CN103624784A - Self-adaptation control method for space multi-arm complicated-connection complex - Google Patents
Self-adaptation control method for space multi-arm complicated-connection complex Download PDFInfo
- Publication number
- CN103624784A CN103624784A CN201310547914.5A CN201310547914A CN103624784A CN 103624784 A CN103624784 A CN 103624784A CN 201310547914 A CN201310547914 A CN 201310547914A CN 103624784 A CN103624784 A CN 103624784A
- Authority
- CN
- China
- Prior art keywords
- control
- mechanical arm
- association
- matrix
- attitude
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25J—MANIPULATORS; CHAMBERS PROVIDED WITH MANIPULATION DEVICES
- B25J9/00—Programme-controlled manipulators
- B25J9/16—Programme controls
- B25J9/1656—Programme controls characterised by programming, planning systems for manipulators
- B25J9/1669—Programme controls characterised by programming, planning systems for manipulators characterised by special application, e.g. multi-arm co-operation, assembly, grasping
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25J—MANIPULATORS; CHAMBERS PROVIDED WITH MANIPULATION DEVICES
- B25J9/00—Programme-controlled manipulators
- B25J9/16—Programme controls
- B25J9/1656—Programme controls characterised by programming, planning systems for manipulators
- B25J9/1664—Programme controls characterised by programming, planning systems for manipulators characterised by motion, path, trajectory planning
Landscapes
- Engineering & Computer Science (AREA)
- Robotics (AREA)
- Mechanical Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Feedback Control In General (AREA)
Abstract
The invention discloses a self-adaptation control method for a space multi-arm complicated-connection complex. The self-adaptation control method for the space multi-arm complicated-connection complex is high in precision, good in adaptability and independent from specific parameter values of the complex, on-line identification does not need to be carried out on parameters in an ontrack mode, only measurable output is needed, and a controller has good robustness on uncertainty of the parameters. According to the self-adaptation control method for the space multi-arm complicated-connection complex, a simple self-adaptation control method is popularized to controlled objects which have high relative orders and non-approximate strict positive realness. When the self-adaptation control method is used for solving the problem of closed-chain control of mechanical arms, mechanical arm system closed-chain motion constraint conditions are introduced into trajectory planning, ideal trajectories, meeting the motion constraint conditions, of the mechanical arms are given through the trajectory planning, and therefore the problem of closed-chain control of the mechanical arms is simplified into the problem that tracking of mechanical arm systems meets the requirement for tracking of the ideal trajectories of kinematics constraint.
Description
Technical field
The present invention relates to the complicated association's self-adaptation control method that connects of a kind of space multi-arm, relate in particular to the complicated association's high-accuracy self-adaptation control method that connects of a kind of space multi-arm, belong to Spacecraft Attitude Control field.
Background technology
In the manipulator motion stage, no matter to catch or exhausting section, the motion of system is typical multi-body system, and wherein the motion of arbitrary body all can have influence on the motion state of other each body in system, and its sports coupling relation is very complicated; Especially when the collaborative target acquisition of multi-arm, form after closed chain, there is Dynamics Coupling relation in the motion of each body not only, and system also exists direct kinematic constraint.Conventionally, in operating process, control target for keeping platform stable, and make each mechanical arm follow the tracks of desired motion track simultaneously.In whole system motion, exist Dynamics Coupling even directly kinematic constraint in the situation that, seek many bodies control method for coordinating to reach the matter of utmost importance that above-mentioned control target is system controller design; The main target of its design is: in the controller design of a certain movable body or kinematic system, seek suitable technological means, reduce the impact of other movable bodies in system as far as possible, make all movable bodies of controlling that need in system all can follow the tracks of its desired motion track with degree of precision, thereby reach many bodies, coordinate the object of controlling; On this basis, the parameter uncertainty of the outer interference of the design of controller reply and system has stronger adaptivity or robustness.
According to two phase controller mentality of designing ,Jiang association's pose stabilization controls and mechanical arm Trajectory Tracking Control above, separate CONTROLLER DESIGN, being coupled as between the two processed distracter each other.Operation task mainly comprises acquisition phase, mass property parameter identification stage and mechanical arm system recovery stage.The complicated association that connects of multi-arm is because structure is very complicated, and mechanical arm system exists flexible problem, makes its system model very complicated.System is in the different operational phases, and because system configuration exists very large variation, its dynamic property exists very large difference, thereby its controller design problem is also different.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provide a kind of space multi-arm the complicated association's self-adaptation control method that connects, the method control accuracy is high.
Technical solution of the present invention is: the complicated association's self-adaptation control method that connects of a kind of space multi-arm, is characterized in that step is as follows:
(1) the multi-arm complicated Self Adaptive Control that connects association in space is resolved into the attitude control of association and the Trajectory Tracking Control of mechanical arm, the attitude of association is controlled and is adopted method shown in step (2) to complete, and the Trajectory Tracking Control of mechanical arm adopts method shown in step (3) to complete;
(2) according to the Attitude control model of room for manoeuvre control method ,Jiang association by the regress simple adaptive control attitude controller design of kinetics equation and kinematical equation, specific implementation process is as follows:
(2.1) first according to association attitude, control and require design reference kinetics equation and with reference to kinematical equation; Reference driving force is learned equation:
State variable x wherein
m=y
m=ω
d,
i
3be 3 rank unit matrix, ω
dfor expectation attitude angular velocity;
With reference to kinematical equation, be:
Q in formula
0d, q
dbe respectively mark portion and the vector part of expectation hypercomplex number,
for q
dantisymmetric matrix,
(2.2) design association attitude is controlled middle control law ω
m: ω
m=A
bdω
d-kq
e, A
bdfor satellite, expect attitude angle body coordinate and be tied to the transition matrix of the actual body coordinate system of satellite, k is positive definite control coefrficient matrix; q
eby association's attitude quaternion error equation
Determine q in formula
e0for the mark portion of error quaternion, q
0, q is respectively mark portion and the vector part of actual hypercomplex number,
antisymmetric matrix for q;
(2.3) the room for manoeuvre simple adaptive control attitude control law T of design association:
(2.4) utilize executing agency, according to the room for manoeuvre simple adaptive control attitude control law T of association of step (2.3) design, association is carried out to attitude control;
(3) according to room for manoeuvre control method, mechanical arm control system is carried out to the room for manoeuvre simple adaptive control contrail tracker design of mechanical arm by kinetics equation and kinematical equation, specific implementation process is as follows:
(3.1) first according to mechanical arm trajectory planning design reference kinetics equation with reference to kinematical equation; Reference driving force is learned equation:
State variable x
2m=y
2m=ω
ar,
b
2m=C
2m=I
7, I
7for unit matrix, ω
arjoint angle speed for each mechanical arm expectation; With reference to kinematical equation, be direct integral relation:
θ
arfor each joint angle of mechanical arm;
(3.2) control law ω in the middle of design mechanical arm Trajectory Tracking Control
arm:
for kinematics output error,
θ
afor the actual joint angle of mechanical arm, k
afor positive definite control coefrficient matrix;
(3.3) design mechanical arm room for manoeuvre simple adaptive control Trajectory Tracking Control T
a:
(3.4) utilize the executing agency on each joint of mechanical arm to restrain T according to the mechanical arm room for manoeuvre simple adaptive control Trajectory Tracking Control of step (3.3) design
amechanical arm is carried out to Trajectory Tracking Control.
The present invention's beneficial effect is compared with prior art:
(1) the complicated high-precision strong adaptive control method that connects association of space multi-arm proposed by the invention does not rely on the design parameter value of association, without in-orbit parameter being carried out to on-line identification, only need output to survey, controller has strong robustness to parameter uncertainty.
(2) control method that the present invention proposes, is generalized to by simple adaptive control method the controlled device that phase match exponents is the non-approximate Strict Positive Realness of high-order.
(3) during processing machine arm closed chain control problem of the present invention, mechanical arm system closed chain kinematic constraint condition is incorporated in trajectory planning, by trajectory planning, provide the ideal trajectory that each mechanical arm meets kinematic constraint condition, thereby mechanical arm closed chain control problem is reduced to the tracking problem that each mechanical arm system is followed the tracks of the ideal trajectory that meets kinematical constraint.
Accompanying drawing explanation
Tu1Wei association attitude stabilization room for manoeuvre simple adaptive control structure chart;
Fig. 2 is mechanical arm track following room for manoeuvre simple adaptive control structure chart.
The specific embodiment
The invention provides the complicated high-precision strong adaptive control method that connects association of a kind of space multi-arm, the equipment that described method is relied on comprises space report control platform and is arranged on the mechanical arm on the report control platform of space, the attitude control system of space report control platform, mechanical arm control system; Method to as if the complicated association that connects of space multi-arm, concrete implementation step is as follows:
(1) the multi-arm complicated Self Adaptive Control that connects association in space is resolved into the attitude control of association and the Trajectory Tracking Control of mechanical arm, the attitude of association is controlled and is adopted method shown in step (2) to complete, and the Trajectory Tracking Control of mechanical arm adopts method shown in step (3) to complete;
(2) according to the Attitude control model of room for manoeuvre control method ,Jiang association by the regress simple adaptive control attitude controller design of kinetics equation and kinematical equation, as shown in Figure 1, specific implementation process is as follows:
(2.1) first according to association attitude, control and require design reference kinetics equation and with reference to kinematical equation; Reference driving force is learned equation:
State variable x wherein
m=y
m=ω
d,
i
3be 3 dimension unit matrix, ω
dfor expectation attitude angular velocity;
With reference to kinematical equation, be:
Q in formula
0d, q
dbe respectively mark portion and the vector part of expectation hypercomplex number,
for q
dantisymmetric matrix,
(2.2) design association attitude is controlled middle control law ω
m: ω
m=A
bdω
d-kq
e, A
bdfor satellite, expect attitude angle body coordinate and be tied to the transition matrix of the actual body coordinate system of satellite, k is positive definite control coefrficient matrix; q
eby association's attitude quaternion error equation
Determine q in formula
e0for the mark portion of error quaternion, q
0dfor (q
0dat 2.1 li, define), q
0, q is respectively mark portion and the vector part of actual hypercomplex number,
antisymmetric matrix for q;
(2.3) the room for manoeuvre simple adaptive control attitude control law T of design association:
(2.4) utilize executing agency, according to the room for manoeuvre simple adaptive control attitude control law T of association of step (2.3) design, association is carried out to attitude control;
(3) according to room for manoeuvre control method, mechanical arm control system is carried out to the room for manoeuvre simple adaptive control contrail tracker design of mechanical arm by kinetics equation and kinematical equation, as shown in Figure 2, specific implementation process is as follows:
(3.1) first according to mechanical arm trajectory planning design reference kinetics equation with reference to kinematical equation; Reference driving force is learned equation:
State variable x
2m=y
2m=ω
ar,
b
2m=C
2m=I
7, I
7for unit matrix, ω
arjoint angle speed for each mechanical arm expectation; With reference to kinematical equation, be direct integral relation:
θ
arfor each joint angle of mechanical arm;
(3.2) control law ω in the middle of design mechanical arm Trajectory Tracking Control
arm:
for kinematics output error,
θ
afor the actual joint angle of mechanical arm, k
afor positive definite control coefrficient matrix;
(3.3) design mechanical arm room for manoeuvre simple adaptive control Trajectory Tracking Control T
a:
(3.4) utilize the executing agency on each joint of mechanical arm to restrain T according to the mechanical arm room for manoeuvre simple adaptive control Trajectory Tracking Control of step (3.3) design
amechanical arm is carried out to Trajectory Tracking Control.
Embodiment: getting one is example with 3 the complicated connection of 7 degree-of-freedom manipulators associations, coupling system dynamics and trajectory planning, the whole process that the target acquistion of system, mass property parameter identification and target are reclaimed is carried out numerical simulation.In system, the quality/inertia parameter of each body is as shown in table 1, and in table, inertia and static moment are all described in the body coordinate system of each body.
Quality/the inertia parameter of each body in table 1 system
? | Quality (Kg) | Inertia (kg.m2) | Static moment (kg.m) |
Satellite body | 3600 | diag(1040,1178,1222) | [0,0,0] T |
Target star | 800 | diag(149,139,160) | [0,0,0] T |
1 grade of arm | 5 | diag(1.979,1.979,1.025)×10 -2 | [0,0,0.25] T |
2 grades of arms | 25 | diag(0.05318.34980349) | [-12.5,0,0] T |
3 grades of arms | 25 | diag(0.053111.03611.036) | [14.375,0,0] T |
4 grades of arms | 3.5 | diag(0.02940.02940.0107) | [0,0,-0.2625] T |
[0044]?
5 grades of arms | 3.5 | diag(0.01070.02940.0294) | [0.2625,0,0] T |
6 grades of arms | 2 | diag(0.00790.00410.0079) | [0,-0.1,0] T |
7 grades of arms | 6 | diag(0.18380.18380.0123) | [0,0,-0.9] T |
The flexible parameter information of system is as shown in table 2.
Flexible parameter in table 2 system
? | The 2nd joint arm | The 3rd joint arm |
Length (m) | 1 | 1.15 |
Quality (kg) | 25 | 25 |
Elastic modelling quantity | 4.5E+10 | 7E+10 |
Fundamental frequency (Hz) | 39.89347 | 40.47306 |
Second order frequency (Hz) | 39.89347 | 40.47306 |
Three order frequencies (Hz) | 233.4357 | 240.5640 |
Quadravalence frequency (Hz) | 233.4357 | 240.5640 |
(1) the initial acquisition stage
The expectation attitude quaternion of initial acquisition stage association's attitude is q
d=[1 00 0]
t, expectation attitude angular velocity is 0, the expectation joint angle of mechanical arm is provided by mechanical arm trajectory planning.The control method proposing according to the present invention, designs respectively attitude control law and mechanical arm Trajectory Tracking Control rule.Controller coefficient is as follows:
Association's attitude control law coefficient:
K
1=0.2,Γ
e=-diag([111])×10
8
K
e(0)=zeros(3,3)
σ=0.01
Mechanical arm Trajectory Tracking Control rule coefficient:
K
2=diag([1?1?1?1?1?1?1])×0.5,Γ
ea=diag([1?1?1?1?1?1])×10
8
Γ
xa=diag([1?1?1?1?1?1?1])×10
2,Γ
ua=diag([1?1?1?1?1?1?1])×10
2
K
ea(0)=zeros(7,7),K
xa(0)=zeros(7,7),K
ua(0)=zeros(7,7)
σ
2=0.01
(2) accurate acquisition phase
The initial value of accurately catching is the final state of initial acquisition, and controller coefficient is as follows:
Association's attitude control law coefficient:
K
1=0.3,Γ
e=-diag([111])×10
12
K
e(0)=zeros(3,3)
σ=0.01
Mechanical arm Trajectory Tracking Control rule coefficient:
K
1a=diag([1?1?1?1?1?1?1])×0.5,Γ
ea=diag([111111])×10
10
Γ
xa=diag([1111111])×10
2,Γ
ua=diag([1111111])×10
2
K
ea(0)=zeros(7,7),K
xa(0)=zeros(7,7),K
ua(0)=zeros(7,7)
σ
2=0.01
(3) recovery stage
The initial value of recovery stage is for accurately catching or the final state in identification stage, and controller coefficient is as follows:
Association's attitude control law coefficient:
K
1=0.3,Γ
e=-diag([111])×10
10
K
e(0)=zeros(3,3)
σ=0.01
Mechanical arm Trajectory Tracking Control rule coefficient:
K
1a=diag([1?1?1?1?1?1])×0.3,Γ
ea=diag([11111])×10
8
Γ
xa=diag([1?1?1?1?1?1])×10
2,Γ
ua=diag([111111])×10
2
K
ea(0)=zeros(6,6),K
xa(0)=zeros(6,6),K
ua(0)=zeros(6,6)
σ
2=0.01
The content not being described in detail in description of the present invention belongs to those skilled in the art's known technology.
Claims (1)
1. multi-arm complexity in space connects association's self-adaptation control method, it is characterized in that step is as follows:
(1) the multi-arm complicated Self Adaptive Control that connects association in space is resolved into the attitude control of association and the Trajectory Tracking Control of mechanical arm, the attitude of association is controlled and is adopted method shown in step (2) to complete, and the Trajectory Tracking Control of mechanical arm adopts method shown in step (3) to complete;
(2) according to the Attitude control model of room for manoeuvre control method ,Jiang association by the regress simple adaptive control attitude controller design of kinetics equation and kinematical equation, specific implementation process is as follows:
(2.1) first according to association attitude, control and require design reference kinetics equation and with reference to kinematical equation; Reference driving force is learned equation:
State variable x wherein
m=y
m=ω
d,
i
3be 3 rank unit matrix, ω
dfor expectation attitude angular velocity;
With reference to kinematical equation, be:
Q in formula
0d, q
dbe respectively mark portion and the vector part of expectation hypercomplex number,
for q
dantisymmetric matrix,
(2.2) design association attitude is controlled middle control law ω
m: ω
m=A
bdω
d-kq
e, A
bdfor satellite, expect attitude angle body coordinate and be tied to the transition matrix of the actual body coordinate system of satellite, the control coefrficient matrix that k is positive definite; q
eby association's attitude quaternion error equation
Determine q in formula
e0for the mark portion of error quaternion, q
0, q is respectively mark portion and the vector part of actual hypercomplex number,
antisymmetric matrix for q;
(2.3) the room for manoeuvre simple adaptive control attitude control law T of design association:
(2.4) utilize executing agency, according to the room for manoeuvre simple adaptive control attitude control law T of association of step (2.3) design, association is carried out to attitude control;
(3) according to room for manoeuvre control method, mechanical arm control system is carried out to the room for manoeuvre simple adaptive control contrail tracker design of mechanical arm by kinetics equation and kinematical equation, specific implementation process is as follows:
(3.1) first according to mechanical arm trajectory planning design reference kinetics equation with reference to kinematical equation; Reference driving force is learned equation:
State variable x
2m=y
2m=ω
ar,
b
2m=C
2m=I
7, I
7for unit matrix, ω
arjoint angle speed for each mechanical arm expectation; With reference to kinematical equation, be direct integral relation:
θ
arfor each joint angle of mechanical arm;
(3.2) control law ω in the middle of design mechanical arm Trajectory Tracking Control
arm:
for kinematics output error,
θ
afor the actual joint angle of mechanical arm, k
afor positive definite control coefrficient matrix;
(3.3) design mechanical arm room for manoeuvre simple adaptive control Trajectory Tracking Control T
a:
(3.4) utilize the executing agency on each joint of mechanical arm to restrain T according to the mechanical arm room for manoeuvre simple adaptive control Trajectory Tracking Control of step (3.3) design
amechanical arm is carried out to Trajectory Tracking Control.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201310547914.5A CN103624784B (en) | 2013-11-06 | 2013-11-06 | A kind of space multi-arm complexity connects association's self-adaptation control method |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201310547914.5A CN103624784B (en) | 2013-11-06 | 2013-11-06 | A kind of space multi-arm complexity connects association's self-adaptation control method |
Publications (2)
Publication Number | Publication Date |
---|---|
CN103624784A true CN103624784A (en) | 2014-03-12 |
CN103624784B CN103624784B (en) | 2015-10-21 |
Family
ID=50206419
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201310547914.5A Active CN103624784B (en) | 2013-11-06 | 2013-11-06 | A kind of space multi-arm complexity connects association's self-adaptation control method |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN103624784B (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104698854A (en) * | 2015-03-26 | 2015-06-10 | 哈尔滨工业大学 | Distributed fuzzy cooperative tracking control method of network Euler-Lagrange system |
CN105446347A (en) * | 2015-11-30 | 2016-03-30 | 上海卫星工程研究所 | On-orbit modal identification system and method for satellite solar cells |
CN105912007A (en) * | 2016-06-02 | 2016-08-31 | 西北工业大学 | Differential geometry nonlinear control method of spatial mechanical arm anti-interference attitude stabilization |
CN106945020A (en) * | 2017-05-18 | 2017-07-14 | 哈尔滨工业大学 | A kind of space double mechanical arms system motion control method for coordinating |
CN108132601A (en) * | 2017-12-06 | 2018-06-08 | 西北工业大学 | A kind of method for inhibiting spacecraft pedestal attitude disturbance using mechanical arm |
CN108453732A (en) * | 2018-02-27 | 2018-08-28 | 北京控制工程研究所 | The adaptive dynamic force of control system closed machine people/Position Hybrid Control method |
CN113172621A (en) * | 2021-04-13 | 2021-07-27 | 哈尔滨工业大学(威海) | Dynamic parameter identification method for SCARA mechanical arm |
CN114378833A (en) * | 2022-03-23 | 2022-04-22 | 珞石(北京)科技有限公司 | Mechanical arm track planning method based on robust constraint control |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5459669A (en) * | 1994-02-14 | 1995-10-17 | Space Systems/Loral, Inc. | Control system and method for spacecraft attitude control |
EP1391383A1 (en) * | 1996-12-02 | 2004-02-25 | Northrop Grumman Corporation | System and method for reducing mechanical disturbances from energy storage flywheels |
CN101077578A (en) * | 2007-07-03 | 2007-11-28 | 北京控制工程研究所 | Mobile Robot local paths planning method on the basis of binary environmental information |
CN102004491A (en) * | 2010-10-11 | 2011-04-06 | 北京控制工程研究所 | Initial sun capturing method during initial injection stage of satellite |
CN103019091A (en) * | 2012-12-20 | 2013-04-03 | 北京航空航天大学 | Flexible spacecraft fault-tolerant attitude control method based on linear extended state observer |
-
2013
- 2013-11-06 CN CN201310547914.5A patent/CN103624784B/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5459669A (en) * | 1994-02-14 | 1995-10-17 | Space Systems/Loral, Inc. | Control system and method for spacecraft attitude control |
EP1391383A1 (en) * | 1996-12-02 | 2004-02-25 | Northrop Grumman Corporation | System and method for reducing mechanical disturbances from energy storage flywheels |
CN101077578A (en) * | 2007-07-03 | 2007-11-28 | 北京控制工程研究所 | Mobile Robot local paths planning method on the basis of binary environmental information |
CN102004491A (en) * | 2010-10-11 | 2011-04-06 | 北京控制工程研究所 | Initial sun capturing method during initial injection stage of satellite |
CN103019091A (en) * | 2012-12-20 | 2013-04-03 | 北京航空航天大学 | Flexible spacecraft fault-tolerant attitude control method based on linear extended state observer |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104698854A (en) * | 2015-03-26 | 2015-06-10 | 哈尔滨工业大学 | Distributed fuzzy cooperative tracking control method of network Euler-Lagrange system |
CN104698854B (en) * | 2015-03-26 | 2017-06-23 | 哈尔滨工业大学 | The distributed fuzzy collaboration tracking and controlling method of network Euler Lagrange systems |
CN105446347A (en) * | 2015-11-30 | 2016-03-30 | 上海卫星工程研究所 | On-orbit modal identification system and method for satellite solar cells |
CN105446347B (en) * | 2015-11-30 | 2018-08-10 | 上海卫星工程研究所 | For the in-orbit modal identification system and method for Satellite vapour image |
CN105912007A (en) * | 2016-06-02 | 2016-08-31 | 西北工业大学 | Differential geometry nonlinear control method of spatial mechanical arm anti-interference attitude stabilization |
CN106945020A (en) * | 2017-05-18 | 2017-07-14 | 哈尔滨工业大学 | A kind of space double mechanical arms system motion control method for coordinating |
CN108132601A (en) * | 2017-12-06 | 2018-06-08 | 西北工业大学 | A kind of method for inhibiting spacecraft pedestal attitude disturbance using mechanical arm |
CN108132601B (en) * | 2017-12-06 | 2020-04-28 | 西北工业大学 | Method for suppressing spacecraft base attitude interference by using mechanical arm |
CN108453732A (en) * | 2018-02-27 | 2018-08-28 | 北京控制工程研究所 | The adaptive dynamic force of control system closed machine people/Position Hybrid Control method |
CN108453732B (en) * | 2018-02-27 | 2020-07-14 | 北京控制工程研究所 | Self-adaptive dynamic force/position hybrid control method for closed robot of control system |
CN113172621A (en) * | 2021-04-13 | 2021-07-27 | 哈尔滨工业大学(威海) | Dynamic parameter identification method for SCARA mechanical arm |
CN114378833A (en) * | 2022-03-23 | 2022-04-22 | 珞石(北京)科技有限公司 | Mechanical arm track planning method based on robust constraint control |
Also Published As
Publication number | Publication date |
---|---|
CN103624784B (en) | 2015-10-21 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN103624784B (en) | A kind of space multi-arm complexity connects association's self-adaptation control method | |
Ye et al. | State damping control: A novel simple method of rotor UAV with high performance | |
CN106773713B (en) | High-precision nonlinear path tracking control method for under-actuated marine vehicle | |
Meng et al. | Space robots with flexible appendages: dynamic modeling, coupling measurement, and vibration suppression | |
CN106527137B (en) | Quadrotor drone fault tolerant control method based on observer | |
Baruh et al. | Issues in the dynamics and control of flexible robot manipulators | |
Cheng et al. | Adaptive neural network control of nonlinear systems with unknown dynamics | |
CN105093934A (en) | Distributed finite time tracking control method for multi-robot system in view of interference and model uncertainty | |
CN106945020A (en) | A kind of space double mechanical arms system motion control method for coordinating | |
CN106873611A (en) | A kind of method for designing of multichannel linear active disturbance rejection controller | |
CN110376882A (en) | Pre-determined characteristics control method based on finite time extended state observer | |
Lendek et al. | Application of Takagi-Sugeno observers for state estimation in a quadrotor | |
CN105912007A (en) | Differential geometry nonlinear control method of spatial mechanical arm anti-interference attitude stabilization | |
Osaki et al. | Delay time compensation for a hybrid simulator | |
Xiao et al. | Adaptive quaternion-based output feedback control for flexible spacecraft attitude tracking with input constraints | |
Young et al. | Control of a nonaffine double-pendulum system via dynamic inversion and time-scale separation | |
Li et al. | Adaptive neural network backstepping control method for aerial manipulator based on coupling disturbance compensation | |
Qi et al. | A force compensation approach toward divergence of hardware-in-the-loop contact simulation system for damped elastic contact | |
Qi et al. | Low-order model based divergence compensation for Hardware-In-The-Loop simulation of space discrete contact | |
Qi et al. | Divergence compensation for hardware-in-the-loop simulation of stiffness-varying discrete contact in space | |
Ghozlane et al. | Nonlinear control via input-output feedback linearization of a robot manipulator | |
Hu et al. | A force and moment compensation method for a hardware-in-the-loop docking simulator based on the stiffness identification of the docking mechanism | |
Lu et al. | Adaptive unscented Kalman filter-based disturbance rejection with application to high precision hydraulic robotic control | |
Qi et al. | Distortion compensation for a robotic hardware-in-the-loop contact simulator | |
Qi et al. | Space robot active collision avoidance maneuver under thruster failure |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C14 | Grant of patent or utility model | ||
GR01 | Patent grant |