CN103900559B  A kind of highprecision attitude resolving system based on Interference Estimation  Google Patents
A kind of highprecision attitude resolving system based on Interference Estimation Download PDFInfo
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 CN103900559B CN103900559B CN201410124597.0A CN201410124597A CN103900559B CN 103900559 B CN103900559 B CN 103900559B CN 201410124597 A CN201410124597 A CN 201410124597A CN 103900559 B CN103900559 B CN 103900559B
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Classifications

 G—PHYSICS
 G01—MEASURING; TESTING
 G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
 G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00  G01C19/00
 G01C21/20—Instruments for performing navigational calculations

 G—PHYSICS
 G01—MEASURING; TESTING
 G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
 G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
Abstract
A kind of highprecision attitude resolving system based on Interference Estimation, processes plate, realtime simulation target machine, gesture stability module and attitude information display module including attitude sensor, attitude information；Wherein attitude sensor is used for the attitude information that sensitive carrier is current, attitude information processes plate and receives the metric data of attitude sensor, use interference estimator and the antiinterference filtration algorithm of robust mixing multiple target wave filter, the original metric data received is filtered, it is met the attitude algorithm result of carrier required precision, and attitude algorithm information is sent to gesture stability module, realtime simulation target machine receives the gesture stability instruction that gesture stability module resolves, call actuator and the kinestate of attitude dynamics module simulation carrier, realize data display function by attitude information display module simultaneously.
Description
Technical field
The present invention relates to a kind of highprecision attitude resolving system based on Interference Estimation, can directly apply to aviation,
The gesture stability loop in the fields such as space flight, can determine as the attitude in gesture stability semiphysical simulation platform again
Unit verifies the determination of various antiinterference attitude.
Background technology
The aircraft such as satellite, space shuttle, guided missile, in order to complete each being undertaken of task, need self
Attitude accurately control, and accurately determining current pose information is that abovementioned aircraft realizes highperformance
The premise of gesture stability, therefore, attitude algorithm system is the important component part of aircraft.
Common attitude algorithm system is mainly i.e. filtered by attitude sensor and corresponding attitude information Processing Algorithm
Algorithm forms, and therefore, the precision of attitude algorithm depends on that the certainty of measurement of attitude sensor itself and filtering are calculated
The performance of method.Conventional attitude sensor part mainly include gyroscope, Star Sensor, sun sensor,
Earth sensor and gaussmeter.Each class sensor has the strong point of self with not enough, true in actual attitude
Determine in system, generally use filtering algorithm that the attitude information measured by dissimilar sensor is merged,
It is thus possible to current pose is estimated with higher precision.The metric data of attitude sensor is being filtered
When ripple processes, inevitably included the perturbation of modeling error, model parameter, sensor random noise
In the impact of interior multisource interference, these interference can not be included into Gaussian noise simply, therefore be appointed in reality
In business, the Kalman filtering algorithm being only capable of process Gaussian noise often cannot meet the precision of attitude and heading reference system
Requirement, the interference free performance of filtering algorithm increasingly becomes focus of concern.Simultaneously for certain filter of checking
The performance of ripple algorithm, needs to carry out semiphysical simulation, and traditional semiphysical simulation needs gyroscope essence
Really it is arranged on the attitude angular rate that could measure three axles on threeaxle table, and turntable is often a set of semi physical
Device the most expensive in emulation platform, makes troubles not only to the dependence of turntable the operation of semiphysical simulation,
And substantially increase cost.
Summary of the invention
The technology of the present invention solves problem: overcome the deficiencies in the prior art, it is provided that a kind of hardware configuration is simple,
Can effectively suppress multisource interference effect, may be conveniently used the high accuracy appearance that desktop is verified at loop simulation
State resolving system.
The technical solution of the present invention is: a kind of highprecision attitude resolving system based on Interference Estimation, its
It is characterised by including that attitude sensor, attitude information process plate, realtime simulation target machine, gesture stability module
With attitude information display module；Wherein attitude sensor includes gyroscope, Star Sensor, sun sensor
And gaussmeter, for the attitude information that sensitive carrier is current, it is sensitive that attitude information processes plate realtime reception attitude
The metric data of device, uses and combines interference estimator and the antiinterference robust of robust mixing multiple target wave filter
Filtering algorithm, is filtered the original metric data received processing, is met carrier required precision
Attitude algorithm result, and attitude algorithm information is sent to gesture stability module, realtime simulation target machine receives
The gesture stability instruction that gesture stability module resolves, calls the actuator in realtime simulation target machine and attitude
Dynamics module simulates the kinestate of true carrier, realizes data by attitude information display module simultaneously and shows
The function shown；
Described combines interference estimator and the antiinterference Robust filtering algorithms of robust mixing multiple target wave filter
Be accomplished by
(1) first using the drift of gyroscope in attitude sensor as interference can be modeled, foundation is expressed as
The interference model of form:
Wherein w (t) is the state variable that can model interference model, and W (t) represents the system battle array that can model interference model,
δ (t) is the random disturbances that can not model of energy bounded, G_{3}T () is the gain battle array that can not model random disturbances；
(2), after using abovementioned interference expressionform, gyroscopic drift is estimated by design interference estimator,
Concrete form is as follows:
Wherein,For the state variable of robust mixing multiple target wave filter, M (k) is corresponding after W (t) discretization
Matrix, K_{a}For interference estimator gain matrix undetermined,The defeated of multiple target wave filter is mixed for robust
Go out；
(3) the robust performance index under then disturbing for model uncertainty and normbounded and guaranteed cost
Performance indications, devise robust mixing multiple target wave filter and suppress it, and concrete form is as follows:
Wherein, the coefficient matrix during A (k), C (k) are attitude and heading reference system state and measurement equation；For shape
The estimated value of state x (k), u (k) is the control input of carrier, u_{c1}(k) and u_{c2}K () two is used for compensating and can build
Mould interference w (k),For the output of robust mixing multiple target wave filter, the many mesh of robust that matrix L is undetermined
Mark filter gain battle array；
(4) last simultaneous interference estimator and robust mixing multiple target wave filter structure closed loop system, use
The LMI workbox (LMI Toolbox) of matlab solves and meets carrier output accuracy requirement
Interference estimator and robust mixing multiple target wave filter.
Described inertia device be directly placed on desktop can by its sensitivity to attitude information pass to attitude
Information processing board processes；Or it is arranged on the attitude information that sensitive carrier on carrier is current.
Described attitude information processes plate hardware by embedded microprocessor, power module, clock module, reset
Unit, I/O unit, random access memory, outer extension memory, data reception module and data transmission blocks composition.
Wherein power module produces voltage signal required when embedded microprocessor runs by voltage stabilizing chip；Clock
Module produces the clock signal needed for embedded microprocessor work；Reset unit selects Special reset chip even
It is connected on the hardware reset pin of embedded microprocessor, it is achieved the reset function of system；I/O unit is by by embedding
The part pin entering microsever is drawn, in order to extend more peripheral hardware, it is ensured that process the extensibility of plate；
Random access memory is for the random storage of embedded microprocessor service data；Outer extension memory compensate for embedding
Microsever chip onchip SRAM and the less deficiency of ROM Space；Data reception module and data are sent out
Module is sent to use serial port chip that serial port resource original on embedded microprocessor is expanded, it is ensured that this
The attitude information of invention processes plate can carry out data with multiple attitude sensors and realtime simulation target machine simultaneously
Alternately.Interference estimator and robust mixing multiple target wave filter is combined at embedded microprocessor described in running
Antiinterference Robust filtering algorithms time, first read metric data according to the current operational mode of carrier, and carry
The current operational mode of body is decided by the attitude of carrier angular speed that the previous resolving cycle calculated, and currently transports
Being filtered resolving after required attitude sensor determines under row mode, microprocessor passes through data receipt unit
The metric data of attitude sensor is read, when the attitude sensor data read are effective with certain frequency
Time, metric data is first unpacked and carries out Conversion of measurement unit by microprocessor, then calls antiinterference robust filtering and calculates
Carrier current pose is estimated by method, and attitude algorithm result will be issued by data transmission unit in real time in real time
Simulation objectives machine is to realize display and gesture stability function.
The principle of the present invention is: when the running environment at attitude algorithm system place of the present invention exists Gauss and not high
When this noise, model uncertainty, Parameter Perturbation and other various forms of interference, we are first inertia
Device drift modeling is single order GaussMarkov process, devises interference estimator and estimates it, root
Result according to estimates offsets inertia device drift.Next step, include model uncertainty, Parameter Perturbation with
And nonGaussian noise permeates a normbounded variable in the interference of other interior form, devise robust and mix
Close multiple target wave filter it is suppressed, wherein H_{∞}Performance suppression normbounded interference, guaranteed cost performance is excellent
Change variance of estimaion error.Finally, interference estimator and robust are mixed multiple target wave filter simultaneous composition to close
Loop systems, uses the LMI workbox (LMI Toolbox) of matlab to interference estimator
Solve with robust mixing multiple target wave filter, make closed loop system meet the requirement of given performance indications, from
And obtain highprecision attitude algorithm result.
Present invention advantage compared with prior art is: the present invention utilizes high performance microprocessor chip structure
Build a kind of highprecision attitude resolving system based on Interference Estimation, and determine calculation as antiinterference attitude
The execution core of method, it has the following characteristics that compared with existing attitude algorithm module
(1) present invention employs and merge the antiinterference attitude of multiple sensor metric data and determine algorithm, with biography
The kalman filter method of system can only process Gaussian noise and amount of calculation is compared more greatly, and the present invention has used antidry
Disturbing the method for robust filtering to suppress multisource to disturb, it need not know exactly which the system of system model and noise
Meter characteristic, can process the uncertainty of normbounded, and utilize interference estimator counteracting can model interference.
When there is the multiple interference such as model uncertainty, noise nongaussian in attitude and heading reference system, it is possible to promote system
The precision of system attitude algorithm.
(2) need accurately to install when being relatively used for verify various filtering algorithm with traditional attitude algorithm module
Each attitude sensor part, gyroscope directly is placed can enter on the table by the attitude algorithm module of the present invention
Row desktop is verified at loop semi physical simulation, the most easy to operate, and provides cost savings.
(3) by attitude sensor sensitive carrier attitude information, utilization combines interference estimator and robust mixes
The filtering algorithm closing multiple target wave filter carries out the filtering resolving of realtime highprecision to carrier current pose.This
The bright gesture stability loop that can directly apply to the fields such as Aeronautics and Astronautics, again can be as gesture stability half thing
Attitude in reason emulation platform determines that unit is to verify that various antiinterference attitude determines the effect of algorithm.
Accompanying drawing explanation
Fig. 1 is that the highprecision attitude of the present invention resolves modular structure composition frame chart；
Fig. 2 is the flow chart that antiinterference attitude of the present invention determines algorithm.
Detailed description of the invention
As it is shown in figure 1, a kind of based on Interference Estimation highprecision attitude resolving system involved in the present invention,
Mainly by attitude sensor, attitude information process plate, realtime simulation target machine, attitude information display module with
And gesture stability module composition.Wherein attitude sensor part includes that gyroscope, Star Sensor, the sun are sensitive
Device and gaussmeter；Realtime simulation target machine connects attitude information display module and gesture stability module；?
When resolving carrier current pose, attitude sensor is arranged on the carriers such as aircraft, and attitude information processes in plate
Running antiinterference Robust filtering algorithms, calculation result is as the input quantity of gesture stability module；For carrying out
During semiphysical simulation checking, attitude sensor can be directly placed on desktop, and attitude information processes in plate and transports
Row filtering algorithm to be verified, calculation result issues simulation objectives machine in real time, and simulation objectives machine is by execution
Mechanism module and the motion of the true carrier of attitude dynamics module simulation, by gesture stability module and display mould
Block realizes the function of gesture stability and realtime curve.
Attitude information process plate mainly by embedded microprocessor, power module, clock module, reset unit,
I/O unit, random access memory, outer extension memory, data reception module and data transmission blocks composition.Embed
Microsever is AT91RM9200 host processor chip based on ARM9 kernel；Power module is by steady
Pressure chip produces 5V, 3.3V, 1.7V voltage signal required when embedded microprocessor runs；Clock mould
Block uses the crystal oscillator of multiple different frequencies to construct multiple clock unit, it is possible to produce the clock letter of several frequency
Number；Reset unit selects Special reset chip to be connected to the hardware reset pin of embedded microprocessor, it is simple to
Researcher debugging routine；I/O unit is by by the part pin extraction of embedded microprocessor, reserved part merit
Can be unused, more peripheral hardware can be extended, it is ensured that process the extensibility of plate；Random access memory is selected
SDRAM chip is for the random storage of embedded microprocessor service data；Outer extension memory is selected
FLASH chip, compensate for embedded microprocessor chip onchip SRAM and the less deficiency of ROM Space；
Data reception module and data transmission blocks use serial port chip to provide original serial ports on embedded microprocessor
Source is expanded, it is ensured that the attitude information of the present invention process plate can simultaneously with multiple attitude sensors and reality
Time simulation objectives machine carry out data interaction.
As in figure 2 it is shown, as a example by experiment model, give the present invention flow process of antiinterference Robust filtering algorithms
Figure.Initially set up the state equation of attitude and heading reference system containing multisource interference and measurement equation and to from
Dispersion；Second step is set up many born of the same parents model of attitude and heading reference system state equation and is described；3rd step design interference is estimated
Gyroscopic drift is estimated by gauge；4th step design robust mixing multiple target wave filter；5th step simultaneous mixes
Close H_{2}/H_{∞}The equation of wave filter and interference estimator constitutes closed loop system；6th step solve interference observer and
Robust mixing multiple target wave filter.Concrete enforcement step is as follows:
1. set up the attitude and heading reference system state containing multisource interference and output equation
According to the attitude angular rate information of gyro output, utilize quaternary number renewal equation to attitude and heading reference system
Attitude error is modeled, using the attitude quaternion of satellite as the state variable of state equation, star is quick
The metric data of sensor, as the output variable of output equation, sets up the attitude and heading reference system containing multisource interference
State equation and output equation as follows:
Wherein, F (t), G (t), G_{1}(t)、G_{2}(t)、C(t)、D(t)、D_{1}(t) and D_{2}T () is known system
Several gusts；X (t) represent attitude and heading reference system three attitude angle, w (t) for interference can be modeled, w_{1}T () is Gauss
Noise, wx (t) is normbounded interference, and y (t) is system output.By this system discretization, have:
Wherein A (k), B (k), B_{1}(k)、B_{2}K () is respectively F (t), G (t), G_{1}(t)、G_{2}(t) discretization
After factor arrays；x(k)、w(k)、w_{1}(k)、w_{2}K () and y (k) are respectively corresponding to x (t), w (t), w_{1}(t)、
w_{2}The discrete state variable of (t) and y (t).
2. the many born of the same parents model setting up attitude and heading reference system state equation describes
Using the most true as system of change of parameter in attitude and heading reference system state equation under satellite body coordinate system
Qualitative, and use many born of the same parents model of uncertain system to describe.Matrix A changes item and includes the constant value of gyro
Drift and random noise, it is exactly mainly by the constant value drift of gyro that error state equation is expressed as many born of the same parents model
Representing with a convex polyhedron with random noise, the summit of this convex polyhedron is attitude and heading reference system state side
Many born of the same parents model of journey describes.
3. pair can model disturbanceproof design interference estimator
Gyroscopic drift is one of interference source main in attitude and heading reference system, it is generally recognized that it meets single order Ma Er
Section's husband's process, is represented by:
Wherein w (t) is the state variable that can model interference model, and W (t) represents the system that can model interference model
Battle array, δ (t) is the random disturbances that can not model of energy bounded, G_{3}T () is the gain battle array that can not model random disturbances；
Design interference observer is as follows:
WhereinFor the state variable of robust mixing multiple target wave filter, M (k) is by right after W (t) discretization
The matrix answered, K_{a}For interference estimator gain matrix undetermined,For robust mixing multiple target wave filter
Output；
4. design robust mixing multiple target wave filter
Structure robust mixing multiple target wave filter is as follows:
Wherein,For the estimated value of state x (k), u (k) is the control input of carrier, u_{c1}(k) and u_{c2}(k)
Two can model interference w (k) for compensation,For the output of robust mixing multiple target wave filter, matrix L is
Robust multiple target filter gain battle array undetermined；
5. simultaneous interference estimator and robust mixing multiple target wave filter structure closed loop system
Definition error state variable: $\stackrel{~}{x}\left(k\right)=x\left(k\right)\hat{x}\left(k\right),\stackrel{~}{w}\left(k\right)=w\left(k\right)\hat{w}\left(k\right),$ Then estimation difference
System is:
The most each coefficient matrix all omits time variable k；K_{a}It is robust multiple target wave filter undetermined with L
Gain battle array.
H_{∞}Reference output be defined as:
H_{2}Reference output be defined as:
Wherein, C_{∞1}, C_{∞2}, C_{21}And C_{22}For selected weight matrix.
6. solve interference estimator and robust mixing multiple target wave filter
Use matlab LMI workbox (LMI Toolbox), utilize convex optimized algorithm, root
Interference estimator and the gain battle array undetermined of robust mixing multiple target wave filter is solved according to the required precision of system output
K_{a}And L.
The content not being described in detail in description of the invention belongs to existing known to professional and technical personnel in the field
Technology.
Claims (3)
1. a highprecision attitude resolving system based on Interference Estimation, it is characterised in that: include that attitude is quick
Sensor, attitude information process plate, realtime simulation target machine, gesture stability module and attitude information display module；
Wherein attitude sensor includes gyroscope, Star Sensor, sun sensor and gaussmeter, carries for sensitivity
The attitude information that body is current, attitude information processes the metric data of plate realtime reception attitude sensor, uses knot
Interference estimator and the antiinterference Robust filtering algorithms of robust mixing multiple target wave filter are closed, to receive
Original metric data is filtered processing, and is met the attitude algorithm result of carrier required precision, and by appearance
State resolves information and is sent to gesture stability module, and realtime simulation target machine receives the appearance that gesture stability module resolves
State control instruction, calls the actuator in realtime simulation target machine and attitude dynamics module simulation truly carries
The kinestate of body, realizes, by attitude information display module, the function that data show simultaneously；Described combination
Being accomplished by of the antiinterference Robust filtering algorithms of interference estimator and robust mixing multiple target wave filter
(1) first using the drift of gyroscope in attitude sensor as interference can be modeled, foundation is expressed as
The interference model of form:
Wherein w (t) is the state variable that can model interference model, and W (t) represents the system battle array that can model interference model,
δ (t) is the random disturbances that can not model of energy bounded, G_{3}T () is the gain battle array that can not model random disturbances；
(2), after using abovementioned interference expressionform, gyroscopic drift is estimated by design interference estimator,
Concrete form is as follows:
WhereinFor the state variable of robust mixing multiple target wave filter, M (k) is corresponding after W (t) discretization
Matrix, K_{a}For interference estimator gain matrix undetermined,The defeated of multiple target wave filter is mixed for robust
Go out；
(3) robust performance index under then disturbing for model uncertainty and normbounded and protecting into
These performance indications, devise robust mixing multiple target wave filter and suppress it, and concrete form is as follows:
Wherein, the coefficient matrix during A (k), C (k) are attitude and heading reference system state and measurement equation；For shape
The estimated value of state x (k), u (k) is the control input of carrier, u_{c1}(k) and u_{c2}K () two can for compensation
Modeling interference w (k),For the output of robust mixing multiple target wave filter, the robust that matrix L is undetermined is many
Target filter gain battle array；
(4) last simultaneous interference estimator and robust mixing multiple target wave filter structure closed loop system, use
The LMI workbox (LMI Toolbox) of matlab solve meet carrier output accuracy want
The interference estimator asked and robust mixing multiple target wave filter.
A kind of highprecision attitude resolving system based on Interference Estimation the most according to claim 1, its
Be characterised by: described gyroscope be directly placed on desktop can by its sensitivity to attitude information pass to
Attitude information processes in plate and processes；Or gyroscope is arranged on the attitude letter that on carrier, sensitive carrier is current
Breath.
A kind of highprecision attitude resolving system based on Interference Estimation the most according to claim 1, its
It is characterised by that attitude information processes plate mainly by embedded microprocessor, power module, clock module, reset
Unit, I/O unit, random access memory, outer extension memory, data reception module and data transmission blocks group
Become；Wherein power module produces voltage signal required when embedded microprocessor runs by voltage stabilizing chip；
Clock module produces the clock signal needed for embedded microprocessor work；Reset unit selects Special reset core
Sheet is connected to the hardware reset pin of embedded microprocessor, it is achieved the reset function of system；I/O unit leads to
Cross and the part pin of embedded microprocessor is drawn, in order to extend more peripheral hardware, it is ensured that process expanding of plate
Malleability；Random access memory is for the random storage of embedded microprocessor service data；Outer extension memory makes up
Embedded microprocessor chip onchip SRAM and the less deficiency of ROM Space；Data reception module and
Data transmission blocks uses serial port chip to be expanded serial port resource original on embedded microprocessor,
Ensure the attitude information of the present invention process plate can simultaneously with multiple attitude sensors and realtime simulation target machine
Carry out data interaction, described in embedded microprocessor operation, combine interference estimator and the robust many mesh of mixing
When marking the antiinterference Robust filtering algorithms of wave filter, first read according to the operational mode that carrier is current and measure number
According to, and the current operational mode of carrier is decided by the attitude of carrier angle speed that the previous resolving cycle calculated
Rate, is filtered resolving after required attitude sensor determines under present mode of operation, microprocessor is by number
According to receiving the unit metric data with certain frequency reading attitude sensor, when the attitude read is sensitive
When device data are effective, metric data is first unpacked and carries out Conversion of measurement unit by microprocessor, then calls antiinterference
Carrier current pose is estimated by Robust filtering algorithms, and attitude algorithm result will be real by data transmission unit
Time issue realtime simulation target machine in case realize display and gesture stability function.
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Citations (4)
Publication number  Priority date  Publication date  Assignee  Title 

US6260805B1 (en) *  19981229  20010717  Hughes Electronics Corporation  Method of controlling attitude of a momentum biased spacecraft during longduration thruster firings 
CN102289211A (en) *  20110624  20111221  北京航空航天大学  Satellite attitude control semiphysical simulation system based on multitarget machine 
CN102620605A (en) *  20120331  20120801  林德福  Global positioning system (GPS) and inertial navigation system (INS) combination guidance system for semiphysical simulation 
CN102749852A (en) *  20120724  20121024  北京航空航天大学  Faulttolerant antiinterference control method for multisource interference system 

2014
 20140329 CN CN201410124597.0A patent/CN103900559B/en active Active
Patent Citations (4)
Publication number  Priority date  Publication date  Assignee  Title 

US6260805B1 (en) *  19981229  20010717  Hughes Electronics Corporation  Method of controlling attitude of a momentum biased spacecraft during longduration thruster firings 
CN102289211A (en) *  20110624  20111221  北京航空航天大学  Satellite attitude control semiphysical simulation system based on multitarget machine 
CN102620605A (en) *  20120331  20120801  林德福  Global positioning system (GPS) and inertial navigation system (INS) combination guidance system for semiphysical simulation 
CN102749852A (en) *  20120724  20121024  北京航空航天大学  Faulttolerant antiinterference control method for multisource interference system 
NonPatent Citations (2)
Title 

Robust Consensus of MultiAgent Systems with Uncertain Exogenous Disturbances;Yang Hongyong et al;《Communications in Theoretical Physics》;20111215;第56卷(第6期);第11611166页 * 
Robust modified projective synchronization of fractionalorder chaotic systems with parameters perturbation and external disturbance;Wang Dongfeng et al;《Chinese Physics B》;20131031;第22卷(第10期);第1005041  1005047页 * 
Cited By (1)
Publication number  Priority date  Publication date  Assignee  Title 

CN110018414A (en) *  20190307  20190716  武汉华中天纬测控有限公司  A kind of disconnecting switch opening and closing state monitoring device and its application 
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