CN106508029B - A kind of spacecraft dynamics parametric synthesis discrimination method - Google Patents
A kind of spacecraft dynamics parametric synthesis discrimination methodInfo
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- CN106508029B CN106508029B CN201010052890.2A CN201010052890A CN106508029B CN 106508029 B CN106508029 B CN 106508029B CN 201010052890 A CN201010052890 A CN 201010052890A CN 106508029 B CN106508029 B CN 106508029B
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- 238000012850 discrimination method Methods 0.000 title claims description 6
- 230000015572 biosynthetic process Effects 0.000 title claims description 5
- 238000003786 synthesis reaction Methods 0.000 title claims description 5
- 238000000034 method Methods 0.000 claims abstract description 30
- 230000008569 process Effects 0.000 claims abstract description 16
- 230000001133 acceleration Effects 0.000 claims description 14
- 238000013519 translation Methods 0.000 claims description 14
- 239000003380 propellant Substances 0.000 claims description 11
- 230000010354 integration Effects 0.000 claims description 6
- 238000009825 accumulation Methods 0.000 claims description 5
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- 230000008450 motivation Effects 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims description 2
- 230000008030 elimination Effects 0.000 claims 1
- 238000003379 elimination reaction Methods 0.000 claims 1
- 238000012545 processing Methods 0.000 claims 1
- 230000035772 mutation Effects 0.000 abstract description 22
- 230000008859 change Effects 0.000 abstract description 14
- 230000008878 coupling Effects 0.000 abstract description 6
- 238000010168 coupling process Methods 0.000 abstract description 6
- 238000005859 coupling reaction Methods 0.000 abstract description 6
- 238000010304 firing Methods 0.000 description 7
- 238000012360 testing method Methods 0.000 description 7
- 241000208340 Araliaceae Species 0.000 description 3
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 3
- 235000003140 Panax quinquefolius Nutrition 0.000 description 3
- 235000008434 ginseng Nutrition 0.000 description 3
- 230000001052 transient effect Effects 0.000 description 3
- 238000005266 casting Methods 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000010606 normalization Methods 0.000 description 2
- 238000007476 Maximum Likelihood Methods 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
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Abstract
本发明公开了一种综合利用质量突变与发动机开关机信息的航天器动力学参数综合辨识方法。综合利用航天器飞行过程中的质量突变与发动机开关机的推力变化信息；利用已知的质量突变信息及相应观测数据实现动力学参数的独立辨识；建立包含质量突变与发动机开关机信息的动力学模型描述整个过程中航天器的飞行；依此进行航天器动力学参数的辨识。该方法可利用更长时间段的观测数据估计参数，有效解决或缓解参数耦合、分布求解误差、观测数据有效信息不足的问题，参数估值更加稳定与准确。
The invention discloses a method for comprehensively identifying dynamic parameters of a spacecraft by comprehensively utilizing the information of mass mutation and engine on/off. Comprehensively utilize the information of the mass mutation and the thrust change information of the engine switching on and off during the flight of the spacecraft; use the known mass mutation information and corresponding observation data to realize the independent identification of dynamic parameters; The model describes the flight of the spacecraft during the whole process; based on this, the dynamic parameters of the spacecraft are identified. This method can use observation data for a longer period of time to estimate parameters, effectively solve or alleviate the problems of parameter coupling, distribution solution errors, and insufficient effective information of observation data, and make parameter estimation more stable and accurate.
Description
Technical field
Caused quality mutation is cast aside the present invention relates to annex during one kind comprehensive utilization spacecraft flight with tail-off machine to believe
The comprehensive discrimination method of the kinetic parameter of breath.
Background technology
In the Parameter Estimation Problem based on spacecraft movable information, if spacecraft thrust parameter, initial mass parameter, quality stream
Amount parameter is unknown, because the multiplying property of parameter is coupled, is only capable of estimating the ratio between parameter, it is impossible to independently pick out foregoing ginseng
Quality mutation excitation can be produced by casting the behavior of known quality appurtenances during number, spacecraft flight aside rapidly in short-term, and this can lead
Cause the acceleration suffered by object to there is a mutation, contribute to realize that the independent of spacecraft dynamics parameter is recognized using this information,
Meanwhile, stress change caused by the suddenly change or tail-off machine of quality (inertia) characteristic can all cause to include and wait to estimate
The change of the kinetics equation concrete form of mechanics parameter, is recognized past from the segmentation parameter of the equation progress of these concrete forms
Enlarging-Errors, estimation parameter are caused to be that optimal in the short period is estimated using insufficient, parameter distributed problem solving toward existence information
Meter (under estimation criterion meaning) the problems such as, set up to be mutated comprising quality and described with the kinetics equation of tail-off machine information
The flight of spacecraft in whole process, effectively using the observation information of longer time section, is conducive to improving parameter identification result.
Parameter identification problem based on flight dynamics model, due to kinetic model structure, (acceleration=power/quality, angle accelerates
Degree=torque/inertia) determined by physics law, it is likely encountered following point when carrying out parameter identification：
1 multiplying property of parameter is coupled
The coupling of multiplying property of parameter, which refers to two parameters in kinetics equation, can turn to the form for being multiplied or being divided by.
In following equation：
Wherein, F is thrust parameter, m1For initial mass parameter, m ' is mass flow parameter, and t is the time.
For the inflight phase described with the equation, no matter how many includes the observed quantity of acceleration information, can not all estimate simultaneously
Go out thrust parameter, initial mass parameter and mass flow parameter, be only capable of estimating the ratio of three.
2 parameter additivitys are coupled
The coupling of parameter additivity, which refers to two parameters in kinetics equation, can turn to the form for being added or subtracting each other.
In following equation：
Wherein, F1, F2For thrust parameter, m0For initial mass parameter, m1', m2' it is mass flow parameter, t is the time,
k1, k2, k3, k4For parameter coefficient, the change for describing thrust, flow integration amount.If coefficient k1, k2Or k3, k4Change always
It is identical or closely, then thrust or flow parameter are difficult to differentiate between in identification problem.
3 distributed problem solving errors
In particular problem, from comprising when the calculating of specific kinetic model concrete form of kinetic parameter is estimated often not
The whole parameter to be estimated of explicit physical meaning can be obtained, distributed problem solving need to introduce intermediate parameters or substitute into previous step estimation parameter value
Next step, which is calculated, to be continued to solve, because the influence of various errors can cause intermediate parameters or upper step parameter estimation to have deviation, further
Using intermediate parameters or the other parameters to be estimated of upper step parametric solution, error can be propagated and may expanded.
4 observation data effective informations are not enough
When the spacecraft inflight phase flight time is too short or section interference is relatively large, the identification kinetic model relative to foundation is seen
The effective information surveyed in data may be not enough, and parametric stability can be caused poor, estimate results contrast is scattered.
Such as to certain rocket trip machine work independently section carry out parameter identification when, because this section of flight time is shorter, at the same interference relative to
Thrust acceleration is larger, using the time interval being slightly different, estimate parameter differences are larger.
The content of the invention
Caused quality mutation and engine are cast aside it is an object of the invention to provide annex during one kind comprehensive utilization spacecraft flight
Switch the spacecraft dynamics parameter identification method of machine information.
The technical scheme is that：This method is specifically included：
(1) the quality mutation during comprehensive utilization spacecraft flight and the thrust variation information of tail-off machine；
(2) the independent identification of kinetic parameter is realized using known quality abrupt information and corresponding observation data；
(3) set up to be mutated comprising quality and describe flying for spacecraft in whole process with the kinetic model of tail-off machine information
OK；
(4) the problem of there is bigger difference for quality mutation, the modeling of tail-off machine transient process and practical flight, adopts
Measure is taken to eliminate its influence：If observed quantity is directly acceleration information, the data with changeover portion are kept away；If observed quantity is to include acceleration
The integration amount of information is spent, new state variable initial parameter is introduced, effectively eliminates the deviation accumulation effect of integral and calculating；
(5) identification of spacecraft dynamics parameter is carried out.
This method preferably make use of the information of dynamics change during spacecraft flight, and promote kinetic parameter has
The problem of imitating identification, solution or the coupling of alleviation parameter, distributed problem solving error, observation data effective information deficiency, effectively utilization
Observation data in longer time obtain the optimal estimation of parameter.
Introduce first in identification problem contributes to the independence for realizing kinetic parameter to recognize using spacecraft mass abrupt information, then says
It is bright to set up the method for being mutated comprising quality and carrying out spacecraft dynamics parameter identification with the kinetic model of tail-off machine information.
In translation dynamics, introducing appurtenances, which cast caused quality abrupt information aside, in the denominator can solve molecule thrust parameter
With the multiplying property coupled problem of denominator mass parameter, effective identification of parameter is realized；Equally, in rotational power equation, dividing
Inertia abrupt information caused by structural form change is introduced in mother can solve molecule thrust (square) parameter and denominator (quality) inertia
The multiplying property coupled problem of parameter, realizes effective identification of parameter.
Consider in t2There is the translation kinetic model of known quality Sudden Changing Rate Δ m spacecraft in the moment：
Wherein, F is thrust parameter, m1, m2Respectively t1, t2The mass parameter at moment, m ' is mass flow parameter, and t is
Time, t2At the time of point, F, m are cast aside for spacecraft appurtenances1, m2, m ' is parameter to be estimated.To first equation
It can estimateWithTwo equations can be estimatedWithBy relationship between quality m0-m′(t2-t1)-Δ m=m1Achievable pair
The estimation of flow parameter：And then thrust parameter, initial mass parameter can be realized
Estimation.
Above-mentioned solution can obtain two groupsParametric results, the mode for preferably utilizing spacecraft annex to cast information aside is to set up inclusion
The kinetic model of weight abrupt information：
Wherein, F is thrust parameter, m1For initial mass parameter, m ' is mass flow parameter, and Δ m is cast aside for appurtenances to be drawn
The quality knots modification risen, t is time variable, t1Certain stabilized flight moment point, t before being cast aside for selected spacecraft annex2For space flight
Device appurtenances cast at the time of point, t aside3Certain stabilized flight moment point after being cast aside for selected spacecraft annex, Step () is step
Function, the quality mutation of description object.
(2) formula of analysis, has broken the multiplying property of thrust to be estimated with mass parameter to the utilization for being mutated quality information and has coupled, can
Realize estimation to thrust parameter and mass flow parameter, it is to avoid the error propagation of distributed problem solving process intermediate parameters, effectively profit
More rational parameter estimation is obtained with the observation data of longer time.
Equally, for there is the spacecraft flight process of tail-off machine, it can also set up comprising tail-off machine information
Kinetic model is recognized to relevant parameter.
Consider in t2Moment engine 1 shuts down, and (herein for convenience, it is assumed that being preferable shutdown, that is, shut down moment thrust, stream
Quantitative change is kinetic model 0)：
Wherein, F1, F2Respectively engine 1,2 thrust parameter, m1, m2Respectively t1, t2The initial mass ginseng at moment
Number, m1', m2' be respectively engine 1,2 mass flow parameter, t is time variable, t1Thrown for selected spacecraft annex
From preceding certain stabilized flight moment point, t2For the shutdown moment point of engine 1, t3Certain is stable winged after being cast aside for selected spacecraft annex
Row moment point.
From two kinetics equation carry out parameter identifications of above-mentioned (4) formula, no matter parameter Estimation is proceeded by from that,
Obtained result is all that the optimal estimation of parameters of data is observed using shorter time period, sets up dynamic comprising tail-off machine information
Mechanical model：
Wherein F1, F2Respectively engine 1,2 thrust parameter, m1For t1The initial mass parameter at moment, m1', m2' respectively
For the mass flow parameter of engine 1,2, t is time variable, t1Certain stabilized flight before being cast aside for selected spacecraft annex
Moment point, t2For the shutdown moment point of engine 1, t3Certain stabilized flight moment point after being cast aside for selected spacecraft annex, Step ()
For jump function, k1To describe the thrust coefficient of the thrust variation of engine 1, k2To describe the thrust system of the thrust variation of engine 2
Number, is k3The discharge coefficient that engine 1 discharges propellant gross mass, k are described4For the description discharge propellant gross mass of engine 2
Discharge coefficient.
Coefficient in kinetic model (5) includes the shutdown information of engine 1, distinguishes difference using the different working times and starts
Thrust parameter and flow parameter between machine, effectively obtain parameter using the observation data of longer time section and more reasonably estimate.
According to the kinetic model (2) comprising spacecraft mass abrupt information and include the kinetic model of tail-off machine information
(5), setting up the kinetic model comprising mass of object mutation and tail-off machine information, (annex is cast aside, engine cutoff is equal
Described using ideal model)：
Wherein F1, F2Respectively engine 1,2 thrust parameter, m1For t1The initial mass parameter at moment, m1', m2' respectively
For the mass flow parameter of engine 1,2, Δ m casts caused quality knots modification aside for appurtenances, and t is time variable, t1For
Selected spacecraft annex casts preceding certain stabilized flight moment point, t aside2The time cast aside for spacecraft appurtenances, t3For engine 1
Shutdown moment point, t4Certain stabilized flight moment point after being cast aside for selected spacecraft annex, Step () is jump function, k1For
The thrust coefficient of the thrust variation of engine 1, k are described2To describe the thrust coefficient of the thrust variation of engine 2, k3Start for description
Machine 1 discharges the discharge coefficient of propellant gross mass, k4The discharge coefficient of propellant gross mass is discharged for description engine 2.
The kinetic model comprising quality abrupt information and tail-off machine process set up can be translation kinetic model or turn
Dynamic kinetic model, is targetedly modeled as the case may be.It should be noted that for attached in translation kinetic model
Category part casts caused quality abrupt information aside and assume that centroid position instantaneously completes change, does not influence in translation kinetics equation
Thrust and quality；But for rotational power model, spacecraft annex casts the change of caused barycenter aside and can change rotational power
The moment of thrust and mass inertia in equation are learned, needs to consider amendment during modeling.
Spacecraft mass mutation and tail-off machine information are contained in the kinetic model of foundation, wherein being mutated quality with sending out
The model that motivation switching on and shutting down transient process is set up and the possible difference of Live Flying are larger, such as engine start practical flight thrust curve
It is larger with hot-firing test data gap.For physical quantity of the observed quantity for measurement spacecraft translation information, translation kinetic model is set up
The problem of carrying out dynamic parameters identification, if observed quantity is directly acceleration information, keeps away the data with changeover portion, if observed quantity is
Integration amount comprising acceleration information, set up another after changeover portion time point be integrated calculating eliminate error accumulation influence, while shape
State variable initial value can also be used as parameter to be estimated.For physical quantity of the observed quantity for measurement spacecraft rotation information, rotational power is set up
The problem of model carries out dynamic parameters identification is learned, processing method is similar.
What method was set up is not suitable for kinetic parameter comprising quality abrupt information and the kinetic model of tail-off machine process
On-line Estimation, is only applicable to the parameter Estimation focused on afterwards.
What method was set up is only the kinetic model with tail-off machine process comprising quality abrupt information, when carrying out parameter Estimation
Need to focus on method afterwards using least square method or maximum-likelihood method etc..
In being mutated comprising spacecraft mass in the kinetic model with tail-off machine information, it is necessary to spacecraft mass for foundation
Mutation is described with tail-off machine behavior, and the coefficient of Model Parameter will be used to express these information.Describing mode can be adopted
With ideal model or the model based on priori, it is mutated below with quality, tail-off machine thrust, tail-off machine stream
Introduced exemplified by the description of amount.
The coefficient k of parameter will not necessarily provide analytical expression, be obtained also by numerical computations.
Quality mutation description：
Mutation quality is described using jump function, coefficient k=Step (t2), then k~t curves such as Fig. 1：
Tail-off machine thrust is described：
Perfect switch machine model, coefficient k=Step (t can be used to motor power1)-Step(t2), then k~t curves such as Fig. 2；
In addition, coefficient k~t can be built by starting shutdown hot-firing test data or engine start shutdown empirical equation using engines ground
Curve, so that using exemplified by hot-firing test data, then k~t curves are such as Fig. 3；
Tail-off machine flow is described：
To engine mass-flow rate of propellant, described according to perfect switch machine model, then propellant normalization flow is closed with the time
System such as Fig. 4；
In kinetics equation, the propellant flow rate coefficient k~t curves such as Fig. 5 that can be asked is integrated；
It is described with reference to hot-firing test data, then propellant normalization flow and time relationship such as Fig. 6；
In kinetics equation, the propellant flow rate coefficient k~t curves such as Fig. 7 that can be asked are integrated
The advantage of the invention is that：
1st, contribute to realize that the independent of kinetic parameter is recognized using the quality abrupt information during spacecraft flight；
2nd, the effective identification for promoting kinetic parameter with the kinetic model of tail-off machine information comprising quality mutation is set up,
Error propagation expands caused by avoiding distributed problem solving, and the optimal estimation of parameter is effectively obtained using the observation data in the longer time；
3rd, the kinetics equation comprising spacecraft mass abrupt information and tail-off machine process set up can be translation dynamics
Equation or rotational power equation；
4th, the problem of there is bigger difference for quality mutation, the modeling of tail-off machine transient process and practical flight, if seeing
Measurement is directly acceleration information, keeps away and uses transition segment data；If observed quantity is the integration amount comprising acceleration information, introduce newly
State variable initial parameter can effectively eliminate the deviation accumulation effect of integral and calculating.
5th, in the kinetic model comprising spacecraft mass abrupt information set up, if initial mass (inertia), flow and thrust
Parameter to be estimated is, appurtenances cast the estimation that caused quality (inertia) abrupt information can be used for realizing aforementioned parameters aside.It is real
On border, if initial mass (inertia), flow and thrust it is any, it is known that mutation quality (inertia) can also serve as parameter progress
Estimation.
6th, set up the kinetic model comprising quality abrupt information in, using quality (inertia) abrupt information realization to thrust,
The estimation of flow parameter, if quality (inertia) Sudden Changing Rate contains δ relative error, can cause the thrust parameter and quality estimated
The flow parameter also relative error containing δ, but not influence the ratio of the two, thus the ratio parameter (specific impulse) estimated be can
Letter.
This method sets up the kinetic model comprising spacecraft mass mutation with tail-off machine information, effectively utilizes the longer time
The observation data estimation parameter of section, solves or alleviates parameter coupling, distributed problem solving error, observation data effective information deficiency are asked
Topic, parameter estimation is more stablized and accurate.
Brief description of the drawings
Fig. 1 is quality mutation description schematic diagram；
Fig. 2 is ideal engine switching on and shutting down thrust coefficient curve map；
Fig. 3 is the tail-off machine thrust coefficient curve map based on hot-firing test data；
Fig. 4 is ideal engine switching on and shutting down flow normalized curve figure；
Fig. 5 is ideal engine switching on and shutting down discharge coefficient curve map；
Fig. 6 is the tail-off machine flow normalized curve figure based on hot-firing test data；
Fig. 7 is the tail-off machine discharge coefficient curve map based on hot-firing test data.
Embodiment
The application of the present invention：
1 has the dynamic parameters identification for the rocket flight section that radome fairing is cast aside
The kinetic model for casting information aside comprising radome fairing is set up, caused quality abrupt information is cast aside using radome fairing and distinguishes thrust
The ratio of parameter and mass flow parameter, thrust and mass flow parameter is specific impulse parameter.
2 have main frame, the dynamic parameters identification of the rocket flight section of slave shutdown
Set up and include main frame, the kinetic model of slave shutdown information, the different time mainly worked using main frame, slave is distinguished
Main frame thrust and slave thrust parameter, the different time worked using main frame, slave distinguish main frame and the flow parameter of slave, main
Machine is corresponding specific impulse parameter with the ratio of mass flow parameter with secondary thrust.
3 have the dynamic parameters identification of the spacecraft posture adjustment section of attitude control engine co-ordination
The kinetic model for including attitude control engine co-ordination information is set up, the different time worked using attitude control engine is distinguished
Thrust and flow parameter between different engines.
4 other spacecraft dynamics parameter identification problems for meeting method and thought.
The kinetic model comprising quality abrupt information and tail-off machine process set up can be translation kinetic model or turn
Dynamic kinetic model, is targetedly modeled as the case may be.
Caused quality abrupt information is cast aside for appurtenances assume that centroid position instantaneously completes to change in translation kinetic model
Become, the thrust and quality in translation kinetics equation are not influenceed；But for rotational power model, object structures metamorphosis draws
The barycenter change risen can change the moment of thrust and mass inertia in rotational power equation.
In the kinetic model comprising quality abrupt information set up, wait to estimate ginseng if initial mass (inertia), flow and thrust are
Number, appurtenances cast the estimation that caused quality (inertia) abrupt information can be used for realizing aforementioned parameters aside.If in fact, just
Prothyl amount (inertia), flow and thrust is any, it is known that mutation quality (inertia) can also serve as parameter and be estimated.
In the kinetic model comprising quality abrupt information set up, realized using quality (inertia) abrupt information to thrust, stream
The estimation of parameter is measured, if quality (inertia) Sudden Changing Rate contains δ relative error, the thrust parameter and quality stream estimated can be caused
The parameter also relative error containing δ, but not influence the ratio of the two is measured, therefore the ratio parameter (specific impulse) estimated is credible
's.
The kinetic model of foundation is directed to comprising quality mutation and the spacecraft flight overall process of tail-off machine, and it is not suitable for
On-line Estimation, is only applicable to the parameter Estimation focused on afterwards.
Contribute to realize the independent identification of kinetic parameter using the quality abrupt information during spacecraft flight, foundation is included
Quality abrupt information and the kinetic model of tail-off machine process, using the observation data estimation parameter of longer time section,
Effective solution alleviates parameter coupling, distributed problem solving error, observes the problem of data effective information is not enough, and parameter estimation is more steady
It is fixed and accurate.
Claims (3)
1. a kind of spacecraft dynamics parametric synthesis discrimination method, it is characterised in that this method is specifically included：
(1) quality information and tail-off machine information during comprehensive utilization spacecraft flight；
(2) the independent identification of kinetic parameter is realized using known quality information and corresponding observation data；
(3) set up the kinetic model comprising quality information and tail-off machine information and describe flying for spacecraft in whole process
OK；The kinetic model is：
k1=1-Step (t2)
k2=1
k4=t-t1
Wherein F1, F2Respectively engine 1,2 thrust parameter, m1For t1The initial mass parameter at moment, m1', m2' respectively
For the mass flow parameter of engine 1,2, Δ m casts caused quality knots modification aside for appurtenances, and t is time variable, t1For
Selected spacecraft annex casts preceding certain stabilized flight moment point, t aside2At the time of point, t are cast aside for spacecraft appurtenances3To start
The shutdown moment point of machine 1, t4Certain stabilized flight moment point after being cast aside for selected spacecraft annex, Step () is jump function, k1
To describe the thrust coefficient of the thrust variation of engine 1, k2To describe the thrust coefficient of the thrust variation of engine 2, k3For description hair
Motivation 1 discharges the discharge coefficient of propellant gross mass, k4The discharge coefficient of propellant gross mass is discharged for description engine 2；
(4) the problem of there is bigger difference for quality information, the modeling of tail-off machine information and practical flight, takes and arranges
Applying elimination, it influences：If observed quantity is directly acceleration information, the data with changeover portion are kept away；If observed quantity is comprising acceleration letter
The integration amount of breath, introduces new state variable initial parameter, effectively eliminates the deviation accumulation effect of integral and calculating；
(5) identification of spacecraft dynamics parameter is carried out.
2. a kind of spacecraft dynamics parametric synthesis discrimination method according to claim 1, it is characterised in that foundation is included
The kinetic model of quality information and tail-off machine information is translation kinetic model or rotational power model.
3. a kind of spacecraft dynamics parametric synthesis discrimination method according to claim 1, it is characterised in that to quality information
The problem of model and the larger possible difference of Live Flying for being set up with tail-off machine information, has carried out effective processing：For observation
Measure to measure the physical quantity of spacecraft translation information, set up the problem of translation kinetic model carries out dynamic parameters identification, if seeing
Measurement is directly acceleration information, keeps away the data with changeover portion, if observed quantity is the integration amount comprising acceleration information, in transition
Section after set up another time point be integrated calculating eliminate error accumulation influence, while state variable initial value is used as parameter to be estimated.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108516104A (en) * | 2018-03-12 | 2018-09-11 | 中国人民解放军国防科技大学 | Multi-stage carrier spacecraft separation reliability simulation platform |
| CN108760365A (en) * | 2018-05-21 | 2018-11-06 | 北京空间飞行器总体设计部 | Detector stress analogy method in a kind of soft landing experiment |
| CN109375515A (en) * | 2018-12-05 | 2019-02-22 | 北京航天自动控制研究所 | An online identification method of dynamic characteristics for online trajectory planning of vertical take-off and landing rockets |
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- 2010-12-16 CN CN201010052890.2A patent/CN106508029B/en not_active Expired - Fee Related
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108516104A (en) * | 2018-03-12 | 2018-09-11 | 中国人民解放军国防科技大学 | Multi-stage carrier spacecraft separation reliability simulation platform |
| CN108516104B (en) * | 2018-03-12 | 2020-02-21 | 中国人民解放军国防科技大学 | Multistage carrier spacecraft separation reliability simulation platform |
| CN108760365A (en) * | 2018-05-21 | 2018-11-06 | 北京空间飞行器总体设计部 | Detector stress analogy method in a kind of soft landing experiment |
| CN108760365B (en) * | 2018-05-21 | 2020-04-07 | 北京空间飞行器总体设计部 | Method for simulating stress state of detector in soft landing test |
| CN109375515A (en) * | 2018-12-05 | 2019-02-22 | 北京航天自动控制研究所 | An online identification method of dynamic characteristics for online trajectory planning of vertical take-off and landing rockets |
| CN109375515B (en) * | 2018-12-05 | 2021-07-13 | 北京航天自动控制研究所 | An online identification method of dynamic characteristics for online trajectory planning of vertical take-off and landing rockets |
| CN110807270A (en) * | 2019-11-13 | 2020-02-18 | 北京环境特性研究所 | Method for inverting engine parameters and predicting trajectory based on tail flame radiation line |
| CN110807270B (en) * | 2019-11-13 | 2023-09-29 | 北京环境特性研究所 | Method for inverting engine parameters and estimating trajectory based on tail flame radiation line type |
| CN114861320A (en) * | 2022-05-19 | 2022-08-05 | 北京航天飞行控制中心 | A spacecraft attitude control thrust modeling and orbit determination solution method |
| CN114861320B (en) * | 2022-05-19 | 2023-02-10 | 北京航天飞行控制中心 | Spacecraft attitude control thrust modeling and orbit determination resolving method |
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