CN103955557A - Multi-disciplinary integrated design optimization method and system for carrier rocket - Google Patents

Multi-disciplinary integrated design optimization method and system for carrier rocket Download PDF

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CN103955557A
CN103955557A CN201410125568.6A CN201410125568A CN103955557A CN 103955557 A CN103955557 A CN 103955557A CN 201410125568 A CN201410125568 A CN 201410125568A CN 103955557 A CN103955557 A CN 103955557A
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carrier rocket
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CN103955557B (en
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王晓慧
李人杰
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Beihang University
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    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract

The invention provides a multi-disciplinary integrated design optimization system for a carrier rocket. The multi-disciplinary integrated design optimization system comprises a system analysis module, an optimization model module and an optimization solving module, wherein the three modules are carried out according to a sequence in a multi-disciplinary integrated design optimization process of the carrier rocket, namely the system analysis module is firstly executed, then the optimization model module is executed and the optimization solving module is lastly executed. A multi-disciplinary integrated design optimization method for the carrier rocket comprises the following three steps: step 1, establishing the system analysis module of the carrier rocket; step 2, establishing a multi-disciplinary optimization model of the carrier rocket; step 3, optimizing and solving. According to the multi-disciplinary integrated design optimization system and method for the carrier rocket, synergistic effects generated by mutual effects of various disciplines are utilized sufficiently to obtain the whole optimal solution of a carrier rocket system; the design period is shortened and the cost is reduced.

Description

A kind of carrier rocket multidisciplinary synthesis design optimization method and system
Technical field
The present invention relates to a kind of carrier rocket multidisciplinary synthesis design optimization method and system, it can realize carrier rocket overall design quickly and efficiently, belongs to field of aerospace technology.
Background technology
The ability that country enters space has determined the ability of its space operation to a great extent, and the level of space application and development, the main spacefaring nation in the world is all weighed its space technology level to enter spacial ability, carrier rocket is the main delivery vehicle that enters in the world space at present, and the development scale of carrier rocket and technical merit have supported the ability that enters space.
Carrier rocket is a complex engineering system that relates to multiple subjects, and as how much master casts, power, pneumatic, space flight mechanics, heat transfer/thermal protection system, structure, control, load, trajectory etc., each subject intercouples and affects.In traditional carrier rocket overall design, first each subsystem specialty proposes the optimum solution of native system, and then is comprehensively proved by overall department.Due to specialty restriction, it is not proper that the native system optimum solution that designer obtains is often considered influencing each other between each subsystem, the just local optimum obtaining like this, non-global optimum, finally to lean on the too much locally optimal solution of each subsystem of wheel checking calculating ability overall equilbrium of overall department warp, obtain globally optimal solution.During this, rely on design report and data file mode to coordinate, in parameter agreement, data file transition and transmittance process, expend a large amount of time, and this manual activity also easily makes mistakes, seriously restricted design efficiency.So, need to apply multidisciplinary design optimization (Multidisciplinary Design Optimization, MDO) and carry out carrier rocket overall design.
Summary of the invention
1, object
The object of this invention is to provide a kind of carrier rocket multidisciplinary synthesis design optimization method and system, to overcome, the design efficiency of traditional carrier rocket design method is low, the cycle is grown, easily make mistakes, can not get the shortcomings such as globally optimal solution;
2, technical scheme
In order to realize foregoing invention object, the present invention by the following technical solutions.
(1) a carrier rocket multidisciplinary synthesis design optimization method, it comprises following step:
Step 1: set up booster system analytical model
Described booster system analytical model is made up of three subject analytical models, is respectively overall subject analytical model, pneumatic subject analytical model and trajectory subject analytical model, between every subjects analytical model, links together by coupling variable.
The set that this overall subject analytical model is one group of mathematical formulae or one section of software program.
Overall subject analytical model:
m 0 = m z ϵ 1 ϵ 2 m i = ρ i πd i 2 4 l i
Wherein, m 0for take off weight; m zfor payload mass; ε 1, ε 2for inter-stage ratio; m iit is the quality of i level rocket; ρ iit is the average density of i level rocket; d iit is the diameter of i level rocket; l ibe the length of i level rocket.
This pneumatic subject analytical model is aerodynamic analysis software DATCOM;
This trajectory subject analytical model is:
Wherein, x, y, z is the component of rocket displacement in launching coordinate system; v x, v y, v zfor the component of rocket speed in launching coordinate system; P is motor power; D is air resistance; M is Rocket mass; for the angle of pitch; V is the mould of velocity; R is the mould of displacement vector.
Step 2: set up the multidisciplinary Optimized model of carrier rocket
The multidisciplinary Optimized model of described carrier rocket is made up of optimization aim, optimized variable, constraint condition three parts, is coordination between each several part.
This optimization aim is a dependent variable that characterizes carrier rocket carrying capacity, as payload mass maximum under the predetermined condition of take off weight, or under the predetermined condition of payload mass take off weight minimum etc., can according to specific design require select.
This optimized variable comprises design variable and coupling variable two parts, is coordination between the two.This design variable is independent variable independently within every subjects in design process, and this coupling variable is the dependent variable of transmitting between every subjects in design process.
This constraint condition be must be satisfied in design process condition, be the set of one group of inequality and equation.
| h - h 0 h 0 | < 0.01 | v - v 0 v 0 | < 0.01
Wherein, h and v are that rocket is entered the orbit highly and the speed of entering the orbit, h 0and v 0for rocket is subscribed enter the orbit height and the reservation speed of entering the orbit.
Step 3: optimizing solves
Utilize optimizing algorithm to solve the multidisciplinary Optimized model of carrier rocket.Described optimizing algorithm is existing method, as the optimizing algorithm based on gradient, intelligent algorithm etc.
(2) a carrier rocket multidisciplinary synthesis design optimization system, it comprises that Systems Analysis Module, Optimized model module and optimizing solve three modules of module.Between it, relation is: three modules are carried out in order in carrier rocket multidisciplinary synthesis design optimization process, and first executive system analytical model module, then carries out Optimized model module, finally carries out optimizing and solves module.
Described Systems Analysis Module is analyzed submodule by several subjects and is formed, and every subjects is analyzed between submodule and linked together by coupling variable.It is set or one section of software program of one group of mathematical formulae that this subject is analyzed submodule.
Described Optimized model module is made up of optimization aim submodule, optimized variable submodule, three submodules of constraint condition submodule, between each submodule, is coordination.This optimization aim submodule is a dependent variable that characterizes carrier rocket carrying capacity, as payload mass maximum under the predetermined condition of take off weight, or under the predetermined condition of payload mass take off weight minimum etc., can according to specific design require select; This optimized variable submodule comprises design variable and coupling variable two parts, coordination between the two: this design variable is independent variable independently within every subjects in design process, and this coupling variable is the dependent variable of transmitting between every subjects in design process; This constraint condition submodule be must be satisfied in design process condition, be the set of one group of inequality and equation.
Described optimizing solves module and is made up of some optimizing algorithms.Described optimizing algorithm is existing method, as the optimizing algorithm based on gradient, intelligent algorithm etc.
3, advantage and effect
The invention provides a kind of carrier rocket multidisciplinary synthesis design optimization method and system, its major advantage is: make full use of the interaction of each subject and the cooperative effect that produces, obtain booster system total optimization solution, shorten the design cycle, and cost-saving.
Brief description of the drawings
Fig. 1 is carrier rocket multidisciplinary synthesis design optimization method process flow diagram.
Fig. 2 is carrier rocket multidisciplinary synthesis design optimization system architecture diagram.
Fig. 3 is that carrier rocket multidisciplinary synthesis design optimization is simplified loop.
Embodiment
Below in conjunction with the two-stage launcher multidisciplinary synthesis design optimization embodiment of accompanying drawing and a trivium, the invention will be further described; but the present embodiment is not limited to the present invention; every employing similarity method of the present invention and similar variation thereof, all should list protection scope of the present invention in.
Can be found out by Fig. 1 and Fig. 3, the invention provides a kind of carrier rocket multidisciplinary synthesis design optimization method, it comprises following step:
Step 1: set up booster system analytical model
Described booster system analytical model is made up of three subject analytical models, is respectively overall subject analytical model, pneumatic subject analytical model and trajectory subject analytical model, between every subjects analytical model, links together by coupling variable.
The set that this overall subject analytical model is one group of mathematical formulae or one section of software program.Specific as follows to the present embodiment:
Overall subject analytical model:
m 0 = m z &epsiv; 1 &epsiv; 2 m i = &rho; i &pi;d i 2 4 l i
Wherein, m 0for take off weight; m zfor payload mass; ε 1, ε 2for inter-stage ratio; m iit is the quality of i level rocket; ρ iit is the average density of i level rocket; d iit is the diameter of i level rocket; l ibe the length of i level rocket.
Pneumatic subject analytical model: aerodynamic analysis software DATCOM;
Trajectory subject analytical model:
Wherein, x, y, z is the component of rocket displacement in launching coordinate system; v x, v y, v zfor the component of rocket speed in launching coordinate system; P is motor power; D is air resistance; M is Rocket mass; for the angle of pitch; V is the mould of velocity; R is the mould of displacement vector.
Step 2: set up the multidisciplinary Optimized model of carrier rocket
The multidisciplinary Optimized model of described carrier rocket is made up of optimization aim, optimized variable, constraint condition three parts, is coordination between each several part.
This optimization aim is a dependent variable that characterizes carrier rocket carrying capacity, is at payload mass m in the present embodiment ztake off weight m under certain condition 0minimum.
This optimized variable comprises design variable and coupling variable two parts, is coordination between the two.This design variable is independent variable independently within every subjects in design process, in the present embodiment for inter-stage compares ε 1and ε 2; This coupling variable is the dependent variable of transmitting between every subjects in design process, in the present embodiment, is the diameter d of i level rocket i, i level rocket length l i, motor power P, resistance coefficient C d, i level rocket quality m i.
This constraint condition be must be satisfied in design process condition, be the set of one group of inequality and equation, be in the present embodiment:
| h - h 0 h 0 | < 0.01 | v - v 0 v 0 | < 0.01
Wherein, h and v are that rocket is entered the orbit highly and the speed of entering the orbit, h 0and v 0for rocket is subscribed enter the orbit height and the reservation speed of entering the orbit.
Step 3: optimizing solves
Utilize optimizing algorithm to solve the multidisciplinary Optimized model of carrier rocket.In the present embodiment, adopt SQP Sequential Quadratic Programming method, this algorithm is a kind of optimizing algorithm of existing maturation.
See Fig. 2, the present invention also provides a kind of carrier rocket multidisciplinary synthesis design optimization system, and it comprises that Systems Analysis Module, Optimized model module and optimizing solve three modules of module.Between it, relation is: three modules are carried out in order in carrier rocket multidisciplinary synthesis design optimization process, and first executive system analysis module, then carries out Optimized model module, finally carries out optimizing and solves module.
Described Systems Analysis Module is analyzed submodule by three subjects and is formed, and is respectively overall subject and analyzes submodule, pneumatic subject analysis submodule and trajectory subject analysis submodule, and every subjects is analyzed between submodule and linked together by coupling variable.This subject is analyzed submodule and is set or one section of software program of one group of mathematical formulae, specific as follows to the present embodiment:
Overall subject is analyzed submodule:
m 0 = m z &epsiv; 1 &epsiv; 2 m i = &rho; i &pi;d i 2 4 l i
Wherein, m 0for take off weight; m zfor payload mass; ε 1, ε 2for inter-stage ratio; m iit is the quality of i level rocket; ρ iit is the average density of i level rocket; d iit is the diameter of i level rocket; l ibe the length of i level rocket.
Pneumatic subject is analyzed submodule: aerodynamic analysis software DATCOM;
Trajectory subject is analyzed submodule:
Wherein, x, y, z is the component of rocket displacement in launching coordinate system; v x, v y, v zfor the component of rocket speed in launching coordinate system; P is motor power; D is air resistance; M is Rocket mass; for the angle of pitch; V is the mould of velocity; R is the mould of displacement vector.
Described Optimized model module is made up of optimization aim submodule, optimized variable submodule and three submodules of constraint condition submodule, between each submodule, is coordination.In the present embodiment, this optimization aim submodule is take off weight minimum under the certain condition of payload mass; This optimized variable submodule comprises design variable and coupling variable two parts, is coordination between each several part: this design variable is independent variable independently within every subjects in design process, in the present embodiment for inter-stage compares ε 1and ε 2, this coupling variable is the dependent variable of transmitting between every subjects in design process, is the diameter d of i level rocket in the present embodiment i, i level rocket length l i, motor power P, resistance coefficient C d, i level rocket quality m i; This constraint condition submodule be must be satisfied in design process condition, be the set of one group of inequality and equation, be in the present embodiment:
| h - h 0 h 0 | < 0.01 | v - v 0 v 0 | < 0.01
Wherein, h and v are that rocket is entered the orbit highly and the speed of entering the orbit, h 0and v 0for rocket is subscribed enter the orbit height and the reservation speed of entering the orbit.。
Described optimizing solves module and is made up of some optimizing algorithms, is SQP Sequential Quadratic Programming method in the present embodiment, and this algorithm is a kind of optimizing algorithm of existing maturation.

Claims (2)

1. a carrier rocket multidisciplinary synthesis design optimization method, is characterized in that: it comprises following step:
Step 1: set up booster system analytical model
Described booster system analytical model is made up of three subject analytical models, is respectively overall subject analytical model, pneumatic subject analytical model and trajectory subject analytical model, between every subjects analytical model, links together by coupling variable;
The set that this overall subject analytical model is one group of mathematical formulae or one section of software program;
Overall subject analytical model:
m 0 = m z &epsiv; 1 &epsiv; 2 m i = &rho; i &pi;d i 2 4 l i
Wherein, m 0for take off weight; m zfor payload mass; ε 1, ε 2for inter-stage ratio; m iit is the quality of i level rocket; ρ iit is the average density of i level rocket; d iit is the diameter of i level rocket; l ibe the length of i level rocket;
This pneumatic subject analytical model is aerodynamic analysis software DATCOM;
This trajectory subject analytical model is:
Wherein, x, y, z is the component of rocket displacement in launching coordinate system; v x, v y, v zfor the component of rocket speed in launching coordinate system; P is motor power; D is air resistance; M is Rocket mass; for the angle of pitch; V is the mould of velocity; R is the mould of displacement vector;
Step 2: set up the multidisciplinary Optimized model of carrier rocket
The multidisciplinary Optimized model of described carrier rocket is made up of optimization aim, optimized variable, constraint condition three parts, is coordination between each several part;
This optimization aim is a dependent variable that characterizes carrier rocket carrying capacity, as payload mass maximum under the predetermined condition of take off weight, or under the predetermined condition of payload mass take off weight minimum, require to select according to specific design;
This optimized variable comprises design variable and coupling variable two parts, is coordination between the two; This design variable is independent variable independently within every subjects in design process, and this coupling variable is the dependent variable of transmitting between every subjects in design process;
This constraint condition be must be satisfied in design process condition, be the set of one group of inequality and equation;
| h - h 0 h 0 | < 0.01 | v - v 0 v 0 | < 0.01
Wherein, h and v are that rocket is entered the orbit highly and the speed of entering the orbit, h 0and v 0for rocket is subscribed enter the orbit height and the reservation speed of entering the orbit;
Step 3: optimizing solves
Utilize optimizing algorithm to solve the multidisciplinary Optimized model of carrier rocket; Described optimizing algorithm is optimizing algorithm and the intelligent algorithm based on gradient.
2. a carrier rocket multidisciplinary synthesis design optimization system, is characterized in that: it comprises that Systems Analysis Module, Optimized model module and optimizing solve three modules of module; Three modules are carried out in order in carrier rocket multidisciplinary synthesis design optimization process, and first executive system analytical model module, then carries out Optimized model module, finally carries out optimizing and solves module;
Described Systems Analysis Module is analyzed submodule by a plurality of subjects and is formed, and every subjects is analyzed between submodule and linked together by coupling variable, and it is set or one section of software program of one group of mathematical formulae that this subject is analyzed submodule;
Described Optimized model module is made up of optimization aim submodule, optimized variable submodule, three submodules of constraint condition submodule, between each submodule, is coordination; This optimization aim submodule is a dependent variable that characterizes carrier rocket carrying capacity, as payload mass maximum under the predetermined condition of take off weight, or under the predetermined condition of payload mass take off weight minimum, it according to specific design require select; This optimized variable submodule comprises design variable and coupling variable two parts, is coordination between the two; This design variable is independent variable independently within every subjects in design process, and this coupling variable is the dependent variable of transmitting between every subjects in design process; This constraint condition submodule be must be satisfied in design process condition, be the set of one group of inequality and equation;
Described optimizing solves module and is made up of a plurality of optimizing algorithms, and described optimizing algorithm is optimizing algorithm and the intelligent algorithm based on gradient.
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CN105005643B (en) * 2015-06-26 2018-01-23 北京航空航天大学 A kind of method and system of manned moon landing's mass Quantity customizing
CN105005643A (en) * 2015-06-26 2015-10-28 北京航空航天大学 Manned lunar-landing quality scale estimation method and system
CN105956281B (en) * 2016-05-05 2019-03-22 中国人民解放军国防科学技术大学 Solid propellant rocket motor charge design method
CN105956281A (en) * 2016-05-05 2016-09-21 中国人民解放军国防科学技术大学 Charging design method of solid rocket engine
CN106446460A (en) * 2016-10-26 2017-02-22 北京宇航系统工程研究所 Lightweight method of super-large three-dimensional model of carrier rocket
CN106446460B (en) * 2016-10-26 2019-06-18 北京宇航系统工程研究所 A kind of ultra-large three-dimensional model lightweight method of carrier rocket
CN107933965A (en) * 2017-11-09 2018-04-20 北京航天自动控制研究所 A kind of carrier rocket servo control mechanism linear smoothing resetting method
CN107933965B (en) * 2017-11-09 2019-09-06 北京航天自动控制研究所 A kind of carrier rocket servo mechanism linear smoothing resetting method
CN108763747A (en) * 2018-05-28 2018-11-06 北京航空航天大学 Carrier rocket dimensional parameters evaluation method
CN108763746A (en) * 2018-05-28 2018-11-06 北京航空航天大学 Carrier rocket mass parameter evaluation method
CN108763747B (en) * 2018-05-28 2020-07-24 北京航空航天大学 Carrier rocket size parameter estimation method
CN108763746B (en) * 2018-05-28 2021-06-25 北京航空航天大学 Carrier rocket mass parameter estimation method
CN108931987A (en) * 2018-07-09 2018-12-04 北京航空航天大学 A kind of Attitude Control System Design method
CN109325288A (en) * 2018-09-17 2019-02-12 北京宇航系统工程研究所 A kind of Solid Launch Vehicle population parameter based on uncertainty optimization determines method and system
CN109325288B (en) * 2018-09-17 2023-04-07 北京宇航系统工程研究所 Uncertainty optimization-based solid carrier overall parameter determination method and system
CN110489922A (en) * 2019-08-30 2019-11-22 北京航空航天大学 Design method of structural parameters, device and the electronic equipment of solid-liquid carrier rocket
CN113742847A (en) * 2021-09-09 2021-12-03 北京航空航天大学 Multidisciplinary design method and system for solid-liquid power rocket aircraft
CN113742847B (en) * 2021-09-09 2023-05-16 北京航空航天大学 Multidisciplinary design method and system for solid-liquid power rocket craft
CN117892558A (en) * 2024-03-14 2024-04-16 西安现代控制技术研究所 Construction method of ultra-remote guidance rocket multidisciplinary dynamic optimization model

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