Rocket load shedding control method and device and electronic equipment

Abstract

The embodiment of the invention provides a rocket load shedding control method and device and electronic equipment, and relates to the technical field of rocket control. The method comprises the steps that real-time flight parameters of a rocket are obtained, target roll angles used for carrying out load shedding on the rocket are determined based on the real-time flight parameters and a preset corresponding relation, load shedding of the rocket is controlled in real time, and the corresponding relation comprises multiple preset flight parameters and the target roll angles corresponding to the preset flight parameters. Wherein the rolling angle corresponding to each preset flight parameter in the corresponding relation is the rolling angle, obtained by carrying out an aerodynamic simulation test on the rocket, of the flight parameter corresponding to the minimum aerodynamic load, and on the basis of the method provided by the embodiment of the invention, in the actual flight of the rocket, the rolling angle corresponding to each preset flight parameter in the corresponding relation is the rolling angle corresponding to the minimum aerodynamic load. The rolling angle with the minimum aerodynamic load corresponding to the real-time flight parameters can be rapidly determined according to the corresponding relation, so that the aerodynamic load borne by the rocket can be effectively reduced in real time, and effective load shedding of the rocket is achieved.

Description

Technical Field

[0001] The present application relates to the field of rocket control technology. Specifically, the present application relates to a rocket load reduction control method, device and electronic equipment. Background Art

[0002] When a rocket flies at high altitude, it will be subjected to a large aerodynamic load, which will affect the safety of the rocket.

[0003] To reduce the aerodynamic load on the rocket, technologies such as trajectory correction compensation can be used, which involves performing trajectory corrections based on meteorological data before launch. However, this method is less than ideal and needs improvement. Summary of the Invention

[0004] The present application provides a method, device, electronic device, computer-readable storage medium, and computer program product for controlling rocket deload. To improve the rocket deload effect, the present application provides the following technical solutions: According to one aspect of an embodiment of the present application, a rocket load reduction control method is provided, the method comprising: Get the real-time flight parameters of the rocket; Determining a target roll angle corresponding to the real-time flight parameter according to a preset correspondence relationship, wherein the correspondence relationship includes a plurality of preset flight parameters and the target roll angle corresponding to each preset flight parameter; controlling the flight of the rocket according to a target roll angle corresponding to the real-time flight parameter; The target roll angle corresponding to each preset flight parameter in the corresponding relationship is obtained by: determining a plurality of flight simulation parameters, each of the flight simulation parameters comprising a preset flight parameter and a corresponding preset roll angle, and for each of the preset flight parameters, at least two flight simulation parameters include the preset flight parameter; Performing an aerodynamic simulation test on the rocket using each of the flight simulation parameters to obtain the aerodynamic load on the rocket when each of the flight simulation parameters is used; The preset roll angle in the target simulation parameter corresponding to each of the preset flight parameters is determined as the target roll angle corresponding to each of the preset flight parameters, and the target simulation parameter corresponding to each of the preset flight parameters is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters including the preset flight parameter.

[0005] According to another aspect of an embodiment of the present application, a rocket deload control device is provided, the device comprising: Real-time flight parameter acquisition module, used to obtain the real-time flight parameters of the rocket; a target roll angle determination module, configured to determine a target roll angle corresponding to the real-time flight parameter based on a preset correspondence relationship, wherein the correspondence relationship includes a plurality of preset flight parameters and the target roll angle corresponding to each preset flight parameter; a control module, configured to control the flight of the rocket according to a target roll angle corresponding to the real-time flight parameter; The target roll angle corresponding to each preset flight parameter in the corresponding relationship is obtained by the simulation test module in the following manner: determining a plurality of flight simulation parameters, each of the flight simulation parameters comprising a preset flight parameter and a corresponding preset roll angle, and for each of the preset flight parameters, at least two flight simulation parameters include the preset flight parameter; Performing an aerodynamic simulation test on the rocket using each of the flight simulation parameters to obtain the aerodynamic load on the rocket when each of the flight simulation parameters is used; The preset roll angle in the target simulation parameter corresponding to each of the preset flight parameters is determined as the target roll angle corresponding to each of the preset flight parameters, and the target simulation parameter corresponding to each of the preset flight parameters is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters including the preset flight parameter.

[0006] Optionally, the simulation test module may be used to construct a three-dimensional grid model of the rocket based on the surface structure of the rocket; An aerodynamic simulation test is performed on the three-dimensional grid model using each of the flight simulation parameters to obtain the aerodynamic load on the rocket when each of the flight simulation parameters is used.

[0007] 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; constructing a three-dimensional grid model of the rocket according to the target surface structure; The preset conditions include at least one of the following: Surface structures with a volume larger than a preset volume; a surface structure located in the arrowhead region of the rocket; The surface structure whose structural complexity meets the preset complexity conditions.

[0008] Optionally, the preset flight parameters include a preset movement speed and a preset total angle of attack, and the real-time flight parameters include the current movement speed and target total angle of attack of the rocket; Among them, the target total angle of attack is obtained by the real-time flight parameter acquisition module in the following manner: obtaining the current movement speed of the rocket at the current wind speed; and determining the target total angle of attack of the rocket based on the current wind speed and the current movement speed.

[0009] Optionally, the real-time flight parameter acquisition module may be configured to determine a combined speed based on the current wind speed and the current movement speed; The target total angle of attack of the rocket is determined based on the resultant velocity.

[0010] Optionally, the control module can be used to control the flight of the rocket according to the target total angle of attack and the target roll angle.

[0011] Optionally, the target roll angle determination module may be configured to, if a preset flight parameter identical to the real-time flight parameter exists in the preset correspondence, determine the target roll angle corresponding to the preset flight parameter identical to the real-time flight parameter as the target roll angle corresponding to the real-time flight parameter; If there is no preset flight parameter that is the same as the real-time flight parameter in the preset corresponding relationship, the target roll angle corresponding to the preset flight parameter that has the smallest difference from the real-time flight parameter in the corresponding relationship is determined as the target roll angle corresponding to the real-time flight parameter.

[0012] According to another aspect of an embodiment 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.

[0013] According to another aspect of the embodiments of the present application, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the steps of the method provided in any optional embodiment of the present application are implemented.

[0014] According to one aspect of an embodiment of the present application, a computer program product is provided, including a computer program, which implements the steps of the method provided in any optional embodiment of the present application when executed by a processor.

[0015] The technical solution provided by the embodiment of the present application has the following beneficial effects: obtaining the real-time flight parameters of the rocket, determining the target roll angle for reducing the load on the rocket based on the real-time flight parameters and the preset corresponding relationship, and controlling the rocket load reduction in real time. The above-mentioned corresponding relationship includes a plurality of preset flight parameters and the target roll angle corresponding to each preset flight parameter. Among them, the roll angle corresponding to each preset flight parameter in the above-mentioned corresponding relationship is the roll angle obtained by performing aerodynamic simulation tests on the rocket when the flight parameter corresponds to the minimum aerodynamic load. Based on the method provided by the embodiment of the present application, in the actual flight of the rocket, the roll angle with the minimum aerodynamic load corresponding to the real-time flight parameter can be quickly determined according to the above-mentioned corresponding relationship, thereby effectively reducing the aerodynamic load on the rocket in real time and achieving effective load reduction on the rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for describing the embodiments of the present application.

[0017] Figure 1 A flow chart of a method for implementing rocket load reduction control provided in an embodiment of the present application; Figure 2 A schematic diagram of the wind attack angle and total attack angle of a rocket provided in an embodiment of the present application; Figure 3 A schematic diagram of a simulation result provided in an embodiment of the present application; Figure 4 A schematic diagram of a fairing transverse explosive bolt is provided for an embodiment of the present application; Figure 5 A schematic diagram of a phased array antenna is provided for an embodiment of the present application; Figure 6 A schematic diagram of a secondary cable cover and a conduit cover is provided for an embodiment of the present application; Figure 7 A schematic diagram of a forward thrust rocket structure is provided for an embodiment of the present application; Figure 8 A schematic structural diagram of a rocket load reduction control device provided in an embodiment of the present application; Figure 9 A schematic structural diagram of an electronic device corresponding to a rocket load reduction control provided in an embodiment of the present application. DETAILED DESCRIPTION

[0018] The following describes the embodiments of the present application in conjunction with the accompanying drawings. It should be understood that the embodiments described below in conjunction with the accompanying drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0019] Those skilled in the art will understand that, unless otherwise stated, the singular forms "a," "an," "said," and "the" used herein may also include the plural forms. It should be further understood that the terms "including" and "comprising" used in the embodiments of the present application mean that the corresponding features can be implemented as the presented features, information, data, steps, operations, elements, and / or components, but do not exclude implementation as other features, information, data, steps, operations, elements, components, and / or combinations thereof supported by the present technical field. It should be understood that when we refer to an element as being "connected" or "coupled" to another element, the element can be directly connected or coupled to the other element, or it can refer to the element and the other element establishing a connection relationship through an intermediate element. In addition, the "connection" or "coupling" used herein may include wireless connection or wireless coupling. The term "and / or" 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 clearly defined, the multiple items may refer to one, multiple or all of the multiple items. For example, the description of "parameter A includes A1, A2, A3" can be implemented as parameter A including A1 or A2 or A3, and can also be implemented as parameter A including at least two of the three items A1, A2, and A3.

[0020] During flight, a launch vehicle generates aerodynamic loads due to relative motion within the atmosphere. Rapid changes in wind speed and direction at high altitudes, particularly due to high-altitude wind shear, can produce significant transverse overloads, or forces perpendicular to the rocket's flight direction. These overloads can adversely affect the rocket's structural safety, controllability, and flight stability.

[0021] Generally speaking, to avoid these effects, rocket design often prioritizes the maximum load envelope, ensuring the rocket's structure can withstand the greatest possible load. However, this can also result in excessively high structural coefficients, preventing the rocket from effectively reducing drag for the same fuel mass, leading to reduced payload capacity and higher launch costs. Pre-launch trajectory corrections can also be made based on meteorological data, but this requires high reliability and limited real-time availability.

[0022] The present invention provides a method for controlling rocket deload. This method can deload a rocket in real time by using real-time flight parameters acquired and pre-set corresponding relationships, resulting in strong real-time performance. Because the present invention effectively reduces the aerodynamic loads on the rocket, the method provided by the present invention is beneficial for reducing the rocket body structural coefficient, improving the rocket's carrying capacity, and lowering launch costs.

[0023] To make the objectives, technical solutions, and advantages of this application more clear, the following describes several exemplary embodiments to illustrate the technical solutions of the embodiments of this application and the technical effects produced by the technical solutions of this application. It should be noted that the following embodiments can refer to, draw on, or combine with each other, and the same terms, similar features, and similar implementation steps in different embodiments will not be repeated.

[0024] Figure 1 The flowchart of the method for realizing rocket deloading control provided in the embodiment of the present application is shown, wherein the method is executed by a control device for deloading the rocket, for example, it can be a control device installed on the rocket, or it can be other control devices that can communicate with the rocket. For the sake of convenience, the embodiment of the present application is described with the control device installed on the rocket as the execution subject. Figure 1 As shown, the method includes S101 to S103: S101: Obtain the real-time flight parameters of the rocket.

[0025] The real-time flight parameters may include the current movement speed, target total angle of attack, etc. The current movement speed is a vector, including movement rate and movement direction.

[0026] The speed of the rocket can be the absolute speed of the rocket or the relative speed of the rocket, for example, the real-time flight speed of the rocket. As an optional solution of the present application, the current speed of the rocket can be represented by the current Mach number of the rocket.

[0027] 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 combined wind speed and the rocket's velocity relative to the ground and the rocket's axial direction. The calm total angle of attack can be referred to as the first total angle of attack, while the windy total angle of attack can be referred to as the second total angle of attack. The variable angle between the first and second total angles of attack is the wind angle of attack.

[0028] As an example, Figure 2 The schematic diagram of the wind attack angle and total attack angle of the rocket provided in the embodiment of the present application is as follows: Figure 2 shown.

[0029] The rocket body coordinate system includes the origin , coordinate axis 、 and (Not shown in the figure ). origin Located at the theoretical apex of the fairing, it can be the center of mass of the rocket. The direction is consistent with the rocket axis, that is, from the tail to the head of the rocket body, and along the longitudinal axis of the rocket body to the head of the rocket body is positive. Perpendicular to , pointing upward in the longitudinal symmetry plane, perpendicular to is positive, It satisfies the right rule and points to the right side of the arrow body (looking forward from the tail of the arrow body) is positive.

[0030] In the absence of wind, the speed of the rocket relative to the ground and the speed of the rocket relative to the air Coincident, rocket longitudinal axis and Angle The total angle of attack of the rocket When there is high altitude wind, due to the wind speed at this time (the speed of air relative to the ground), At this time, the total angle of attack The rocket's longitudinal axis The speed of the rocket relative to the air The angle increases to + , which is equivalent to adding a wind attack angle The wind attack angle reflects the change in the total attack angle under the influence of wind speed.

[0031] When acquiring the rocket's real-time flight parameters, the control device may measure the rocket's acceleration and angular velocity using the inertial measurement unit and integrate these to determine the rocket's current velocity (speed relative to the ground). The rocket's current velocity may also be determined based on the lateral acceleration and normal acceleration measured in real time by a lateral-normal instrument in the rocket, although this is not a limitation in this embodiment of the present application.

[0032] Since the parameters obtained are the real-time parameters of the rocket, the subsequent rocket load reduction control operations based on the real-time parameters are more real-time and can complete the load reduction without relying on meteorological data.

[0033] S102: Determine a target roll angle corresponding to the real-time flight parameter according to a preset correspondence relationship, where the correspondence relationship includes a plurality of preset flight parameters and a target roll angle corresponding to each preset flight parameter.

[0034] The target roll angle corresponding to each preset flight parameter in the corresponding relationship is obtained by: determining a plurality of flight simulation parameters, each flight simulation parameter including a preset flight parameter and a corresponding preset roll angle, and for each preset flight parameter, at least two flight simulation parameters including the preset flight parameter; Performing an aerodynamic simulation test on the rocket using each flight simulation parameter to obtain the aerodynamic load on the rocket when each flight simulation parameter is used; The preset roll angle in the target simulation parameter 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 including the preset flight parameter.

[0035] The target roll angle is in the range [0°, 360°]. Each preset flight parameter can include a preset motion speed and a preset total angle of attack. Combining a preset flight parameter with a preset roll angle yields a flight simulation parameter. For example, a preset motion speed of 1, a preset total angle of attack of 1, and a roll angle of 1 can be flight simulation parameter 1, while a preset motion speed of 1, a preset total angle of attack of 1, and a roll angle of 2 can be flight simulation parameter 2.

[0036] It should be noted that the execution entity of the aerodynamic simulation test of the rocket can be an electronic device such as a server, and the embodiments of the present application do not limit this. In order to determine the optimal preset roll angle, when performing the simulation, a preset flight parameter must at least simulate the aerodynamic loads corresponding to two preset roll angles. Continuing with the above example, when the preset flight parameters are the preset motion speed 1 and the preset total attack angle 1, it is necessary to simulate the aerodynamic load on the rocket when the preset roll angle is roll angle 1, and simulate the aerodynamic load on the rocket when the preset roll angle is roll angle 2, and then determine the optimal preset roll angle and obtain the target roll angle in the corresponding relationship. In other words, for each preset flight parameter, there are at least two flight simulation parameters that include the preset flight parameter.

[0037] Figure 3 A schematic diagram of a simulation result provided in an embodiment of the present application is shown in FIG. Figure 3 shown.

[0038] The Mach number can be determined according to the preset movement speed. Taking the Mach number and total angle of attack as a preset flight parameter, when the determined Mach number is 1.2939 and the total angle of attack is When the preset roll angle is 6.667°, the aerodynamic load on the rocket is the simulation result. Indicates that CN is the aerodynamic load.

[0039] 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, among multiple flight simulation parameters including the preset flight parameter, the preset roll angle corresponding to the flight simulation parameter with the smallest aerodynamic load is determined 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 subsequently.

[0040] Using the example of flight simulation parameters 1 and 2, if the aerodynamic load on the rocket is the smallest when the preset roll angle is roll angle 1, then the roll angle 1 is the target roll angle, and the corresponding relationship is obtained. In this corresponding relationship, the preset motion speed 1, the preset total attack angle 1 and the roll angle 1 correspond to each other. Figure 3 For example, when the roll angle is 90°, the aerodynamic load is the smallest, so the Mach number is kept at 1.2939 and the total angle of attack is The corresponding preset roll angle of 6.667° is 90°.

[0041] By pre-determining multiple preset flight parameters and the target roll angle corresponding to each preset flight parameter, the roll angle is the roll angle at which aerodynamic load is minimized. Therefore, during actual rocket motion, based on the real-time flight parameters, the corresponding preset flight parameters can be determined to match the real-time flight parameters. The target roll angle corresponding to the preset flight parameters can then be determined as the target roll angle corresponding to the real-time flight parameters. This allows the roll angle corresponding to the minimum aerodynamic load on the rocket to be determined in real time during flight, thereby controlling the rocket's load reduction.

[0042] S103: Controlling the flight of the rocket according to the target roll angle corresponding to the real-time flight parameter.

[0043] The control device can obtain the current roll angle of the rocket. If the current roll angle does not match the target roll angle, it adjusts the current roll angle to the target roll angle to control the rocket's flight. During simulation tests, the aerodynamic load on the rocket is minimized when the target roll angle is used. However, since the current roll angle does not match the target roll angle, the aerodynamic load on the rocket when it rotates at the current roll angle is greater than the aerodynamic load on the rocket when it rotates at the target roll angle. Therefore, adjusting the current roll angle to the target roll angle can reduce the aerodynamic load on the rocket.

[0044] The embodiments of the present application offer strong real-time performance, ensuring that the aerodynamic loads on the rocket during flight are kept to a minimum within a controllable range, thereby improving the rocket's flight safety. Furthermore, because the embodiments of the present application ensure that the aerodynamic loads on the rocket during flight are kept to a minimum within a controllable range, the rocket body structural coefficient can be reduced during rocket design, thereby increasing the rocket's carrying capacity and reducing launch costs.

[0045] For step S101, the preset flight parameters include a preset movement speed and a preset total angle of attack, and the real-time flight parameters include the current movement speed and the target total angle of attack of the rocket; wherein, the target total angle of attack is obtained by: obtaining the current wind speed and the current movement speed of the rocket; and determining the target total angle of attack of the rocket based on the current wind speed and the current movement speed.

[0046] The current wind speed and the current movement speed are both vectors.

[0047] Specifically, the control equipment can determine the rocket's speed relative to the ground (i.e., current speed) through ground radar, satellite tracking systems, etc. Before launch, it can obtain wind speed and direction data at different heights near the launch site through weather balloons or other meteorological monitoring equipment to determine the current wind speed.

[0048] Determine the resultant speed based on the current wind speed and the current movement speed; and determine the target total angle of attack of the rocket based on the resultant speed.

[0049] By vector addition, the resultant velocity vector of the rocket velocity vector (current motion speed) and the wind speed vector can be determined, and then the total angle of attack of the target can be obtained.

[0050] For example, the current movement speed is , the wind speed vector is , then the resultant velocity vector is , the target total attack angle is Direction and Angle.

[0051] By determining the real-time flight parameters of the rocket, it is possible to promptly determine whether the real-time flight parameters of the rocket need to be adjusted, thereby reducing the aerodynamic load on the rocket and completing the rocket deloading in real time.

[0052] It is understood that the control device can also achieve load reduction by adjusting the target total angle of attack. Since adjusting the target total angle of attack can achieve load reduction once, subsequently adjusting the target roll angle can achieve further load reduction, thus optimizing the load reduction method. Of course, the parameter value of the target total angle of attack after the reduction can be determined first. When the current roll angle is subsequently adjusted to the target roll angle, the parameter value of the target total angle of attack is adjusted to the parameter value of the previously determined target total angle of attack after the reduction. Of course, load reduction can also be achieved by adjusting the direction of movement.

[0053] Since changes in 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 in conjunction to further improve the load reduction effect.

[0054] Furthermore, when determining the target roll angle, if a preset flight parameter identical to the real-time flight parameter exists in the preset correspondence, the target roll angle corresponding to the preset flight parameter identical to the real-time flight parameter is determined as the target roll angle corresponding to the real-time flight parameter. Of course, due to insufficient simulation data, it is possible that in actual application, no preset flight parameter matching the real-time flight parameter exists, i.e., no preset flight parameter consistent with the real-time flight parameter exists. In this case, if no preset flight parameter identical to the real-time flight parameter exists in the preset 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 may be the numerical difference between the parameter value of the real-time flight parameter and the parameter value of the preset flight parameter.

[0055] Since the preset flight parameters include a preset movement speed and a preset total angle of attack, the control device can determine the preset flight parameter corresponding to at least one of the parameters in the preset corresponding relationship. That is, a preset movement speed equal to the current movement speed can be determined and / or a preset total angle of attack equal to the target total angle of attack can be determined. It is understood that, conversely, there are also situations where the preset flight parameters that are equal to the real-time flight parameters do not exist in the three preset corresponding relationships. That is, the corresponding relationship does not contain a preset total angle of attack equal to the target total angle of attack and / or the corresponding relationship does not contain a preset movement speed equal to the current movement speed.

[0056] For example, if only a preset total attack angle that is the same as the target total attack angle is determined, and there is no preset total attack angle target that is the same as the target total attack angle in the corresponding relationship, if the target total attack angle is 30.4°, preset total attack angle 1 is 30°, and preset total attack angle 2 is 35°, then the target total attack angle is closest to preset total attack angle 1, and the target roll angle corresponding to preset total attack angle 1 can be selected.

[0057] Taking the example of only determining the preset motion speed that is the same as the current motion speed, and there being no preset motion speed that is the same as the current motion speed in the corresponding relationship, if the preset motion speed is a range value, such as the preset motion speed 1 is 30~35km / s, the preset motion speed 2 is 40~45km / s, and the current motion speed is 43km / s, it falls within the range of the preset motion speed 2, and the target roll corresponding to the preset motion speed 2 can be selected.

[0058] For example, if there is no preset motion speed equal to the current motion speed, and no preset total angle of attack equal to the target total angle of attack, a 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 a first difference between the current motion speed and each preset motion speed, and a second difference between the target total angle of attack and each preset total angle of attack. For example, a first weight for the first difference and a second weight for the second difference can be obtained. Based on the first weight, the first difference, the second weight, and the second difference, a 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.

[0059] Continuing with the above example, the target roll angle with the smallest total difference is when the preset total attack angle 1 is 30° and the preset movement speed 2 is 40-45 km / s.

[0060] Selecting the target roll angle determined by the preset flight parameters with the smallest difference can also reduce the load on the rocket and optimize the load reduction effect.

[0061] In step S103, the load reduction control device can control the rocket's load reduction based solely on the target roll angle, or it can control the rocket's flight based on 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.

[0062] Furthermore, when determining the corresponding relationship, a three-dimensional mesh model of the rocket is constructed based on the surface structure of the rocket. Aerodynamic simulation tests are then conducted on the three-dimensional mesh model using each flight simulation parameter to obtain the aerodynamic loads on the rocket when each flight simulation parameter is used. The surface structure of the rocket includes a protruding structure.

[0063] Figures 4 to 7 A schematic diagram of the surface structure provided in an embodiment of the present application.

[0064] Figure 4 A schematic diagram of a fairing transverse explosive bolt is provided for an embodiment of the present application. Figure 5 A schematic diagram of a phased array antenna is provided for an embodiment of the present application. Figure 6 A schematic diagram of a secondary cable cover and a conduit cover is provided for an embodiment of the present application. Figure 7 A schematic diagram of a forward thrust rocket structure is provided for an embodiment of the present application.

[0065] Existing rocket deloading schemes fail to account for the varying loads experienced at different angles along the circumference of the rocket body due to wind conditions. In reality, rocket surfaces are typically equipped with a variety of protrusions of varying shapes and sizes, tailored to various functional needs. These protrusions include cable covers, duct covers, forward / reverse thruster fairings, explosive bolt housings, vent fairings, and docking frames. These distributed surface protrusions alter the flow characteristics of the smooth rocket body, causing complex localized loads and impacting the overall aerodynamic loads. This, in particular, results in uneven load distribution across the rocket body in varying wind directions, which can impact the rocket's safety performance.

[0066] In other words, the current rocket flight load reduction method does not take into account the normal overload caused by the protrusions on the rocket surface and the circumferential non-uniform distribution characteristics. In the total angle of attack and roll angle coordinate system, the incoming flow (the airflow relative to the rocket flow) may be located at a circumferential angle with a larger aerodynamic load, so the load reduction effect is not optimal.

[0067] In order to address the impact of the surface structure on the aerodynamic load and obtain a more accurate picture of the actual aerodynamic load on the rocket, the embodiment of the present application constructs a three-dimensional grid model of the rocket based on the surface structure of the rocket during simulation testing. Then, when the three-dimensional grid model is subsequently subjected to aerodynamic simulation testing, the aerodynamic load obtained is closer to the aerodynamic load actually experienced by the rocket, and the preset roll angle corresponding to the minimum aerodynamic load experienced by the rocket is obtained more accurately. In other words, based on the results of precise aerodynamic simulation of the rocket body surface structure, the embodiment of the present application determines the roll angle with the smallest load under different flight simulation parameters, and by actively rolling the rocket body posture, the aerodynamic load experienced by the rocket is kept to a minimum, thereby achieving the optimal load reduction effect.

[0068] Taking the server as the execution body for explanation, when constructing the three-dimensional grid model of the rocket, the surface structure of the rocket can also be screened, retaining only part of the surface structure, reducing the simulation test time and improving the efficiency of the simulation test.

[0069] Specifically, the rocket's surface structures are screened based on preset conditions to obtain target surface structures that meet the conditions. A three-dimensional mesh model of the rocket is constructed based on the target surface structures. The preset conditions include at least one of the following: a surface structure with a volume greater than a preset volume; a surface structure located in the rocket's arrowhead region; or a surface structure with a structural complexity that meets a preset complexity condition. The arrowhead region is defined as the area between the rocket's tip and the rocket's body, which is a preset distance and can be set as needed.

[0070] Generally speaking, the larger the volume of the surface structure, the greater the impact on the aerodynamic load. This is because the larger the volume, the larger the surface area may be, and more surface may be exposed to the incoming air, so the surface structure may bear a greater aerodynamic load.

[0071] Furthermore, the impact of surface structures on aerodynamic loads varies depending on where they are located. Generally, surface structures located in the arrowhead region have a greater impact on aerodynamic loads. This is because the arrowhead design is crucial for reducing air drag (a type of aerodynamic load) on the entire rocket. Generally speaking, a streamlined design can significantly reduce air drag, improving efficiency and performance. However, the presence of a raised structure in the arrowhead region disrupts the streamlined structure, potentially increasing the drag experienced by the rocket and affecting its overall performance. Therefore, it is necessary to preserve the surface structure located in the arrowhead region of this rocket.

[0072] Of course, the greater the structural complexity of a surface structure, the greater the impact of aerodynamic loads on the rocket. Structural complexity can be related to the surface structure's shape, and the specific structural complexity can be set as needed. For example, a surface structure can be divided into multiple regularly shaped structural blocks. The greater the number of structural blocks, the higher the structural complexity of the surface structure. The greater the variety of shapes of the structural blocks, the higher the structural complexity of the surface structure.

[0073] Structural complexity can be correlated with surface structure shape because objects of different shapes experience different aerodynamic forces at the same speed and atmospheric conditions. For example, a slender rocket will have a lower drag coefficient than a wide, flat design, as the former is closer to the ideal aerodynamic shape. Therefore, higher surface structure complexity increases the impact of aerodynamic loads on the rocket.

[0074] The embodiment of the present application provides a rocket load reduction control device, such as Figure 8 As shown, the rocket deload 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: Real-time flight parameter acquisition module 801, used to obtain the real-time flight parameters of the rocket; a target roll angle determination module 802, configured to determine a target roll angle corresponding to the real-time flight parameter based on a preset correspondence relationship, wherein the correspondence relationship includes a plurality of preset flight parameters and the target roll angle corresponding to each preset flight parameter; A control module 803 is configured to control the flight of the rocket according to a target roll angle corresponding to the real-time flight parameter; The target roll angle corresponding to each preset flight parameter in the corresponding relationship is obtained by the simulation test module 804 in the following manner: determining a plurality of flight simulation parameters, each of the flight simulation parameters comprising a preset flight parameter and a corresponding preset roll angle, and for each of the preset flight parameters, at least two flight simulation parameters include the preset flight parameter; Performing an aerodynamic simulation test on the rocket using each of the flight simulation parameters to obtain the aerodynamic load on the rocket when each of the flight simulation parameters is used; The preset roll angle in the target simulation parameter corresponding to each of the preset flight parameters is determined as the target roll angle corresponding to each of the preset flight parameters, and the target simulation parameter corresponding to each of the preset flight parameters is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters including the preset flight parameter.

[0075] Optionally, the simulation test module 804 may be used to construct a three-dimensional mesh model of the rocket based on the surface structure of the rocket; An aerodynamic simulation test is performed on the three-dimensional grid model using each of the flight simulation parameters to obtain the aerodynamic load on the rocket when each of the flight simulation parameters is used.

[0076] Optionally, the surface structure of the rocket includes a protruding structure; the simulation test module 804 may 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; constructing a three-dimensional grid model of the rocket according to the target surface structure; The preset conditions include at least one of the following: Surface structures with a volume larger than a preset volume; a surface structure located in the arrowhead region of the rocket; The surface structure whose structural complexity meets the preset complexity conditions.

[0077] Optionally, the preset flight parameters include a preset movement speed and a preset total angle of attack, and the real-time flight parameters include the current movement speed and target total angle of attack of the rocket; Among them, the target total angle of attack is obtained by the real-time flight parameter acquisition module 801 in the following manner: obtaining the current wind speed and the current movement speed of the rocket; and determining the target total angle of attack of the rocket based on the current wind speed and the current movement speed.

[0078] Optionally, the real-time flight parameter acquisition module 801 may be configured to determine a combined speed based on the current wind speed and the current movement speed; The target total angle of attack of the rocket is determined based on the resultant velocity.

[0079] Optionally, the control module 803 may be configured to control the flight of the rocket according to the target total angle of attack and the target roll angle.

[0080] Optionally, the target roll angle determining module 802 may be configured to, if a preset flight parameter identical to the real-time flight parameter exists in the preset correspondence, determine the target roll angle corresponding to the preset flight parameter identical to the real-time flight parameter as the target roll angle corresponding to the real-time flight parameter; If there is no preset flight parameter that is the same as the real-time flight parameter in the preset corresponding relationship, the target roll angle corresponding to the preset flight parameter that has the smallest difference from the real-time flight parameter in the corresponding relationship is determined as the target roll angle corresponding to the real-time flight parameter.

[0081] The devices of the embodiments of the present application can execute the methods provided in the embodiments of the present application, and their implementation principles are similar and have corresponding technical effects. The actions performed by each module in the devices of the embodiments of the present application correspond to the steps in the methods of the embodiments of the present application. For detailed functional descriptions of each module of the device, please refer to the descriptions of the corresponding methods shown above, and will not be repeated here.

[0082] An embodiment of the present application provides an electronic device, including a memory, a processor, and a computer program stored in the memory, and the processor executes the above computer program to implement the steps of the method provided in any optional embodiment of the present application.

[0083] In an alternative embodiment, an electronic device is provided, such as Figure 9 As shown, Figure 9 The electronic device 4000 shown 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 may be used for data exchange between the electronic device and other electronic devices, such as data transmission and / or data reception. It should be noted that in actual applications, the number of transceivers 4004 is not limited to one, and the structure of the electronic device 4000 does not constitute a limitation on the embodiments of the present application.

[0084] 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 device, transistor logic device, hardware component, or any combination thereof. It may implement or execute the various exemplary logic blocks, modules, and circuits described in conjunction with the present disclosure. Processor 4001 may also be a combination that implements computing functions, such as a combination of one or more microprocessors, or a combination of a DSP and a microprocessor.

[0085] Bus 4002 may include a path for transmitting information between the above components. Bus 4002 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus. Bus 4002 may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 9 Only one thick line is used in the diagram, but this does not mean that there is only one bus or one type of bus.

[0086] The memory 4003 may be a ROM (Read Only Memory) or other type of static storage device that can store static information and instructions, a RAM (Random Access Memory) or other type of dynamic storage device that can store information and instructions, or an EEPROM (Electrically Erasable Programmable Read Only Memory), a CD-ROM (Compact Disc Read Only Memory) or other optical disk storage, optical disk storage (including compact discs, laser discs, optical discs, digital versatile discs, Blu-ray discs, etc.), magnetic disk storage media, other magnetic storage devices, or any other medium that can be used to carry or store computer programs and can be read by a computer, without limitation herein.

[0087] The memory 4003 is used to store the computer program for executing the embodiments of the present disclosure, and the execution is controlled by the processor 4001. The processor 4001 is used to execute the computer program stored in the memory 4003 to implement the steps shown in the above method embodiments.

[0088] An embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, the steps and corresponding contents of the aforementioned method embodiment can be implemented.

[0089] An embodiment of the present application also provides a computer program product, including a computer program, which can implement the steps and corresponding contents of the aforementioned method embodiment when executed by a processor.

[0090] It should be understood that, although each operation step is indicated by arrows in the flowchart of the embodiment of the present application, the order of implementation of these steps is not limited to the order indicated by the arrows. Unless otherwise clearly stated herein, in some implementation scenarios of the embodiment of the present application, the implementation steps in each flowchart can be performed in other orders according to demand. In addition, some or all of the steps in each flowchart can include multiple sub-steps or multiple stages based on actual implementation scenarios. Some or all of these sub-steps or stages can be executed at the same time, and each sub-step or stage in these sub-steps or stages can also be executed at different times respectively. Under different scenarios at the execution time, the execution order of these sub-steps or stages can be flexibly configured according to demand, and the embodiment of the present application does not limit this.

[0091] The above description is only an optional implementation method for some implementation scenarios of the present disclosure. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the solution of the embodiments of the present application, other similar implementation methods based on the technical ideas of the present disclosure are also within the protection scope of the embodiments of the present application.

Claims

1. A rocket load reduction control method, characterized in that: include: Get the real-time flight parameters of the rocket; Determining a target roll angle corresponding to the real-time flight parameter according to a preset correspondence relationship, wherein the correspondence relationship includes a plurality of preset flight parameters and the target roll angle corresponding to each preset flight parameter; controlling the flight of the rocket according to a target roll angle corresponding to the real-time flight parameter; The target roll angle corresponding to each preset flight parameter in the corresponding relationship is obtained by: determining a plurality of flight simulation parameters, each of the flight simulation parameters comprising a preset flight parameter and a corresponding preset roll angle, and for each of the preset flight parameters, at least two flight simulation parameters include the preset flight parameter; Performing an aerodynamic simulation test on the rocket using each of the flight simulation parameters to obtain the aerodynamic load on the rocket when each of the flight simulation parameters is used; The preset roll angle in the target simulation parameter corresponding to each of the preset flight parameters is determined as the target roll angle corresponding to each of the preset flight parameters, and the target simulation parameter corresponding to each of the preset flight parameters is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters including the preset flight parameter.

2. The method according to claim 1, characterized in that The aerodynamic simulation test is performed on the rocket using each of the flight simulation parameters to obtain the aerodynamic load on the rocket when each of the flight simulation parameters is used, including: Constructing a three-dimensional grid model of the rocket according to the surface structure of the rocket; An aerodynamic simulation test is performed on the three-dimensional grid model using each of the flight simulation parameters to obtain the aerodynamic load on the rocket when each of the flight simulation parameters is used.

3. The method according to claim 2, characterized in that The surface structure of the rocket includes a raised structure; The step of constructing a three-dimensional grid model of the rocket according to the surface structure of the rocket comprises: Screening the surface structure of the rocket according to preset conditions to obtain a target surface structure that meets the preset conditions; constructing a three-dimensional grid model of the rocket according to the target surface structure; The preset conditions include at least one of the following: Surface structures with a volume larger than a preset volume; a surface structure located in the arrowhead region of the rocket; The surface structure whose structural complexity meets the preset complexity conditions.

4. The method according to claim 1, wherein The preset flight parameters include a preset movement speed and a preset total angle of attack, and the real-time flight parameters include the current movement speed and target total angle of attack of the rocket; The target total attack angle is obtained by: Obtain the current wind speed and the current moving speed of the rocket; The target total angle of attack of the rocket is determined according to the current wind speed and the current movement speed.

5. The method according to claim 4, characterized in that Determining the target total angle of attack of the rocket based on the current wind speed and the current motion speed includes: determining a combined speed according to the current wind speed and the current movement speed; The target total angle of attack of the rocket is determined based on the resultant velocity.

6. The method according to claim 5, characterized in that The step of controlling the rocket flight according to the target roll angle includes: The rocket is controlled to fly according to the target total angle of attack and the target roll angle.

7. The method according to any one of claims 1 to 4, characterized in that Determining the target roll angle corresponding to the real-time flight parameter according to the preset corresponding relationship includes: If there is a preset flight parameter that is the same as the real-time flight parameter in the preset corresponding relationship, determining the target roll angle corresponding to the preset flight parameter that is the same as the real-time flight parameter as the target roll angle corresponding to the real-time flight parameter; If there is no preset flight parameter that is the same as the real-time flight parameter in the preset corresponding relationship, the target roll angle corresponding to the preset flight parameter that has the smallest difference from the real-time flight parameter in the corresponding relationship is determined as the target roll angle corresponding to the real-time flight parameter.

8. A rocket load reduction control device, characterized in that: include: Real-time flight parameter acquisition module, used to obtain the real-time flight parameters of the rocket; a target roll angle determination module, configured to determine a target roll angle corresponding to the real-time flight parameter based on a preset correspondence relationship, wherein the correspondence relationship includes a plurality of preset flight parameters and the target roll angle corresponding to each preset flight parameter; a control module, configured to control the flight of the rocket according to a target roll angle corresponding to the real-time flight parameter; The target roll angle corresponding to each preset flight parameter in the corresponding relationship is obtained by the simulation test module in the following manner: determining a plurality of flight simulation parameters, each of the flight simulation parameters comprising a preset flight parameter and a corresponding preset roll angle, and for each of the preset flight parameters, at least two flight simulation parameters include the preset flight parameter; Performing an aerodynamic simulation test on the rocket using each of the flight simulation parameters to obtain the aerodynamic load on the rocket when each of the flight simulation parameters is used; The preset roll angle in the target simulation parameter corresponding to each of the preset flight parameters is determined as the target roll angle corresponding to each of the preset flight parameters, and the target simulation parameter corresponding to each of the preset flight parameters is: the flight simulation parameter corresponding to the minimum aerodynamic load in the flight simulation parameters including the preset flight parameter.

9. 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 7.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 7 are implemented.

11. A computer program product comprising a computer program, characterized in that When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 7 are implemented.

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