Method for identifying aerodynamic parameters of first-level flight section of carrier rocket and related equipment

Abstract

The invention discloses a carrier rocket first-level flight section aerodynamic parameter identification method and related equipment, and relates to the field of carrier rockets, and the method comprises the steps: calculating an attack angle and a sideslip angle of a rocket first-level flight section according to actually measured wind field data and flight telemetry data of the launching day; obtaining angular acceleration information according to angular velocity information in the flight telemetry data; calculating the resultant moment information of the rocket body according to the angular acceleration information and the rotational inertia of the rocket body; according to the rocket body resultant moment information, the dynamic pressure information and the rocket body size information, rocket body moment coefficient information is calculated, and the rocket body size information comprises rocket body reference area information and rocket body length information; reverse interpolation operation is carried out according to known aerodynamic parameters and the aerodynamic torque coefficient to obtain rudder deflection control quantities, the known aerodynamic parameters comprise the attack angle, the sideslip angle and the Mach number, and the rudder deflection control quantities comprise the pitching rudder deflection control quantity, the yawing rudder deflection control quantity and the rolling rudder deflection control quantity; and comparing the rudder deviation control quantity with the rudder deviation during actual flight to judge aerodynamic parameters.

Description

Technical Field

[0001] The present specification relates to the field of launch vehicles, and more specifically, the present application relates to a method for identifying aerodynamic parameters of a first-stage flight segment of a launch vehicle and related equipment. Background Art

[0002] When a launch vehicle accelerates through the atmosphere in the active phase, the aerodynamic force and aerodynamic torque generated by the airflow on the rocket body have a great impact on the stability of the launch vehicle flight. During the flight, the rocket body needs to withstand large axial and lateral overloads, dynamic pressure, and thermal environment, which puts forward requirements for the rocket body structure. The aerodynamic characteristics of the rocket determine the ballistic shape and related motion parameters of the active phase flight, and these motion parameters serve as inputs to the rocket flight control system and affect the design of the flight control system; dynamic pressure and overload serve as inputs to the design of the rocket body structure system and affect the design of the rocket body structure. Therefore, the accuracy of the rocket's aerodynamic parameters plays a key role in the rocket's flight in the atmosphere. Summary of the invention

[0003] A series of simplified concepts are introduced in the Summary of the Invention section, which will be further described in detail in the Detailed Description of the Invention section. The Summary of the Invention section of this application does not mean to attempt to define the key features and essential technical features of the claimed technical solution, nor does it mean to attempt to determine the scope of protection of the claimed technical solution.

[0004] In the first aspect, the present application proposes a method for identifying aerodynamic parameters of a first-stage flight stage of a launch vehicle, the method comprising:

[0005] Calculate the angle of attack and sideslip of the first stage of the rocket flight based on the measured wind field data and flight telemetry data on the launch day;

[0006] Obtaining angular acceleration information according to the angular velocity information in the flight telemetry data;

[0007] Calculate the arrow body torque information based on the above angular acceleration information and the arrow body moment of inertia;

[0008] Calculating the arrow body moment coefficient information according to the arrow body resultant moment information, dynamic pressure information and arrow body size information, wherein the arrow body size information includes arrow body reference area information and arrow body length information;

[0009] Performing a reverse interpolation operation according to known aerodynamic parameters and the aerodynamic torque coefficient to obtain a rudder control amount, wherein the known aerodynamic parameters include the angle of attack, the sideslip angle and the Mach number, and the rudder control amount includes a pitch rudder control amount, a yaw rudder control amount and a roll rudder control amount;

[0010] The aerodynamic parameters are judged based on the comparison between the above rudder deflection control amount and the rudder deflection during actual flight.

[0011] In a feasible implementation manner, the above method further includes:

[0012] When the rudder deflection control amount and the rudder deflection during actual flight exceed a preset threshold, determining a moment coefficient correction amount based on the rudder deflection and the moment coefficient correction coefficient of the rudder deflection control amount and the rudder deflection during actual flight;

[0013] The aerodynamic moment coefficient is corrected based on the moment coefficient correction amount so that the rudder deviation of the rudder control amount and the rudder deviation during actual flight is reduced to within the preset threshold value.

[0014] In a feasible implementation manner, the above-mentioned calculation of the angle of attack and sideslip angle of the first stage of the rocket flight segment based on the measured wind field data and flight telemetry data on the launch day includes:

[0015] Calculate the relative speed of the rocket body relative to the airflow based on the measured wind field data and flight telemetry data on the launch day;

[0016] According to the above relative speed of the rocket body relative to the airflow and the conversion matrix from the launch system to the rocket body, determine the component of the speed of the rocket relative to the airflow in the rocket system;

[0017] The above-mentioned angle of attack and sideslip angle are calculated based on the component of the velocity of the above-mentioned rocket relative to the airflow in the arrow system.

[0018] In a feasible implementation manner, the angle of attack and the sideslip angle are calculated according to the component of the velocity of the rocket relative to the airflow in the arrow system, including:

[0019] Calculate the angle of attack based on the x- and y-direction components of the velocity of the rocket relative to the airflow in the arrow system;

[0020] The sideslip angle is calculated based on the components of the rocket's velocity relative to the airflow in the x, y and z directions under the arrow system.

[0021] In a feasible implementation manner, the step of obtaining angular acceleration information according to the angular velocity information in the flight telemetry data includes:

[0022] Using a preset filter to filter the angular velocity information output by the inertial group in the flight telemetry data to obtain filtered angular velocity information, wherein the filtered angular velocity information includes filtered rolling angular velocity information, filtered yaw angular velocity information and filtered pitch angular velocity information;

[0023] The filtered angular velocity information is derivatized to obtain angular acceleration information.

[0024] In a feasible implementation manner, the preset filter includes a Chebyshev low-pass filter.

[0025] In a feasible implementation manner, the arrow body moment coefficient information includes first moment information, second moment information and third moment information, the first moment information is x-direction moment information, the second moment information is y-direction moment information, the third moment information is z-direction moment information, and the arrow body size information;

[0026] The calculation of the arrow body moment coefficient information based on the arrow body combined moment information, dynamic pressure information and arrow body size information includes:

[0027] The moment components in three directions according to the above information of the total moment of the rocket body;

[0028] The first moment information, the second moment information and the third moment information are calculated respectively according to the moment components in the three directions, the dynamic pressure information, the arrow body reference area information and the arrow body length information.

[0029] In a second aspect, the present application embodiment provides an aerodynamic parameter identification device for a first-stage flight stage of a launch vehicle, comprising:

[0030] The first calculation unit is used to calculate the angle of attack and sideslip angle of the first stage of the rocket according to the measured wind field data and flight telemetry data on the launch day;

[0031] A first acquisition unit, used to acquire angular acceleration information according to the angular velocity information in the flight telemetry data;

[0032] A second calculation unit is used to calculate the arrow body torque information according to the angular acceleration information and the arrow body moment of inertia;

[0033] a third calculation unit, configured to calculate the arrow body moment coefficient information according to the arrow body resultant moment information, the dynamic pressure information and the arrow body size information, wherein the arrow body size information includes the arrow body reference area information and the arrow body length information;

[0034] a second acquisition unit, configured to perform a reverse interpolation operation according to known aerodynamic parameters and the aerodynamic torque coefficient to acquire a rudder deflection control amount, wherein the known aerodynamic parameters include the angle of attack, the sideslip angle, and the Mach number, and the rudder deflection control amount includes a pitch rudder deflection control amount, a yaw rudder deflection control amount, and a roll rudder deflection control amount;

[0035] The judging unit is used to compare the rudder deflection control amount with the rudder deflection during actual flight to judge the aerodynamic parameters.

[0036] In a third aspect, an electronic device comprises: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor is used to implement the steps of the method for identifying aerodynamic parameters of the first-stage flight segment of a launch vehicle as described in any one of the first aspects above when executing the computer program stored in the memory.

[0037] In a fourth aspect, the present application further proposes a computer-readable storage medium having a computer program stored thereon, and when the computer program is executed by a processor, the method for identifying aerodynamic parameters of the first-stage flight segment of a launch vehicle of any one of the first aspects is implemented.

[0038] In summary, the method for identifying aerodynamic parameters of the first-stage flight segment of a carrier rocket of an embodiment of the present application includes: calculating the angle of attack and sideslip angle of the first-stage flight segment of the rocket according to the measured wind field data and flight telemetry data on the day of launch; obtaining angular acceleration information according to the angular velocity information in the above-mentioned flight telemetry data; calculating the rocket body resultant torque information according to the above-mentioned angular acceleration information and the rocket body moment of inertia; calculating the rocket body torque coefficient information according to the above-mentioned rocket body resultant torque information, dynamic pressure information and rocket body size information, wherein the above-mentioned rocket body size information includes rocket body reference area information and rocket body length information; performing reverse interpolation operation according to known aerodynamic parameters and the above-mentioned aerodynamic torque coefficient to obtain the rudder deflection control amount, wherein the above-mentioned known aerodynamic parameters include the above-mentioned angle of attack, the above-mentioned sideslip angle and Mach number, and the above-mentioned rudder deflection control amount includes the pitch rudder deflection control amount, the yaw rudder deflection control amount and the roll rudder deflection control amount; comparing the above-mentioned rudder deflection control amount with the rudder deflection during actual flight to judge the aerodynamic parameters. The present invention discloses a method for identifying aerodynamic parameters of a first-stage flight segment of a carrier rocket. The method calculates the angle of attack and sideslip angle of the first-stage flight segment of the rocket according to the measured wind field data and flight telemetry data on the day of launch; the angular velocity information of the rocket body output by the inertial group in the telemetry data is filtered and then differentiated to calculate the angular acceleration of the rocket body; the torque coefficient of the rocket body is calculated according to the angular acceleration, moment of inertia, dynamic pressure, etc. of the rocket body; finally, the reverse interpolation is performed according to the known aerodynamic parameters to obtain the identified rudder deflection angle, which is compared with the actual rudder deflection angle transmitted by telemetry, and the accuracy of the aerodynamic parameters is judged. For the flight feature points with large deviations, the corresponding aerodynamic parameter points are adjusted and corrected until the identified rudder deflection angle is consistent with the actual rudder deflection angle, and accurate aerodynamic parameters can be obtained. Finally, the flight stability and reliability of the carrier rocket are improved through iterative design. The present invention discloses a method for identifying aerodynamic parameters of a first-stage flight segment of a carrier rocket. The method is simple and easy to implement, and has high engineering application value. The aerodynamic parameter identification method of the first-stage flight segment of a launch vehicle proposed in this application, and other advantages, objectives and features of this application will be partially reflected through the following description, and will also be partially understood by technical personnel in this field through research and practice of this application. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present specification. Also, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0040] Figure 1 A schematic diagram of the process of identifying aerodynamic parameters of a first-stage flight stage of a launch vehicle provided in an embodiment of the present application;

[0041] Figure 2 A structural schematic diagram of an aerodynamic parameter identification device for the first stage flight of a launch vehicle provided in an embodiment of the present application;

[0042] Figure 3 A schematic diagram of the structure of an electronic device for identifying aerodynamic parameters of the first-stage flight stage of a launch vehicle provided in an embodiment of the present application. DETAILED DESCRIPTION

[0043] The terms "first", "second", "third", "fourth", etc. (if any) in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments described herein can be implemented in an order other than that illustrated or described herein. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices. The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments.

[0044] See also Figure 1 , which is a flow chart of a method for identifying aerodynamic parameters of a first-stage flight stage of a launch vehicle provided in an embodiment of the present application, which may specifically include:

[0045] S110, calculating the angle of attack and sideslip angle of the first stage of the rocket flight according to the measured wind field data and flight telemetry data on the launch day;

[0046] For example, the angle of attack (AoA) refers to the angle between the rocket's forward direction and its body axis, which affects the rocket's lift and drag.

[0047] The sideslip angle is the angle between the axis of the rocket body in the horizontal plane and its actual flight direction, which reflects the lateral stability of the rocket.

[0048] Calculating these two angles using the measured wind field data on the launch day and flight telemetry data (including speed and direction) can help evaluate the rocket's aerodynamic performance and flight efficiency.

[0049] S120, acquiring angular acceleration information according to the angular velocity information in the flight telemetry data;

[0050] For example, the angular acceleration information is calculated by the rate of change of the angular velocity information (the rotation speed of the rocket around each axis) in the flight telemetry data. Angular acceleration is the rate of change of angular velocity, which is important for understanding the rotational dynamics of the rocket and the response of the control system.

[0051] S130, calculating the arrow body combined torque information according to the angular acceleration information and the arrow body moment of inertia;

[0052] For example, the total torque of the rocket body refers to the product of the distance from each torque point to the rotation center and the force, which reflects the rotation effect of the torque on the rocket body. The total torque can be calculated through angular acceleration information and the moment of inertia of the rocket body (the inertia of the object to rotation), which is crucial to understanding the rotational stability and control efficiency of the rocket.

[0053] S140, calculating the arrow body moment coefficient information according to the arrow body resultant moment information, dynamic pressure information and arrow body size information, wherein the arrow body size information includes arrow body reference area information and arrow body length information;

[0054] For example, the moment coefficient is an important aerodynamic parameter that reflects the normalized value of the moment relative to the dynamic pressure, reference area and rocket body length. The dynamic pressure is a parameter that is proportional to the square of the flight speed, and the reference area and rocket body length are the geometric characteristics of the rocket. With this information, the moment coefficient can be calculated to better understand the aerodynamic characteristics of the rocket.

[0055] S150, performing a reverse interpolation operation according to known aerodynamic parameters and the aerodynamic torque coefficient to obtain a rudder control amount, wherein the known aerodynamic parameters include the angle of attack, the sideslip angle and the Mach number, and the rudder control amount includes a pitch rudder control amount, a yaw rudder control amount and a roll rudder control amount;

[0056] Exemplarily, a reverse interpolation operation is performed through known aerodynamic parameters (angle of attack, sideslip angle and Mach number) and aerodynamic moment coefficients to obtain the rudder control amount, including the control amount of the pitch rudder, yaw rudder and roll rudder. The rudder control amount refers to the rudder angle that needs to be applied to achieve the expected flight attitude.

[0057] The specific formula can be obtained as follows:

[0058] Given the angle of attack, sideslip angle, and Mach number, according to the known aerodynamic parameters, there is a one-to-one mapping relationship between the rudder deflection angle and the aerodynamic torque coefficient. According to the torque coefficient, the pitch, yaw, and roll rudder deflection control values ​​can be obtained by reverse interpolation:

[0059] δ ′ p =fδ p (Ma,Cm,α,β)

[0060] δ′ y =fδ y (Ma,Cn,α,β)

[0061] δ′ r =fδ r (Ma,Cl,α,β)

[0062] Where: δ′ p is the identified pitch rudder control value, δ′ y is the identified yaw rudder control value, δ′ r is the identified roll rudder control quantity, Cl is the roll moment coefficient, Cn is the yaw moment coefficient, Cm is the pitch moment coefficient; α is the attack angle and β is the sideslip angle; Ma is the Mach number, fδ p is the mapping relationship between the pitch rudder control amount and related parameters, fδ y is the mapping relationship between the yaw rudder control amount and related parameters, fδ r It is the mapping relationship between the roll rudder control amount and related parameters.

[0063] S160: Compare the rudder deflection control amount with the rudder deflection during actual flight to judge the aerodynamic parameters.

[0064] For example, by comparing the actual rudder deflection in flight with the calculated rudder deflection control amount, the accuracy of aerodynamic parameters and the effectiveness of control strategies can be judged. Identifying and correcting rocket aerodynamic parameters through flight test data can improve the accuracy of rocket aerodynamic parameters, which is conducive to improving the flight stability and reliability of launch vehicles.

[0065] In summary, the present disclosure provides a method for identifying aerodynamic parameters of the first stage of a launch vehicle. The method calculates the angle of attack and sideslip angle of the first stage of the rocket according to the measured wind field data and flight telemetry data on the day of launch; the angular velocity information of the rocket body output by the inertial group in the telemetry data is filtered and then differentiated to calculate the angular acceleration of the rocket body; the torque coefficient of the rocket body is calculated according to the angular acceleration, moment of inertia, dynamic pressure, etc. of the rocket body; finally, the reverse interpolation is performed according to the known aerodynamic parameters to obtain the identified rudder deflection angle, which is compared with the actual rudder deflection angle transmitted by telemetry, and the accuracy of the aerodynamic parameters is judged. For the flight feature points with large deviations, the corresponding aerodynamic parameter points are adjusted and corrected until the identified rudder deflection angle is consistent with the actual rudder deflection angle, and accurate aerodynamic parameters can be obtained. Finally, the flight stability and reliability of the launch vehicle are improved through iterative design. The present disclosure proposes a method for identifying aerodynamic parameters of the first stage of a launch vehicle. The method is simple and easy to implement, and has high engineering application value.

[0066] In a feasible implementation manner, the above method further includes:

[0067] When the rudder deflection control amount and the rudder deflection during actual flight exceed a preset threshold, determining a moment coefficient correction amount based on the rudder deflection and the moment coefficient correction coefficient of the rudder deflection control amount and the rudder deflection during actual flight;

[0068] The aerodynamic moment coefficient is corrected based on the moment coefficient correction amount so that the rudder deviation of the rudder control amount and the rudder deviation during actual flight is reduced to within the preset threshold value.

[0069] For example, the preset threshold is a pre-set standard for judging whether the deviation between the rudder control amount and the rudder in actual flight is within an acceptable range. If the deviation exceeds the preset threshold, it means that the aerodynamic moment coefficient needs to be adjusted to correct the deviation.

[0070] When the deviation between the rudder control value and the actual rudder deviation exceeds the preset threshold, a torque coefficient correction value needs to be calculated. This correction value is calculated based on the rudder deviation, that is, the difference between the control value and the actual value, and the torque coefficient correction factor, that is, an adjustment factor based on experience or testing.

[0071] According to the calculated moment coefficient correction, the existing aerodynamic moment coefficient is corrected and the aerodynamic model of the rocket is adjusted to make it more suitable for actual flight conditions, thereby ensuring the accuracy of the rudder control amount.

[0072] Specifically, it can be corrected by the following formula:

[0073] ΔCm=K p (δ p -δ′ p )

[0074] ΔCn=K y (δ y -δ′ y )

[0075] ΔCl=K r (δ r -δ′ r )

[0076] Where: p is the actual pitch rudder control value, δ y is the actual yaw rudder control value, δ r is the actual roll rudder control value, K p ,K y ,K r are the pitch, yaw and roll moment coefficient correction coefficients, which are selected based on experience; ΔCm, ΔCn, ΔCl are the pitch, yaw and roll moment coefficient correction values.

[0077] Through the above correction operations, the goal is to reduce the deviation between the rudder control amount and the actual rudder deviation in flight to within the preset threshold. This process may need to be iterative, through continuous adjustment and comparison until the target deviation range is reached, thereby ensuring the stability of the rocket flight and the accuracy of control. Identifying and correcting the rocket's aerodynamic parameters through flight test data and improving the accuracy of the rocket's aerodynamic parameters will help improve the flight stability and reliability of the launch vehicle.

[0078] In a feasible implementation manner, the above-mentioned calculation of the angle of attack and sideslip angle of the first stage of the rocket flight segment based on the measured wind field data and flight telemetry data on the launch day includes:

[0079] Calculate the relative speed of the rocket body relative to the airflow based on the measured wind field data and flight telemetry data on the launch day;

[0080] According to the above relative speed of the rocket body relative to the airflow and the conversion matrix from the launch system to the rocket body, determine the component of the speed of the rocket relative to the airflow in the rocket system;

[0081] The above-mentioned angle of attack and sideslip angle are calculated based on the component of the velocity of the above-mentioned rocket relative to the airflow in the arrow system.

[0082] For example, first, it is necessary to collect the measured wind field data on the day of launch, which provides information on wind speed and direction in the rocket launch environment. At the same time, using flight telemetry data, the real-time position, speed and other information of the rocket can be obtained.

[0083] The relative speed of the rocket body to the airflow is calculated by the vector difference between the actual speed of the rocket and the surrounding wind speed. This relative speed is the basis for further analysis because it directly affects the aerodynamic force faced by the rocket.

[0084] The motion of a rocket can be described in different reference frames. The launch frame is usually a fixed reference frame based on the ground, while the arrow frame is a reference frame that moves with the rocket itself. The velocity of the rocket relative to the ground can be converted to its component in the arrow frame by using the transformation matrix from the launch frame to the arrow frame.

[0085] Finally, using the component of the rocket's relative airflow velocity in the arrow system obtained in the above steps, the rocket's angle of attack and sideslip angle can be calculated.

[0086] It should be noted that the relative speed of the arrow body relative to the airflow can be calculated by the following formula:

[0087] V xd =V fs +v_wind

[0088]

[0089] Where: V fs is the velocity vector of the rocket body in the launch system, is the conversion matrix from the launch system to the arrow system, v_wind is the wind speed vector in the launch system;

[0090] In a feasible implementation manner, the angle of attack and the sideslip angle are calculated according to the component of the velocity of the rocket relative to the airflow in the arrow system, including:

[0091] Calculate the angle of attack based on the x- and y-direction components of the velocity of the rocket relative to the airflow in the arrow system;

[0092] The sideslip angle is calculated based on the components of the rocket's velocity relative to the airflow in the x, y and z directions under the arrow system.

[0093] Exemplarily, an arrow system is usually defined as follows: the x-axis points in the direction of the rocket's forward motion, the y-axis is usually horizontal and perpendicular to the x-axis, pointing to the right side of the rocket, and the z-axis is perpendicular to the xy plane and usually points upward.

[0094] The attack angle α and sideslip angle β of the first stage of the rocket flight can be calculated by the following formula:

[0095] α=-arctan(v bxdy / v bxdx )

[0096]

[0097] V bxd is the velocity of the rocket relative to the airflow in the arrow system

[0098] In a feasible implementation manner, the step of obtaining angular acceleration information according to the angular velocity information in the flight telemetry data includes:

[0099] Using a preset filter to filter the angular velocity information output by the inertial group in the flight telemetry data to obtain filtered angular velocity information, wherein the filtered angular velocity information includes filtered rolling angular velocity information, filtered yaw angular velocity information and filtered pitch angular velocity information;

[0100] The filtered angular velocity information is derivatized to obtain angular acceleration information.

[0101] For example, the purpose of the filtering operation is to remove noise from the angular velocity information output by the inertial measurement unit (IMU), or "inertial group", to obtain smoother and more reliable data. In actual flight, due to various environmental factors and the characteristics of the equipment itself, the original telemetry data often contains a certain amount of noise.

[0102] The preset filter can be any effective digital or analog filter, such as a low-pass filter, a Kalman filter, etc., which is used to filter out high-frequency noise and retain useful signals.

[0103] The filtered angular velocity information includes three main rotation axes - roll, yaw and pitch. The angular velocity of each axis describes the rotation speed of the rocket around that axis and is the key data for rocket attitude analysis.

[0104] The derivative operation refers to calculating the rate of change of the filtered angular velocity over time, i.e., angular acceleration. Angular acceleration is a physical quantity that describes the dynamic changes in the rotation of the rocket. It shows how the rotation speed of the rocket on each rotation axis speeds up or slows down over time. Angular acceleration information, including roll angular acceleration, yaw angular acceleration, and pitch angular acceleration, provides real-time feedback to the rocket control system to help optimize the rocket's flight attitude and trajectory.

[0105] Specifically, the filtered angular velocity is differentiated to obtain the angular acceleration;

[0106] ω lb =G lb ·ω

[0107]

[0108] Where: ω is the angular velocity output by the inertial group, G lb is a low-pass filter, ω lb is the angular velocity after filtering, ΔT is the time interval between two adjacent data beats;

[0109] In a feasible implementation manner, the preset filter includes a Chebyshev low-pass filter.

[0110] For example, the Chebyshev filter pays special attention to the transition characteristics between the passband and the stopband, and achieves a steeper transition slope by allowing certain fluctuations in the passband or the stopband. This characteristic makes the Chebyshev filter particularly effective in filtering out high-frequency noise while retaining the main part of the signal.

[0111] A low-pass filter is a filter that allows signals below a certain cutoff frequency to pass through, but blocks signals above this frequency from passing through. When processing angular velocity signals, a low-pass filter can effectively remove noise components caused by vibration, electrical noise or other high-frequency disturbances.

[0112] In the processing of rocket flight telemetry data, the quality of angular velocity signals can be optimized by using a Chebyshev low-pass filter. By setting a suitable cutoff frequency, the Chebyshev filter can effectively filter out unwanted high-frequency noise while retaining important information about the rocket's rotational dynamics as much as possible. The processed angular velocity information, namely the filtered roll angular velocity, yaw angular velocity, and pitch angular velocity, will be smoother and more accurate, providing a more reliable basis for calculating angular acceleration.

[0113] In a feasible implementation manner, the arrow body moment coefficient information includes first moment information, second moment information and third moment information, the first moment information is x-direction moment information, the second moment information is y-direction moment information, the third moment information is z-direction moment information, and the arrow body size information;

[0114] The calculation of the arrow body moment coefficient information based on the arrow body combined moment information, dynamic pressure information and arrow body size information includes:

[0115] The moment components in three directions according to the above information of the total moment of the rocket body;

[0116] The first moment information, the second moment information and the third moment information are calculated respectively according to the moment components in the three directions, the dynamic pressure information, the arrow body reference area information and the arrow body length information.

[0117] For example, first, it is necessary to determine the components of the rocket body torque information in three directions, including the torque components around the x, y, and z axes, which correspond to the tendency of the rocket to rotate around these three axes.

[0118] Dynamic pressure is generated by the motion of the rocket relative to the airflow, and its value depends on the square of the rocket's velocity and the air density. The rocket body reference area usually refers to the area of ​​the rocket's cross section, while the rocket body length is the long dimension of the rocket. These two parameters are the basic reference quantities for calculating the torque coefficient.

[0119] For each direction (x, y, z), the moment coefficient is calculated based on the moment component in the corresponding direction, the dynamic pressure, the reference area of ​​the rocket body, and the length of the rocket body. In this way, the first moment coefficient (x direction, which may represent the pitch moment coefficient), the second moment coefficient (y direction, which may represent the yaw moment coefficient), and the third moment coefficient (z direction, which may represent the roll moment coefficient) can be obtained.

[0120] The specific can be determined by the following formula:

[0121] According to the angular acceleration and moment of inertia of the arrow body, calculate the resultant torque on the arrow body:

[0122]

[0123] Where: J is the moment of inertia of the arrow body. The moment coefficient of the arrow body is calculated by the moment of force on the arrow body:

[0124]

[0125] Where: q is the dynamic pressure, s is the reference area of ​​the arrow body, l is the length of the arrow body, Cl is the rolling moment coefficient, Cn is the yaw moment coefficient, and Cm is the pitch moment coefficient.

[0126] See also Figure 2 , a structural schematic diagram of an aerodynamic parameter identification device for a first-stage flight segment of a launch vehicle provided in an embodiment of the present application may include:

[0127] The first calculation unit 21 is used to calculate the angle of attack and sideslip angle of the first stage of the rocket flight according to the measured wind field data and flight telemetry data on the launch day;

[0128] A first acquisition unit 22 is used to acquire angular acceleration information according to the angular velocity information in the flight telemetry data;

[0129] A second calculation unit 23 is used to calculate the arrow body torque information according to the above angular acceleration information and the arrow body moment of inertia;

[0130] The third calculation unit 24 is used to calculate the arrow body moment coefficient information according to the arrow body resultant moment information, the dynamic pressure information and the arrow body size information, wherein the arrow body size information includes the arrow body reference area information and the arrow body length information;

[0131] a second acquisition unit 25, configured to perform a reverse interpolation operation according to known aerodynamic parameters and the aerodynamic torque coefficient to obtain a rudder deflection control amount, wherein the known aerodynamic parameters include the angle of attack, the sideslip angle and the Mach number, and the rudder deflection control amount includes a pitch rudder deflection control amount, a yaw rudder deflection control amount and a roll rudder deflection control amount;

[0132] The judging unit 26 is used to compare the rudder deflection control amount with the rudder deflection during actual flight to judge the aerodynamic parameters.

[0133] like Figure 3 As shown, an embodiment of the present application also provides an electronic device 300, including a memory 310, a processor 320, and a computer program 311 stored in the memory 310 and executable on the processor. When the processor 320 executes the computer program 311, the steps of any method for identifying the aerodynamic parameters of the first-stage flight segment of the launch vehicle are implemented.

[0134] Since the electronic device introduced in this embodiment is a device used to implement a device for identifying aerodynamic parameters of the first-stage flight segment of a carrier rocket in the embodiment of the present application, based on the method introduced in the embodiment of the present application, technical personnel in this field can understand the specific implementation mode of the electronic device of this embodiment and its various variations. Therefore, how the electronic device implements the method in the embodiment of the present application will not be described in detail here. As long as the equipment used by technical personnel in this field to implement the method in the embodiment of the present application falls within the scope of protection of this application.

[0135] In the specific implementation process, when the computer program 311 is executed by the processor, it can achieve Figure 1 Any implementation manner in the corresponding embodiments.

[0136] It should be noted that in the above embodiments, the description of each embodiment has its own emphasis, and for parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0137] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment in combination with software and hardware. Moreover, the present application may adopt the form of a computer program product implemented in one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that include computer-usable program code.

[0138] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded computer, or other programmable data processing device to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1A process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0139] These computer program instructions may also be stored in a computer-readable memory capable of directing a computer or other programmable data processing device to operate in a specific manner, so that the instructions stored in the computer-readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0140] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0141] An embodiment of the present application also provides a computer program product, which includes computer software instructions. When the computer software instructions are executed on a processing device, the processing device executes the process of identifying the aerodynamic parameters of the first-stage flight segment of a launch vehicle in the corresponding embodiment.

[0142] The computer program product includes one or more computer instructions. When the computer program instructions are loaded and executed on the computer, the process or function according to the embodiment of the present application is generated in whole or in part. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable devices. The computer instructions can be stored in a computer-readable storage medium, or transmitted from one computer-readable storage medium to another computer-readable storage medium. For example, the computer instructions can be transmitted from a website site, a computer, a server or a data center by wired (e.g., coaxial cable, optical fiber, digital subscriber line (digital subscriber line, DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) mode to another website site, computer, server or data center. The computer-readable storage medium can be any available medium that a computer can store or a data storage device such as a server or a data center that includes one or more available media integration. The available medium can be a magnetic medium, (e.g., a floppy disk, a hard disk, a tape), an optical medium (e.g., a DVD), or a semiconductor medium (e.g., a solid state drive (SSD)), etc.

[0143] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working processes of the systems, devices and units described above can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0144] In the several embodiments provided in the present application, it should be understood that the disclosed systems, devices and methods can be implemented in other ways. For example, the device embodiments described above are only schematic. For example, the division of units is only a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be an indirect coupling or communication connection through some interfaces, devices or units, which can be electrical, mechanical or other forms.

[0145] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0146] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0147] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present application is essentially or the part that contributes to the prior art or all or part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions to enable a computer device (which can be a personal computer, server, or network device, etc.) to perform all or part of the steps of the various embodiments of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (Read-Only Memory, ROM), random access memory (Random Access Memory, RAM), disk or optical disk and other media that can store program codes.

[0148] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some of the technical features therein by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A method for identifying aerodynamic parameters of a launch vehicle's first stage flight segment, characterized in that: include: Calculate the angle of attack and sideslip of the first stage of the rocket flight based on the measured wind field data and flight telemetry data on the launch day; Acquiring angular acceleration information according to the angular velocity information in the flight telemetry data; Calculating the arrow body resultant torque information according to the angular acceleration information and the arrow body moment of inertia; Calculating the arrow body moment coefficient information according to the arrow body resultant moment information, the dynamic pressure information and the arrow body size information, wherein the arrow body size information includes the arrow body reference area information and the arrow body length information; Performing a reverse interpolation operation according to known aerodynamic parameters and the aerodynamic moment coefficient to obtain a rudder deflection control amount, wherein the known aerodynamic parameters include the angle of attack, the sideslip angle and the Mach number, and the rudder deflection control amount includes a pitch rudder deflection control amount, a yaw rudder deflection control amount and a roll rudder deflection control amount; The aerodynamic parameters are judged based on the comparison between the rudder deflection control amount and the rudder deflection during actual flight.

2. The method for identifying aerodynamic parameters of a first stage flight segment of a launch vehicle according to claim 1, characterized in that: Also includes: When the rudder deflection control amount and the rudder deflection during actual flight exceed a preset threshold, determining a moment coefficient correction amount based on the rudder deflection and the moment coefficient correction coefficient of the rudder deflection control amount and the rudder deflection during actual flight; The aerodynamic moment coefficient is corrected based on the moment coefficient correction amount so that the rudder deviation of the rudder control amount and the rudder deviation during actual flight is reduced to within the preset threshold value.

3. The method for identifying aerodynamic parameters of a first stage flight segment of a launch vehicle according to claim 1, characterized in that: The method of calculating the angle of attack and sideslip angle of the first stage of the rocket flight according to the measured wind field data and flight telemetry data on the launch day includes: Calculating the relative speed of the rocket body relative to the airflow based on the measured wind field data and flight telemetry data on the launch day; Determine the component of the velocity of the rocket relative to the airflow in the arrow system according to the relative velocity of the rocket body relative to the airflow and the conversion matrix from the launch system to the rocket body; The angle of attack and the sideslip angle are calculated based on the component of the velocity of the rocket relative to the airflow in the arrow system.

4. The method for identifying aerodynamic parameters of a first stage flight segment of a launch vehicle according to claim 3, characterized in that: Calculating the angle of attack and the sideslip angle according to the component of the velocity of the rocket relative to the airflow under the arrow system includes: Calculating the angle of attack based on the x- and y-direction components of the rocket's velocity relative to the airflow in the arrow system; The sideslip angle is calculated based on the components of the rocket's velocity relative to the airflow in the x-direction, the y-direction and the z-direction in the arrow system.

5. The method for identifying aerodynamic parameters of a first stage flight segment of a launch vehicle according to claim 1, characterized in that: The step of obtaining angular acceleration information according to the angular velocity information in the flight telemetry data includes: Using a preset filter to filter the angular velocity information output by the inertial group in the flight telemetry data to obtain filtered angular velocity information, wherein the filtered angular velocity information includes filtered rolling angular velocity information, filtered yaw angular velocity information and filtered pitch angular velocity information; A derivative operation is performed on the filtered angular velocity information to obtain angular acceleration information.

6. The method for identifying aerodynamic parameters of a launch vehicle first stage flight segment according to claim 1, characterized in that: The preset filter includes a Chebyshev low-pass filter.

7. The method for identifying aerodynamic parameters of a first stage flight segment of a launch vehicle according to claim 1, characterized in that: The arrow body moment coefficient information includes first moment information, second moment information and third moment information, the first moment information is x-direction moment information, the second moment information is y-direction moment information, the third moment information is z-direction moment information, and the arrow body size information; The calculating of the arrow body moment coefficient information according to the arrow body combined moment information, dynamic pressure information and arrow body size information includes: The moment components in three directions according to the arrow body resultant moment information; The first moment information, the second moment information and the third moment information are calculated respectively according to the moment components in the three directions, the dynamic pressure information, the arrow body reference area information and the arrow body length information.

8. A device for identifying aerodynamic parameters of a first stage flight stage of a launch vehicle, characterized in that: include: The first calculation unit is used to calculate the angle of attack and sideslip angle of the first stage of the rocket according to the measured wind field data and flight telemetry data on the launch day; A first acquisition unit, configured to acquire angular acceleration information according to the angular velocity information in the flight telemetry data; A second calculation unit is used to calculate the arrow body torque information according to the angular acceleration information and the arrow body moment of inertia; a third calculation unit, configured to calculate the arrow body moment coefficient information according to the arrow body resultant moment information, the dynamic pressure information and the arrow body size information, wherein the arrow body size information includes the arrow body reference area information and the arrow body length information; a second acquisition unit, configured to perform a reverse interpolation operation according to known aerodynamic parameters and the aerodynamic moment coefficient to acquire a rudder deflection control amount, wherein the known aerodynamic parameters include the angle of attack, the sideslip angle, and the Mach number, and the rudder deflection control amount includes a pitch rudder deflection control amount, a yaw rudder deflection control amount, and a roll rudder deflection control amount; The judging unit is used to compare the rudder deflection control amount with the rudder deflection during actual flight to judge the aerodynamic parameters.

9. An electronic device, comprising: A memory and a processor, characterized in that the processor is used to implement the steps of the method for identifying aerodynamic parameters of the first-stage flight segment of a launch vehicle as described in any one of claims 1-7 when executing the computer program stored in the memory.

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 for identifying aerodynamic parameters of the first-stage flight segment of a launch vehicle as described in any one of claims 1-7 are implemented.

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