the release limits for the engine control swashplate angle or flight Qα is still unclear.

[0005] The Qα release value traditionally used for domestic rockets is based on the overall design results during the rocket's development and design phase, with a certain design margin retained, and constrained by a uniform Qα release value throughout the entire flight. This traditional method of using a uniform Qα release value across all time periods suffers from a low release probability.

[0006] Summary of the Invention

[0007] This application provides a method for designing and implementing rocket Qα release values ​​in different time periods based on structural load-bearing capacity. The purpose is to provide a method for designing Qα release values ​​for launch vehicle flight in different time periods, while also exploring the margin of structural load-bearing capacity. Before the actual launch, flight Qα target assessment is carried out through the predicted wind correction method, and flight parameters are set in near real-time, overcoming the problem of low release probability caused by the traditional all-time uniform Qα release value design method.

[0008] Firstly, a method for designing and implementing rocket time-segmented release values ​​based on structural load-bearing characteristics is provided, including:

[0009] Statistical analysis of measured upper-altitude wind data was conducted at the rocket launch site to generate upper-altitude wind statistics.

[0010] Conduct standard flight trajectory design for rockets and generate standard trajectory data results;

[0011] The calculation results of the attack angle under the standard trajectory of the rocket were carried out, and the preliminary design results of Qα as a function of flight time were obtained.

[0012] Conduct rocket flight load calculations, as well as rocket structural design and optimization, to ensure that the rocket's structure meets the carrying capacity requirements;

[0013] Develop time-segmented Qα release values ​​for the rocket launch site, including obtaining multiple incremental Qα values ​​based on the preliminary Qα design results, and outputting the maximum Qα release value that meets the maximum load-bearing bending moment requirement as the time-segmented Qα release value based on the lateral bending moment load corresponding to the Qα value.

[0014] Before launch, high-altitude wind measurements are conducted, and based on the results of the high-altitude wind measurements and the Qα release values ​​for different time periods, a launch release assessment is performed just before launch.

[0015] In conjunction with the first aspect, in certain implementations of the first aspect, the determination of the time-segmented Qα release value for the rocket launch site includes:

[0016] Preliminary calculation of Qα release values ​​for different time periods;

[0017] The total rocket load is calculated based on the determined Qα release value;

[0018] The strength calculation results and safety factor data are presented.

[0019] Based on the calculation results, a positive closed-loop verification of the structural bearing capacity is performed, including closed-loop verification of overall and local loads. When the closed-loop verification meets the requirements, the design result of the time-segmented Qα release value is output. When the closed-loop verification does not meet the requirements, the structure that does not meet the closed-loop verification is redesigned, and the time-segmented Qα release value is re-determined.

[0020] In conjunction with the first aspect, in some implementations of the first aspect, the preliminary calculation of the time-segmented release value Qα includes:

[0021] Calculations of non-bending moment load terms under several typical working conditions are carried out based on the load design method.

[0022] Calculate the maximum bearing bending moment load Mn based on the main structure's experimental or theoretical bearing capacity.

[0023] By actively changing the shear wind, a set of incremental Qα values ​​is constructed according to the attitude control attack angle design method, and the corresponding engine sway angle is output to form the attack angle design matrix;

[0024] Based on a set of increasing Qα values ​​and the engine sway angle matrix, the lateral bending moment load M corresponding to different Qα values ​​is obtained through load calculation;

[0025] By comparing the maximum bearing bending moment Mn of the rocket body structure with the lateral bending moment loads corresponding to different Qα values, a maximum Qα value was found that satisfies the condition that the calculated bending moment loads of all main structures are not greater than the maximum bearing bending moment. Thus, the maximum Qα limit value that the existing rocket body structure can bear was initially determined.

[0026] In conjunction with the first aspect, in some implementations of the first aspect, the non-bending moment load term includes at least one of the following: axial force T, compartment wall temperature t, liquid tank pressure Pz, and liquid tank column pressure Pq.

[0027] In conjunction with the first aspect, in some implementations of the first aspect, the maximum bearing bending moment Mn = (Tc + Tpz - T) * R / 2, where Tc is the test or theoretical bearing (axial pressure) capacity at the wall temperature under this working condition, Tpz is the lower limit of the tank pressure of the tank structure to offset the axial pressure, T is the axial force load, and R is the radius of the compartment.

[0028] In conjunction with the first aspect, in some implementations of the first aspect, the set of incremental Qα values ​​includes a0, a0+Δ, ..., a0+nΔ, where a0 is the initial Qα value, Δ is an integer multiple of 50 Pa·rad, and n is the number of increments Δ.

[0029] In conjunction with the first aspect, in certain implementations of the first aspect, the launch release assessment includes:

[0030] Predict the wind forecast for the launch window based on measured wind data at different times before launch;

[0031] Standard flight parameters are generated based on the standard ballistic trajectory, and n sets of wind-corrected flight parameters are generated based on the wind forecast windows at different times before launch.

[0032] For the standard flight parameters and the n sets of flight parameters that have been generated, a total of 1+n sets of parameters, Monte Carlo target simulation calculations are performed in the wind forecast window before launch to obtain the maximum statistical value of Qα, Qamax, and compare it with the time-segmented Qα release value. If at least one set of flight parameters meets the release value constraint, the launch is approved; otherwise, the launch window is postponed.

[0033] In conjunction with the first aspect, in some implementations of the first aspect, under the condition of satisfying the release value constraint, the flight data corresponding to the lowest Qamax value is selected for binding.

[0034] In conjunction with the first aspect, in certain implementations of the first aspect, the provision that the rocket's structure satisfies the carrying capacity includes:

[0035] The structural weight is assessed to determine whether the carrying capacity is met. If the carrying capacity index is not met, a ballistic wind correction scheme is designed. After the launch probability assessment, the preliminary design result of Qα as a function of flight time is re-determined until the carrying capacity index is met.

[0036] In a second aspect, an electronic device is provided for executing the rocket time-sharing Qα release value design implementation method as described in any of the implementations of the first aspect above.

[0037] Compared with the prior art, the solution provided in this application has at least the following beneficial technical effects:

[0038] This invention proposes a rocket time-segmented Qα release value design and implementation method related to structural load-bearing capacity. In the Qα release value design, calculations are performed for different flight periods, while considering the residual strength margin of the structural load-bearing capacity. Compared with traditional design methods, this improves the Qα release value design results and increases the release probability. During the launch implementation phase, the time-segmented Qα release value method allows for more reasonable load threshold settings for each period. Combined with verification of multiple sets of flight parameters in the window forecast wind, it can further improve the probability of launch in the first window. Attached Figure Description

[0039] Figure 1 is a flowchart of the design and implementation of the rocket's time-segmented Qα release value.

[0040] Figure 2 is a flowchart for determining the time-segmented Qα release value.

[0041] Figure 3 is a schematic diagram of the pre-launch assessment. Detailed Implementation

[0042] The present application will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0043] As shown in Figure 1, the present invention provides a method for designing and implementing rocket time-segmented release values ​​based on structural load-bearing characteristics. The specific steps are as follows.

[0044] Step (1) Statistical analysis of measured high-altitude wind data at the rocket launch site location is carried out to form high-altitude wind statistical results.

[0045] Step (2) is to carry out the standard flight trajectory design of the rocket and generate standard trajectory data results.

[0046] Step (3) Calculate the attack angle under the standard trajectory of the rocket to obtain the preliminary design result of Qα as it changes with flight time.

[0047] Step (4): Perform rocket flight payload calculations.

[0048] Step (5) involves the structural design and optimization of the rocket. The structural weight is used to assess whether the payload capacity is met. If the payload capacity is not met, proceed to step (6). If the payload capacity is met, proceed to step (8).

[0049] Step (6): Design a ballistic wind correction scheme.

[0050] Step (7): Conduct a launch probability assessment and return to step (3).

[0051] Step (8): Determine the time-segmented Qα release values ​​for the rocket launch site.

[0052] Referring to Figure 2, the specific steps for determining the time-segmented Qα release value are as follows.

[0053] (8.1) Preliminary calculation of the time-segmented Qα release value, which is the maximum Qα release value corresponding to the transverse bending moment load meeting the maximum bearing bending moment requirement.

[0054] (8.2) Calculate the total rocket load based on the determined Qα release value.

[0055] (8.3) Formation of strength calculation and safety factor data.

[0056] (8.4) Perform a positive closed-loop verification of the structural bearing capacity based on the calculation results, including closed-loop verification of overall and local loads. When the closed-loop verification meets the requirements, proceed to step (8.6). When the closed-loop verification does not meet the requirements, proceed to step (8.5).

[0057] (8.5) For structures that do not meet the closed-loop check, redesign and return to step (8.1).

[0058] (8.6) Complete the design results of the time-segmented Qα release value.

[0059] In some embodiments, the specific steps for initially calculating the time-segmented Qα release value in step (8.1) are as follows.

[0060] (8.1.1) Calculate non-bending moment loads such as axial force T, compartment wall temperature t, liquid tank pressure Pz, and liquid tank column pressure Pq under several typical working conditions according to the load design method.

[0061] (8.1.2) Calculate the maximum bearing bending moment load Mn based on the test or theoretical bearing capacity of the main structure. The maximum bearing bending moment under a certain working condition is Mn = (Tc + Tpz - T) * R / 2, where Tc is the test or theoretical bearing (axial pressure) capacity at the wall temperature under that working condition, Tpz is the lower limit of the tank pressure of the tank structure to offset the axial pressure, T is the axial force load, and R is the radius of the compartment.

[0062] (8.1.3) Referring to Table 1, by actively changing the shear wind, a set of incremental Qα values ​​is constructed according to the attitude control attack angle design method, and the corresponding engine swing angle is output to form the attack angle design matrix. a0 is the initial Qα value, and Δ is generally taken as an integer multiple of 50 Pa.rad.

[0063] Table 1

[0064] (8.1.4) Based on the Qα and engine sway angle matrix obtained in (8.1.3), the lateral bending moment load M corresponding to different Qα values ​​is obtained by load calculation.

[0065] (8.1.5) Compare the maximum bearing bending moment Mn of the rocket body structure in (8.1.2) with the lateral bending moment loads corresponding to different Qα values ​​in (8.1.4) to find a maximum Qα value that satisfies the condition that the calculated bending moment loads of all main structures are not greater than the maximum bearing bending moment. Thus, the maximum Qα limit value that the existing rocket body structure can withstand has been preliminarily determined.

[0066] Step (9): Conduct high-altitude wind measurements before launch.

[0067] Step (10): Based on the measured results of high-altitude winds and the time-segmented Qα release values, conduct a launch release assessment before launch.

[0068] Referring to Figure 3, the specific steps for launch release assessment are as follows.

[0069] (10.1) Estimate the wind forecast for the launch window based on measured wind data at different times before launch (e.g., -48h, -24h).

[0070] (10.2) Generate standard flight parameters based on standard ballistics, and generate n sets of wind-corrected flight parameters based on the wind forecast windows at different times before launch.

[0071] (10.3) For the standard flight parameters and the n sets of flight parameters already generated, a total of 1+n sets of parameters, Monte Carlo target simulation calculations are performed in the predicted wind before the launch window to obtain the maximum statistical value of Qα, Qamax, and compare it with the time-segmented Qα release values ​​in (8.6). If at least one set of flight parameters meets the release value constraint, it is released, and the flight parameter corresponding to the one with the lowest Qamax is selected for binding. Otherwise, the launch window is postponed, and step (10.1) is restarted.

[0072] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope defined in the claims of the present invention.

Claims

1. A method for implementing a structure-carrying associated rocket time-segment Qa release value design, characterized in that, include: Statistical analysis of measured upper-altitude wind data was conducted at the rocket launch site to generate upper-altitude wind statistics. Conduct standard flight trajectory design for rockets and generate standard trajectory data results; The calculation results of the attack angle under the standard trajectory of the rocket were carried out, and the preliminary design results of Qα as a function of flight time were obtained. Conduct rocket flight load calculations, as well as rocket structural design and optimization, to ensure that the rocket's structure meets the carrying capacity requirements; Develop time-segmented Qα release values ​​for the rocket launch site, including obtaining multiple incremental Qα values ​​based on the preliminary Qα design results, and outputting the maximum Qα release value that meets the maximum load-bearing bending moment requirement as the time-segmented Qα release value based on the lateral bending moment load corresponding to the Qα value. Before launch, high-altitude wind measurements are conducted, and based on the results of the high-altitude wind measurements and the Qα release values ​​for different time periods, a launch release assessment is performed just before launch.

2. The method of claim 1, wherein, The determination of the time-segmented Qα release values ​​for the rocket launch site includes: Preliminary calculation of Qα release values ​​for different time periods; The total rocket load is calculated based on the determined Qα release value; The strength calculation results and safety factor data are presented. Based on the calculation results, a positive closed-loop verification of the structural bearing capacity is performed, including closed-loop verification of overall and local loads. When the closed-loop verification meets the requirements, the design result of the time-segmented Qα release value is output. When the closed-loop verification does not meet the requirements, the structure that does not meet the closed-loop verification is redesigned, and the time-segmented Qα release value is re-determined.

3. The method of claim 2, wherein, The preliminary calculation of the time-segmented release value Qα includes: Calculations of non-bending moment load terms under several typical working conditions are carried out based on the load design method. Calculate the maximum bearing bending moment load Mn based on the main structure's experimental or theoretical bearing capacity. By actively changing the shear wind, a set of incremental Qα values ​​is constructed according to the attitude control attack angle design method, and the corresponding engine sway angle is output to form the attack angle design matrix; Based on a set of increasing Qα values ​​and the engine sway angle matrix, the lateral bending moment load M corresponding to different Qα values ​​is obtained through load calculation; By comparing the maximum bearing bending moment Mn of the rocket body structure with the lateral bending moment loads corresponding to different Qα values, a maximum Qα value was found that satisfies the condition that the calculated bending moment loads of all main structures are not greater than the maximum bearing bending moment. Thus, the maximum Qα limit value that the existing rocket body structure can bear was initially determined.

4. The method of claim 3, wherein, The non-bending moment load items include at least one of the following: axial force T, compartment wall temperature t, liquid tank pressure Pz, and liquid tank column pressure Pq.

5. The method of claim 3, wherein, The maximum load-bearing bending moment Mn = (Tc + Tpz - T) * R / 2, where Tc is the test or theoretical load-bearing (axial pressure) capacity at the wall temperature under this working condition, Tpz is the lower limit of the tank pressure of the storage tank structure to offset the axial pressure, T is the axial force load, and R is the radius of the compartment.

6. The method of claim 3, wherein, The set of increasing Qα values ​​includes a0, a0+Δ, ..., a0+nΔ, where a0 is the initial Qα value, Δ is an integer multiple of 50 Pa·rad, and n is the number of increments of Δ.

7. The method of claim 1, wherein, The launch release assessment includes: Predict the wind forecast for the launch window based on measured wind data at different times before launch; Standard flight parameters are generated based on the standard ballistic trajectory, and n sets of wind-corrected flight parameters are generated based on the wind forecast windows at different times before launch. For the standard flight parameters and the n sets of flight parameters that have been generated, a total of 1+n sets of parameters, Monte Carlo target simulation calculations are performed in the wind forecast window before launch to obtain the maximum statistical value of Qα, Qamax, and compare it with the time-segmented Qα release value. If at least one set of flight parameters meets the release value constraint, the launch is approved; otherwise, the launch window is postponed.

8. The method of claim 7, wherein, Under the condition that the release value constraint is met, select the flight data corresponding to the lowest Qamax value for binding.

9. The method of claim 1, wherein, The method for ensuring the rocket's structure meets its carrying capacity includes: The structural weight is assessed to determine whether the carrying capacity is met. If the carrying capacity index is not met, a ballistic wind correction scheme is designed. After the launch probability assessment, the preliminary design result of Qα as a function of flight time is re-determined until the carrying capacity index is met.

10. An electronic device, comprising: The electronic device is used to execute the rocket time-sharing Qα release value design implementation method associated with structural bearing as described in any one of claims 1 to 9.

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