CN112182787B - Method, system, terminal and medium for determining total deviation amount of carrier rocket - Google Patents
Method, system, terminal and medium for determining total deviation amount of carrier rocket Download PDFInfo
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Abstract
The embodiment of the application provides a method, a system, a terminal and a medium for determining the total deviation amount of a carrier rocket, and relates to the total design technology of the carrier rocket. The method for determining the total deviation amount of the carrier rocket comprises the following steps: acquiring a probability distribution model of a pre-established total deviation amount according to at least one of deviation source information and interference information; acquiring a pre-established overall parameter model; and determining the total deviation amount of the target carrier rocket according to the random numbers subjected to the probability distribution model and the total parameter model.
Description
Technical Field
The present application relates to the general design technology of a launch vehicle, and more particularly, to a method, system, terminal and medium for determining a total deviation amount of a launch vehicle.
Background
The total deviation amount refers to the maximum possible deviation amount of the data given in the initial data design of the carrier rocket and the actual value of the product, and is the important content of the initial data. The rocket overall deviation amount mainly comprises the contents of rocket structure size deviation, mass characteristic deviation, engine performance deviation, overall parameter deviation and the like. The design of the rocket can be directly influenced by the magnitude of the deviation, and the too large deviation easily causes the over-conservative design of the rocket, thereby increasing the design difficulty; if the deviation is too small, the entire deviation cannot be covered, which brings risks to the design.
In the related technology, the determination of the total deviation of the rocket is obtained according to theoretical analysis and statistical analysis of various actually existing data. In the initial stage of development, due to the lack of actual data, the data of the past model is generally analyzed or borrowed by a bias theory; along with the progress of engineering development work, data are continuously accumulated, and deviation is corrected, so that the determination of the deviation is closer to an actual value.
The commercial rocket takes 'low cost and high reliability' as a design guiding idea, a system optimization design considering the cost is carried out at the initial stage of scheme design, the commercial rocket generally adopts a control execution mechanism to simplify the overall scheme, and if the deviation amount is not adapted according to the traditional rough deviation accumulation design method, the control system cannot be adapted, so that how to improve the refinement of the deviation amount becomes an urgent problem to be solved in the industry.
Disclosure of Invention
In order to solve one of the technical defects, the embodiment of the application provides a method, a system, a terminal and a medium for determining the total deviation amount of a carrier rocket.
The embodiment of the first aspect of the application provides a method for determining the total deviation amount of a carrier rocket, which comprises the following steps:
acquiring a probability distribution model of a pre-established total deviation amount according to at least one of deviation source information and interference information; acquiring a pre-established overall parameter model;
and determining the total deviation amount of the target carrier rocket according to the random numbers subjected to the probability distribution model and the total parameter model.
In a second aspect, an embodiment of the present application provides a system for determining an overall deviation amount of a launch vehicle, including:
the first processing module is used for acquiring a probability distribution model of a pre-established total deviation amount according to at least one of deviation source information and interference information; a pre-established overall parameter model is also obtained;
and the second processing module is used for determining the total deviation amount of the target carrier rocket according to the random numbers obeying the probability distribution model and the total parameter model.
An embodiment of a third aspect of the present application provides a terminal, including:
a memory;
a processor; and
a computer program;
wherein the computer program is stored in the memory and configured to be executed by the processor to implement a method as claimed in any preceding claim.
A fourth aspect of the present application provides a computer-readable storage medium, having a computer program stored thereon; the computer program is executed by a processor to implement a method as claimed in any preceding claim.
The embodiment of the application provides a method, a system, a terminal and a medium for determining the total deviation amount of a carrier rocket, the total deviation amount of a target carrier rocket is determined and determined according to a probability distribution model and a total parameter model of the total deviation amount, the traditional mode of deviation amount limit combination is not adopted, all deviation amounts are combined according to a probabilistic model according to the distribution characteristics of the deviation amounts and the independent relation among the deviation amounts, and finally the probabilistic design result of the total deviation amount is obtained through large sample analysis, so that the refined design of the total deviation amount is realized, the design difficulty of a control system and a guidance system is reduced, and the performance of the carrier rocket is effectively improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
FIG. 1 is a schematic flow chart of a method provided in an exemplary embodiment;
FIG. 2 is a diagram illustrating a deviation amount probabilistic combination provided in an exemplary embodiment;
FIG. 3 is a diagram illustrating a quality deviation statistic provided in an exemplary embodiment;
FIG. 4 is a schematic diagram of longitudinal centroid deviation statistics provided in an exemplary embodiment;
FIG. 5 is a schematic diagram of a lateral centroid deviation statistic provided in an exemplary embodiment;
fig. 6 is a block diagram of a system provided in an exemplary embodiment.
Detailed Description
In order to make the technical solutions and advantages of the embodiments of the present application more apparent, the following further detailed description of the exemplary embodiments of the present application with reference to the accompanying drawings makes it clear that the described embodiments are only a part of the embodiments of the present application, and are not exhaustive of all embodiments. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
In the related technology, the determination of the total deviation of the rocket is obtained according to theoretical analysis and statistical analysis of various actually existing data. In the initial stage of development, due to the lack of actual data, the data of the past model is generally analyzed or borrowed by a bias theory; along with the progress of engineering development work, data are continuously accumulated, and deviation is corrected, so that the determination of the deviation is closer to an actual value.
The commercial rocket takes 'low cost and high reliability' as a design guiding idea, system optimization design considering cost is carried out at the initial stage of scheme design, and the following characteristics exist in the overall scheme compared with the traditional model, and bring new challenges to the design of the overall deviation amount.
1. The commercial rocket adopts a simplified overall scheme of a control execution mechanism, the design margin of the control force is greatly reduced compared with the traditional model, and if the deviation is designed according to the traditional rough deviation accumulation method, the control system cannot adapt, so that the demand of the commercial rocket control system on the fine design of the deviation is urgent;
2. the commercial rocket is usually a multi-stage rocket, the number of power systems in the multi-stage rocket is large, and the power systems are main sources of the total deviation, so that the design of the total deviation of the multi-stage rocket needs more variables to be considered, and the complexity is high;
3. the final rocket body of the multi-stage rocket has small mass, the mass center transverse displacement of the final rocket body is greatly influenced by equipment installation and mass characteristic deviation, and the mass center transverse displacement influence caused by uncertainty of propellant consumption of the attitude control power system is considered to be large, so that the mass characteristic of the final rocket body, particularly mass center calculation, needs to be more refined.
In order to overcome the above problems, the present embodiment provides a method, a system, a terminal, and a medium for determining a total deviation amount of a launch vehicle, where probabilistic modeling is performed on main deviation sources affecting the total deviation amount such as mass and centroid in advance, when determining the total deviation amount, a traditional manner of deviation amount limit combination is not used any longer, but each deviation amount is combined according to a probabilistic model according to its own distribution characteristics and an independent relationship therebetween, that is, a random number combination method, and finally, a probabilistic design result of the total deviation amount is obtained through large sample analysis, so that a refined design of the total deviation amount is achieved, the design difficulty of a control system and a guidance system is reduced, and the performance of the launch vehicle is effectively improved.
The function and implementation of the method for determining the total deviation amount of the launch vehicle provided by the embodiment are described below with reference to the accompanying drawings.
As shown in fig. 1, the present embodiment provides a method for determining an overall deviation amount of a launch vehicle, including:
s101, acquiring a probability distribution model of a pre-established total deviation amount according to at least one of deviation source information and interference information; acquiring a pre-established overall parameter model;
and S102, determining the total deviation amount of the target carrier rocket according to the random number obeying the probability distribution model and the total parameter model.
Before step S101, the main deviation sources and interferences affecting the total deviation amount are counted according to the existing model measured data, a probability distribution model is established, and then a calculation model for calculating the total deviation amount based on the probabilistic model random combination is established.
And establishing a probability distribution model in advance. Specifically, when it is determined that deviation source information causing deviation exists, actual measurement data of a deviation source is acquired; when the interference information causing deviation is determined to exist, acquiring actual measurement data of the interference information; and establishing a probability distribution model of the total deviation amount according to the acquired measured data.
Wherein the total deviation amount comprises at least one of: mass deviation, longitudinal mass center deviation, mass center random sideslip and mass center sideslip direction. The probability distribution model includes: a deviation term, and at least one of a probability distribution and an amount of deviation corresponding to the deviation term. That is, the probability distribution model includes: deviation items and their corresponding probability distributions; or, the probability distribution model includes: deviation terms and their corresponding deviation amounts; or, the probability distribution model includes: and the deviation item and the corresponding probability distribution and deviation amount thereof.
During specific implementation, modeling can be carried out according to main deviation sources of the total deviation quantity of deviation items such as the influence quality and the mass center; wherein, the deviation source can be simply called as deviation source. The main sources of deviation may include: mass and center of mass deviation of the solid engine, and position and mass deviation of all instrument and equipment installation. Wherein the centroid deviation may include: the center of mass deviation caused by the non-perpendicularity of the butt joint surface of the rocket body cabin section and the center of mass deviation caused by the uncertain consumption of the liquid attitude control power system. And performing probabilistic modeling on each deviation item by using a large amount of actual measurement data of the existing model as a basis and applying a statistical principle to obtain a probability distribution model of each deviation item.
In this example, sources of uncertainty (sources of bias with uncertainty) are considered in the probabilistic modeling process. Sources of uncertainty include: process, installation, measurement, etc. The method for determining the total deviation amount of the rocket depends on a description mode of uncertainty information and mainly comprises a non-probability method and a probability method, wherein common analysis methods comprise a non-probability interval analysis method, an exhaustion method, an engineering approximation method, a probability accurate method, a sampling method, a Taylor expansion method and the like. In the process of processing the uncertainty problem of the rocket design process, a non-probability exhaustion method is the most widely applied in the rocket engineering design, but the calculation result of the method is relatively conservative, more redundancy can be brought to the design work, and the method is suitable for the design work in the early stage of scheme demonstration. The probability method analyzes the possibility of each situation from the angle of probability, meets the requirement of reliability, can reduce the calculation range of the objective function, and can be used for the fine design of the rocket system.
Illustratively, the analysis process based on sources of uncertainty such as process, installation, measurement, etc. may be as follows: analyzing uncertainty sources in a physical process; establishing a mathematical model according to the result of the physical process, the description of the design problem and the uncertainty of the decision; and establishing and calculating a simulation model according to the external input uncertainty, and outputting a result. The uncertainty source is considered in the building of the mathematical model, the building of the simulation model, the calculation and the output of the result, namely, the uncertainty source is considered in the modeling and the simulation. The mathematical model may include a probability distribution model and an overall parametric model.
According to the characteristic of fine design of a control system of a certain type of commercial rocket, the deviation amount with low sensitivity of the control system and ballistic guidance design, such as length deviation, air vane installation deviation, rotational inertia deviation and the like, is determined by a non-probabilistic method of engineering experience and deviation combination by taking the actual measurement data of the previous type as reference. And aiming at the deviation amount with larger sensitivity of a control system and ballistic guidance design, such as mass, mass center, additional attack angle and the like, a deviation probabilistic determination method is adopted.
When the probability processing of the deviation is carried out, the probability distribution form of each deviation amount can refer to the big data statistical analysis results of commercial rockets of other models, the setting of probability distribution parameters is determined after the comprehensive analysis is carried out by considering the uncertainty of the process, the installation, the measurement and the like, the condition that the probability distribution of each deviation amount can envelop the actual possible occurrence is ensured, and the real characteristics of each deviation amount are reflected as far as possible.
Through statistical analysis of a large amount of measured data and calculated data, the deviation of each commercial rocket is subjected to standard normal distribution or random distribution. Wherein, according to the result of statistical analysis, a probability distribution model of the total deviation of the commercial rocket is established, see table 1 specifically.
TABLE 1 probability distribution model of total deviation for commercial rockets
And establishing an overall parameter model determined based on probabilistic model random combination. The overall parameter model comprises: a mass bias model and a centroid bias model. Specifically, first, determining each disturbance force and disturbance moment by using random numbers which obey certain distribution, then, taking the algebraic sum of each disturbance force and disturbance moment, wherein the disturbance force and disturbance moment caused by each deviation will cause mass deviation and mass center deviation, and the combined model of the mass deviation and the mass center deviation is as follows:
a) quality of
b) Center of mass
Wherein m represents the overall mass of the product; m is i Representing the quality of the ith product; delta m i Indicating the deviation of the ith product; x c Representing the overall longitudinal centroid of the product; x ci Representing the longitudinal centroid of the ith product; delta X ci Representing the deviation of the longitudinal mass center of the ith product; y is c Representing the overall normal centroid of the product; y is ci Representing the normal centroid of the ith product; delta Y ci Representing the normal centroid deviation of the ith product; z c Representing the overall transverse centroid of the product; z ci Representing the transverse centroid of the ith product; delta Z ci The deviation of the transverse mass center of the ith product is shown.
Specifically, as shown in fig. 2, the sum-mean-square is determined according to the measured deviation of the measured product and the deviation caused by the non-perpendicularity; monte Carlo combination can be carried out according to the determined mean square sum and final repair propellant consumption deviation, the deviation of an unmeasured product 1, the deviation of an unmeasured product 2 and the deviation of the combustion process of the engine, so that various interference forces and interference moments are determined, and further, a combined model of mass and mass center deviation is determined. The number of unmeasured product deviations is not limited thereto, and this embodiment is only an example here, and may be specifically set according to actual needs.
In step S101, a deviation term of the total deviation amount required to be determined at this time may be determined, and then a probability distribution model corresponding to the deviation term is obtained. Or obtaining a probability distribution model of each deviation item.
And selecting a corresponding model from the combined model of the mass and the centroid deviation according to the total deviation amount to be determined.
In step S102, the total deviation amount of the target launch vehicle is determined by means of the deviation probability combination. Specifically, obtaining a random number obeying a probability distribution model; and determining the total deviation amount of the target carrier rocket according to the random number, a pre-established mass deviation model and a mass center deviation model.
The process may be a process of performing simulation analysis according to the acquired random number and the deviation model. During specific implementation, a plurality of subsamples of the total deviation amount can be obtained according to the obtained random number and the total parameter model, the distribution characteristic of the total deviation amount can be obtained by carrying out statistical analysis on the subsamples, and the total deviation amount of the target carrier rocket is determined according to the statistical result of the distribution characteristic; illustratively, the standard deviation σ can be obtained according to the distribution characteristics of the total deviation amount, and 3 σ is taken as the total deviation amount.
The following is described with reference to specific examples.
Aiming at the general scheme of a certain type of carrier rocket, the probabilistic modeling simulation calculation of the total deviation is completed by adopting the method to verify the effectiveness of the optimization design method of the total deviation.
Taking the design of three-stage total deviation of a certain solid carrier rocket as an example, the deviation is refined by adopting the method.
First, bias probabilistic modeling is performed.
Probabilistic modeling is performed on the total deviation amount constituent elements of the third-order whole arrow according to the input conditions of the total deviation amount, as shown in table 2.
TABLE 2 probability distribution model of Total deviation
Second, an overall deviation amount is determined based on the deviation probabilistic model.
Based on the probabilistic deviation model, the overall parameter model (i.e., the mass deviation model and the centroid deviation model) is utilized to perform simulation calculation on the overall parameters, and simulation analysis of 5000 subsamples is completed in total, so that the distribution characteristics of the overall deviation amount are shown in fig. 3, 4 and 5.
Through statistical analysis, 3 sigma of the probability statistical result is taken as the design result of the total deviation amount, and the results of three-level mass, longitudinal mass center and transverse mass center deviation are obtained and are shown in table 3.
TABLE 3 Total deviation
| Item | Unit of | Total deviation (3 sigma) |
| Deviation of mass | kg | ±20 |
| Deviation of longitudinal centroid | mm | ±15 |
| Transverse centroid deviation | mm | ±5.5 |
For an example product, quality characteristic measurement work is performed, an actual measurement result is compared with a probabilistic deviation result and a traditional limit combination deviation design result, and the comparative analysis result is shown in table 4.
TABLE 4 Total deviation design results
| Item | Unit | Deviation from limit | Probability deviation (3 sigma) | Deviation from actual measurement |
| Deviation of mass | kg | ±30 | ±20 | 14.32 |
| Deviation of longitudinal centroid | mm | ±25 | 15 | -7.54 |
| Transverse centroid deviation | mm | ±9.5 | 5.5 | 3.97 |
Therefore, by adopting the method provided by the embodiment, the mass deviation is reduced by more than 20% compared with the traditional method, the centroid deviation is reduced by more than 40%, the refinement level of the overall parameter design is greatly improved, and the design difficulty of the control system is reduced. Analysis shows that the actual measurement result is within a design deviation envelope range and has a certain margin, and compared with the traditional limit combination design method, the deviation range is greatly reduced, and the rationality of deviation amount design is verified.
As shown in fig. 6, the present embodiment further provides a system for determining the total deviation amount of a launch vehicle, including:
the first processing module 11 is configured to acquire a probability distribution model that is pre-established with respect to a total deviation amount according to at least one of deviation source information and interference information; a pre-established overall parameter model is also obtained;
and the second processing module 12 is used for determining the total deviation amount of the target carrier rocket according to the random numbers obeying the probability distribution model and the total parameter model.
In one possible implementation manner, the first processing module 11 is further configured to:
when determining that deviation source information causing deviation exists, acquiring actual measurement data of a deviation source;
when the interference information causing deviation is determined to exist, acquiring actual measurement data of the interference information;
and establishing a probability distribution model of the total deviation amount according to the acquired measured data.
In one possible implementation, the total deviation amount includes at least one of: mass deviation, longitudinal mass center deviation, mass center random sideslip and mass center sideslip direction.
In one possible implementation, the probability distribution model includes: a deviation term, and at least one of a probability distribution and an amount of deviation.
In one possible implementation manner, the second processing unit 12 is specifically configured to:
obtaining a random number obeying a probability distribution model;
and determining the total deviation amount of the target carrier rocket according to the random number, a pre-established mass deviation model and a mass center deviation model.
In one possible implementation, the mass deviation model and the centroid deviation model are as follows:
wherein m represents the overall mass of the product; m is i Representing the quality of the ith product; delta m i Indicating the deviation of the ith product; x c Representing the overall longitudinal centroid of the product; x ci Representing the longitudinal centroid of the ith product; delta X ci Representing the deviation of the longitudinal mass center of the ith product; y is c Representing the overall normal centroid of the product; y is ci Representing the normal centroid of the ith product; delta Y ci Representing the normal centroid deviation of the ith product; z c Representing the overall transverse centroid of the product; z ci Representing the transverse centroid of the ith product; delta Z ci The deviation of the transverse center of mass of the ith product is shown.
In one possible implementation manner, the second processing unit 12 is specifically configured to:
obtaining a plurality of subsamples of the total deviation amount according to the random number, the mass deviation model and the centroid deviation model;
carrying out statistical analysis on the plurality of subsamples to obtain the distribution characteristic of the total deviation amount;
and determining the total deviation amount of the target carrier rocket according to the distribution characteristics.
This embodiment provides a terminal device, including:
a memory;
a processor; and
a computer program;
wherein the computer program is stored in the memory and configured to be executed by the processor to implement the respective method. For specific implementation, reference may be made to the method embodiments, which are not described herein again.
The memory is used for storing a computer program, and the processor executes the computer program after receiving the execution instruction, and the method executed by the apparatus defined by the flow process disclosed in the foregoing corresponding embodiments can be applied to or implemented by the processor.
The Memory may comprise a Random Access Memory (RAM) and may also include a non-volatile Memory, such as at least one disk Memory. The memory can implement communication connection between the system network element and at least one other network element through at least one communication interface (which may be wired or wireless), and the internet, a wide area network, a local network, a metropolitan area network, and the like can be used.
The processor may be an integrated circuit chip having signal processing capabilities. In implementation, the steps of the method disclosed in the first embodiment may be implemented by hardware integrated logic circuits in a processor or instructions in the form of software. The Processor may be a general-purpose Processor, and includes a Central Processing Unit (CPU), a Network Processor (NP), and the like; but may also be a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), an off-the-shelf programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components. The corresponding methods, steps, and logic blocks disclosed in the embodiments of the present invention may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like.
The steps of the method disclosed in connection with the embodiments of the present invention may be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software elements in the decoding processor. The software elements may be located in ram, flash, rom, prom, or eprom, registers, among other storage media that are well known in the art. The storage medium is located in a memory, and a processor reads information in the memory and completes the steps of the method in combination with hardware of the processor.
The present embodiment provides a computer-readable storage medium having stored thereon a computer program; the computer program is executed by a processor in a corresponding method. For specific implementation, reference may be made to the method embodiments, which are not described herein again.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all alterations and modifications as fall within the scope of the application.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (12)
1. A method of determining an amount of total deviation of a launch vehicle, comprising:
acquiring a probability distribution model of a pre-established total deviation amount according to at least one of deviation source information and interference information; acquiring a pre-established overall parameter model;
determining the total deviation amount of the target carrier rocket according to the random number obeying the probability distribution model and the total parameter model, and specifically comprising the following steps:
obtaining a random number obeying the probability distribution model;
obtaining a plurality of subsamples of the total deviation amount according to the random number, the mass deviation model and the mass center deviation model;
carrying out statistical analysis on the plurality of subsamples to obtain the distribution characteristic of the total deviation amount;
and determining the total deviation amount of the target carrier rocket according to the distribution characteristics.
2. The method of claim 1, prior to obtaining a pre-established model of probability distribution of total deviation measure based on at least one of deviation source information and interference information, comprising:
when determining that deviation source information causing deviation exists, acquiring measured data of the deviation source;
when the interference information causing deviation is determined to exist, acquiring measured data of the interference information;
and establishing a probability distribution model of the total deviation amount according to the obtained measured data.
3. The method of claim 1, wherein the total deviation amount comprises at least one of: mass deviation amount, longitudinal centroid deviation amount, centroid random transverse shift amount and centroid transverse shift direction.
4. The method of claim 1, wherein the probability distribution model comprises: a deviation term, and at least one of a probability distribution and an amount of deviation corresponding to the deviation term.
5. The method of claim 1, wherein the mass bias model and the centroid bias model are as follows:
wherein m represents the overall mass of the product; m is i Representing the quality of the ith product; delta m i Indicating the deviation of the ith product; x c To representThe overall longitudinal mass center of the product; x ci Representing the longitudinal centroid of the ith product; delta X ci Representing the deviation of the longitudinal mass center of the ith product; y is c Representing the overall normal centroid of the product; y is ci Representing the normal centroid of the ith product; delta Y ci Representing the normal centroid deviation of the ith product; z c Representing the overall transverse centroid of the product; z ci Representing the transverse centroid of the ith product; delta Z ci The deviation of the transverse mass center of the ith product is shown.
6. A system for determining an amount of total deflection of a launch vehicle, comprising:
the first processing module is used for acquiring a probability distribution model of a pre-established total deviation amount according to at least one of deviation source information and interference information; a pre-established overall parameter model is also obtained;
a second processing module, configured to determine a total deviation amount of the target launch vehicle according to the random numbers obeying the probability distribution model and the total parameter model; the method specifically comprises the following steps: obtaining a random number obeying the probability distribution model;
obtaining a plurality of subsamples of the total deviation amount according to the random number, the mass deviation model and the mass center deviation model;
carrying out statistical analysis on the plurality of subsamples to obtain the distribution characteristic of the total deviation amount;
and determining the total deviation amount of the target carrier rocket according to the distribution characteristics.
7. The system of claim 6, wherein the first processing module is further configured to:
when determining that deviation source information causing deviation exists, acquiring measured data of the deviation source;
when the interference information causing deviation is determined to exist, acquiring measured data of the interference information;
and establishing a probability distribution model of the total deviation amount according to the obtained measured data.
8. The system of claim 6, wherein the total amount of deviation comprises at least one of: mass deviation, longitudinal mass center deviation, mass center random sideslip and mass center sideslip direction.
9. The system of claim 6, wherein the probability distribution model comprises: a deviation term, and at least one of a probability distribution and an amount of deviation corresponding to the deviation term.
10. The system of claim 6, wherein the mass bias model and the centroid bias model are as follows:
wherein m represents the overall mass of the product; m is i Representing the quality of the ith product; delta m i Indicating the deviation of the ith product; x c Representing the overall longitudinal centroid of the product; x ci Representing the longitudinal centroid of the ith product; delta X ci Representing the deviation of the longitudinal mass center of the ith product; y is c Representing the overall normal centroid of the product; y is ci Representing the normal centroid of the ith product; delta Y ci Representing the normal centroid deviation of the ith product; z c Representing the overall transverse centroid of the product; z ci Representing the transverse centroid of the ith product; delta Z ci The deviation of the transverse center of mass of the ith product is shown.
11. A terminal, comprising:
a memory;
a processor; and
a computer program;
wherein the computer program is stored in the memory and configured to be executed by the processor to implement the method of any one of claims 1-5.
12. A computer-readable storage medium, having stored thereon a computer program; the computer program is executed by a processor to implement the method of any one of claims 1-5.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108763746A (en) * | 2018-05-28 | 2018-11-06 | 北京航空航天大学 | Carrier rocket mass parameter evaluation method |
| CN108959702A (en) * | 2018-05-25 | 2018-12-07 | 首都航天机械公司 | A kind of Rocket tank Deviation Analysis Method based on the transmitting of face deviation |
| CN109325288A (en) * | 2018-09-17 | 2019-02-12 | 北京宇航***工程研究所 | A kind of Solid Launch Vehicle population parameter based on uncertainty optimization determines method and system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3019592B1 (en) * | 2014-04-03 | 2016-04-22 | Snecma | METHOD AND DEVICE FOR MONITORING A PARAMETER OF A ROTOR MOTOR |
| CN109703645B (en) * | 2018-12-29 | 2020-05-22 | 深圳市优必选科技有限公司 | Robot centroid position adjusting method and device, robot and data storage medium |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108959702A (en) * | 2018-05-25 | 2018-12-07 | 首都航天机械公司 | A kind of Rocket tank Deviation Analysis Method based on the transmitting of face deviation |
| CN108763746A (en) * | 2018-05-28 | 2018-11-06 | 北京航空航天大学 | Carrier rocket mass parameter evaluation method |
| CN109325288A (en) * | 2018-09-17 | 2019-02-12 | 北京宇航***工程研究所 | A kind of Solid Launch Vehicle population parameter based on uncertainty optimization determines method and system |
Non-Patent Citations (1)
| Title |
|---|
| 近地轨道运载火箭轨迹/总体参数一体化优化设计;罗亚中等;《中国空间科学技术》;20031025(第05期);全文 * |
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