CN108984903A - A kind of preferred/optimum design method of Guidance Parameter - Google Patents
A kind of preferred/optimum design method of Guidance Parameter Download PDFInfo
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Abstract
The present invention relates to a kind of preferred/optimum design methods of Guidance Parameter, construct objective function using required orbital tracking precision index and deviation, carry out the selection or optimization of Guidance Parameter.The optimization and determination that the present invention is carried out for the system parameter of terminal multi-parameter index request, Multi-indices constraints are comprehensively considered, it is handled and is judged by nondimensionalization, the objective function that processing is equalized, integrates is carried out to effective, nondimensional independence index, an overall target optimization problem is converted by multi-specification optimization problem, simplifies the workload in system design process midcourse guidance parameter tuning process；Evaluation index function is constructed based on orbital tracking, determines Guidance Parameter in conjunction with optimization algorithm, dexterously constructs target equation, there is extensive engineer application.
Description
Technical field
The present invention relates to a kind of preferred/optimum design method of Guidance Parameter, mainly for there is clear technical requirement
Situation, core is the design of optimization object function, can be used for that carrier rocket is entered the orbit, the multiple targets balance optimizing such as Satellite Orbit Maneuver is set
Meter, belongs to Guidance and control technical field.
Background technique
In recent years, China accelerated the deployment of the spaces such as Beidou Navigation System, space station, telecommunication satellite, and carrier rocket transmitting is appointed
Business quantity cumulative year after year.Increasingly high-intensitive, highdensity transmitting proposes higher want to precision, the reliability of carrier rocket
It asks.Meanwhile to meet the microsatellites development trends such as long-life, small deadweight, need to reduce as possible by satellite Autonomous change rail
Pressure makes great efforts to improve the precision that the payload such as satellite are sent into planned orbit by carrier rocket.
Currently, the orbit injection accuracy evaluation to the carrier rocket satellite and the rocket separation moment is generally measured according to six individual index:
Perigee altitude deviation delta Hp, orbital period deviation delta T, orbit inclination angle deviation delta i, argument of perigee deviation delta ω, ascending node
Right ascension deviation delta Ω, time deviation of entering the orbit Δ t etc..If this six indexs comply fully with technical requirement, illustrate guidance system
System precision is met the requirements.How in the design process of Guidance Parameter, carry out parameter using computer technology of continuous development etc.
Automatic Optimal Design, reduction manually adjusts dependence of the design parameter to experience, that is, reduces the requirement to designer's level, drop
Low labor intensity reduces the lack of uniformity that technical indicator is realized, while improving design efficiency, is the pressing problem for needing to face,
Therefore, carrying out rapid Optimum to Guidance Parameter is this field technical problem urgently to be resolved.
Summary of the invention
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of preferred/optimization design sides of Guidance Parameter
Method can reasonably integrate independent multiple indexs at an index, so that fortune be effectively reduced on the basis of guaranteeing effect
Calculate complexity.
The object of the invention is achieved by following technical solution:
A kind of preferred method of Guidance Parameter is provided, is included the following steps:
(1) according to task, Guidance Equation is established；
(2) multiple groups Guidance Parameter is set, established Guidance Equation is emulated respectively, obtaining multiple groups has required precision
Orbital tracking value；
(3) deviation of every group of orbital tracking value and required standard value is calculated；
(4) nondimensionalization processing is carried out to the deviation of calculating；
(5) judge dimensionless treated that deviation is greater than 1 situation with the presence or absence of absolute value, directly sentence if presence and do not conform to
Otherwise lattice enter step (6)；
(6) it averages m, standard deviation sigma to the deviation of every group of nondimensionalization；
(7) multiple target equalization target function is constructed:
(8) the smallest one group of Guidance Parameter of the corresponding target function value L of more every group of parameter, selection target functional value L.
Preferably, the orbital tracking value described in step (2) with required precision is perigee altitude Hp, the orbital period
T, orbit inclination angle i, argument of perigee ω, right ascension of ascending node Ω, enter the orbit time t.
Preferably, deviation described in step (3) includes perigee altitude deviation delta Hp, orbital period deviation delta T, track
Inclination deviation Δ i, argument of perigee deviation delta ω, right ascension of ascending node deviation delta Ω, time deviation of entering the orbit Δ t, calculation method is such as
Under:
ΔHp=Hp-Hpr
Δ T=T-Tr
Δ i=i-ir
Δ ω=ω-ωr
Δ Ω=Ω-Ωr
Δ t=t-tr
Wherein, Hpr、Tr、i、ωr、Ωr、trIt is perigee altitude, orbital period, orbit inclination angle, the near-earth under standard trajectory
Point argument, is entered the orbit the time at right ascension of ascending node.
Preferably, to the deviation progress nondimensionalization processing of calculating, the specific method is as follows in step (4):
Wherein, Δ Hpr、ΔTr、Δir、Δωr、ΔΩr、ΔtrFor technical requirement maximum allowable offset；uhp、uT、
ui、uω、uΩ、utIndicate that nondimensional perigee altitude deviation, orbital period deviation, orbit inclination angle deviation, argument of perigee are inclined
Difference, right ascension of ascending node deviation, time deviation of entering the orbit.
Preferably, averaging in step (6) to the deviation of every group of nondimensionalization, the specific method is as follows for m, standard deviation sigma:
Wherein, n is the number of the orbital tracking value of terminal required precision.
A kind of optimization method of Guidance Parameter is provided simultaneously, is included the following steps:
(1) according to task, Guidance Equation is established；
(2) Guidance Parameter initial value is arranged according to selected optimization algorithm, established Guidance Equation is emulated respectively,
Obtain the orbital tracking value that multiple groups have required precision；
(3) deviation of every group of orbital tracking value and required standard value is calculated；
(4) nondimensionalization processing is carried out to the deviation of calculating；
(5) judge dimensionless treated that deviation is greater than 1 situation with the presence or absence of absolute value, directly sentence if presence and do not conform to
Otherwise lattice enter step (6)；
(6) it averages m, standard deviation sigma to the deviation of every group of nondimensionalization；
(7) multiple target balance optimizing objective function is constructed:
(8) it using multiple target balance optimizing objective function as the objective function in optimization algorithm, is carried out using optimization algorithm
Iterative solution sets the condition of convergence until meeting, the Guidance Parameter after obtaining one group of optimization.
Preferably, the orbital tracking value described in step (2) with required precision is perigee altitude Hp, the orbital period
T, orbit inclination angle i, argument of perigee ω, right ascension of ascending node Ω, enter the orbit time t.
Preferably, deviation described in step (3) includes perigee altitude deviation delta Hp, orbital period deviation delta T, track
Inclination deviation Δ i, argument of perigee deviation delta ω, right ascension of ascending node deviation delta Ω, time deviation of entering the orbit Δ t, calculation method is such as
Under:
ΔHp=Hp-Hpr
Δ T=T-Tr
Δ i=i-ir
Δ ω=ω-ωr
Δ Ω=Ω-Ωr
Δ t=t-tr
Wherein, Hpr、Tr、i、ωr、Ωr、trIt is perigee altitude, orbital period, orbit inclination angle, the near-earth under standard trajectory
Point argument, is entered the orbit the time at right ascension of ascending node.
Preferably, to the deviation progress nondimensionalization processing of calculating, the specific method is as follows in step (4):
Wherein, Δ Hpr、ΔTr、Δir、Δωr、ΔΩr、ΔtrFor corresponding technical requirement maximum allowable offset；uhp、
uT、ui、uω、uΩ、utIndicate nondimensional perigee altitude deviation, orbital period deviation, orbit inclination angle deviation, argument of perigee
Deviation, right ascension of ascending node deviation, time deviation of entering the orbit.
Preferably, averaging in step (6) to the deviation of every group of nondimensionalization, the specific method is as follows for m, standard deviation sigma:
Wherein, n is the number of the orbital tracking value of terminal required precision.
Preferably, the optimization algorithm uses genetic algorithm, particle swarm algorithm or ant group algorithm.
The invention has the following advantages over the prior art:
(1) present invention is directed to the optimization of specified point, Multi-indices constraints has been comprehensively considered, and carried out nondimensionalization, to nothing
The independence index of dimension carries out the processing objective function that is equalized, integrates, by multi-specification optimization problem be converted into one it is comprehensive
Index optimization problem is closed, simplifies workload during ground design during Guidance Parameter adjustment and to computing resource
Consumption, the final dependence reduced to designer's design experiences, and it is obviously improved the harmony of technical indicator realization.
(2) the present invention is based on the orbital trackings with terminal required precision to construct evaluation index function, in conjunction with optimization algorithm
It determines Guidance Parameter, dexterously constructs target equation, there is extensive engineer application.
(3) present invention simultaneously provides a kind of preferred method of Guidance Parameter, face multiple groups Guidance Parameter convenient for designer
When, it can rapidly and accurately determine the Guidance Parameter optimized, improve design efficiency.
Detailed description of the invention
Fig. 1 is the optimization method flow diagram of Guidance Parameter of the present invention；
Fig. 2 is orbital tracking schematic diagram.
Specific embodiment
The present invention is described further below with reference to specific example.
When designer faces multiple groups Guidance Parameter, it usually needs each Guidance Parameter is adjusted repeatedly respectively, according to operation
As a result, judging whether every guidance precision index meets the requirements, so that the design process of Guidance Parameter extremely very complicated.In order to
Reduce design efforts would and the consumption to computing resource, the final dependence reduced to designer's design experiences, lift technique
The harmony that index is realized, the present invention integrate Guidance Parameter, it is balanced assess, provide a kind of Guidance Parameter it is preferred/
Optimum design method.
A kind of Guidance Parameter preferred method provided by the invention, specific calculating process are as follows:
(1) according to task, Guidance Equation is established using existing method；
(2) multiple groups Guidance Parameter is set, established Guidance Equation is emulated respectively, obtaining multiple groups has terminal precision
It is required that orbital tracking value, such as may include perigee altitude Hp, orbital period T, orbit inclination angle i, argument of perigee ω, rise
Intersection point right ascension Ω, enter the orbit time t；Orbital tracking schematic diagram is referring to fig. 2.
(3) deviation of every group of orbital tracking value, including perigee altitude deviation delta H are calculatedp, orbital period deviation delta T, rail
Road inclination deviation delta i, argument of perigee deviation delta ω, right ascension of ascending node deviation delta Ω, time deviation of entering the orbit Δ t.
ΔHp=Hp-Hpr
Δ T=T-Tr
Δ i=i-ir
Δ ω=ω-ωr
Δ Ω=Ω-Ωr
Δ t=t-tr
Wherein, Hpr、Tr、i、ωr、Ωr、trIt is perigee altitude, orbital period, orbit inclination angle, the near-earth under standard trajectory
Point argument, right ascension of ascending node, time of entering the orbit, calculate according to the normal trajectory of design and obtain.
(4) nondimensionalization processing is carried out to the deviation of every group of orbital tracking value.The specific method is as follows:
Wherein, Δ Hpr、ΔTr、Δir、Δωr、ΔΩr、ΔtrFor corresponding technical requirement maximum allowable offset；uhp、
uT、ui、uω、uΩ、utIndicate nondimensional perigee altitude deviation, orbital period deviation, orbit inclination angle deviation, argument of perigee
Deviation, right ascension of ascending node deviation, time deviation of entering the orbit are the preliminary parameters of subsequent processing.
(5) judge dimensionless treated that deviation is greater than 1 situation with the presence or absence of absolute value, directly sentence if presence and do not conform to
Otherwise lattice enter step (6)；
(6) it averages m, standard deviation sigma to every group of deviation.The specific method is as follows:
Wherein, n is the number of the orbital tracking value of terminal required precision, usually 6.
(7) multiple target equalization target function constructs.
(8) the smallest one group of Guidance Parameter of the corresponding target function value L of more every group of parameter, selection target functional value L is made
For final design parameter.
Guidance Parameter is rule of thumb adjusted repeatedly for designer, and present invention introduces optimization algorithms, and provide one kind
Balanced multi-objective restriction objective function.A kind of optimization method of Guidance Parameter provided by the invention, specific calculating process are as follows:
(1) according to task, Guidance Equation is established using existing method；
(2) Guidance Parameter initial value is arranged according to selected optimization algorithm, established Guidance Equation is emulated respectively,
Obtain the orbital tracking value that multiple groups have terminal required precision, including perigee altitude Hp, it is orbital period T, orbit inclination angle i, close
Place argument ω, right ascension of ascending node Ω, enter the orbit time t；
(3) deviation of every group of orbital tracking value, including perigee altitude deviation delta H are calculatedp, orbital period deviation delta T, rail
Road inclination deviation delta i, argument of perigee deviation delta ω, right ascension of ascending node deviation delta Ω, time deviation of entering the orbit Δ t.
ΔHp=Hp-Hpr
Δ T=T-Tr
Δ i=i-ir
Δ ω=ω-ωr
Δ Ω=Ω-Ωr
Δ t=t-tr
Wherein, Hpr、Tr、i、ωr、Ωr、trIt is perigee altitude, orbital period, orbit inclination angle, the near-earth under standard trajectory
Point argument, right ascension of ascending node, time of entering the orbit, calculate according to the normal trajectory of design and obtain.
(4) nondimensionalization processing is carried out to the deviation of every group of orbital tracking value.The specific method is as follows:
Wherein, Δ Hpr、ΔTr、Δir、Δωr、ΔΩr、ΔtrFor corresponding technical requirement maximum allowable offset；uhp、
uT、ui、uω、uΩ、utIndicate nondimensional perigee altitude deviation, orbital period deviation, orbit inclination angle deviation, argument of perigee
Deviation, right ascension of ascending node deviation, time deviation of entering the orbit are the preliminary parameters of subsequent processing.
(5) judge dimensionless treated that deviation is greater than 1 situation with the presence or absence of absolute value, directly sentence if presence and do not conform to
Otherwise lattice enter step (6)；
(6) it averages m, standard deviation sigma to every group of deviation.The specific method is as follows:
Wherein, n is the number of the orbital tracking value of terminal required precision, usually 6.
(7) multiple target balance optimizing objective function is constructed.Its maximum value should be no more than 2, and it is smaller show guidance system essence
It spends higher.
s.t|ΔHp|-|ΔHpr|≤0
|ΔT|-|ΔTr|≤0
|Δi|-|Δir|≤0
|Δω|-|Δωr|≤0
|ΔΩ|-|ΔΩr|≤0
|Δt|-|Δtr|≤0
(8) it using multiple target balance optimizing objective function as the objective function in optimization algorithm, is carried out using optimization algorithm
Iterative solution sets the condition of convergence until meeting, the Guidance Parameter after obtaining one group of optimization.
Genetic algorithm, particle swarm algorithm, ant group algorithm etc. can be used in the optimization algorithm.Optimization method of the invention,
By carrying out equilibrium to every terminal precision index, synthetically handling, the objective function in optimization algorithm is constructed, and then obtain excellent
Guidance Parameter after change.Can be applied to the Master System Design stage to specified point, have specific targets constrain carrier rocket enter the orbit
Accuracy assessment, the design of Guidance Parameter.Also low rail reenters the change rail precision for returning to aircraft in orbit aerocraft, space in can be used for
Evaluation, the design of Guidance Parameter.
The above, optimal specific embodiment only of the invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.
The content that the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (11)
1. a kind of preferred method of Guidance Parameter, which comprises the steps of:
(1) according to task, Guidance Equation is established；
(2) multiple groups Guidance Parameter is set, established Guidance Equation is emulated respectively, obtains the rail that multiple groups have required precision
Road radical value；
(3) deviation of every group of orbital tracking value and required standard value is calculated；
(4) nondimensionalization processing is carried out to the deviation of calculating；
(5) judge dimensionless treated that deviation is greater than 1 situation with the presence or absence of absolute value, directly sentence if presence it is unqualified,
Otherwise (6) are entered step；
(6) it averages m, standard deviation sigma to the deviation of every group of nondimensionalization；
(7) multiple target equalization target function is constructed:
(8) the smallest one group of Guidance Parameter of the corresponding target function value L of more every group of parameter, selection target functional value L.
2. the preferred method of Guidance Parameter as described in claim 1, which is characterized in that have precision described in step (2)
It is required that orbital tracking value be perigee altitude Hp, orbital period T, orbit inclination angle i, argument of perigee ω, right ascension of ascending node Ω,
Enter the orbit time t.
3. the preferred method of Guidance Parameter as claimed in claim 2, which is characterized in that deviation described in step (3) includes
Perigee altitude deviation delta Hp, orbital period deviation delta T, orbit inclination angle deviation delta i, argument of perigee deviation delta ω, ascending node
Right ascension deviation delta Ω, time deviation of entering the orbit Δ t, calculation method are as follows:
ΔHp=Hp-Hpr
Δ T=T-Tr
Δ i=i-ir
Δ ω=ω-ωr
Δ Ω=Ω-Ωr
Δ t=t-tr
Wherein, Hpr、Tr、i、ωr、Ωr、trIt is perigee altitude, orbital period, orbit inclination angle, the perigee width under standard trajectory
Angle, is entered the orbit the time at right ascension of ascending node.
4. the preferred method of Guidance Parameter as claimed in claim 3, which is characterized in that in step (4) to the deviation of calculating into
The specific method is as follows for the processing of row nondimensionalization:
Wherein, Δ Hpr、ΔTr、Δir、Δωr、ΔΩr、ΔtrFor technical requirement maximum allowable offset；uhp、uT、ui、uω、
uΩ、utIt indicates nondimensional perigee altitude deviation, orbital period deviation, orbit inclination angle deviation, argument of perigee deviation, rise and hand over
Point right ascension deviation, time deviation of entering the orbit.
5. the preferred method of Guidance Parameter as claimed in claim 4, which is characterized in that every group of nondimensionalization in step (6)
Deviation average that the specific method is as follows for m, standard deviation sigma:
Wherein, n is the number of the orbital tracking value of terminal required precision.
6. a kind of optimization method of Guidance Parameter, which comprises the steps of:
(1) according to task, Guidance Equation is established；
(2) Guidance Parameter initial value is arranged according to selected optimization algorithm, established Guidance Equation is emulated respectively, obtained
Multiple groups have the orbital tracking value of required precision；
(3) deviation of every group of orbital tracking value and required standard value is calculated；
(4) nondimensionalization processing is carried out to the deviation of calculating；
(5) judge dimensionless treated that deviation is greater than 1 situation with the presence or absence of absolute value, directly sentence if presence it is unqualified,
Otherwise (6) are entered step；
(6) it averages m, standard deviation sigma to the deviation of every group of nondimensionalization；
(7) multiple target balance optimizing objective function is constructed:
(8) it using multiple target balance optimizing objective function as the objective function in optimization algorithm, is iterated using optimization algorithm
It solves, sets the condition of convergence until meeting, the Guidance Parameter after obtaining one group of optimization.
7. the optimization method of Guidance Parameter as claimed in claim 6, which is characterized in that have precision described in step (2)
It is required that orbital tracking value be perigee altitude Hp, orbital period T, orbit inclination angle i, argument of perigee ω, right ascension of ascending node Ω,
Enter the orbit time t.
8. the optimization method of Guidance Parameter as claimed in claim 7, which is characterized in that deviation described in step (3) includes
Perigee altitude deviation delta Hp, orbital period deviation delta T, orbit inclination angle deviation delta i, argument of perigee deviation delta ω, ascending node
Right ascension deviation delta Ω, time deviation of entering the orbit Δ t, calculation method are as follows:
ΔHp=Hp-Hpr
Δ T=T-Tr
Δ i=i-ir
Δ ω=ω-ωr
Δ Ω=Ω-Ωr
Δ t=t-tr
Wherein, Hpr、Tr、i、ωr、Ωr、trIt is perigee altitude, orbital period, orbit inclination angle, the perigee width under standard trajectory
Angle, is entered the orbit the time at right ascension of ascending node.
9. the optimization method of Guidance Parameter as claimed in claim 8, which is characterized in that in step (4) to the deviation of calculating into
The specific method is as follows for the processing of row nondimensionalization:
Wherein, Δ Hpr、ΔTr、Δir、Δωr、ΔΩr、ΔtrFor corresponding technical requirement maximum allowable offset；uhp、uT、
ui、uω、uΩ、utIndicate that nondimensional perigee altitude deviation, orbital period deviation, orbit inclination angle deviation, argument of perigee are inclined
Difference, right ascension of ascending node deviation, time deviation of entering the orbit.
10. the optimization method of Guidance Parameter as claimed in claim 9, which is characterized in that every group of nondimensionalization in step (6)
Deviation average that the specific method is as follows for m, standard deviation sigma:
Wherein, n is the number of the orbital tracking value of terminal required precision.
11. the optimization method of Guidance Parameter as claimed in claim 10, which is characterized in that the optimization algorithm is calculated using heredity
Method, particle swarm algorithm or ant group algorithm.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111210167A (en) * | 2020-02-20 | 2020-05-29 | 山东鲁阳浩特高技术纤维有限公司 | Method for regulating and controlling aluminum oxide fiber blanket blank |
| CN113734468A (en) * | 2021-08-30 | 2021-12-03 | 北京宇航系统工程研究所 | Orbital plane accurate control method based on iterative guidance |
| CN118094779A (en) * | 2024-04-23 | 2024-05-28 | 西安现代控制技术研究所 | Guided rocket large airspace glide increase Cheng Dandao optimization method based on ant colony algorithm |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030228867A1 (en) * | 2002-01-29 | 2003-12-11 | David Castiel | Virtually geostationary satellite array with optimized parameters |
| US20120053764A1 (en) * | 2010-08-30 | 2012-03-01 | King Fahd University Of Petroleum And Minerals | Particle swarm-based micro air launch vehicle trajectory optimization method |
| CN106250625A (en) * | 2016-07-29 | 2016-12-21 | 北京航天自动控制研究所 | A kind of optimization method of spacecraft interative guidance |
| CN106707758A (en) * | 2017-02-16 | 2017-05-24 | 北京航天自动控制研究所 | Autonomous orbit reprogramming method of spaceflight aircraft |
| CN106892136A (en) * | 2017-02-16 | 2017-06-27 | 北京航天自动控制研究所 | A kind of aerospace craft metro planning method based on world communication |
| CN107092731A (en) * | 2017-04-05 | 2017-08-25 | 北京临近空间飞行器系统工程研究所 | Specific thrust trajectory Integrated Optimization between sub-orbital booster level |
| CN107798187A (en) * | 2017-10-24 | 2018-03-13 | 北京理工大学 | A kind of efficiently satellite constellation Multipurpose Optimal Method |
-
2018
- 2018-07-16 CN CN201810779762.4A patent/CN108984903B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030228867A1 (en) * | 2002-01-29 | 2003-12-11 | David Castiel | Virtually geostationary satellite array with optimized parameters |
| US20120053764A1 (en) * | 2010-08-30 | 2012-03-01 | King Fahd University Of Petroleum And Minerals | Particle swarm-based micro air launch vehicle trajectory optimization method |
| CN106250625A (en) * | 2016-07-29 | 2016-12-21 | 北京航天自动控制研究所 | A kind of optimization method of spacecraft interative guidance |
| CN106707758A (en) * | 2017-02-16 | 2017-05-24 | 北京航天自动控制研究所 | Autonomous orbit reprogramming method of spaceflight aircraft |
| CN106892136A (en) * | 2017-02-16 | 2017-06-27 | 北京航天自动控制研究所 | A kind of aerospace craft metro planning method based on world communication |
| CN107092731A (en) * | 2017-04-05 | 2017-08-25 | 北京临近空间飞行器系统工程研究所 | Specific thrust trajectory Integrated Optimization between sub-orbital booster level |
| CN107798187A (en) * | 2017-10-24 | 2018-03-13 | 北京理工大学 | A kind of efficiently satellite constellation Multipurpose Optimal Method |
Non-Patent Citations (1)
| Title |
|---|
| 李超兵 等: ""一种基于轨道根数约束的最优制导方法"", 《航空学报》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111210167A (en) * | 2020-02-20 | 2020-05-29 | 山东鲁阳浩特高技术纤维有限公司 | Method for regulating and controlling aluminum oxide fiber blanket blank |
| CN111210167B (en) * | 2020-02-20 | 2023-06-20 | 山东鲁阳浩特高技术纤维有限公司 | Regulation and control method of alumina fiber blanket blank |
| CN113734468A (en) * | 2021-08-30 | 2021-12-03 | 北京宇航系统工程研究所 | Orbital plane accurate control method based on iterative guidance |
| CN118094779A (en) * | 2024-04-23 | 2024-05-28 | 西安现代控制技术研究所 | Guided rocket large airspace glide increase Cheng Dandao optimization method based on ant colony algorithm |
| CN118094779B (en) * | 2024-04-23 | 2024-07-12 | 西安现代控制技术研究所 | Guided rocket large airspace glide increase Cheng Dandao optimization method based on ant colony algorithm |
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