Method, device and computer equipment for processing rocket power coefficient

Abstract

An embodiment of the present application provides a method for processing a rocket's power coefficient, wherein the power coefficient is a power coefficient in a linearized dynamic equation. The method includes: obtaining a deviation factor under at least one deviation condition, corresponding to obtaining at least one deviation factor; obtaining a standard curve model of the rocket, wherein the standard curve model is used to characterize the functional relationship between the rocket's power coefficient and time within a flight cycle in which no deviation condition exists; performing a deviation calculation on the standard curve model based on each of the deviation factors, generating a deviation curve model group corresponding to the deviation factor, and obtaining at least one deviation curve model group; based on the at least one deviation curve model group, correcting the standard curve model to generate an upper envelope curve model and a lower envelope curve model of the rocket's power coefficient.

Description

Technical Field

[0001] The present application relates to the field of rocket data processing, and more specifically, to a method, device, and electronic equipment for processing rocket power coefficients. Background Art

[0002] Reusable liquid-propellant launch vehicles face a more complex and variable flight environment during re-entry, and are susceptible to a variety of deviation conditions during flight. This places high demands on the robustness of the attitude control system, ensuring that it is well adaptable to deviations in the environment.

[0003] Therefore, technical personnel in this field urgently need a method for processing rocket power coefficients to reasonably calculate the pulling state of the rocket's flight state and provide important data support for the design of the flight attitude control system. Summary of the Invention

[0004] The embodiments of the present application provide a method, apparatus, and computer equipment for processing rocket power coefficients, which can determine, at least to a certain extent, the range of change in the rocket's power coefficients during flight, providing important data support for designing a flight attitude control system.

[0005] Other features and advantages of the present application will become apparent from the following detailed description, or may be learned in part by practice of the present application.

[0006] According to one aspect of the present application, a method for processing a rocket's power coefficient is provided, wherein the power coefficient is a power coefficient in a linearized dynamic equation, and the method includes: obtaining a deviation factor under at least one deviation condition, and correspondingly obtaining at least one deviation factor; obtaining a standard curve model of the rocket, and the standard curve model is used to characterize the functional relationship between the rocket's power coefficient and time within a flight cycle in which there is no deviation condition; based on each of the deviation factors, performing a deviation calculation on the standard curve model, generating a deviation curve model group corresponding to the deviation factor, and obtaining at least one deviation curve model group; based on the at least one deviation curve model group, correcting the standard curve model, and generating an upper envelope curve model and a lower envelope curve model of the rocket's power coefficient.

[0007] In one embodiment of the present application, the deviation condition includes at least one of the center of mass deviation condition of the rocket, the moment of inertia deviation condition of the rocket, the thrust deviation condition of the rocket, the aerodynamic force deviation condition of the rocket, the center of pressure deviation condition of the rocket, and the atmospheric density deviation condition of the flight environment.

[0008] In one embodiment of the present application, the deviation curve model group includes a first deviation curve model and a second deviation curve model, and the deviation curve model group corresponding to the deviation factor is generated by performing a deviation calculation on the standard curve model based on each deviation factor, including: performing a positive deviation calculation on the standard curve model based on each deviation factor to generate a first deviation curve model; performing a negative deviation calculation on the standard curve model based on each deviation factor to generate a second deviation curve model.

[0009] In one embodiment of the present application, an upper envelope curve model of the power coefficient of the rocket is generated in the following manner, including: for each first deviation curve model, subtracting the first deviation curve model from the standard curve model to obtain at least one first difference curve model; based on the at least one first difference curve model, correcting the standard curve model to obtain the upper envelope curve model of the power coefficient of the rocket.

[0010] In one embodiment of the present application, the standard curve model is corrected based on the at least one first difference curve model to obtain the upper envelope curve model of the power coefficient of the rocket, including: calculating the geometric sum of the at least one first difference curve model to obtain a first geometric sum curve model; summing the first geometric sum curve model and the standard curve model to obtain the upper envelope curve model of the power coefficient of the rocket.

[0011] In one embodiment of the present application, a lower envelope curve model of the power coefficient of the rocket is generated in the following manner, including: for each second deviation curve model, subtracting the second deviation curve model from the standard curve model to obtain at least one second difference curve model; based on the at least one second difference curve model, correcting the standard curve model to obtain the lower envelope curve model of the power coefficient of the rocket.

[0012] In one embodiment of the present application, the standard curve model is corrected based on the at least one second difference curve model to obtain the envelope curve model of the rocket's power coefficient, including: calculating the geometric sum of the at least one second difference curve model to obtain a second geometric sum curve model; and subtracting the second geometric sum curve model from the standard curve model to obtain the envelope curve model of the rocket's power coefficient.

[0013] In one embodiment of the present application, the method also includes: obtaining the wind attack angle variation range of the rocket at at least one moment in a flight cycle in the presence of wind interference; determining the maximum power coefficient and the minimum power coefficient at each moment based on the wind attack angle variation range at each moment, and generating the maximum power coefficient curve model and the minimum power coefficient curve model of the rocket; performing a pull-off calculation on the maximum power coefficient curve model based on each of the deviation factors, generating a deviation curve model group corresponding to the deviation factor, and obtaining at least one deviation curve model group; correcting the maximum power coefficient curve model based on the at least one deviation curve model group, and generating an upper envelope curve model and a lower envelope curve model of the maximum power coefficient; performing a pull-off calculation on the minimum power coefficient curve model based on each of the deviation factors, generating a deviation curve model group corresponding to the deviation factor, and obtaining at least one deviation curve model group; correcting the minimum power coefficient curve model based on the at least one deviation curve model group, and generating an upper envelope curve model and a lower envelope curve model of the minimum power coefficient.

[0014] According to one aspect of the present application, a device for processing a rocket's power coefficient is provided, wherein the power coefficient is a coefficient related to each torque in a linearized dynamic equation, and the device includes: a first acquisition unit, used to obtain a deviation factor under at least one deviation condition, and correspondingly obtain at least one deviation factor; a second acquisition unit, used to obtain a standard curve model of the rocket, and the standard curve model is used to characterize the functional relationship between the rocket's power coefficient and time within a flight cycle when there is no deviation condition; a first generation unit, used to perform a deviation calculation on the standard curve model based on each of the deviation factors, and generate a deviation curve model group corresponding to the deviation factor, and obtain at least one deviation curve model group; a second generation unit, used to correct the standard curve model based on the at least one deviation curve model group, and generate an upper envelope curve model and a lower envelope curve model of the rocket's power coefficient.

[0015] According to one aspect of the present application, a computer device is provided, which includes one or more processors and one or more memories, wherein at least one program code is stored in the one or more memories, and the at least one program code is loaded and executed by the one or more processors to implement the operations performed by the method for processing the rocket power coefficient as described.

[0016] Based on the above solution, this application has at least the following advantages or improvements:

[0017] In this application, the curve model of the power coefficient when a single deviation factor exists is calculated, and multiple curve models are integrated to correct the standard curve of the power coefficient. The upper and lower envelope curve models of the power coefficient when multiple deviation factors exist at the same time are calculated, which can reflect the changes in the power coefficient of the rocket during actual flight to a certain extent. The upper and lower envelope curve model group finally obtained can provide important data support for the design of subsequent flight attitude control systems.

[0018] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings are incorporated into and constitute a part of the specification, illustrating embodiments consistent with the present application and, together with the specification, explaining the principles of the present application. Obviously, the drawings described below are only some embodiments of the present application, and those skilled in the art can derive other drawings based on these drawings without inventive effort. In the drawings:

[0020] Figure 1 A simplified flowchart of a method for processing rocket power coefficients in one embodiment of the present application is shown;

[0021] Figure 2 A simplified flowchart of a method for calculating an upper envelope curve model of a rocket power coefficient in one embodiment of the present application is shown;

[0022] Figure 3 A simplified flow chart of a method for correcting the standard curve model in one embodiment of the present application is shown;

[0023] Figure 4 A simplified flowchart of a method for calculating a lower envelope curve model of a rocket power coefficient in one embodiment of the present application is shown;

[0024] Figure 5 A simplified flow chart of a method for correcting the standard curve model in one embodiment of the present application is shown;

[0025] Figure 6 A simplified flowchart of a method for processing rocket power coefficients in one embodiment of the present application is shown;

[0026] Figure 7 A simplified structural diagram of a device for processing rocket power coefficients in one embodiment of the present application is shown;

[0027] Figure 8 A schematic diagram of the structure of a computer system suitable for implementing the embodiments of the present application is shown. DETAILED DESCRIPTION

[0028] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this application will be thorough and complete and will fully convey the concepts of the example embodiments to those skilled in the art.

[0029] In addition, described feature, structure or characteristic can be combined in one or more embodiments in any suitable manner.In the following description, many specific details are provided so as to provide a full understanding of the embodiments of the present application. However, it will be appreciated by those skilled in the art that the technical scheme of the present application can be put into practice without one or more of the specific details, or other methods, components, devices, steps etc. can be adopted. In other cases, known methods, devices, implementations or operations are not shown or described in detail to avoid blurring the various aspects of the application.

[0030] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically separate entities. That is, these functional entities may be implemented in software, in one or more hardware modules or integrated circuits, or in different networks and / or processor devices and / or microcontroller devices.

[0031] The flowcharts shown in the accompanying drawings are for illustrative purposes only and do not necessarily include all contents and operations / steps, nor must they be executed in the order described. For example, some operations / steps may be decomposed, while others may be combined or partially combined. Therefore, the actual execution order may vary depending on the actual situation.

[0032] It should be noted that the terms "first," "second," and the like in the specification and claims of this application and the accompanying drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, such that the embodiments of the present application described herein can be implemented in an order other than that illustrated or described.

[0033] Next, the technical solution provided in this application will be described in detail with reference to the accompanying drawings.

[0034] See Figure 1 , Figure 1 A simplified flowchart of a method for processing a rocket power coefficient in an embodiment of the present application is shown. The power coefficient is the power coefficient in a linearized dynamics equation. The method may include steps S101-S104:

[0035] Step S101: Obtain a deviation factor under at least one deviation condition, and obtain at least one corresponding deviation factor.

[0036] Step S102: Obtain a standard curve model of the rocket, where the standard curve model is used to characterize the functional relationship between the power coefficient of the rocket and time within a flight cycle in the absence of deviation conditions.

[0037] Step S103: Based on each of the deviation factors, a deviation calculation is performed on the standard curve model to generate a deviation curve model group corresponding to the deviation factor, thereby obtaining at least one deviation curve model group.

[0038] Step S104: Based on the at least one deviation curve model group, the standard curve model is corrected to generate an upper envelope curve model and a lower envelope curve model of the power coefficient of the rocket.

[0039] In this application, a standard curve model of the rocket's power coefficient can be obtained first. The power coefficient can be a power coefficient b2 and a power coefficient b3. The power coefficient b2 represents a coefficient related to the aerodynamic stability torque, and the power coefficient b3 represents a coefficient related to the control torque. The power coefficient b2 can be calculated by the following expression:

[0040]

[0041] in, is the derivative of the pitching dynamic coefficient with respect to the angle of attack, which has a functional relationship with the flight time; q is the dynamic pressure, which has a functional relationship with the flight time; S m is the reference area; L l is the reference length; J Z1 It is the moment of inertia around the z-axis of the rocket body and has a functional relationship with the flight time.

[0042] The dynamic coefficient b3 can be calculated by the following expression:

[0043]

[0044] Among them, n c is the number of swing engines; P0 is the thrust of a single engine, and its function relationship with flight time; x R is the distance from the engine swing point to the theoretical tip; x z is the distance from the center of mass of the arrow to the theoretical apex, which has a functional relationship with the flight time; m R is the mass of the swinging part of a single engine; is the longitudinal apparent acceleration, which has a functional relationship with the flight time; l R is the distance from the center of mass of the swing part of a single engine to the swing axis, J Z1 It is the moment of inertia around the z-axis of the rocket body and has a functional relationship with the flight time.

[0045] First calculate the b2 standard curve model b2 标and b3 standard curve model b3 标 . Then, the curve models of multiple power coefficients when a single deviation factor exists are calculated. By combining multiple curve models, the upper and lower envelope curve models of the power coefficients when multiple deviation factors exist at the same time are calculated. This can reflect the changes in the power coefficients of the rocket during actual flight to a certain extent. The upper and lower envelope curve model group finally obtained can provide important data support for the design of subsequent flight attitude control systems.

[0046] In one embodiment of the present application, the deviation condition includes at least one of the center of mass deviation condition of the rocket, the moment of inertia deviation condition of the rocket, the thrust deviation condition of the rocket, the aerodynamic force deviation condition of the rocket, the center of pressure deviation condition of the rocket, and the atmospheric density deviation condition of the flight environment.

[0047] In one embodiment of the present application, the deviation curve model group includes a first deviation curve model and a second deviation curve model, and the deviation curve model group corresponding to the deviation factor is generated by performing a deviation calculation on the standard curve model based on each deviation factor, including: performing a positive deviation calculation on the standard curve model based on each deviation factor to generate a first deviation curve model; performing a negative deviation calculation on the standard curve model based on each deviation factor to generate a second deviation curve model.

[0048] In this application, when each deviation factor exists, it will cause the power coefficient to deviate positively or negatively from the standard curve, and the power coefficient curve model under positive and negative deviation conditions needs to be calculated separately.

[0049] For example, when considering the existence of the rocket's center of mass deviation condition alone, the dynamic coefficient curve model b2 with positive deviation is calculated. s1 , and then calculate the dynamic coefficient curve model b2 with negative deviation x1 The dynamic coefficient curve model b2 with positive deviation s1 That is, the first deviation curve model, the negative deviation dynamic coefficient curve model b2 x1 That is the second deviation curve model. The first deviation curve model and the first deviation curve model can be regarded as the positive and negative pull curve models of the standard curve model b2, which can reflect the change of the dynamic coefficient b2 when the center of mass deviation condition of the rocket exists alone.

[0050] See Figure 2 , Figure 2 A simplified flowchart of a method for calculating an upper envelope curve model of a rocket power coefficient in an embodiment of the present application is shown. The calculation method may include steps S201-S202:

[0051] Step S201 : For each first deviation curve model, a difference is calculated between the first deviation curve model and the standard curve model to obtain at least one first difference curve model.

[0052] Step S202: Based on the at least one first difference curve model, the standard curve model is corrected to obtain an upper envelope curve model of the power coefficient of the rocket.

[0053] In this application, the situation where multiple deviation factors exist at the same time can be considered to calculate multiple first difference curve models. For example, when the center of mass deviation condition and the moment of inertia deviation condition of the rocket exist at the same time, the upper envelope curve model of the power coefficient b2 can be calculated by first calculating the standard curve model b2 of the power coefficient b2. 标 , and then calculate the two first deviation curves: b2 s1 and b2 s2 , the first difference curve model can be calculated according to the following formula:

[0054] Δb2 si =|b2 标 -b2 si |

[0055] Calculate Δb2 s1 and Δb2 s2 , based on Δb2 s1 and Δb2 s2 , for b2 标 The correction is performed to obtain the upper envelope curve model of the dynamic coefficient b2.

[0056] See Figure 3 , Figure 3 A simplified flowchart of a method for correcting the standard curve model in one embodiment of the present application is shown. The correction method may include steps S301-S302:

[0057] Step S301 : Calculate the geometric sum of the at least one first difference curve model to obtain a first geometric sum curve model.

[0058] Step S302: summing the first geometric and curve model with the standard curve model to obtain an upper envelope curve model of the power coefficient of the rocket.

[0059] In this application, the situation where multiple deviation factors exist at the same time can be considered to calculate multiple first difference curve models. For example, when there are rocket center of mass deviation conditions and rocket moment of inertia deviation conditions, the upper envelope curve model of the power coefficient b2 can be calculated. The standard curve model b2 of the power coefficient b2 can be calculated first. 标 , and then calculate the two first deviation curve models: b2 s1 and b2s2 , the first difference curve model can be calculated according to the following formula:

[0060] Δb2 si =|b2 标 -b2 si |

[0061] Calculate Δb2 s1 and Δb2 s2 , based on Δb2 s1 and Δb2 s2 , the first geometric and curvilinear models can be calculated:

[0062]

[0063] For b2 标 After correction, the upper envelope curve model of the dynamic coefficient b2 can be obtained according to the following formula:

[0064]

[0065] See Figure 4 , Figure 4 A simplified flowchart of a method for calculating a lower envelope curve model of a rocket power coefficient in an embodiment of the present application is shown. The calculation method may include steps S401-S402:

[0066] Step S401: for each second deviation curve model, calculating the difference between the second deviation curve model and the standard curve model to obtain at least one second difference curve model.

[0067] Step S402: Based on the at least one second difference curve model, the standard curve model is corrected to obtain a lower envelope curve model of the power coefficient of the rocket.

[0068] In this application, the situation where multiple deviation factors exist at the same time can be considered to calculate multiple second difference curve models. For example, when there are both rocket thrust deviation conditions and rocket aerodynamic deviation conditions, the lower envelope curve model of the power coefficient b3 can be calculated by first calculating the standard curve model b3 of the power coefficient b3. 标 , and then calculate the two second deviation curve models: b3 x1 and b3 x2 , the second difference curve model can be calculated according to the following formula:

[0069] Δb3 xi =|b3 标 -b3 xi |

[0070] Calculated Δb3 x1 and Δb3x2 , based on Δb3 x1 and Δb2 x2 , for b3 标 After correction, the lower envelope curve model of the dynamic coefficient b3 is obtained.

[0071] See Figure 5 , Figure 5 A simplified flowchart of a method for correcting the standard curve model in one embodiment of the present application is shown. The correction method may include steps S501-S502:

[0072] Step S501 : Calculate the geometric sum of the at least one second difference curve model to obtain a second geometric sum curve model.

[0073] Step S502: Calculate the difference between the second geometric and curve model and the standard curve model to obtain the lower envelope curve model of the power coefficient of the rocket.

[0074] In this application, the situation where multiple deviation factors exist at the same time can be considered to calculate multiple second difference curve models. For example, when there are both rocket thrust deviation conditions and rocket aerodynamic deviation conditions, the lower envelope curve model of the power coefficient b3 can be calculated by first calculating the standard curve model b3 of the power coefficient b3. 标 , and then calculate the two second deviation curve models: b3 x1 and b3 x2 , the second difference curve model can be calculated according to the following formula:

[0075] Δb3 xi =|b3 标 -b3 xi |

[0076] Calculated Δb3 x1 and Δb3 x2 , based on Δb3 x1 and Δb3 x2 , the second geometric and curvilinear model can be calculated:

[0077]

[0078] For b3 标 After correction, the lower envelope curve model of the dynamic coefficient b3 can be obtained according to the following formula:

[0079]

[0080] See Figure 6 , Figure 6 A simplified flowchart of a method for processing a rocket power coefficient in an embodiment of the present application is shown. The processing method may include steps S601-S604:

[0081] Step S601: obtaining a wind attack angle variation range of the rocket at at least one moment in a flight cycle with wind interference.

[0082] Step S602: Based on the wind attack angle variation range at each moment, the maximum power coefficient and the minimum power coefficient at each moment are determined, and a maximum power coefficient curve model of the rocket and a minimum power coefficient curve model of the rocket are generated.

[0083] Step S603 : Based on each of the deviation factors, a deviation calculation is performed on the maximum power coefficient curve model to generate a deviation curve model group corresponding to the deviation factor, thereby obtaining at least one deviation curve model group.

[0084] Step S604 : Based on the at least one deviation curve model group, the maximum power coefficient curve model is modified to generate an upper envelope curve model and a lower envelope curve model of the maximum power coefficient.

[0085] Step S605 : Based on each of the deviation factors, a deviation calculation is performed on the minimum power coefficient curve model to generate a deviation curve model group corresponding to the deviation factor, thereby obtaining at least one deviation curve model group.

[0086] Step S606 : Based on the at least one deviation curve model group, the minimum power coefficient curve model is modified to generate an upper envelope curve model and a lower envelope curve model of the minimum power coefficient.

[0087] In this application, the dynamic coefficient b2 can be calculated using the following formula:

[0088]

[0089] in, is the derivative of the pitching dynamic coefficient with respect to the angle of attack, which has a functional relationship with the flight time; q is the dynamic pressure, which has a functional relationship with the flight time; S m is the reference area; L l is the reference length; It is the moment of inertia around the z-axis of the rocket body and has a functional relationship with the flight time.

[0090] Can be achieved through Determine the linearity of the power coefficient curve model. When there is wind interference, the linearity of the power coefficient curve model may be poor, so it is necessary to further modify the upper and lower envelope curve models of the power coefficient. The wind attack angle during flight can be calculated based on the wind interference conditions:

[0091]

[0092] Among them, ν w is the wind speed, θ is the flight inclination angle, and ν is the flight speed.

[0093] The wind attack angle can be set to a range of 0 to α w , generate b2 within the range of wind attack angle variation max 、b2 min Curve model. For example, at time point t i There is a range of wind attack angle variation. Calculate b2 within this range, get the maximum and minimum values, and then calculate the next time point t i+1 , repeat the above steps until the entire trajectory time, the maximum power coefficient curve model of the rocket and the minimum power coefficient curve model of the rocket are calculated; then refer to the deviation correction process of the standard curve model, and perform deviation correction on the maximum power coefficient curve model and the minimum power coefficient curve model respectively to obtain the upper and lower envelope curve models of the maximum power coefficient and the upper and lower envelope curve models of the minimum power coefficient. The upper and lower envelope curve models for the standard curve model, the upper and lower envelope curve models for the maximum power coefficient, and the upper and lower envelope curve models for the minimum power coefficient can be combined as the upper and lower envelope curve models of the final power coefficient.

[0094] Next, an embodiment of a device of the present application will be introduced with reference to the accompanying drawings.

[0095] Figure 7 A simplified structural diagram of a device for processing rocket power coefficients in an embodiment of the present application is shown. The power coefficients are coefficients related to various torques in a linearized dynamic equation. The device for processing rocket power coefficients may include: a first acquisition unit 701, a second acquisition unit 702, a first generation unit 703, and a second generation unit 704.

[0096] In the present application, the processing device 700 can be configured as follows: a first acquisition unit 701 is used to obtain a deviation factor under at least one deviation condition, corresponding to at least one deviation factor; a second acquisition unit 702 is used to obtain a standard curve model of the rocket, and the standard curve model is used to characterize the functional relationship between the power coefficient of the rocket and time in a flight cycle when there is no deviation condition; a first generation unit 703 is used to perform a deviation calculation on the standard curve model based on each of the deviation factors, generate a deviation curve model group corresponding to the deviation factor, and obtain at least one deviation curve model group; a second generation unit 704 is used to correct the standard curve model based on the at least one deviation curve model group, and generate an upper envelope curve model and a lower envelope curve model of the power coefficient of the rocket.

[0097] Figure 8A schematic diagram of the structure of a computer system suitable for implementing the embodiments of the present application is shown.

[0098] It should be noted that Figure 8 The computer system 800 shown is only an example and should not limit the functions and scope of use of the embodiments of the present application.

[0099] like Figure 8 As shown, the computer system 800 includes a central processing unit (CPU) 801, which can perform various appropriate actions and processes according to the program stored in the read-only memory (ROM) 802 or the program loaded from the storage part 808 into the random access memory (RAM) 803, such as executing the method described in the above embodiment. Various programs and data required for system operation are also stored in the RAM 803. The CPU 801, ROM 802 and RAM 803 are connected to each other via a bus 804. An input / output (I / O) interface 805 is also connected to the bus 804.

[0100] The following components are connected to the I / O interface 805: an input section 806 including a keyboard, a mouse, and the like; an output section 807 including devices such as a cathode ray tube (CRT), a liquid crystal display (LCD), and a speaker; a storage section 808 including a hard disk and the like; and a communication section 809 including a network interface card such as a LAN (Local Area Network) card or a modem. The communication section 809 performs communication processing via a network such as the Internet. A drive 810 is also connected to the I / O interface 805 as needed. Removable media 811, such as a magnetic disk, an optical disk, a magneto-optical disk, or a semiconductor memory, is installed in the drive 810 as needed, so that computer programs read therefrom can be installed into the storage section 808 as needed.

[0101] In particular, according to an embodiment of the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, an embodiment of the present application includes a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from a network via the communication section 809, and / or installed from a removable medium 811. When the computer program is executed by the central processing unit (CPU) 801, the various functions defined in the system of the present application are executed.

[0102] It should be noted that the computer-readable medium shown in the embodiments of the present application can be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer-readable storage media can include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM), a flash memory, an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present application, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, device or device. In the present application, a computer-readable signal medium can include a data signal propagated in baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium that can transmit, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code embodied on a computer-readable medium may be transmitted using any suitable medium, including but not limited to wireless, wired, or any suitable combination thereof.

[0103] The flowcharts and block diagrams in the accompanying drawings illustrate the possible implementation architecture, functions and operations of the systems, methods and computer program products according to various embodiments of the present application. Among them, each box in the flowchart or block diagram can represent a module, program segment, or part of the code, and the above-mentioned module, program segment, or part of the code contains one or more executable instructions for implementing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in an order different from that marked in the accompanying drawings. For example, two boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram or flowchart, and the combination of boxes in the block diagram or flowchart, can be implemented with a dedicated hardware-based system that performs the specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0104] The units involved in the embodiments described in this application may be implemented by software or hardware, and the units described may also be set in a processor. In some cases, the names of these units do not constitute limitations on the units themselves.

[0105] As another aspect, the present application further provides a computer program product or computer program, which includes computer instructions stored in a computer-readable storage medium. A processor of a computer device reads the computer instructions from the computer-readable storage medium and executes the computer instructions, causing the computer device to perform the processing method described in the above embodiments.

[0106] As another aspect, the present application further provides a computer-readable medium, which may be included in the electronic device described in the above embodiments, or may exist independently without being incorporated into the electronic device. The computer-readable medium carries one or more programs, and when the one or more programs are executed by the electronic device, the electronic device implements the processing method described in the above embodiments.

[0107] It should be noted that, although several modules or units of the device for action execution are mentioned in the above detailed description, this division is not mandatory. In fact, according to the embodiment of the application, the features and functions of two or more modules or units described above can be concretized in one module or unit. On the contrary, the features and functions of one module or unit described above can be further divided into multiple modules or units to be concretized.

[0108] Through the description of the above embodiments, it is easy for those skilled in the art to understand that the example embodiments described herein can be implemented by software or by combining software with necessary hardware. Therefore, the technical solution according to the embodiments of the present application can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network, and includes several instructions to enable a computing device (which can be a personal computer, a server, a touch terminal, or a network device, etc.) to execute the method according to the embodiments of the present application.

[0109] Those skilled in the art will readily conceive of other embodiments of the present application after considering the specification and practicing the embodiments disclosed herein. This application is intended to cover any variations, uses, or adaptations of the present application that follow the general principles of this application and include common knowledge or customary techniques in the art that are not disclosed herein.

[0110] It should be understood that the present application is not limited to the exact structures described above and shown in the drawings, and that various modifications and changes may be made without departing from the scope thereof. The scope of the present application is limited only by the appended claims.

Claims

1. A method for processing rocket dynamic coefficients, wherein the dynamic coefficients are coefficients related to various moments in the linearized dynamic equations, characterized in that: The method comprises: Obtaining a deviation factor under at least one deviation condition, and correspondingly obtaining at least one deviation factor; Obtaining a standard curve model of the rocket, wherein the standard curve model is used to represent a functional relationship between the power coefficient of the rocket and time within a flight cycle in the absence of deviation conditions; Based on each of the deviation factors, performing a deviation calculation on the standard curve model to generate a deviation curve model group corresponding to the deviation factor, thereby obtaining at least one deviation curve model group; Based on the at least one deviation curve model group, the standard curve model is modified to generate an upper envelope curve model and a lower envelope curve model of the power coefficient of the rocket; The deviation curve model group includes a first deviation curve model and a second deviation curve model. Based on each of the deviation factors, the standard curve model is subjected to deviation calculation to generate a deviation curve model group corresponding to the deviation factor, including: Based on each of the deviation factors, performing a positive deviation calculation on the standard curve model to generate a first deviation curve model; Based on each of the deviation factors, performing a negative deviation calculation on the standard curve model to generate a second deviation curve model; The upper envelope curve model of the power coefficient of the rocket is generated by the following method, including: For each first deviation curve model, calculating the difference between the first deviation curve model and the standard curve model to obtain at least one first difference curve model; Based on the at least one first difference curve model, the standard curve model is corrected to obtain an upper envelope curve model of the power coefficient of the rocket; The lower envelope curve model of the power coefficient of the rocket is generated by the following method, including: For each second deviation curve model, calculating the difference between the second deviation curve model and the standard curve model to obtain at least one second difference curve model; Based on the at least one second difference curve model, the standard curve model is corrected to obtain the lower envelope curve model of the power coefficient of the rocket.

2. The method according to claim 1, characterized in that The deviation conditions include at least one of the center of mass deviation condition of the rocket, the moment of inertia deviation condition of the rocket, the thrust deviation condition of the rocket, the aerodynamic force deviation condition of the rocket, the center of pressure deviation condition of the rocket, and the atmospheric density deviation condition of the flight environment.

3. The method according to claim 1, characterized in that The method of correcting the standard curve model based on the at least one first difference curve model to obtain an upper envelope curve model of the power coefficient of the rocket includes: calculating a geometric sum of the at least one first difference curve model to obtain a first geometric sum curve model; The first geometric and curve model is summed with the standard curve model to obtain the upper envelope curve model of the power coefficient of the rocket.

4. The method according to claim 1, wherein The method of correcting the standard curve model based on the at least one second difference curve model to obtain a lower envelope curve model of the power coefficient of the rocket includes: calculating a geometric sum of the at least one second difference curve model to obtain a second geometric sum curve model; The second geometric and curve model is differentiated from the standard curve model to obtain the lower envelope curve model of the power coefficient of the rocket.

5. The method according to claim 1, wherein The method further comprises: Obtaining a range of wind attack angle variation of the rocket at at least one moment in a flight cycle in the presence of wind interference; Determining the maximum power coefficient and the minimum power coefficient at each moment based on the range of wind attack angle variation at each moment, and generating a maximum power coefficient curve model and a minimum power coefficient curve model of the rocket; Based on each of the deviation factors, performing a deviation calculation on the maximum power coefficient curve model, generating a deviation curve model group corresponding to the deviation factor, and obtaining at least one deviation curve model group; Based on the at least one deviation curve model group, the maximum power coefficient curve model is modified to generate an upper envelope curve model and a lower envelope curve model of the maximum power coefficient; Based on each of the deviation factors, performing a deviation calculation on the minimum power coefficient curve model, generating a deviation curve model group corresponding to the deviation factor, and obtaining at least one deviation curve model group; Based on the at least one deviation curve model group, the minimum power coefficient curve model is modified to generate an upper envelope curve model and a lower envelope curve model of the minimum power coefficient.

6. A device for processing rocket dynamic coefficients, wherein the dynamic coefficients are coefficients related to various moments in a linearized dynamic equation, characterized in that: The device comprises: A first obtaining unit is used to obtain a deviation factor under at least one deviation condition, and correspondingly obtain at least one deviation factor; The second acquisition unit is used to obtain a standard curve model of the rocket, wherein the standard curve model is used to represent a functional relationship between the power coefficient of the rocket and time within a flight cycle in the absence of a deviation condition; A first generating unit is configured to perform a deviation calculation on the standard curve model based on each of the deviation factors, generate a deviation curve model group corresponding to the deviation factor, and obtain at least one deviation curve model group; The deviation curve model group includes a first deviation curve model and a second deviation curve model, and based on each of the deviation factors, a positive deviation calculation is performed on the standard curve model to generate a first deviation curve model; Based on each of the deviation factors, performing a negative deviation calculation on the standard curve model to generate a second deviation curve model; a second generating unit, configured to modify the standard curve model based on the at least one deviation curve model group to generate an upper envelope curve model and a lower envelope curve model of the power coefficient of the rocket; For each first deviation curve model, calculating the difference between the first deviation curve model and the standard curve model to obtain at least one first difference curve model; Based on the at least one first difference curve model, the standard curve model is corrected to obtain an upper envelope curve model of the power coefficient of the rocket; For each second deviation curve model, calculating the difference between the second deviation curve model and the standard curve model to obtain at least one second difference curve model; Based on the at least one second difference curve model, the standard curve model is corrected to obtain the lower envelope curve model of the power coefficient of the rocket.

7. A computer device, characterized in that: The computer device includes one or more processors and one or more memories, and at least one program code is stored in the one or more memories. The at least one program code is loaded and executed by the one or more processors to implement the operations performed by the method for processing the rocket power coefficient as described in any one of claims 1 to 5.

Images