A Rolling Evaluation Method for Rocket Wind Correction Applicable to GTO Long Window Missions

Abstract

This invention discloses a rolling evaluation method for rocket wind correction applicable to GTO long-window missions. First, for each decision point on the launch day, a near-real-time wind-corrected trajectory design and evaluation is performed, followed by a release decision. If the release conditions are met, the launch process can proceed directly; if not, a decision is made regarding whether a launch delay of a certain duration 't' is permissible. If delay is not allowed, launch abort is recommended; if a delay of 't' is permitted, the launch delay process begins, proceeding to the next decision point, and so on. This invention enables existing near-real-time wind-corrected trajectory design technology to be better applied to such missions, maximizing the rocket's adaptability to complex weather conditions on the launch day, and improving the rocket's release probability and flight safety.

Description

Technical Field

[0001] This invention relates to a rocket wind correction rolling evaluation method applicable to GTO long window missions, belonging to the field of launch vehicle trajectory design. Background Technology

[0002] Near-real-time wind correction for rocket trajectories is a crucial means to improve launch probability and ensure flight safety. In recent years, near-real-time two-way wind correction technology has been successively applied in the launch procedures of various rocket types in my country, making significant contributions to reducing flight loads and improving launch probability. In the practical application of wind correction, the impact of wind field changes on the adaptability of design results has been further deepened, especially on launch days with drastic weather changes or in missions with long launch windows (over 2 hours), where the impact of these changes cannot be ignored. In traditional near-real-time wind correction launch procedures, only a fixed window is targeted for near-real-time wind correction design and evaluation. When launch fails within such long windows, there are currently no effective means or methods to address the issue. Therefore, it is necessary to further optimize existing near-real-time wind correction methods, combining current technological capabilities, to better adapt to such missions and improve the launch probability of rockets in complex weather conditions.

[0003] According to literature review, research on single-shot wind-corrected trajectories is relatively complete, as evidenced by published papers and internal standards such as "Research on Dynamics and Wind Correction Technology of Sounding Rockets" (Master's Thesis, National University of Defense Technology), "Joint Optimization Control Technology for Launch Vehicle Flight Payloads" (Journal of Astronautics), and "Design Specifications for Wind-Corrected Trajectories of Launch Vehicles" (Standard of the General Design Department, China Academy of Launch Vehicle Technology). However, there is currently no universally accepted effective method for applying quasi-real-time wind correction technology to long-window rolling release evaluation, thus requiring further research. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a rocket wind correction rolling evaluation method suitable for GTO long window missions, which improves the rocket's adaptability to complex weather conditions on launch day, while also improving the rocket's release probability and flight safety.

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

[0006] S1. For a specific launch date decision point, in the preparation phase, according to the launch date 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 the design and evaluation of the quasi-real-time wind-corrected trajectory, perform 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 at this decision point.

[0008] S3. Based on the near-real-time wind-corrected trajectory design and evaluation calculation results, and combined with the rocket's minimum launch conditions, determine whether the rocket meets the release conditions: if it does, proceed to S4; if it does not, proceed to S5.

[0009] S4. Generate flight parameters based on the program angle that meets the release conditions, verify the flight parameters, and load the rocket into flight preparation. The overall process of this decision point ends.

[0010] S5. Since the release conditions for this decision point are not met, consider continuing the rolling evaluation and judgment in the window after a certain delay of t: if the judgment determines that the delay of t is not allowed, proceed to S6; if the judgment determines that the delay of t is allowed, proceed to step 7.

[0011] S6. If the rocket does not meet the release conditions at this decision point and is not allowed to be delayed for a duration t, the launch is aborted, the launch day process ends, and the overall process at this decision point ends.

[0012] S7. When the rocket meets the release conditions at this decision point, it enters the launch delay time t process, sets a new window, names it the new decision point, and returns to step S1 to repeat the rocket quasi-real-time wind correction release rolling evaluation 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 includes: standard trajectory data, wind field data, and target launch window time.

[0014] Preferably, the standard ballistic data should be consistent with the actual flight of the rocket, using the actual fueling mass, engine calibration test performance parameters, and raw data deviations; if it is not possible to obtain the actual parameter values, theoretical values ​​should be used instead.

[0015] The wind field data should include wind field data from the rocket's takeoff altitude to an altitude of 20km. 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 windy area.

[0016] For the target launch window time, it should first be determined whether it is a single long window or intermittent multiple windows, and secondly, the time length of each window should be determined, which will be used to determine the delay time in step S5.

[0017] Preferably, in step S2, when performing specific program angle design and flight load evaluation calculations and conducting corresponding simulation verifications, attention should be paid to recording 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 during which the rocket can be postponed to the next window for wind correction. When the sum of the wind correction program angle design time, load evaluation time, and simulation verification time is t1, the shortest time interval for the rocket to postpone wind correction to the next window cannot be less than t1.

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

[0019] Preferably, in step S3, when determining whether the rocket meets the release conditions, the release conditions are generally a time-varying threshold for the rocket's flight qα value. This threshold is predetermined, and only the comparison needs to be performed according to the threshold during release.

[0020] Preferably, in step S4, when verifying flight parameters and loading them onto the rocket, the timing of loading flight parameters onto the rocket varies depending on the rocket model. In the actual pre-launch workflow, this time should be used as the node, and the timing of each wind correction parameter work should be arranged backward to ensure smooth execution.

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

[0022] At the same time, the duration t should also be greater than the minimum time interval for meteorological departments to provide upper-level wind field data.

[0023] Preferably, multiple decision points can be set as needed during the actual launch mission.

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

[0025] (1) This invention proposes a practical and feasible quasi-real-time wind correction release rolling evaluation method applicable to long windows, which can be directly applied to the actual engineering launch missions of various types of rockets. It has strong versatility, simple execution method, and can reliably guide the design of pre-launch process and contingency plan for long-window quasi-real-time wind correction of existing and future rockets, effectively improving the rocket's release capability in the face of complex weather.

[0026] (2) This invention proposes a 2-hour time interval requirement for rolling evaluation of quasi-real-time wind correction release within a long window, and explains the technical details and elements of this time interval setting. This time setting takes into account the characteristics of high-altitude wind changes at different launch sites, the rocket system's ability 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 rockets in my country, without significantly increasing the complexity of the pre-launch process, while effectively utilizing the time length of the long window to create the most favorable conditions for rocket release. Attached Figure Description

[0027] Figure 1 This is the overall flowchart of the near real-time wind correction release rolling evaluation method applicable to long windows of the present invention;

[0028] Figure 2 This is a flowchart illustrating the quasi-real-time wind correction release rolling evaluation method applicable to long windows, using two decision points as an example. Detailed Implementation

[0029] With the optimization of launch site procedures and the improvement of networked parameter generation and testing capabilities, technological advancements and capability upgrades in various aspects have provided the foundation for further improving the near-real-time performance of pre-launch wind correction, enabling a further acceleration of the speed and timeliness of near-real-time wind correction. Therefore, for long-window missions such as GTO and deep space missions (several hours or more), a rollout evaluation method suitable for current capabilities can be proposed to further improve the launch probability of rockets in complex weather conditions and long launch windows.

[0030] Based on the above starting point and background technology, this invention describes a pre-launch near real-time wind correction release rolling evaluation method for launch vehicles suitable for long-window GTO missions, for use in subsequent launch missions.

[0031] A rolling evaluation method for rocket wind correction applicable to GTO long-window missions first performs near-real-time wind-corrected trajectory design and evaluation for each decision point on the launch day, followed by a release decision. If the release conditions are met, the launch process can proceed directly; if not, a decision is made on whether a 2-hour launch delay is permissible. If a 2-hour delay is not allowed, launch abort is recommended; if a 2-hour delay is allowed, the 2-hour delay launch process begins, and the process continues to the next decision point, and so on.

[0032] The flowchart for this method can be found here. Figure 1 This method is also applicable to near-real-time wind correction release assessments for launches delayed over long launch windows due to various other reasons. The following example, using a launch date with two decision points, provides the specific implementation steps. The flowchart for the method using two decision points is shown below. Figure 2 .

[0033] first step:

[0034] Proceed to the launch day decision point 1 preparation stage. At this stage, according to the launch day workflow requirements, acquire the basic data needed for near-real-time wind-corrected 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 rocket flight conditions, using actual fuel loading mass, engine calibration test performance parameters, and raw data deviations. If actual parameter values ​​are unavailable, theoretical values ​​should be used instead. The wind field data should include full-layer wind field data from the rocket's liftoff altitude to an altitude of 20 km. The height layer interval of the wind field data should not be less than the rocket's flight altitude within the wind correction program angle setting step time in high wind areas (e.g., if the program angle setting step time is 1 second, and the rocket's flight altitude can reach 300m within 1 second, then the wind field data height layer interval should not be less than 300m). For the target launch window time, first clarify whether it is a single long window or intermittent multiple windows, and secondly, clarify the duration of each window for determining the delay time in step S5. After this step, proceed to step two.

[0035] Step Two:

[0036] The process then proceeds to the first near-real-time wind-corrected trajectory design and evaluation phase. Based on the fundamental data required for this phase, specific program angle design and flight load evaluation calculations are performed, followed by corresponding simulation verification. It is crucial to record the time spent on each of these three tasks: wind correction program angle design, load evaluation, and simulation verification. The sum of these three times determines the permissible time interval for delaying wind correction to the next window. For example, if wind correction program angle design takes 5 minutes, load evaluation takes 20 minutes, and simulation verification takes 50 minutes, the total time for these three tasks sequentially is 75 minutes. Therefore, the minimum time interval for delaying wind correction to the next window cannot be less than 75 minutes. If some tasks can be performed in parallel, such as load evaluation and simulation verification, the time can be reduced. After this step, the process moves to the third step.

[0037] Step 3:

[0038] The process then proceeds to the release judgment stage. At this point, based on the near-real-time wind-corrected trajectory design and evaluation calculations, and considering the rocket's minimum launch conditions, it is determined whether the rocket meets the release criteria. This release criterion is generally a time-varying threshold for the rocket's flight qα value. This threshold is pre-defined, and during release, only a comparison against the threshold is needed. If the criteria are met, proceed to step four; otherwise, proceed to step five.

[0039] Step 4:

[0040] The process then moves to the parameter generation and binding stage. At this point, flight parameters are generated based on the program angles that meet the release conditions, flight parameters are verified, and the parameters are bound to the rocket in preparation for flight. The overall process then concludes.

[0041] Depending on the rocket model, the timing for setting flight parameters onto the rocket varies, for example, -1 hour. In the actual pre-launch workflow, this time should be used as a reference point, and the timing of all previous wind correction parameters should be scheduled backwards to ensure smooth execution.

[0042] Step 5:

[0043] The process then proceeds to determine whether a 2-hour delay is permissible. Since the release conditions of the first decision point are no longer met, a rolling evaluation must be conducted after the delay window. The determination of whether a 2-hour delay is permissible involves multiple rocket systems, but these are not the core protection points of this method and will not be elaborated upon. If the determination is that a 2-hour delay is not permissible, proceed to step six; if the determination is that a 2-hour delay is permissible, proceed to step seven.

[0044] It should be noted that the 2h mentioned here is a typical example time. Different rocket models and mission procedures can be adjusted according to the specific execution time and launch window. For example, if the time for each task in step S2 can be further shortened, then this 2h can be shortened to 1.5h or even less. This time should also be greater than the minimum time interval for upper-air wind field data provided by the meteorological department.

[0045] Step 6:

[0046] The launch abort recommendation process has begun. At this point, the rocket does not meet the release conditions at the first decision point, and a 2-hour delay is not permitted. Therefore, the launch must be aborted, ending the launch day's process and concluding the overall process.

[0047] Step 7:

[0048] The launch process then proceeds to the 2-hour launch delay stage. At this point, the rocket completes the new launch window setting, which must meet the target launch window time established in the first step. All systems then prepare for launch according to the new window. After this step, proceed to step eight.

[0049] Step 8:

[0050] Proceed to the preparation phase for Launch Day Decision Point 2. This phase is identical to the first step, "Preparation Phase for Launch Day Decision Point 1," except for the timing. At this stage, following the launch day workflow requirements, acquire the fundamental data necessary for near-real-time wind-corrected trajectory design and evaluation at Decision Point 2, including standard trajectory data, wind field data, and target launch window time. After this step, proceed to step nine.

[0051] Step 9:

[0052] The second phase of near-real-time wind-corrected trajectory design and evaluation is then initiated. This phase is identical to the first phase, except for the timing. Based on the fundamental data required for the near-real-time wind-corrected trajectory design and evaluation, a second detailed program angle design and flight load evaluation calculation are performed, followed by corresponding simulation verification. After this step, the tenth step begins.

[0053] Step 10:

[0054] The second release assessment stage begins. This stage is identical to the first release assessment stage, except for the timing. Based on the results of the second near-real-time wind-corrected trajectory design and evaluation calculations, and considering the rocket's minimum launch conditions, it is determined whether the rocket meets the release requirements. If it does, proceed to step eleven; otherwise, proceed to step twelfth.

[0055] Step 11:

[0056] The process then moves to the parameter generation and binding stage. At this point, flight parameters are generated based on the program angles that meet the release conditions, flight parameters are verified, and the parameters are bound to the rocket in preparation for flight. The overall process then concludes.

[0057] Step 12:

[0058] The launch abort recommendation phase has begun. At this point, the rocket does not meet the release conditions at either the first or second decision point, and there are no further possible decision points. Therefore, the launch must be aborted, ending the launch day's process and concluding the overall process. It should be noted that this example uses two decision points; in actual launch missions, there can be multiple decision points. For example, if the total launch window is 4 hours, then three decision points could be set, and so on.

[0059] The contents not described in detail in this specification are existing technologies known to those skilled in the art.

Claims

1. A rocket wind correction rolling evaluation method suitable for GTO long window missions, characterized in that... include: S1. For a specific launch date decision point, in the preparation phase, according to the launch date 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 the design and evaluation of the quasi-real-time wind-corrected trajectory, perform 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 at this decision point. S3. Based on the near-real-time wind-corrected trajectory design and evaluation calculation results, and combined with the rocket's minimum launch conditions, determine whether the rocket meets the release conditions: This release condition is a time-varying threshold for the rocket's flight qα value. This threshold is predetermined, and only the threshold needs to be compared during release; if it is met, proceed to S4; if it is not met, proceed to S5. S4. Generate flight parameters based on the program angle that meets the release conditions, verify the flight parameters, and load the rocket into flight preparation. The overall process of this decision point ends. S5. Since the release conditions for this decision point are not met, consider continuing the rolling evaluation and judgment in the window after a certain delay of t: if the judgment determines that the delay of t is not allowed, proceed to S6; if the judgment determines that the delay of t is allowed, proceed to step 7. S6. If the rocket does not meet the release conditions at this decision point and is not allowed to be delayed for a duration t, the launch is aborted, the launch day process ends, and the overall process at this decision point ends. S7. When the rocket meets the release conditions at this decision point, it enters the launch delay time t process, sets a new window, names it the new decision point, and returns to step S1 to repeat the rocket quasi-real-time wind correction release rolling evaluation for the GTO mission in the same way.

2. The rocket wind correction rolling evaluation method applicable to 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. The rocket wind correction rolling evaluation method applicable to GTO long window missions according to claim 2, characterized in that: Standard ballistic data should be consistent with the actual flight conditions of the rocket, using actual fueling mass, engine calibration test performance parameters, and raw data deviations; if actual parameter values ​​are not available, theoretical values ​​should be used instead. The wind field data should include wind field data from the rocket's takeoff altitude to an altitude of 20km. 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 windy area. For the target launch window time, it should first be determined whether it is a single long window or intermittent multiple windows, and secondly, the time length of each window should be determined, which will be used to determine the delay time in step S5.

4. The rocket wind correction rolling evaluation method applicable to GTO long window missions according to claim 1, characterized in that: In step S2, when performing specific program angle design and flight load evaluation calculations and conducting corresponding simulation verifications, attention should be paid to recording the time spent on the three tasks: wind correction program angle design, load evaluation, and simulation verification. The sum of the time spent on these three tasks determines the time interval during which the rocket can postpone wind correction to the next window. When the sum of the wind correction program angle design time, load evaluation time, and simulation verification time is t1, the shortest time interval for the rocket to postpone wind correction to the next window cannot be less than t1.

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

6. The rocket wind correction rolling evaluation method applicable to GTO long window missions according to claim 1, characterized in that: In step S4, when verifying flight parameters and loading them onto the rocket, the timing of loading flight parameters onto the rocket varies depending on the rocket model. In the actual pre-launch workflow, this time should be used as the node, and the timing of each wind correction parameter work should be arranged backward to ensure smooth execution.

7. The rocket wind correction rolling evaluation method for GTO long-window missions according to claim 1, characterized in that: In step S5, we consider continuing the rolling evaluation and judgment in the window after a certain delay of a certain time t. In different rocket models and mission procedures, the time t needs to be adjusted according to the length of the work execution time and the launch window time of this model. At the same time, the duration t should also be greater than the minimum time interval for meteorological departments to provide upper-level wind field data.

8. The rocket wind correction rolling evaluation method for GTO long-window missions according to claim 1, characterized in that: During actual launch missions, multiple decision points can be set as needed.

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