Rocket wind correction rolling evaluation method suitable for GTO long-window task

Abstract

The invention discloses a rocket wind correction rolling evaluation method suitable for a GTO long-window task, and the method comprises the steps: firstly carrying out the quasi-real-time wind correction trajectory design and evaluation for each decision point of a launching day, and then carrying out the release judgment. If the current release condition is met, the launch process can be directly entered; if the current release condition is not met, judging whether the transmission is allowed to be delayed for a certain time length t or not, and if the transmission is not allowed to be delayed, suggesting that the transmission is stopped; and if the delay time t emission is allowed, entering a delay time t emission process at the moment, and then entering a next decision point, and so on. According to the method, the existing quasi-real-time wind correction trajectory design technology can be better applied to such tasks, the adaptability of the rocket to complex weather conditions in the launching day can be improved to the greatest extent, and the release probability and the flight safety of the rocket are improved.

Description

Technical Field

[0001] The invention relates to a rocket wind correction rolling assessment method suitable for a GTO long window mission, and belongs to the field of launch vehicle trajectory design. Background Art

[0002] Quasi-real-time wind correction of rocket trajectory is an important means to improve the release probability and ensure flight safety. In recent years, quasi-real-time bidirectional wind correction technology has been applied in the launch process of various types of rockets in my country, making important contributions to reducing flight loads and improving the release probability. In the practice of wind correction, the impact of wind field changes on the adaptability of design results has been further understood, especially on launch days with drastic weather changes or in missions with a long launch window (more than 2 hours). The impact of this change cannot be ignored. In the traditional quasi-real-time wind correction release process, only a fixed window is targeted for quasi-real-time wind correction design and evaluation. When faced with release failures in such long windows, there is no effective means and method to deal with it. Therefore, it is necessary to combine existing technical capabilities to further optimize the existing quasi-real-time wind correction method to better adapt to such tasks and improve the release probability of rockets facing complex weather processes.

[0003] According to literature research, the technical research on single wind correction trajectory is relatively complete, such as "Research on Sounding Rocket Dynamics and Wind Correction Technology" (Master's degree thesis of National University of Defense Technology), "Joint Optimization Control Technology of Launch Vehicle Flight Payload" (Journal of Astronautics), "Design Specifications for Launch Vehicle Wind Correction Trajectory" (Standard of General Design Department of China Academy of Launch Vehicle Technology), etc. Public papers or internal standards can be found. However, there is no recognized effective method for how to apply quasi-real-time wind correction technology to long-window rolling release assessment, so further research is needed. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide a rocket wind correction rolling assessment method suitable for GTO long-window missions, to improve the rocket's adaptability to complex weather conditions on the launch day, and at the same time to improve the rocket's release probability and flight safety.

[0005] The technical solution of the present invention is: a rocket wind correction rolling assessment method suitable for GTO long window missions, wherein:

[0006] S1. For a launch day decision point, in the preparation phase, according to the launch day workflow requirements, obtain the basic data required for quasi-real-time wind-corrected trajectory design and evaluation, and complete the preparation work;

[0007] S2. Based on the basic data required for quasi-real-time wind-corrected trajectory design and evaluation, carry out specific program angle design and flight load evaluation calculations, and conduct corresponding simulation verification to complete the quasi-real-time wind-corrected trajectory design and evaluation of the decision point;

[0008] S3: Based on the quasi-real-time wind-corrected trajectory design and evaluation calculation results and the minimum launch conditions of the rocket, determine whether the rocket meets the release conditions: if so, proceed to S4; if not, proceed to S5;

[0009] S4. Generate flight parameters according to the program angle that meets the release conditions, perform flight parameter verification, and bind the arrow to prepare for flight. The overall process of this decision point ends;

[0010] S5. Since the release condition of the decision point is not met, the rolling evaluation judgment is continued in the window after a certain delay of t: if it is determined that the launch is not allowed to be delayed for a period of t, then go to S6; if it is determined that the launch is allowed to be delayed for a period of t, then go to step 7;

[0011] S6: If the rocket does not meet the release conditions at this decision point and the launch cannot be postponed for a period of time t, the launch is aborted, the launch day process ends, and the overall process of this decision point ends;

[0012] S7. When the rocket meets the release conditions at this decision point, it enters the launch process link with a delay of time t, sets a new window, names it as a new decision point, and returns to step S1 to re-perform the quasi-real-time wind correction release rolling assessment of the rocket for the GTO mission in the same way.

[0013] Preferably, in step S1, the basic data required for quasi-real-time wind-corrected trajectory design and evaluation include: standard trajectory data, wind field data, and target launch window time.

[0014] Preferably, the standard trajectory data should be consistent with the actual flight conditions of the rocket, using the actual filling mass, engine calibration test performance parameters, and raw data deviations; if the actual parameter values ​​are not available, theoretical values ​​are used instead;

[0015] The wind field data should include the entire layer of wind field data from the rocket take-off altitude to 20km above sea level. The height interval of the wind field data should not be less than the rocket's flight altitude within the rocket wind correction program angle binding step time in the high wind area;

[0016] For the target transmission window time, it should be first determined whether it is a single long window or discontinuous multiple windows, and secondly, the time length of each window should be determined for determining the postponement time in step S5.

[0017] Preferably, in step S2, when performing specific program angle design and flight load assessment calculation work and corresponding simulation verification, it should be noted that the time spent on the three tasks of wind correction program angle design, load assessment, and simulation verification is recorded: the sum of the time spent on the three tasks determines the time interval that the rocket is allowed to postpone to the next window for wind correction. When the sum of the wind correction program angle design time, load assessment time, and simulation verification time is t1, the shortest time interval for the rocket to postpone wind correction to the next window cannot be shorter than t1.

[0018] Preferably, load evaluation and simulation verification can be performed in parallel to reduce time consumption.

[0019] Preferably, in step S3, when judging whether the rocket meets the release condition, the release condition is generally a time-varying threshold of the rocket flight qα value, which is set in advance and only needs to be compared according to the threshold when releasing the rocket.

[0020] Preferably, in step S4, when the flight parameters are checked and bound onto the arrow, the time nodes for binding the flight parameters onto the arrow vary depending on the rocket model. In the formulation of the actual pre-launch workflow, this time should be used as the node, and the time for the previous wind correction parameter work should be reversed to ensure smooth execution.

[0021] Preferably, in step S5, it is considered to continue the rolling evaluation and judgment in the window after a certain time t is postponed. In different rocket models and mission processes, the time t needs to be adjusted according to the working execution time length and launch window time of this model;

[0022] At the same time, the duration t should also be greater than the minimum time interval for high-altitude wind field data provided by the meteorological department.

[0023] Preferably, when the actual launch mission is performed, multiple decision points can be set according to the situation.

[0024] Compared with the prior art, the present invention has the following advantages:

[0025] (1) The present invention proposes a practical and feasible rolling assessment method for long-window quasi-real-time wind correction release, which can be directly applied to the actual engineering launch missions of various types of rockets. It has strong versatility and a simple execution method. It can reliably guide the pre-launch process design and plan formulation of long-window quasi-real-time wind correction for existing and future rockets, and effectively improve the release capability of rockets in complex weather conditions.

[0026] (2) The present invention proposes a 2h time interval requirement for long-window quasi-real-time wind correction release rolling assessment, and explains the technical details and elements for setting this time interval. The setting of this time takes into account the characteristics of high-altitude wind changes at different launch sites, the ability of the rocket system to implement quasi-real-time wind correction design, and the time cycle factors of the launch site system for high-altitude wind measurement and forecasting. It can be effectively applied to the current pre-launch process of my country's rockets, without significantly increasing the complexity of the pre-launch process, while effectively utilizing the long window time length to create the greatest favorable conditions for rocket release. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a general flow chart of the quasi-real-time wind correction release rolling assessment method applicable to a long window of the present invention;

[0028] Figure 2 The present invention is a general flow chart of a quasi-real-time wind correction release rolling assessment method suitable for a long window, taking two decision points as an example. DETAILED DESCRIPTION

[0029] With the current launch site process optimization, networked element generation and testing capabilities, all aspects of technological progress and capability upgrades have provided the basic conditions for further improving the quasi-real-time performance of pre-launch wind correction, enabling the speed and timeliness of quasi-real-time wind correction to be further accelerated. Therefore, for GTO, deep space and other long-window missions of more than several hours, a set of release rolling assessment methods suitable for current capabilities can be proposed to further improve the probability of rocket release in complex weather processes and long windows.

[0030] Based on the above starting point and background technology, the present invention describes a quasi-real-time wind correction release rolling assessment method for a launch vehicle before launch that is suitable for a long-window GTO mission, for use in subsequent launch missions.

[0031] A rolling assessment method for rocket wind correction suitable for GTO long-window missions first conducts quasi-real-time wind correction trajectory design and assessment for each decision point on the launch day, followed by a release judgment. If the release conditions are met, the launch process can be directly entered; if the release conditions are not met, a judgment is made on whether to postpone the launch for 2 hours. If the postponement for 2 hours is not allowed, it is recommended to abort the launch; if the postponement for 2 hours is allowed, the launch postponement process for 2 hours is entered at this time, and then the next decision point is entered, and so on.

[0032] The flowchart of this method is shown in Figure 1 This method is also applicable to the quasi-real-time wind correction release assessment for other reasons that cause long-window launch delays. The following takes the launch day with two decision points as an example to give specific implementation steps. The method flow chart using two decision points as an example is shown in Figure 2 .

[0033] first step:

[0034] Enter the launch day decision point 1 preparation link. At this time, according to the launch day workflow requirements, obtain the basic information required for quasi-real-time wind correction trajectory design and evaluation, including standard trajectory data, wind field data, and target launch window time. The standard trajectory data should be consistent with the actual flight situation of the rocket, using the actual filling mass, engine calibration test performance parameters, and original data deviation. If you do not have the ability to obtain the actual parameter value, replace it with a theoretical value. In the wind field data, the whole layer of wind field data information from the rocket take-off altitude to 20km above sea level should be included, and the height layer interval of the wind field data should not be less than the rocket's flight altitude within the rocket wind correction program angle binding step time in the high wind area (for example, the program angle binding step length is 1s, and the rocket can fly up to 300m in 1s, then the wind field data height layer interval should not be less than 300m). For the target launch window time, it should first be clarified as a single long window or an intermittent multi-window, and secondly, the time length of each window should be clarified, which is used for the postponement time determination of step S5. Enter the second step after this step ends.

[0035] Step 2:

[0036] Enter the first quasi-real-time wind-corrected trajectory design and evaluation phase. At this time, according to the basic data required for quasi-real-time wind-corrected trajectory design and evaluation, carry out specific program angle design and flight load evaluation calculation work, and carry out corresponding simulation verification. At this time, it is necessary to record the time spent on the three tasks of wind correction program angle design, load evaluation, and simulation verification. The sum of the time spent on these three tasks determines the time interval that the rocket can be allowed to postpone to the next window for wind correction. For example, the wind correction program angle design takes 5 minutes, the load evaluation takes 20 minutes, and the simulation verification takes 50 minutes. The three tasks take 75 minutes in series. The shortest time interval for the rocket to postpone the wind correction to the next window cannot be less than 75 minutes. If some of the tasks have parallel conditions, such as load evaluation and simulation verification can be parallel, the time has the ability to be reduced. After this step, enter the third step.

[0037] Step 3:

[0038] Enter the release judgment phase. At this time, based on the quasi-real-time wind-corrected trajectory design and evaluation calculation results, combined with the rocket's minimum launch conditions, determine whether the rocket meets the release conditions. This release condition is generally the time-varying threshold of the rocket's flight qα value. This threshold is set in advance, and when releasing, it is only necessary to compare according to the threshold. If it is satisfied, enter the fourth step; if it is not satisfied, enter the fifth step.

[0039] Step 4:

[0040] Enter the phase of element generation and binding. At this time, the flight elements are generated according to the program angle that meets the release conditions, the flight elements are checked, and the arrows are bound and ready for flight, and the overall process ends.

[0041] Depending on the rocket model, the time node for binding the flight parameters to the arrow varies, for example, -1h. In the formulation of the actual pre-launch workflow, this time should be used as the node, and the time for the previous wind correction parameters should be reversed to ensure smooth execution.

[0042] Step 5:

[0043] Enter the stage of judging whether to allow a 2-hour postponement. At this time, since the release conditions of the first decision point are no longer met, we can only consider continuing the rolling evaluation judgment after the postponement window. The judgment of whether to allow a 2-hour postponement involves multiple systems of the rocket. The content here is not the core protection point of this method, so it will not be described in detail. If it is judged that a 2-hour postponement of the launch is not allowed, proceed to step 6; if it is judged that a 2-hour postponement of the launch is allowed, proceed to step 7.

[0044] It should be noted that the 2h here is a typical example time. Different rocket models and mission processes can be adjusted according to the length of the work execution time and the launch window time of this model. For example, if the working time in step S2 can be further shortened, the 2h here can also be shortened to 1.5h or even shorter. This time should also be greater than the minimum time interval for the meteorological department to provide high-altitude wind field data.

[0045] Step 6:

[0046] Enter the launch abort phase. At this point, the rocket does not meet the release conditions at the first decision point, and the launch cannot be postponed for 2 hours. Therefore, the only option is to abort the launch, ending the launch day process and the overall process.

[0047] Step 7:

[0048] Enter the 2h launch delay process. At this time, the rocket completes the setting of the new window. The time setting of the new window should meet the target launch window time prepared in the first step. All systems aim at the new window to prepare for the pre-launch process. After this step, enter the eighth step.

[0049] Step 8:

[0050] Enter the preparation phase for launch day decision point 2. This phase is the same as the first step, "launch day decision point 1 preparation phase", except that the time has changed. At this time, according to the launch day workflow requirements, obtain the basic data required for quasi-real-time wind correction trajectory design and evaluation at decision point 2, including standard trajectory data, wind field data, and target launch window time. After this step, enter step 9.

[0051] Step 9:

[0052] Enter the second quasi-real-time wind-corrected trajectory design and evaluation phase. This phase is the same as the "first quasi-real-time wind-corrected trajectory design and evaluation phase", only the time changes. At this time, based on the basic data required for quasi-real-time wind-corrected trajectory design and evaluation, the second specific program angle design and flight load evaluation calculation work are carried out, and corresponding simulation verification is carried out. After this step, enter the tenth step.

[0053] Step 10:

[0054] Enter the second release judgment phase. This phase is the same as the "first release judgment phase", only the time changes. At this time, based on the second quasi-real-time wind correction trajectory design and evaluation calculation results, combined with the rocket's minimum launch conditions, determine whether the rocket meets the release conditions. If it does, enter step 11; if not, enter step 12.

[0055] Step 11:

[0056] Enter the phase of element generation and binding. At this time, the flight elements are generated according to the program angle that meets the release conditions, the flight elements are checked, and the arrows are bound and ready for flight, and the overall process ends.

[0057] Step 12:

[0058] Enter the recommended launch abort phase. At this point, the rocket does not meet the release conditions at both the first and second decision points, and there are no subsequent possible decision points, so the only option is to abort the launch, ending the launch day process and the overall process. It should be noted that this example uses two decision points as an example to illustrate the steps. When the actual launch mission is executed, the number of decision points can be multiple. For example, if the total window time length is 4 hours, then three decision points can be set, and so on.

[0059] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in this field.

Claims

1. A rocket wind correction rolling assessment method suitable for GTO long-window missions, characterized in that include: S1. For a launch day decision point, in the preparation phase, according to the launch day workflow requirements, obtain the basic data required for quasi-real-time wind-corrected trajectory design and evaluation, and complete the preparation work; S2. Based on the basic data required for quasi-real-time wind-corrected trajectory design and evaluation, carry out specific program angle design and flight load evaluation calculations, and conduct corresponding simulation verification to complete the quasi-real-time wind-corrected trajectory design and evaluation of the decision point; S3: Based on the quasi-real-time wind-corrected trajectory design and evaluation calculation results and the minimum launch conditions of the rocket, determine whether the rocket meets the release conditions: if so, proceed to S4; if not, proceed to S5; S4. Generate flight parameters according to the program angle that meets the release conditions, perform flight parameter verification, and bind the arrow to prepare for flight. The overall process of this decision point ends; S5. Since the release condition of the decision point is not met, the rolling evaluation judgment is continued in the window after a certain delay of time t: if it is determined that the launch is not allowed to be delayed for a period of time t, then go to S6; if it is determined that the launch is allowed to be delayed for a period of time t, then go to step 7; S6: If the rocket does not meet the release conditions at this decision point and the launch cannot be postponed for a period of time t, the launch is aborted, the launch day process ends, and the overall process of this decision point ends; S7. When the rocket meets the release conditions at this decision point, it enters the launch process link with a delay of time t, sets a new window, names it as a new decision point, and returns to step S1 to re-perform the quasi-real-time wind correction release rolling assessment of the rocket for the GTO mission in the same way.

2. A rocket wind correction rolling assessment method suitable for GTO long window missions according to claim 1, characterized in that: In step S1, the basic data required for quasi-real-time wind-corrected trajectory design and evaluation include: standard trajectory data, wind field data, and target launch window time.

3. A rocket wind correction rolling assessment method suitable for GTO long window missions according to claim 2, characterized in that: The standard trajectory data should be consistent with the actual flight conditions of the rocket, using the actual filling mass, engine calibration test performance parameters, and original data deviations; if it is not possible to obtain the actual parameter values, the theoretical values ​​shall be used instead; The wind field data should include the entire layer of wind field data from the rocket take-off altitude to 20km altitude. The height interval of the wind field data should not be less than the rocket's flight altitude within the rocket wind correction program angle binding step time in the high wind area; For the target transmission window time, it should be first determined whether it is a single long window or discontinuous multiple windows, and secondly, the time length of each window should be determined for determining the postponement time in step S5.

4. The method of claim 1 for the rolling assessment of rocket wind correction for GTO long-window missions, characterized in that: In step S2, when performing specific program angle design and flight load assessment calculation work and corresponding simulation verification, it is necessary to record the time spent on the three tasks of wind correction program angle design, load assessment, and simulation verification: the sum of the time spent on these three tasks determines the time interval that the rocket is allowed to postpone to the next window for wind correction. When the sum of the wind correction program angle design time, load assessment time, and simulation verification time is t1, the shortest time interval for the rocket to postpone to the next window for wind correction cannot be shorter than t1.

5. A rocket wind correction rolling assessment method suitable for GTO long window missions according to claim 4, characterized in that: Load evaluation and simulation verification can be performed in parallel to reduce time consumption.

6. The method of claim 1 for rocket wind correction rolling assessment for GTO long window missions, characterized in that: In step S3, it is determined whether the rocket meets the release condition. This release condition is generally a time-varying threshold of the rocket flight qα value. The threshold is set in advance, and only the threshold needs to be compared when releasing the rocket.

7. The method of claim 1 for the rolling assessment of rocket wind correction for GTO long-window missions, characterized in that: In step S4, when the flight parameters are checked and bound onto the arrow, the time nodes for binding the flight parameters onto the arrow vary depending on the rocket model. In the formulation of the actual pre-launch workflow, this time should be used as the node, and the time for the previous wind correction parameter work should be reversed to ensure smooth execution.

8. The method of claim 1 for the rolling assessment of rocket wind correction for GTO long-window missions, characterized in that: In step S5, consider continuing the rolling evaluation and judgment in the window after a certain delay of time t. In different rocket models and mission processes, the time t needs to be adjusted according to the working execution time length and launch window time of this model; At the same time, the duration t should also be greater than the minimum time interval for high-altitude wind field data provided by the meteorological department.

9. The method of claim 1 for rocket wind correction rolling assessment for GTO long window missions, characterized in that: During the actual launch mission execution, multiple decision points can be set according to the situation.

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