This article presents a novel method to measure unbalanced moments in a two-axis gimbaled seeker commonly believed to seviously influence the tracking accuracy and stabilizing capability. This method enables individua...This article presents a novel method to measure unbalanced moments in a two-axis gimbaled seeker commonly believed to seviously influence the tracking accuracy and stabilizing capability. This method enables individual measurement of unbalanced moments, and judgment of the seeker＇ s status-balanced or not. Furthermore, an instrument is designed based on this method and calibrated. The effectiveness of the proposed method is validated through a simulation. The experimental results show a satisfied level of accuracy the measurements have. This work forms a basis for the further development of a more stabilized gimbaled seeker with less induced vibration and consumed power.展开更多
Attitude control system is one of the most important subsystems in a spacecraft.As a key actuator,the control moment gyroscope(CMG)mainly determines the performance of attitude control system.Whereas,the control accur...Attitude control system is one of the most important subsystems in a spacecraft.As a key actuator,the control moment gyroscope(CMG)mainly determines the performance of attitude control system.Whereas,the control accuracy and output torque smoothness of the CMG depends more on its gimbal servo system.Considering the constraints of size,mass and power consumption for a small satellite,here,a mini-CMG is designed,in which the gimbal servo system is driven by an ultrasonic motor.The good performances of the CMG are obtained by both the ultrasonic motor and the rotary inductosyn.The direct drive of gimbal improves its dynamic performance,with the output bandwidth above 20 Hz.The angular and speed closed-loop control obtains the 0.02°/s gimbal rate,and the output torque resolution better than 2×10^(-3) N·m.The ultrasonic motor provides 1.0N·m self-lock torque during power-off,with 12arc-second position accuracy.展开更多
This research is focused on the singularity analysis for single-gimbal control moment gyros systems （SCMGs） which include two types, with constant speed （CSCMG） or variable speed （VSCMG） rotors. Through angular ...This research is focused on the singularity analysis for single-gimbal control moment gyros systems （SCMGs） which include two types, with constant speed （CSCMG） or variable speed （VSCMG） rotors. Through angular momentum hypersurfaces of singular states, the passable and impassable singular points are discriminated easily, meanwhile the information about how much the angular momentum workspace as well as the steering capability available is provided directly. It is obvious that the null motions of steering laws are more effective for the five pyramid configuration（FPC） than for the pyramid configuration（PC） from the singular plots. The possible degenerate hyperbolic singular points of the preceding configurations are calculated and the distinctness of them is denoted by the Gaussian curvature. Furthermore, failure problems to steer integrated power and attitude control system （IPACS） are also analyzed. A sufficient condition of choosing configurations of VSCMGs to guarantee the IPACS steering is given. The angular momentum envelops of VSCMGs, in a given energy and a limited range of rotor speeds, are plotted. The connection and distinctness between CSCMGs and VSCMGs are obtained from the point of view of envelops.展开更多
The attitude control problem of a spacecraft underactuated by two single-gimbal control moment gyros （SGCMGs） is investigated. Small-time local controllability （STLC） of the attitude dynamics of the spacecraft-SGC...The attitude control problem of a spacecraft underactuated by two single-gimbal control moment gyros （SGCMGs） is investigated. Small-time local controllability （STLC） of the attitude dynamics of the spacecraft-SGCMGs system is analyzed via nonlinear controllability theory. The conditions that guarantee STLC of the spacecraft attitude by two non-coaxial SGCMGs are obtained with the momentum of the SGCMGs as inputs, implying that the spacecraft attitude is STLC when the total angular momentum of the whole system is zero. Moreover, our results indi- cate that under the zero-momentum restriction, full attitude stabilization is possible for a spacecraft using two non-coaxial SGCMGs. For the case of two coaxial SGCMGs, the STLC property of the spacecraft cannot be determined. In this case, an improvement to the previous full attitude stabilizing control law, which requires zero-momentum presumption, is proposed to account for the singu- larity of SGCMGs and enhance the steady state performance. Numerical simulation results demonstrate the effectiveness and advantages of the new control law.展开更多
Angular velocity stabilization control and attitude stabilization control for an underactuated spacecraft using only two single gimbal control moment gyros （SGCMGs） as actuators is investigated. First of all, the dy...Angular velocity stabilization control and attitude stabilization control for an underactuated spacecraft using only two single gimbal control moment gyros （SGCMGs） as actuators is investigated. First of all, the dynamic model of the underactuated spacecraft is established and the singularity of different configurations with the two SGCMGs is analyzed. Under the assumption that the gimbal axes of the two SGCMGs are installed in any direction, and that the total system angular momentum is not zero, a state feedback control law via Lyapunov method is designed to globally asymptotically stabilize the angular velocity of spacecraft. Under the assumption that the gimbal axes of the two SGCMGs are coaxially installed along anyone of the three principal axes of spacecraft inertia, and that the total system angular momentum is zero, a discontinuous state feedback control law is designed to stabilize three-axis attitude of spacecraft with respect to the inertial frame. Furthermore, the singularity escape of SGCMGs for the above two control problems is also studied. Simulation results demonstrate the validity of the control laws.展开更多
The application of the guided missile seeker is to provide stability to the sensor’s line of sight toward a target by isolating it from the missile motion and vibration.The main objective of this paper is not only to...The application of the guided missile seeker is to provide stability to the sensor’s line of sight toward a target by isolating it from the missile motion and vibration.The main objective of this paper is not only to present the physical modeling of two axes gimbal system but also to improve its performance through using fuzzy logic controlling approach.The paper is started by deriving the mathematical model for gimbals motion using Newton’s second law,followed by designing the mechanical parts of model using SOLIDWORKS and converted to xml file to connect dc motors and sensors using MATLAB/SimMechanics.Then,a Mamdani-type fuzzy and a Proportional-Integral-Derivative(PID)controllers were designed using MATLAB software.The performance of both controllers was evaluated and tested for different types of input shapes.The simulation results showed that self-tuning fuzzy controller provides better performance,since no overshoot,small steady-state error and small settling time compared to PID controller.展开更多
This paper presents a low-cost remote vision system for use in unmanned aircraft that provide a first person view （FPV） to vehicle operators in real-time. The system does not require a traditional electromechanical ...This paper presents a low-cost remote vision system for use in unmanned aircraft that provide a first person view （FPV） to vehicle operators in real-time. The system does not require a traditional electromechanical gimbal setup. Instead, the system uses a wide-angle （fisheye） lens and a video camera setup that is fixed on the vehicle and captures the full viewing area as seen from the cockpit in each video frame. Video is transmitted to a ground station wirelessly. On the ground, the pilot is outfitted with virtual reality goggles with integrated attitude and heading sensors. The received video is recertified and cropped by the ground station to provide the goggles with the appropriate view based on head orientation. Compared to traditional electromechanical setups, the presented system features reduced weight, reduced video lag, lower power consumption, and reduced drag on the airborne vehicle in addition to requiring only a unidirectional downlink. The video processing is preformed on the ground, further reducing computational resources and bandwidth requirements. These advantages, in conjunction with the advancement in miniature optical sensors and lenses, make the proposed approach a viable option for miniature remotely controlled vehicles. The system was successfully implemented and tested using an R/C airplane.展开更多
A new attitude control method for solar sails is proposed using a single-axis gimbal mechanism and three-axis reaction wheels.The gimbal angle is varied to change the geometrical relationship between the force due to ...A new attitude control method for solar sails is proposed using a single-axis gimbal mechanism and three-axis reaction wheels.The gimbal angle is varied to change the geometrical relationship between the force due to solar radiation pressure(SRP)and the center of mass of the spacecraft,such that the disturbance torque is minimized during attitude maintenance for orbit control.Attitude maneuver and maintenance are performed by the reaction wheels based on the quaternion feedback control method.Even if angular momentum accumulates on the reaction wheels due to modelling error,it can also be unloaded by using the gimbal to produce suitable torque due to SRP.In this study,we analyzed the attitude motion under the reaction wheel control by linearizing the equations of motion around the equilibrium point.Further,we newly derived the propellent-free unloading method based on the analytical formulation.Finally,we constructed the integrated attitude–orbit control method,and its validity was verified in integrated attitude–orbit control simulations.展开更多
Autonomous underwater vehicles are at present being used for scientific,commercial and military submerged applications.In this paper,a system has been proposed which can be used underwater as remotely operated underwa...Autonomous underwater vehicles are at present being used for scientific,commercial and military submerged applications.In this paper,a system has been proposed which can be used underwater as remotely operated underwater vehicle for submerged survey for different purposes.These systems require self-sufficient direction and control frameworks so as to perform submerged assignments.Displaying,framework identification and control of these vehicles are as yet real dynamic zones of innovative work.This theory is worried about the plan and improvement of an Autonomous Underwater Vehicle(AUV)specifically proposed for passage into global submerged vehicle rivalries.The theory comprises of two stages;the first includes the plan and development of the vehicle while the subsequent stage is worried about the demonstrating and framework identification of the vehicle,just as the reproduction of a control system.The structure and advancement of the vehicle comprised of actualizing a mechanical and electrical framework,just as the reconciliation of subsystems.The framework identification of the vehicle parameters comprised of utilizing locally available sensors to perform static and dynamic tests.Least squares estimation was utilized to gauge the parameters from the pre-researched data obtained.展开更多
文摘This article presents a novel method to measure unbalanced moments in a two-axis gimbaled seeker commonly believed to seviously influence the tracking accuracy and stabilizing capability. This method enables individual measurement of unbalanced moments, and judgment of the seeker＇ s status-balanced or not. Furthermore, an instrument is designed based on this method and calibrated. The effectiveness of the proposed method is validated through a simulation. The experimental results show a satisfied level of accuracy the measurements have. This work forms a basis for the further development of a more stabilized gimbaled seeker with less induced vibration and consumed power.
基金supported by the National Natural Science Foundation of China(No.51575260)the Fundamental Research Funds for the Central Universities(No.NJ20160001)
文摘Attitude control system is one of the most important subsystems in a spacecraft.As a key actuator,the control moment gyroscope(CMG)mainly determines the performance of attitude control system.Whereas,the control accuracy and output torque smoothness of the CMG depends more on its gimbal servo system.Considering the constraints of size,mass and power consumption for a small satellite,here,a mini-CMG is designed,in which the gimbal servo system is driven by an ultrasonic motor.The good performances of the CMG are obtained by both the ultrasonic motor and the rotary inductosyn.The direct drive of gimbal improves its dynamic performance,with the output bandwidth above 20 Hz.The angular and speed closed-loop control obtains the 0.02°/s gimbal rate,and the output torque resolution better than 2×10^(-3) N·m.The ultrasonic motor provides 1.0N·m self-lock torque during power-off,with 12arc-second position accuracy.
文摘This research is focused on the singularity analysis for single-gimbal control moment gyros systems （SCMGs） which include two types, with constant speed （CSCMG） or variable speed （VSCMG） rotors. Through angular momentum hypersurfaces of singular states, the passable and impassable singular points are discriminated easily, meanwhile the information about how much the angular momentum workspace as well as the steering capability available is provided directly. It is obvious that the null motions of steering laws are more effective for the five pyramid configuration（FPC） than for the pyramid configuration（PC） from the singular plots. The possible degenerate hyperbolic singular points of the preceding configurations are calculated and the distinctness of them is denoted by the Gaussian curvature. Furthermore, failure problems to steer integrated power and attitude control system （IPACS） are also analyzed. A sufficient condition of choosing configurations of VSCMGs to guarantee the IPACS steering is given. The angular momentum envelops of VSCMGs, in a given energy and a limited range of rotor speeds, are plotted. The connection and distinctness between CSCMGs and VSCMGs are obtained from the point of view of envelops.
基金supported by the National Natural Science Foundation of China (No.10902003)
文摘The attitude control problem of a spacecraft underactuated by two single-gimbal control moment gyros （SGCMGs） is investigated. Small-time local controllability （STLC） of the attitude dynamics of the spacecraft-SGCMGs system is analyzed via nonlinear controllability theory. The conditions that guarantee STLC of the spacecraft attitude by two non-coaxial SGCMGs are obtained with the momentum of the SGCMGs as inputs, implying that the spacecraft attitude is STLC when the total angular momentum of the whole system is zero. Moreover, our results indi- cate that under the zero-momentum restriction, full attitude stabilization is possible for a spacecraft using two non-coaxial SGCMGs. For the case of two coaxial SGCMGs, the STLC property of the spacecraft cannot be determined. In this case, an improvement to the previous full attitude stabilizing control law, which requires zero-momentum presumption, is proposed to account for the singu- larity of SGCMGs and enhance the steady state performance. Numerical simulation results demonstrate the effectiveness and advantages of the new control law.
文摘Angular velocity stabilization control and attitude stabilization control for an underactuated spacecraft using only two single gimbal control moment gyros （SGCMGs） as actuators is investigated. First of all, the dynamic model of the underactuated spacecraft is established and the singularity of different configurations with the two SGCMGs is analyzed. Under the assumption that the gimbal axes of the two SGCMGs are installed in any direction, and that the total system angular momentum is not zero, a state feedback control law via Lyapunov method is designed to globally asymptotically stabilize the angular velocity of spacecraft. Under the assumption that the gimbal axes of the two SGCMGs are coaxially installed along anyone of the three principal axes of spacecraft inertia, and that the total system angular momentum is zero, a discontinuous state feedback control law is designed to stabilize three-axis attitude of spacecraft with respect to the inertial frame. Furthermore, the singularity escape of SGCMGs for the above two control problems is also studied. Simulation results demonstrate the validity of the control laws.
基金Taif University Researchers Supporting Project number(TURSP-2020/260),Taif University,Taif,Saudi Arabia.
文摘The application of the guided missile seeker is to provide stability to the sensor’s line of sight toward a target by isolating it from the missile motion and vibration.The main objective of this paper is not only to present the physical modeling of two axes gimbal system but also to improve its performance through using fuzzy logic controlling approach.The paper is started by deriving the mathematical model for gimbals motion using Newton’s second law,followed by designing the mechanical parts of model using SOLIDWORKS and converted to xml file to connect dc motors and sensors using MATLAB/SimMechanics.Then,a Mamdani-type fuzzy and a Proportional-Integral-Derivative(PID)controllers were designed using MATLAB software.The performance of both controllers was evaluated and tested for different types of input shapes.The simulation results showed that self-tuning fuzzy controller provides better performance,since no overshoot,small steady-state error and small settling time compared to PID controller.
文摘This paper presents a low-cost remote vision system for use in unmanned aircraft that provide a first person view （FPV） to vehicle operators in real-time. The system does not require a traditional electromechanical gimbal setup. Instead, the system uses a wide-angle （fisheye） lens and a video camera setup that is fixed on the vehicle and captures the full viewing area as seen from the cockpit in each video frame. Video is transmitted to a ground station wirelessly. On the ground, the pilot is outfitted with virtual reality goggles with integrated attitude and heading sensors. The received video is recertified and cropped by the ground station to provide the goggles with the appropriate view based on head orientation. Compared to traditional electromechanical setups, the presented system features reduced weight, reduced video lag, lower power consumption, and reduced drag on the airborne vehicle in addition to requiring only a unidirectional downlink. The video processing is preformed on the ground, further reducing computational resources and bandwidth requirements. These advantages, in conjunction with the advancement in miniature optical sensors and lenses, make the proposed approach a viable option for miniature remotely controlled vehicles. The system was successfully implemented and tested using an R/C airplane.
基金supported by the Japan Society for the Promotion of Science,KAKENHI Grant Numbers JP21K14345 and JP21H04588.
文摘A new attitude control method for solar sails is proposed using a single-axis gimbal mechanism and three-axis reaction wheels.The gimbal angle is varied to change the geometrical relationship between the force due to solar radiation pressure(SRP)and the center of mass of the spacecraft,such that the disturbance torque is minimized during attitude maintenance for orbit control.Attitude maneuver and maintenance are performed by the reaction wheels based on the quaternion feedback control method.Even if angular momentum accumulates on the reaction wheels due to modelling error,it can also be unloaded by using the gimbal to produce suitable torque due to SRP.In this study,we analyzed the attitude motion under the reaction wheel control by linearizing the equations of motion around the equilibrium point.Further,we newly derived the propellent-free unloading method based on the analytical formulation.Finally,we constructed the integrated attitude–orbit control method,and its validity was verified in integrated attitude–orbit control simulations.
文摘Autonomous underwater vehicles are at present being used for scientific,commercial and military submerged applications.In this paper,a system has been proposed which can be used underwater as remotely operated underwater vehicle for submerged survey for different purposes.These systems require self-sufficient direction and control frameworks so as to perform submerged assignments.Displaying,framework identification and control of these vehicles are as yet real dynamic zones of innovative work.This theory is worried about the plan and improvement of an Autonomous Underwater Vehicle(AUV)specifically proposed for passage into global submerged vehicle rivalries.The theory comprises of two stages;the first includes the plan and development of the vehicle while the subsequent stage is worried about the demonstrating and framework identification of the vehicle,just as the reproduction of a control system.The structure and advancement of the vehicle comprised of actualizing a mechanical and electrical framework,just as the reconciliation of subsystems.The framework identification of the vehicle parameters comprised of utilizing locally available sensors to perform static and dynamic tests.Least squares estimation was utilized to gauge the parameters from the pre-researched data obtained.
