The gravitational wave spacecraft is a complex multi-input multi-output dynamic system.The gravitational wave detection mission requires the spacecraft to achieve single spacecraft with two laser links and high-precis...The gravitational wave spacecraft is a complex multi-input multi-output dynamic system.The gravitational wave detection mission requires the spacecraft to achieve single spacecraft with two laser links and high-precision control.Establishing one spacecraftwith two laser links,compared to one spacecraft with a single laser link,requires an upgraded decoupling algorithmfor the link establishment.The decoupling algorithmwe designed reassigns the degrees of freedomand forces in the control loop to ensure sufficient degrees of freedomfor optical axis control.In addressing the distinct dynamic characteristics of different degrees of freedom,a transfer function compensation method is used in the decoupling process to further minimize motion coupling.The open-loop frequency response of the systemis obtained through simulation.The upgraded decoupling algorithms effectively reduce the open-loop frequency response by 30 dB.The transfer function compensation method efficiently suppresses the coupling of low-frequency noise.展开更多
In order to reduce the coupling between pitch, yaw and roll channels of the bank-to-turn （BTT） missile caused due to missile body roll. A new structure actuator for reducing the coupling of BTT missiles is studied. ...In order to reduce the coupling between pitch, yaw and roll channels of the bank-to-turn （BTT） missile caused due to missile body roll. A new structure actuator for reducing the coupling of BTT missiles is studied. The new structure actuator can roll independently along the longitudinal axis of the missile. The actu- ator instead of airframe needs to steer when controlling BTT missile roll. So the rolling speed of main airframe and thus the coupling of missile introduced by airframe rolling are reduced. And control logic is designed for the missile using roll actuator. Finally, analysis and simulation results demonstrate the effectiveness of the rolling actuator in decoupling a BTT missile.展开更多
This paper carries out an experiment study of decoupling performance for a novel lateral axis micromachined gyroscope with varying environmental parameters. The non-ideal mathematical model for the coupling mechanism ...This paper carries out an experiment study of decoupling performance for a novel lateral axis micromachined gyroscope with varying environmental parameters. The non-ideal mathematical model for the coupling mechanism of the gyroscope is estab-lished through the gyro dynamic response matrix. The coupling components varying with ambient pressure and temperature induced by stiffness coupling, damping coupling and electrostatic force coupling are semi-analytically discussed. The overall coupling ratio is evaluated via experiments in the custom-built installation. The testing results show that the decoupling per-formance of the gyroscope is sensitive to the environmental parameters and all the non-ideal errors are determined as a function of ambient pressure and temperature. The coupling error varies from 0.05% to 0.25% within the pressure range of 100 Pa-100 kPa. The characteristics of coupling with temperature are measured from 20℃ to 100℃ with a variation from 0.35% to 0.41%. The results also indicate that within the range of measured ambient pressure and temperature, the minimum coupling ratio occurs at 100 Pa and room temperature. The overall performance of the gyroscope is tested under the pressure of about 2000 Pa and room temperature to achieve a relatively low coupling ratio. The scale factor is measured to be 7.8 mV （°）-1 s-1 with nonlinearity about 0.45% in the full-scale range of 600 （°） s-1. The short-term bias stability is approximately 0.06 （°）s-1 （1σ） for 20 min with noise equivalent angular rate evaluated to be 0.077 （°） s-1 Hz-1/2.展开更多
基金supported by the National Key Research and Development Program of China(2022YFC2203700).
文摘The gravitational wave spacecraft is a complex multi-input multi-output dynamic system.The gravitational wave detection mission requires the spacecraft to achieve single spacecraft with two laser links and high-precision control.Establishing one spacecraftwith two laser links,compared to one spacecraft with a single laser link,requires an upgraded decoupling algorithmfor the link establishment.The decoupling algorithmwe designed reassigns the degrees of freedomand forces in the control loop to ensure sufficient degrees of freedomfor optical axis control.In addressing the distinct dynamic characteristics of different degrees of freedom,a transfer function compensation method is used in the decoupling process to further minimize motion coupling.The open-loop frequency response of the systemis obtained through simulation.The upgraded decoupling algorithms effectively reduce the open-loop frequency response by 30 dB.The transfer function compensation method efficiently suppresses the coupling of low-frequency noise.
文摘In order to reduce the coupling between pitch, yaw and roll channels of the bank-to-turn （BTT） missile caused due to missile body roll. A new structure actuator for reducing the coupling of BTT missiles is studied. The new structure actuator can roll independently along the longitudinal axis of the missile. The actu- ator instead of airframe needs to steer when controlling BTT missile roll. So the rolling speed of main airframe and thus the coupling of missile introduced by airframe rolling are reduced. And control logic is designed for the missile using roll actuator. Finally, analysis and simulation results demonstrate the effectiveness of the rolling actuator in decoupling a BTT missile.
文摘This paper carries out an experiment study of decoupling performance for a novel lateral axis micromachined gyroscope with varying environmental parameters. The non-ideal mathematical model for the coupling mechanism of the gyroscope is estab-lished through the gyro dynamic response matrix. The coupling components varying with ambient pressure and temperature induced by stiffness coupling, damping coupling and electrostatic force coupling are semi-analytically discussed. The overall coupling ratio is evaluated via experiments in the custom-built installation. The testing results show that the decoupling per-formance of the gyroscope is sensitive to the environmental parameters and all the non-ideal errors are determined as a function of ambient pressure and temperature. The coupling error varies from 0.05% to 0.25% within the pressure range of 100 Pa-100 kPa. The characteristics of coupling with temperature are measured from 20℃ to 100℃ with a variation from 0.35% to 0.41%. The results also indicate that within the range of measured ambient pressure and temperature, the minimum coupling ratio occurs at 100 Pa and room temperature. The overall performance of the gyroscope is tested under the pressure of about 2000 Pa and room temperature to achieve a relatively low coupling ratio. The scale factor is measured to be 7.8 mV （°）-1 s-1 with nonlinearity about 0.45% in the full-scale range of 600 （°） s-1. The short-term bias stability is approximately 0.06 （°）s-1 （1σ） for 20 min with noise equivalent angular rate evaluated to be 0.077 （°） s-1 Hz-1/2.
