A rocket load reduction control method, device and electronic equipment

Abstract

This application provides a rocket load reduction control method, device, and electronic device, relating to the field of rocket control technology. The method includes: acquiring real-time flight parameters of the rocket; determining a target roll angle for load reduction based on the real-time flight parameters and a preset correspondence; and controlling the rocket load reduction in real time. The correspondence includes multiple preset flight parameters and a target roll angle corresponding to each preset flight parameter. The roll angle corresponding to each preset flight parameter in the correspondence is obtained by aerodynamic simulation testing of the rocket, and corresponds to the roll angle at minimum aerodynamic load. Based on the method provided in this application, during actual rocket flight, the roll angle corresponding to the minimum aerodynamic load with respect to the real-time flight parameters can be quickly determined according to the above correspondence, thereby effectively reducing the aerodynamic load on the rocket in real time and achieving effective load reduction.

Description

Technical Field

[0001] This application relates to the field of rocket control technology, and more specifically, to a rocket load reduction control method, device, and electronic equipment. Background Technology

[0002] When a rocket is flying at high altitude, it will be subjected to large aerodynamic loads, which will affect the rocket's safety.

[0003] To reduce the aerodynamic loads on the rocket, techniques such as trajectory correction compensation can be employed, which involves making trajectory corrections based on meteorological data before launch. However, this method is not entirely effective and requires improvement. Summary of the Invention

[0004] This application provides a rocket load reduction control method, device, electronic device, computer-readable storage medium, and computer program product. To improve rocket load reduction performance, the technical solutions provided by this application are as follows:

[0005] According to one aspect of the embodiments of this application, a rocket load reduction control method is provided, the method comprising:

[0006] Obtain the rocket's real-time flight parameters;

[0007] Based on a preset correspondence, the target roll angle corresponding to the real-time flight parameters is determined. The correspondence includes multiple preset flight parameters and the target roll angle corresponding to each preset flight parameter.

[0008] The rocket's flight is controlled based on the target roll angle corresponding to the real-time flight parameters;

[0009] The target roll angle corresponding to each preset flight parameter in the correspondence is obtained in the following way:

[0010] Multiple flight simulation parameters are determined, each of which includes a preset flight parameter and a corresponding preset roll angle. For each preset flight parameter, at least two flight simulation parameters include that preset flight parameter.

[0011] The rocket is subjected to aerodynamic simulation tests using each of the flight simulation parameters to obtain the aerodynamic loads on the rocket when each of the flight simulation parameters is used;

[0012] The preset roll angle in the target simulation parameters corresponding to each preset flight parameter is determined as the target roll angle corresponding to each preset flight parameter. The target simulation parameter corresponding to each preset flight parameter is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters of the preset flight parameter.

[0013] According to another aspect of the embodiments of this application, a rocket load reduction control device is provided, the device comprising:

[0014] The real-time flight parameter acquisition module is used to acquire the rocket's real-time flight parameters;

[0015] The target roll angle determination module is used to determine the target roll angle corresponding to the real-time flight parameters according to a preset correspondence relationship, wherein the correspondence relationship includes multiple preset flight parameters and the target roll angle corresponding to each preset flight parameter;

[0016] The control module is used to control the rocket's flight based on the target roll angle corresponding to the real-time flight parameters;

[0017] The target roll angle corresponding to each preset flight parameter in the correspondence is obtained by the simulation test module in the following way:

[0018] Multiple flight simulation parameters are determined, each of which includes a preset flight parameter and a corresponding preset roll angle. For each preset flight parameter, at least two flight simulation parameters include that preset flight parameter.

[0019] The rocket is subjected to aerodynamic simulation tests using each of the flight simulation parameters to obtain the aerodynamic loads on the rocket when each of the flight simulation parameters is used;

[0020] The preset roll angle in the target simulation parameters corresponding to each preset flight parameter is determined as the target roll angle corresponding to each preset flight parameter. The target simulation parameter corresponding to each preset flight parameter is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters of the preset flight parameter.

[0021] Optionally, the simulation test module can be used to construct a three-dimensional mesh model of the rocket based on the surface structure of the rocket;

[0022] Aerodynamic simulation tests were performed on the three-dimensional mesh model using each of the flight simulation parameters to obtain the aerodynamic loads on the rocket when each of the flight simulation parameters was used.

[0023] Optionally, the surface structure of the rocket includes a protruding structure; the simulation test module can be used to screen the surface structure of the rocket according to preset conditions to obtain a target surface structure that meets the preset conditions;

[0024] Based on the target surface structure, construct a three-dimensional mesh model of the rocket;

[0025] The preset conditions include at least one of the following:

[0026] Surface structures with a volume larger than a preset volume;

[0027] The surface structure located in the arrow region of the rocket;

[0028] Surface structures whose structural complexity meets the preset complexity conditions.

[0029] Optionally, the preset flight parameters include a preset velocity and a preset total angle of attack, and the real-time flight parameters include the rocket's current velocity and the target's total angle of attack;

[0030] The target total angle of attack is obtained by the real-time flight parameter acquisition module in the following way: acquiring the current wind speed and the current velocity of the rocket; and determining the target total angle of attack of the rocket based on the current wind speed and the current velocity.

[0031] Optionally, the real-time flight parameter acquisition module can be used to determine the resultant velocity based on the current wind speed and the current speed of motion;

[0032] The total angle of attack of the rocket is determined based on the combined velocity.

[0033] Optionally, the control module can be used to control the rocket's flight based on the target's total angle of attack and the target's roll angle.

[0034] Optionally, the target roll angle determination module can be used to determine the target roll angle corresponding to the real-time flight parameter as the target roll angle corresponding to the real-time flight parameter if there is a preset flight parameter in the preset correspondence that is the same as the real-time flight parameter;

[0035] If there is no preset flight parameter in the preset correspondence that is the same as the real-time flight parameter, then the target roll angle corresponding to the preset flight parameter with the smallest difference from the real-time flight parameter in the correspondence is determined as the target roll angle corresponding to the real-time flight parameter.

[0036] According to another aspect of the present application, an electronic device is provided, including a memory, a processor, and a computer program stored in the memory, wherein the processor executes the computer program to implement the steps of the method provided in any optional embodiment of the present application.

[0037] According to another aspect of the embodiments of this application, a computer-readable storage medium is provided, on which a computer program is stored, which, when executed by a processor, implements the steps of the method provided in any optional embodiment of this application.

[0038] According to one aspect of the embodiments of this application, a computer program product is provided, including a computer program that, when executed by a processor, implements the steps of the method provided in any optional embodiment of this application.

[0039] The beneficial effects of the technical solution provided in this application are as follows: Real-time flight parameters of the rocket are obtained; based on the real-time flight parameters and a preset correspondence, a target roll angle for reducing the rocket's load is determined; and the rocket's load reduction is controlled in real time. The aforementioned correspondence includes multiple preset flight parameters and the target roll angle corresponding to each preset flight parameter. Specifically, the roll angle corresponding to each preset flight parameter in the aforementioned correspondence is the roll angle corresponding to the minimum aerodynamic load, obtained through aerodynamic simulation testing of the rocket. Based on the method provided in this application, during actual rocket flight, the roll angle corresponding to the minimum aerodynamic load with respect to the real-time flight parameters can be quickly determined according to the aforementioned correspondence, thereby effectively reducing the aerodynamic load on the rocket in real time and achieving effective load reduction. Attached Figure Description

[0040] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments of this application will be briefly introduced below.

[0041] Figure 1 A schematic flowchart illustrating the rocket load reduction control method provided in this application embodiment;

[0042] Figure 2 A schematic diagram showing the wind angle of attack and total angle of attack of a rocket, provided for embodiments of this application;

[0043] Figure 3 A schematic diagram of a simulation result provided for an embodiment of this application;

[0044] Figure 4 A schematic diagram of the fairing lateral explosion bolts is provided for embodiments of this application;

[0045] Figure 5 A schematic diagram of a phased array antenna is provided for an embodiment of this application;

[0046] Figure 6 A schematic diagram of a secondary cable cover and a conduit cover is provided for embodiments of this application;

[0047] Figure 7 A schematic diagram of a thrust-propellant rocket structure is provided for embodiments of this application;

[0048] Figure 8 A schematic diagram of a rocket load reduction control device provided in this application embodiment;

[0049] Figure 9This is a schematic diagram of the structure of an electronic device for rocket load reduction control provided in an embodiment of this application. Detailed Implementation

[0050] The embodiments of this application are described below with reference to the accompanying drawings. It should be understood that the embodiments described below with reference to the accompanying drawings are exemplary descriptions for explaining the technical solutions of the embodiments of this application, and do not constitute a limitation on the technical solutions of the embodiments of this application.

[0051] Those skilled in the art will understand that, unless otherwise stated, the singular forms “a,” “an,” “the,” and “the” used herein may also include the plural forms. It should be further understood that the terms “comprising” and “including” as used in embodiments of this application mean that the corresponding feature can be implemented as the presented feature, information, data, step, operation, element, and / or component, but do not exclude implementation as other features, information, data, step, operation, element, component, and / or combinations thereof supported by the art. It should be understood that when we say that an element is “connected” or “coupled” to another element, the element can be directly connected or coupled to the other element, or it can mean that the element and the other element establish a connection relationship through an intermediate element. Furthermore, “connected” or “coupled” as used herein can include wireless connection or wireless coupling. The term “and / or” as used herein indicates at least one of the items defined by the term, for example, “A and / or B” or “A, B” indicates implementation as “A,” or implementation as “B,” or implementation as “A and B.” When describing multiple (two or more) items, if the relationship between the multiple items is not explicitly defined, the multiple items can refer to one, several or all of the multiple items. For example, the description of "parameter A includes A1, A2, A3" can be implemented as parameter A includes A1 or A2 or A3, or it can be implemented as parameter A includes at least two of the three items A1, A2 and A3.

[0052] During flight within the atmosphere, launch vehicles generate aerodynamic loads due to relative motion, especially at high altitudes where rapid changes in wind speed and direction, particularly wind shear, produce significant lateral overloads—forces perpendicular to the rocket's flight direction. These overloads can adversely affect the rocket's structural safety, handling performance, and flight stability.

[0053] Generally, to avoid the aforementioned effects, rocket body structural strength is typically designed based on the maximum load envelope, ensuring the rocket body structure can withstand the largest possible load. However, this can result in an excessively high structural coefficient, making it impossible to effectively reduce drag with the same fuel mass, leading to reduced payload capacity and high launch costs. Trajectory corrections can also be performed based on meteorological data before launch, but this requires high reliability of the meteorological data and lacks real-time capability.

[0054] This application provides a rocket load reduction control method. This method can reduce the rocket's load in real time by acquiring real-time flight parameters and a preset correspondence, exhibiting strong real-time performance. Since this method can effectively reduce the aerodynamic load on the rocket, it is beneficial for reducing the rocket's structural coefficient, improving its carrying capacity, and reducing launch costs.

[0055] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of the embodiments of this application and the technical effects produced by the technical solutions of this application are described below through the description of several exemplary embodiments. It should be noted that the following embodiments can be referenced, borrowed, or combined with each other, and the same terms, similar features, and similar implementation steps in different embodiments will not be described again.

[0056] Figure 1 This is a flowchart illustrating a rocket load reduction control method provided in an embodiment of this application. The method is executed by a control device for controlling the rocket's load reduction. For example, it could be a control device installed on the rocket, or other control device capable of communicating with the rocket. For ease of explanation, this embodiment uses a control device installed on the rocket as the executing entity. Figure 1 As shown, the method includes S101~S103:

[0057] S101: Obtain the rocket's real-time flight parameters.

[0058] The real-time flight parameters may include current velocity, target total angle of attack, etc. Current velocity is a vector, including velocity and direction of motion.

[0059] The rocket's velocity can be its absolute velocity or its relative velocity; for example, it can be the rocket's real-time flight velocity. As an optional embodiment of this application, the rocket's current velocity can be represented by its current Mach number.

[0060] In calm conditions, the total angle of attack can be interpreted as the angle between the direction of the rocket's velocity relative to the ground and the rocket's axial direction. In windy conditions, the total angle of attack can be interpreted as the angle between the direction of the resultant velocity of the wind speed and the rocket's velocity relative to the ground and the rocket's axial direction. The total angle of attack in calm conditions can be called the first total angle of attack, and the total angle of attack in windy conditions can be called the second total angle of attack. The variable angle between the first and second total angles of attack is the wind angle of attack.

[0061] As an example, Figure 2 The schematic diagrams provided for embodiments of this application regarding the wind angle of attack and total angle of attack of the rocket are as follows: Figure 2 As shown.

[0062] The arrow's coordinate system includes the origin. coordinate axes , and (Not shown in the figure) ). origin Located at the theoretical apex of the fairing, it can be considered the rocket's center of mass. Aligning with the rocket's axis, that is, pointing from the tail of the arrow towards the head of the rocket body, along the longitudinal axis of the rocket body towards the head of the arrow body is considered positive. Perpendicular to Pointing upwards within the longitudinal plane of symmetry, perpendicular to For positive, If the right-hand rule is satisfied, then pointing to the right side of the arrow (looking forward from the tail of the arrow) is considered positive.

[0063] In windless conditions, the rocket's velocity relative to the ground and the rocket's speed relative to the air Overlap, rocket longitudinal axis and The included angle That is, the rocket's total angle of attack. When there are high-altitude winds, due to the wind speed at that time... The effect of (air velocity relative to the ground), At this moment, the all-out attack angle That is, the rocket's longitudinal axis Speed ​​of the rocket relative to the air The included angle increases to + This is equivalent to adding a wind attack angle. The angle of attack reflects the change in the total angle of attack under the influence of wind speed.

[0064] When acquiring the rocket's real-time flight parameters, the control equipment can measure the rocket's acceleration and angular velocity using the inertial measurement unit and perform integration to determine the rocket's current velocity (velocity relative to the ground). The current velocity can also be determined using the lateral and normal acceleration measured in real-time by the lateral normalizer in the rocket; however, this embodiment does not impose limitations on this method.

[0065] Since the parameters obtained are real-time parameters of the rocket, the subsequent rocket load reduction control operations based on these parameters are more real-time and can be completed without relying on meteorological data.

[0066] S102: Determine the target roll angle corresponding to the real-time flight parameter according to the preset correspondence. The correspondence includes multiple preset flight parameters and the target roll angle corresponding to each preset flight parameter.

[0067] The target roll angle corresponding to each preset flight parameter in this correspondence is obtained in the following way:

[0068] Multiple flight simulation parameters are determined. Each flight simulation parameter includes a preset flight parameter and a corresponding preset roll angle. For each preset flight parameter, there are at least two flight simulation parameters that include that preset flight parameter.

[0069] Aerodynamic simulation tests were conducted on the rocket using each flight simulation parameter to obtain the aerodynamic loads experienced by the rocket under each flight simulation parameter.

[0070] The preset roll angle in the target simulation parameters corresponding to each preset flight parameter is determined as the target roll angle corresponding to each preset flight parameter. The target simulation parameters corresponding to each preset flight parameter are: the flight simulation parameters corresponding to the minimum aerodynamic load in the flight simulation parameters of the preset flight parameter.

[0071] The target roll angle is within the range of [0°, 360°]. Each preset flight parameter can include a preset motion speed and a preset total angle of attack. A combination of a preset flight parameter and a preset roll angle yields a flight simulation parameter. For example, preset motion speed 1, preset total angle of attack 1, and roll angle 1 can be flight simulation parameter 1, and preset motion speed 1, preset total angle of attack 1, and roll angle 2 can be flight simulation parameter 2.

[0072] It should be noted that the entity performing aerodynamic simulation tests on the rocket can be an electronic device such as a server, and this application embodiment does not impose any restrictions on this. To determine the optimal preset roll angle, during simulation, at least two aerodynamic loads corresponding to preset roll angles must be simulated for each preset flight parameter. Continuing with the above example, when the preset flight parameters are preset velocity 1 and preset total angle of attack 1, the aerodynamic loads on the rocket when the preset roll angle is roll angle 1, and the aerodynamic loads on the rocket when the preset roll angle is roll angle 2, must be simulated to determine the optimal preset roll angle and obtain the target roll angle in the corresponding relationship. In other words, for each preset flight parameter, at least two flight simulation parameters include that preset flight parameter.

[0073] Figure 3 A schematic diagram of a simulation result provided for an embodiment of this application, such as... Figure 3 As shown.

[0074] The Mach number can be determined based on the preset speed. Taking Mach number and total angle of attack as preset flight parameters as an example, when the determined Mach number is 1.2939, the total angle of attack... The simulation results represent the magnitude of the aerodynamic loads on the rocket at various preset roll angles, where the roll angle is 6.667°. The preset roll angles are... CN indicates that CN represents the aerodynamic load.

[0075] After conducting aerodynamic simulation tests on the rocket using each flight simulation parameter and obtaining the aerodynamic load corresponding to each flight simulation parameter, for each preset flight parameter, the preset roll angle corresponding to the flight simulation parameter with the smallest aerodynamic load is determined from multiple flight simulation parameters including the preset flight parameter. This is taken as the target roll angle so that the optimal roll angle corresponding to the real-time flight parameter can be selected from each target roll angle in the future.

[0076] Using the examples of flight simulation parameters 1 and 2, if the rocket experiences the minimum aerodynamic load when the preset roll angle is roll angle 1, then this roll angle 1 is the target roll angle, thus obtaining the corresponding relationship. In this relationship, the preset velocity 1 and the preset total angle of attack 1 correspond to the roll angle 1. Figure 3 For example, the aerodynamic load is minimal at a roll angle of 90°; therefore, the Mach number is retained at 1.2939, and the total angle of attack is... The corresponding preset roll angle is 90° for 6.667°.

[0077] By pre-determining multiple preset flight parameters and the target roll angle corresponding to each preset flight parameter (which is the roll angle at which the aerodynamic load is minimized), during the actual rocket motion, preset flight parameters matching the real-time flight parameters can be determined based on the real-time flight parameters. This allows for the determination of the target roll angle corresponding to the preset flight parameters, which in turn serves as the target roll angle corresponding to the real-time flight parameters. This enables real-time determination of the roll angle corresponding to the minimum aerodynamic load on the rocket during flight, thereby controlling rocket load reduction.

[0078] S103: Control the rocket's flight based on the target roll angle corresponding to the real-time flight parameters.

[0079] The control equipment can acquire the rocket's current roll angle. If the current roll angle is inconsistent with the target roll angle, it will be adjusted to the target roll angle to control the rocket's flight. During simulation testing, the rocket experiences the minimum aerodynamic load when rotating at the target roll angle. However, since the current roll angle is inconsistent with the target roll angle, the aerodynamic load experienced by the rocket when rotating at the current roll angle is greater than that experienced when rotating at the target roll angle. Therefore, adjusting the current roll angle to the target roll angle reduces the aerodynamic load on the rocket.

[0080] The embodiments of this application have strong real-time performance, thus ensuring that the aerodynamic loads experienced by the rocket during flight are kept within a controllable minimum, thereby improving the rocket's flight safety. Furthermore, because the embodiments of this application can ensure that the aerodynamic loads experienced by the rocket during flight are kept within a controllable minimum, the rocket's structural coefficient can be reduced during design, thereby increasing the rocket's carrying capacity and reducing launch costs.

[0081] For step S101, the preset flight parameters include preset motion speed and preset total angle of attack. The real-time flight parameters include the rocket's current motion speed and target total angle of attack. The target total angle of attack is obtained by: acquiring the current wind speed and the rocket's current motion speed; and determining the rocket's target total angle of attack based on the current wind speed and current motion speed.

[0082] Both the current wind speed and the current velocity are vectors.

[0083] Specifically, the control equipment can determine the rocket's velocity relative to the ground (i.e., its current velocity) through ground radar, satellite tracking systems, etc. Before launch, it can obtain wind speed and direction data at different altitudes near the launch site through weather balloons or other weather monitoring equipment to determine the current wind speed.

[0084] Determine the resultant velocity based on the current wind speed and current velocity; determine the rocket's total angle of attack based on the resultant velocity.

[0085] By using vector addition, the resultant velocity vector after combining the rocket's velocity vector (current velocity) and the wind speed vector can be determined, and thus the total angle of attack of the target can be obtained.

[0086] For example, the current speed of movement is The wind speed vector is The resultant velocity vector is The target's overall angle of attack is direction and The included angle.

[0087] Determining the rocket's real-time flight parameters allows for timely assessment of whether adjustments are needed, thereby reducing the aerodynamic load on the rocket and enabling real-time load reduction.

[0088] Understandably, the control equipment can also reduce load by adjusting the target total angle of attack. Since adjusting the target total angle of attack completes one load reduction, subsequent adjustments to the target roll angle can reduce load again, thus optimizing the load reduction method. Of course, the parameter value of the reduced target total angle of attack can be determined first, and when the current roll angle is subsequently adjusted to the target roll angle, the parameter value of the target total angle of attack can be adjusted to the previously determined value. Alternatively, load reduction can also be achieved by adjusting the direction of motion.

[0089] Since changing the total angle of attack can also change the aerodynamic load on the rocket, the target total angle of attack and the target roll angle can be used together to further improve the load reduction effect.

[0090] Furthermore, when determining the target roll angle, if a preset flight parameter identical to the real-time flight parameter exists in the pre-defined correspondence, the target roll angle corresponding to this preset flight parameter is determined as the target roll angle corresponding to the real-time flight parameter. However, due to insufficient data during simulation, a pre-defined flight parameter matching the real-time flight parameter may not exist in actual application. In such cases, if no pre-defined flight parameter identical to the real-time flight parameter exists in the pre-defined correspondence, the target roll angle corresponding to the preset flight parameter with the smallest difference from the real-time flight parameter in the correspondence is determined as the target roll angle corresponding to the real-time flight parameter. The difference can be the numerical difference between the parameter value of the real-time flight parameter and the parameter value of the preset flight parameter.

[0091] Since the preset flight parameters include both preset motion speed and preset total angle of attack, the control device can determine the preset flight parameter corresponding to at least one of these parameters from the preset correspondence. That is, it can determine a preset motion speed that is the same as the current motion speed and / or a preset total angle of attack that is the same as the target's total angle of attack. It is understandable that, conversely, there are also cases where no preset flight parameter is found that matches the real-time flight parameter in the three preset correspondences. That is, there is no preset total angle of attack that matches the target's total angle of attack in the correspondences, and / or there is no preset motion speed that matches the current motion speed in the correspondences.

[0092] Taking the example of determining only the preset total angle of attack that is the same as the target's total angle of attack, and there is no target with the same preset total angle of attack in the corresponding relationship, if the target's total angle of attack is 30.4°, the preset total angle of attack 1 is 30°, and the preset total angle of attack 2 is 35°, then the target's total angle of attack is closest to the preset total angle of attack 1, and the target roll angle corresponding to the preset total angle of attack 1 can be selected.

[0093] Taking the example of determining only the preset movement speed that is the same as the current movement speed, and there is no preset movement speed that is the same as the current movement speed in the corresponding relationship, if the preset movement speed is a range value, such as preset movement speed 1 is 30~35km / s, preset movement speed 2 is 40~45km / s, and the current movement speed is 43km / s, then it falls within the range of preset movement speed 2, and the target roll corresponding to preset movement speed 2 can be selected.

[0094] Taking the example of a preset motion speed that is not the same as the current motion speed, and a preset total angle of attack that is not the same as the target's total angle of attack, the total difference can be determined, and the target roll angle corresponding to the preset flight parameter with the smallest total difference can be selected. This total difference can be determined based on the first difference between the current motion speed and each preset motion speed, and the second difference between the target's total angle of attack and each preset total angle of attack. For example, the first weight of the first difference and the second weight of the second difference can be obtained. Based on the first weight, the first difference, the second weight, and the second difference, the total difference can be determined, and the target roll angle corresponding to the preset flight parameter with the smallest total difference can be selected. Alternatively, the first difference and the second difference can be directly summed to obtain the total difference.

[0095] Using the above example, the smallest total difference is the target roll angle when the preset total angle of attack 1 is 30° and the preset movement speed 2 is 40~45km / s.

[0096] The target roll angle determined by selecting the preset flight parameters with the smallest difference can also be used to reduce the rocket's load and optimize the load reduction effect.

[0097] Regarding step S103, the load reduction control equipment can control the rocket to reduce its load based solely on the target roll angle, or it can control the rocket's flight based on both the target total angle of attack and the target roll angle to achieve load reduction. Combining the target total angle of attack and the target roll angle further improves the load reduction effect.

[0098] Furthermore, in determining the correspondence, a three-dimensional mesh model of the rocket was constructed based on its surface structure. Aerodynamic simulation tests were then conducted on this three-dimensional mesh model using each flight simulation parameter to obtain the aerodynamic loads experienced by the rocket under each parameter. The rocket's surface structure includes protruding structures.

[0099] Figures 4-7 A schematic diagram of the surface structure provided for an embodiment of this application.

[0100] Figure 4 A schematic diagram of the transverse explosion bolts of the fairing is provided for embodiments of this application. Figure 5 A schematic diagram of a phased array antenna is provided for an embodiment of this application. Figure 6 A schematic diagram of a secondary cable cover and a conduit cover is provided for embodiments of this application. Figure 7 A schematic diagram of a thrust rocket structure is provided for an embodiment of this application.

[0101] Current rocket load reduction schemes do not consider the load differences caused by wind fields at different angles along the rocket's circumference. In reality, the rocket's outer surface can typically be equipped with various protrusions of different shapes and sizes to meet various functional requirements, such as cable covers, duct covers, forward / reverse thrust rocket fairings, explosive bolt boxes, vented fairings, and section docking frames. These distributed surface protrusions alter the aerodynamic characteristics of the smooth rocket body, causing complex local loads and affecting the aerodynamic loads on the entire rocket. In particular, they cause uneven load distribution on the rocket body under different wind directions, which can impact the rocket's safety performance.

[0102] In other words, current rocket flight load reduction methods do not take into account the normal overload caused by protrusions on the rocket surface and the non-uniform circumferential distribution characteristics. In the coordinate system of total angle of attack and roll angle, the incoming flow (the airflow relative to the rocket flow) may be located at the circumferential angle with a large aerodynamic load, so the load reduction effect is not optimal.

[0103] To address the impact of surface structure on aerodynamic loads and obtain a more accurate estimate of the actual aerodynamic loads experienced by the rocket, this application embodiment constructs a three-dimensional mesh model of the rocket based on its surface structure during simulation testing. Subsequent aerodynamic simulation tests on this three-dimensional mesh model yield aerodynamic loads that more closely approximate the actual aerodynamic loads experienced by the rocket, leading to a more accurate preset roll angle corresponding to the minimum aerodynamic load on the rocket. In other words, this application embodiment, based on the results of precise aerodynamic simulation of the rocket's surface structure, determines the roll angle with the smallest load under different flight simulation parameters. By actively controlling the rocket's attitude and roll, the aerodynamic load on the rocket is minimized, thereby achieving optimal load reduction.

[0104] Using the server as the execution entity, when constructing the three-dimensional mesh model of the rocket, the surface structure of the rocket can be filtered, retaining only a portion of the surface structure, thereby reducing simulation test time and improving simulation test efficiency.

[0105] Specifically, the surface structures of the rocket are screened according to preset conditions to obtain target surface structures that meet these conditions. Based on these target surface structures, a three-dimensional mesh model of the rocket is constructed. The preset conditions include at least one of the following: surface structures with a volume greater than a preset volume; surface structures located in the arrow region of the rocket; and surface structures with a structural complexity that meets a preset complexity condition. The arrow region is the area from the rocket tip to the rocket body at a preset distance, which can be set as needed.

[0106] Generally speaking, the larger the volume of a surface structure, the greater its impact on aerodynamic loads. This is because a larger volume means a larger surface area, which may expose more surface to the incoming airflow, thus allowing the surface structure to withstand greater aerodynamic loads.

[0107] Furthermore, the impact of surface structures on aerodynamic loads varies depending on the region where the structure is located; generally, surface structures in the arrow region have a greater impact on aerodynamic loads. This is because the arrow design is crucial for reducing air resistance (a type of aerodynamic load) experienced by the entire rocket. Generally, streamlined designs can significantly reduce air resistance and improve efficiency and performance. Therefore, the presence of protruding structures in the arrow region disrupts the streamlined structure of the arrow, potentially increasing drag on the rocket and affecting its overall performance. Thus, it is necessary to preserve the surface structures located in the arrow region of the rocket.

[0108] Of course, the higher the structural complexity of the surface structure, the greater its impact on the aerodynamic loads on the rocket. Structural complexity can be related to the shape of the surface structure, and the specific complexity can be set as needed. For example, a surface structure can be divided into multiple regularly shaped structural blocks. The more structural blocks obtained, the higher the structural complexity of the surface structure; the more types of shapes of the structural blocks obtained, the higher the structural complexity of the surface structure.

[0109] The relationship between structural complexity and surface shape stems from the fact that objects of different shapes experience different aerodynamic load distributions under the same speed and atmospheric conditions. For example, a long, narrow rocket will have a lower drag coefficient than a wide, flat design, as the former is closer to an ideal aerodynamic shape. Therefore, a higher structural complexity of the surface structure has a greater impact on the aerodynamic loads experienced by the rocket.

[0110] This application provides a rocket load reduction control device, such as... Figure 8 As shown, the rocket load reduction control device 80 may include: a real-time flight parameter acquisition module 801, a target roll angle determination module 802, a control module 803, and a simulation test module 804, wherein:

[0111] The real-time flight parameter acquisition module 801 is used to acquire the rocket's real-time flight parameters;

[0112] The target roll angle determination module 802 is used to determine the target roll angle corresponding to the real-time flight parameters according to a preset correspondence relationship, wherein the correspondence relationship includes multiple preset flight parameters and the target roll angle corresponding to each preset flight parameter;

[0113] Control module 803 is used to control the rocket flight according to the target roll angle corresponding to the real-time flight parameters;

[0114] The target roll angle corresponding to each preset flight parameter in the correspondence is obtained by the simulation test module 804 in the following way:

[0115] Multiple flight simulation parameters are determined, each of which includes a preset flight parameter and a corresponding preset roll angle. For each preset flight parameter, at least two flight simulation parameters include that preset flight parameter.

[0116] The rocket is subjected to aerodynamic simulation tests using each of the flight simulation parameters to obtain the aerodynamic loads on the rocket when each of the flight simulation parameters is used;

[0117] The preset roll angle in the target simulation parameters corresponding to each preset flight parameter is determined as the target roll angle corresponding to each preset flight parameter. The target simulation parameter corresponding to each preset flight parameter is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters of the preset flight parameter.

[0118] Optionally, the simulation test module 804 can be used to construct a three-dimensional mesh model of the rocket based on the surface structure of the rocket;

[0119] Aerodynamic simulation tests were performed on the three-dimensional mesh model using each of the flight simulation parameters to obtain the aerodynamic loads on the rocket when each of the flight simulation parameters was used.

[0120] Optionally, the surface structure of the rocket includes a protruding structure; the simulation test module 804 can be used to screen the surface structure of the rocket according to preset conditions to obtain a target surface structure that meets the preset conditions.

[0121] Based on the target surface structure, construct a three-dimensional mesh model of the rocket;

[0122] The preset conditions include at least one of the following:

[0123] Surface structures with a volume larger than a preset volume;

[0124] The surface structure located in the arrow region of the rocket;

[0125] Surface structures whose structural complexity meets the preset complexity conditions.

[0126] Optionally, the preset flight parameters include a preset velocity and a preset total angle of attack, and the real-time flight parameters include the rocket's current velocity and the target's total angle of attack;

[0127] The target total angle of attack is obtained by the real-time flight parameter acquisition module 801 in the following way: acquiring the current wind speed and the current velocity of the rocket; and determining the target total angle of attack of the rocket based on the current wind speed and the current velocity.

[0128] Optionally, the real-time flight parameter acquisition module 801 can be used to determine the resultant velocity based on the current wind speed and the current speed of motion;

[0129] The total angle of attack of the rocket is determined based on the combined velocity.

[0130] Optionally, the control module 803 can be used to control the rocket flight based on the target's total angle of attack and the target's roll angle.

[0131] Optionally, the target roll angle determination module 802 can be used to determine the target roll angle corresponding to the real-time flight parameter as the target roll angle corresponding to the real-time flight parameter if there is a preset flight parameter in the preset correspondence that is the same as the real-time flight parameter;

[0132] If there is no preset flight parameter in the preset correspondence that is the same as the real-time flight parameter, then the target roll angle corresponding to the preset flight parameter with the smallest difference from the real-time flight parameter in the correspondence is determined as the target roll angle corresponding to the real-time flight parameter.

[0133] The apparatus in this application embodiment can execute the method provided in this application embodiment, and its implementation principle is similar, and it has corresponding technical effects. The actions performed by each module in the apparatus of each embodiment of this application correspond to the steps in the method of each embodiment of this application. For a detailed functional description of each module of the apparatus, please refer to the description in the corresponding method shown above, which will not be repeated here.

[0134] This application provides an electronic device, including a memory, a processor, and a computer program stored in the memory. The processor executes the computer program to implement the steps of the method provided in any optional embodiment of this application.

[0135] In one alternative embodiment, an electronic device is provided, such as Figure 9 As shown, Figure 9 The illustrated electronic device 4000 includes a processor 4001 and a memory 4003. The processor 4001 and the memory 4003 are connected, for example, via a bus 4002. Optionally, the electronic device 4000 may further include a transceiver 4004, which can be used for data interaction between the electronic device and other electronic devices, such as sending and / or receiving data. It should be noted that in practical applications, the transceiver 4004 is not limited to one type, and the structure of the electronic device 4000 does not constitute a limitation on the embodiments of this application.

[0136] Processor 4001 may be a CPU (Central Processing Unit), a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), or other programmable logic devices, transistor logic devices, hardware components, or any combination thereof. It may implement or execute the various exemplary logic blocks, modules, and circuits described in conjunction with this disclosure. Processor 4001 may also be a combination that implements computational functions, such as including one or more microprocessor combinations, a combination of a DSP and a microprocessor, etc.

[0137] Bus 4002 may include a pathway for transmitting information between the aforementioned components. Bus 4002 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. Bus 4002 can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 9 The bus is represented by a single thick line, but this does not mean that there is only one bus or one type of bus.

[0138] The memory 4003 may be ROM (Read Only Memory) or other types of static storage devices capable of storing static information and instructions, RAM (Random Access Memory) or other types of dynamic storage devices capable of storing information and instructions, or EEPROM (Electrically Erasable Programmable Read Only Memory), CD-ROM (Compact Disc Read Only Memory) or other optical disc storage, optical disc storage (including compressed optical discs, laser discs, optical discs, digital universal optical discs, Blu-ray discs, etc.), magnetic disk storage media, other magnetic storage devices, or any other medium capable of carrying or storing computer programs and capable of being read by a computer, without limitation herein.

[0139] The memory 4003 is used to store computer programs that execute embodiments of the present disclosure, and is controlled by the processor 4001 to execute them. The processor 4001 is used to execute the computer programs stored in the memory 4003 to implement the steps shown in the foregoing method embodiments.

[0140] This application provides a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, it can implement the steps and corresponding content of the aforementioned method embodiments.

[0141] This application also provides a computer program product, including a computer program that, when executed by a processor, can implement the steps and corresponding content of the aforementioned method embodiments.

[0142] It should be understood that although arrows indicate various operation steps in the flowcharts of this application's embodiments, the order in which these steps are implemented is not limited to the order indicated by the arrows. Unless explicitly stated herein, in some implementation scenarios of this application's embodiments, the implementation steps in each flowchart can be executed in other orders as required. Furthermore, some or all steps in each flowchart, based on the actual implementation scenario, may include multiple sub-steps or multiple stages. Some or all of these sub-steps or stages can be executed at the same time, and each sub-step or stage can also be executed at different times. In scenarios where execution times differ, the execution order of these sub-steps or stages can be flexibly configured according to requirements, and this application's embodiments do not limit this.

[0143] The above description is only an optional implementation of some implementation scenarios of this disclosure. It should be noted that for those skilled in the art, other similar implementation methods based on the technical concept of this disclosure without departing from the technical concept of the embodiments of this application also fall within the protection scope of the embodiments of this application.

Claims

1. A rocket load reduction control method, characterized in that, include: Obtain the rocket's real-time flight parameters; Based on a preset correspondence, the target roll angle corresponding to the real-time flight parameters is determined. The correspondence includes multiple preset flight parameters and the target roll angle corresponding to each preset flight parameter. The rocket's flight is controlled based on the target roll angle corresponding to the real-time flight parameters; The target roll angle corresponding to each preset flight parameter in the correspondence is obtained in the following way: Multiple flight simulation parameters are determined, each of which includes a preset flight parameter and a corresponding preset roll angle. For each preset flight parameter, at least two flight simulation parameters include that preset flight parameter. The rocket is subjected to aerodynamic simulation tests using each of the flight simulation parameters to obtain the aerodynamic loads on the rocket when each of the flight simulation parameters is used; The preset roll angle in the target simulation parameters corresponding to each preset flight parameter is determined as the target roll angle corresponding to each preset flight parameter. The target simulation parameter corresponding to each preset flight parameter is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters of the preset flight parameter. The aerodynamic simulation test of the rocket using each of the flight simulation parameters, to obtain the aerodynamic loads on the rocket under each of the flight simulation parameters, includes: Based on the surface structure of the rocket, a three-dimensional mesh model of the rocket is constructed; Aerodynamic simulation tests were performed on the three-dimensional mesh model using each of the flight simulation parameters to obtain the aerodynamic loads on the rocket when each of the flight simulation parameters was used. The surface structure of the rocket includes a protruding structure; The step of constructing a three-dimensional mesh model of the rocket based on its surface structure includes: The surface structure of the rocket is screened according to preset conditions to obtain a target surface structure that meets the preset conditions; Based on the target surface structure, construct a three-dimensional mesh model of the rocket; The preset conditions include at least one of the following: Surface structures with a volume larger than a preset volume; The surface structure located in the arrow region of the rocket; Surface structures whose structural complexity meets the preset complexity conditions.

2. The method according to claim 1, characterized in that, The preset flight parameters include preset velocity and preset total angle of attack, and the real-time flight parameters include the rocket's current velocity and target total angle of attack; The target's total angle of attack is obtained in the following way: Obtain the current wind speed and the current velocity of the rocket; The target total angle of attack of the rocket is determined based on the current wind speed and the current velocity.

3. The method according to claim 2, characterized in that, Determining the target total angle of attack of the rocket based on the current wind speed and the current velocity includes: Determine the resultant velocity based on the current wind speed and the current speed of movement; The total angle of attack of the rocket is determined based on the combined velocity.

4. The method according to claim 3, characterized in that, Controlling the rocket's flight based on the target roll angle includes: The rocket's flight is controlled based on the target's total angle of attack and the target's roll angle.

5. The method according to any one of claims 1 to 2, characterized in that, The step of determining the target roll angle corresponding to the real-time flight parameters according to a preset correspondence includes: If there is a preset flight parameter in the preset correspondence that is the same as the real-time flight parameter, then the target roll angle corresponding to the preset flight parameter that is the same as the real-time flight parameter is determined as the target roll angle corresponding to the real-time flight parameter; If there is no preset flight parameter in the preset correspondence that is the same as the real-time flight parameter, then the target roll angle corresponding to the preset flight parameter with the smallest difference from the real-time flight parameter in the correspondence is determined as the target roll angle corresponding to the real-time flight parameter.

6. A rocket load reduction control device, characterized in that, include: The real-time flight parameter acquisition module is used to acquire the rocket's real-time flight parameters; The target roll angle determination module is used to determine the target roll angle corresponding to the real-time flight parameters according to a preset correspondence relationship, wherein the correspondence relationship includes multiple preset flight parameters and the target roll angle corresponding to each preset flight parameter; The control module is used to control the rocket's flight based on the target roll angle corresponding to the real-time flight parameters; The target roll angle corresponding to each preset flight parameter in the correspondence is obtained by the simulation test module in the following way: Multiple flight simulation parameters are determined, each of which includes a preset flight parameter and a corresponding preset roll angle. For each preset flight parameter, at least two flight simulation parameters include that preset flight parameter. The rocket is subjected to aerodynamic simulation tests using each of the flight simulation parameters to obtain the aerodynamic loads on the rocket when each of the flight simulation parameters is used; The preset roll angle in the target simulation parameters corresponding to each preset flight parameter is determined as the target roll angle corresponding to each preset flight parameter. The target simulation parameter corresponding to each preset flight parameter is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters of the preset flight parameter. The simulation test module is specifically used for: Based on the surface structure of the rocket, a three-dimensional mesh model of the rocket is constructed; Aerodynamic simulation tests were performed on the three-dimensional mesh model using each of the flight simulation parameters to obtain the aerodynamic loads on the rocket when each of the flight simulation parameters was used. The surface structure of the rocket includes a protruding structure; The simulation test module is also used for: The surface structure of the rocket is screened according to preset conditions to obtain a target surface structure that meets the preset conditions; Based on the target surface structure, construct a three-dimensional mesh model of the rocket; The preset conditions include at least one of the following: Surface structures with a volume larger than a preset volume; The surface structure located in the arrow region of the rocket; Surface structures whose structural complexity meets the preset complexity conditions.

7. An electronic device comprising a memory, a processor, and a computer program stored in the memory, characterized in that, The processor executes the computer program to implement the steps of the method according to any one of claims 1 to 5.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method described in any one of claims 1 to 5.

9. A computer program product, comprising a computer program, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 5.

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