Structural bearing associated rocket time-phased Q alpha release value design and implementation method

Abstract

The invention discloses a structural bearing associated rocket time-phased Q alpha release value design implementation method. The method comprises the following steps: carrying out statistical analysis on actually measured high-altitude wind data aiming at a rocket launching site position to form a high-altitude wind statistical result; carrying out flight standard trajectory design of the rocket to form a standard trajectory data result; developing an attack tilt angle calculation result under a rocket standard trajectory to obtain a Q alpha preliminary design result changing along with flight time; rocket flight load calculation and rocket structure design and optimization are carried out, so that the structure of the rocket meets the carrying capacity; the time-phased Q alpha release value of the rocket launching site is formulated, multiple incremental Q alpha values are obtained on the basis of the preliminary design result of Q alpha, and the corresponding maximum Q alpha release value meeting the maximum bearing bending moment requirement serves as the time-phased Q alpha release value to be output according to the transverse bending moment load corresponding to the Q alpha values; and before emission, emission release evaluation is performed according to the release value of the time-segmented Qalpha. Therefore, the problem of low release probability in a traditional method is solved.

Description

Technical Field

[0001] The present application relates to the technical field of overall design of launch vehicles, and in particular to a method for designing and implementing the time-segment Qα release value of a rocket associated with structural load-bearing. Background Art

[0002] The amount of lateral wind interference that a launch vehicle can withstand during flight is limited. Therefore, high-altitude wind measurements and forecasts are required before launch to assess whether the rocket structure can withstand the crosswind during actual flight, and then decide whether the launch can be carried out.

[0003] The Delta rockets of the United States limit the engine control swing angle or flight Qα based on the actual measured and predicted high-altitude wind speed on the flight day. The engine control swing angle is statistically calculated and limited to change with the flight time. It is not clear how the release limit value of the engine control swing angle or flight Qα is designed.

[0004] The Qα release value traditionally used by domestic rockets is based on the overall design results of the rocket development and design stage, and after retaining a certain design margin, it is constrained by the unified Qα release value for the entire flight. The traditional full-time unified Qα release value design method has the problem of low release probability. Summary of the invention

[0005] The present application provides a method for designing and implementing the rocket's time-segment Qα release value associated with structural load-bearing capacity. The purpose is to provide a method for designing the launch vehicle's flight Qα release value in time periods, while exploring the margin of the structural load-bearing capacity. Before the actual launch, a flight Qα target evaluation is carried out through a forecast wind correction method, and the flight parameters are bound in quasi-real time, thereby overcoming the problem of low release probability caused by the traditional full-time unified Qα release value design method.

[0006] First, a design and implementation method for the rocket time-segment Qα release value associated with structural load is provided, including:

[0007] Conduct statistical analysis of measured high-altitude wind data at the rocket launch site to generate high-altitude wind statistics;

[0008] Carry out standard trajectory design for rocket flight and generate standard trajectory data results;

[0009] The calculation results of the attack and swing angle under the standard trajectory of the rocket were carried out, and the preliminary design results of Qα varying with the flight time were obtained;

[0010] Carry out rocket flight load calculation, as well as rocket structural design and optimization, so that the rocket structure meets the carrying capacity;

[0011] Formulate the time-segment Qα release value for the rocket launch site, including obtaining multiple incremental Qα values ​​based on the Qα preliminary design results, and outputting the maximum Qα release value corresponding to the maximum load-bearing moment requirement as the time-segment Qα release value according to the lateral bending moment load corresponding to the Qα value;

[0012] Conduct actual high-altitude wind measurements before launch, and perform a launch release assessment before launch based on the measured high-altitude wind results and the time-phased Qα release values.

[0013] In conjunction with the first aspect, in certain implementations of the first aspect, formulating the time-segmented Qα release value of the rocket launch site includes:

[0014] Preliminary calculation of Qα release value in different time periods;

[0015] Carry out full arrow load calculation based on the determined Qα release value;

[0016] Form strength calculation and safety factor data;

[0017] A positive closed-loop check of the structural bearing capacity is performed based on the calculation results, including the closed-loop of the overall and local loads. When the closed-loop check meets the requirements, the design results of the time-phased Qα release value are output. When the closed-loop check does not meet the requirements, the structure that does not meet the closed-loop check is redesigned and the time-phased Qα release value is re-determined.

[0018] In combination with the first aspect, in certain implementations of the first aspect, the preliminarily calculating the time period-based Qα release value includes:

[0019] Carry out calculation of non-bending moment load items under several typical working conditions according to the load design method;

[0020] Calculate the maximum bearing moment load Mn based on the main structure test or theoretical bearing capacity;

[0021] By actively changing the shear wind, a set of increasing Qα values ​​is constructed according to the attitude control attack and swing angle design method, and the corresponding engine swing angle is output to form the attack and swing angle design matrix;

[0022] According to a set of increasing Qα values ​​and the engine swing angle matrix, the lateral bending moment load M corresponding to different Qα values ​​is obtained through load calculation;

[0023] The maximum bearing bending moment Mn of the rocket body structure is compared with the lateral bending moment load corresponding to different Qα values ​​to find a maximum Qα value that satisfies the requirement that all calculated bending moment loads of the main structure are no greater than the maximum bearing bending moment. At this point, the maximum Qα limit value that the existing rocket body structure can bear is preliminarily determined.

[0024] In combination with the first aspect, in certain implementations of the first aspect, the non-bending moment load item includes at least one of the following: axial force T, compartment wall temperature t, liquid tank pressure Pz, and liquid column pressure Pq of the liquid tank.

[0025] In combination with the first aspect, in certain implementations of the first aspect, the maximum bearing bending moment Mn = (Tc + Tpz - T) * R / 2, Tc is the test or theoretical bearing (axial pressure) capacity under the wall temperature of the operating 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 cabin.

[0026] In combination with the first aspect, in certain implementations of the first aspect, 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 increasing Δ.

[0027] In conjunction with the first aspect, in certain implementations of the first aspect, the emission release assessment includes:

[0028] Estimate the launch window forecast wind based on measured wind data at different times before launch;

[0029] Generate standard flight parameters based on the standard trajectory, and generate n sets of wind-corrected flight parameters based on the window wind forecast at different times before launch;

[0030] For the standard flight parameters and the n sets of generated flight parameters, a total of 1+n sets of parameters, Monte Carlo target shooting simulation calculations are performed in the forecast wind window before launch to obtain the Qα statistical maximum value Qamax, and compare it with the Qα release value in the time period. If there is at least one set of flight parameters that meets the release value constraint, it is released; otherwise, the launch window is postponed.

[0031] In combination with the first aspect, in certain implementations of the first aspect, when the release value constraint is met, the corresponding flight elements with the lowest Qamax are selected for binding.

[0032] In conjunction with the first aspect, in certain implementations of the first aspect, making the structure of the rocket meet the carrying capacity includes:

[0033] The carrying capacity is determined based on the structural weight. If the carrying capacity index is not met, the ballistic wind correction scheme is designed. After the launch probability is evaluated, the preliminary design result of Qα that changes with flight time is re-determined until the carrying capacity index is met.

[0034] In a second aspect, an electronic device is provided, which is used to execute the design and implementation method of the rocket time-segment Qα release value associated with the structural load as described in any one of the implementation methods in the first aspect above.

[0035] Compared with the prior art, the solution provided by this application includes at least the following beneficial technical effects:

[0036] The present invention proposes a design and implementation method for the rocket's time-segment Qα release value associated with structural load-bearing. In the Qα release value design, calculations are performed in different flight periods, and the residual strength coefficient margin of the structural load-bearing is considered. Compared with the traditional design method, the Qα release value design result is improved and the release probability is improved. In the launch implementation stage, the time-segment Qα release value method is used, and the load threshold value setting for each period is more reasonable. Combined with the verification of the window forecast wind by multiple sets of flight parameters, the launch probability of the first window can be further improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 Design and implement a flow chart for the rocket's time-segment Qα release value.

[0038] Figure 2 A flow chart for formulating Qα release values ​​for different time periods.

[0039] Figure 3 Schematic diagram of launch release assessment before launch. DETAILED DESCRIPTION

[0040] The present application is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0041] like Figure 1 As shown, the present invention provides a method for designing and implementing the rocket's time-segment Qα release value associated with structural load-bearing, and the specific steps are as follows.

[0042] Step (1) conducts statistical analysis of measured high-altitude wind data at the rocket launch site to generate high-altitude wind statistical results.

[0043] Step (2) is to carry out the standard trajectory design of the rocket and generate standard trajectory data results.

[0044] Step (3), carry out the calculation results of the attack and swing angle under the standard trajectory of the rocket, and obtain the preliminary design results of Qα that changes with the flight time.

[0045] Step (4), carry out rocket flight load calculation.

[0046] Step (5) is to carry out the structural design and optimization of the rocket, and evaluate whether the carrying capacity is met based on the structural weight. If the carrying capacity index is not met, proceed to step (6); if the carrying capacity index is met, jump to step (8).

[0047] Step (6), design a ballistic wind correction scheme.

[0048] Step (7), carry out emission probability assessment and return to step (3).

[0049] Step (8), formulate the time-segment Qα release value for the rocket launch site.

[0050] Reference Figure 2 The specific steps for formulating the time-segment Qα release value are as follows.

[0051] (8.1) Preliminary calculation of the time-phased Qα release value, which is the maximum Qα release value corresponding to the lateral bending moment load that meets the maximum bearing moment requirement.

[0052] (8.2) Carry out full arrow load calculation based on the determined Qα release value.

[0053] (8.3) Form strength calculation and safety factor data.

[0054] (8.4) Perform a positive closed-loop check of the structural bearing capacity based on the calculation results, including the closed-loop of the overall and local loads. When the closed-loop check meets the requirements, proceed to step (8.6). When the closed-loop check does not meet the requirements, proceed to step (8.5).

[0055] (8.5) Redesign the structure that does not meet the closed-loop check and return to step (8.1).

[0056] (8.6) Complete the design results of the Qα release value for each time period.

[0057] In some embodiments, the specific steps for preliminarily calculating the time period Qα release value in step (8.1) are as follows.

[0058] (8.1.1) According to the load design method, calculations of non-bending moment load items such as axial force T, compartment wall temperature t, liquid tank pressure Pz, and liquid column pressure Pq in the liquid tank are carried out under several typical working conditions.

[0059] (8.1.2) The maximum bearing moment load Mn is calculated based on the test or theoretical bearing capacity of the main structure. The maximum bearing moment Mn under a certain working condition is (Tc+Tpz-T)*R / 2, where Tc is the test or theoretical bearing (axial pressure) capacity under the wall temperature of the 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.

[0060] (8.1.3) Referring to Table 1, by actively changing the shear wind, according to the attitude control attack and swing angle design method, a set of increasing Qα values ​​is constructed, and the corresponding engine swing angle is output to form the attack and swing angle design matrix, where a0 is the initial Qα value, and Δ is generally taken as an integer multiple of 50 Pa.rad.

[0061] Table 1

[0062]

[0063] (8.1.4) Based on Qα and the engine swing angle matrix obtained in (8.1.3), the lateral bending moment load M corresponding to different Qα values ​​is obtained through load calculation.

[0064] (8.1.5) Compare the maximum bearing moment Mn of the rocket body structure in (8.1.2) with the transverse bending moment loads corresponding to different Qα values ​​in (8.1.4) to find a maximum Qα value that satisfies that all the calculated bending moment loads of the main structure are not greater than the maximum bearing moment. At this point, the maximum Qα limit value that the existing rocket body structure can bear is preliminarily determined.

[0065] Step (9), conduct high-altitude wind measurement before launch.

[0066] Step (10), based on the actual measurement results of the upper air wind and the Qα release value in different time periods, a launch release assessment is performed before the launch.

[0067] refer to Figure 3 ,The specific steps of launch release assessment are as follows.

[0068] (10.1) Estimate the launch window forecast wind based on the measured wind data at different times before launch (e.g. -48h, -24h).

[0069] (10.2) Generate standard flight parameters based on the standard trajectory, and generate n sets of wind-corrected flight parameters based on the window forecast wind at different times before launch.

[0070] (10.3) For the standard flight parameters and the generated n sets of flight parameters, a total of 1+n sets of parameters, Monte Carlo target shooting simulation calculations are performed in the pre-launch window forecast wind to obtain the maximum value Qamax of Qα statistics, and compare it with the time-segment Qα release value in (8.6). If there is at least one set of flight parameters that meets the release value constraint, it is released and the corresponding flight parameters with the lowest Qamax are selected for binding. Otherwise, the launch window is postponed and step (10.1) is re-entered.

[0071] Although the present invention is 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 without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention shall be based on the scope defined by the claims of the present invention.

Claims

1. A design and implementation method for rocket time-segment Qα release value associated with structural load, characterized in that: include: Conduct statistical analysis of measured high-altitude wind data at the rocket launch site to generate high-altitude wind statistics; Carry out standard trajectory design for rocket flight and generate standard trajectory data results; The calculation results of the attack and swing angle under the standard trajectory of the rocket were carried out, and the preliminary design results of Qα varying with the flight time were obtained; Carry out rocket flight load calculation, as well as rocket structural design and optimization, so that the rocket structure meets the carrying capacity; Formulate the time-segment Qα release value for the rocket launch site, including obtaining multiple incremental Qα values ​​based on the Qα preliminary design results, and outputting the maximum Qα release value corresponding to the maximum load-bearing moment requirement as the time-segment Qα release value according to the lateral bending moment load corresponding to the Qα value; Conduct actual high-altitude wind measurements before launch, and perform a launch release assessment before launch based on the measured high-altitude wind results and the time-phased Qα release values.

2. The method according to claim 1, characterized in that The formulation of the time-segment Qα release value of the rocket launch site includes: Preliminary calculation of Qα release value in different time periods; Carry out full arrow load calculation based on the determined Qα release value; Form strength calculation and safety factor data; A positive closed-loop check of the structural bearing capacity is performed based on the calculation results, including the closed-loop of the overall and local loads. When the closed-loop check meets the requirements, the design results of the time-phased Qα release value are output. When the closed-loop check does not meet the requirements, the structure that does not meet the closed-loop check is redesigned and the time-phased Qα release value is re-determined.

3. The method according to claim 2, characterized in that The preliminary calculation of the time-division Qα release value includes: Carry out calculation of non-bending moment load items under several typical working conditions according to the load design method; Calculate the maximum bearing moment load Mn based on the main structure test or theoretical bearing capacity; By actively changing the shear wind, a set of increasing Qα values ​​is constructed according to the attitude control attack and swing angle design method, and the corresponding engine swing angle is output to form the attack and swing angle design matrix; According to a set of increasing Qα values ​​and the engine swing angle matrix, the lateral bending moment load M corresponding to different Qα values ​​is obtained through load calculation; The maximum bearing bending moment Mn of the rocket body structure is compared with the lateral bending moment load corresponding to different Qα values ​​to find a maximum Qα value that satisfies the requirement that all calculated bending moment loads of the main structure are no greater than the maximum bearing bending moment. At this point, the maximum Qα limit value that the existing rocket body structure can bear is preliminarily determined.

4. The method according to claim 3, characterized in that The non-bending moment load item includes at least one of the following: axial force T, compartment wall temperature t, liquid tank pressure Pz, and liquid column pressure Pq of the liquid tank.

5. The method according to claim 3, characterized in that: The maximum bearing bending moment Mn = (Tc + Tpz - T) * R / 2, Tc is the test or theoretical bearing (axial pressure) capacity under the wall temperature of the 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 cabin.

6. The method according to claim 3, characterized in that The group 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 increasing Δ.

7. The method according to claim 1, characterized in that The launch release assessment includes: Estimate the launch window forecast wind based on measured wind data at different times before launch; Generate standard flight parameters based on the standard trajectory, and generate n sets of wind-corrected flight parameters based on the window wind forecast at different times before launch; For the standard flight parameters and the n sets of generated flight parameters, a total of 1+n sets of parameters, Monte Carlo target shooting simulation calculations are performed in the forecast wind window before launch to obtain the Qα statistical maximum value Qamax, and compare it with the Qα release value in the time period. If there is at least one set of flight parameters that meets the release value constraint, it is released; otherwise, the launch window is postponed.

8. The method according to claim 7, characterized in that Under the condition that the release value constraint is met, the corresponding flight parameters with the lowest Qamax are selected for binding.

9. The method according to claim 1, characterized in that: The structure of the rocket is made to meet the carrying capacity, including: The carrying capacity is determined based on the structural weight. If the carrying capacity index is not met, the ballistic wind correction scheme is designed. After the launch probability is evaluated, the preliminary design result of Qα that changes with flight time is re-determined until the carrying capacity index is met.

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

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