6 results about "Attitude control" patented technology

A system and method is provided for thruster control in a flight vehicle. The system and method uses a proportional derivative matrix control technique to determine thrust commands in a Divert and Attitude control (DAC) system. The proportional derivative matrix control system is configured to receive pitch, roll and yaw commands as inputs, and generate thrust commands as outputs. The performance of the proportional derivative matrix controller is such that the thrust commands can achieve the desired attitude angles quickly and with reduced fuel consumption. The matrix control system can efficiently control a variety of thrusters, including asymmetric thrusters having different moment arms. The matrix control system is particularly suitable to the control of DAC systems with asymmetric thrusters that are configured for attitude control.

The invention discloses a control method and system for high-reliability use of a three-floating gyroscope. The control method comprises the following steps: selecting a plurality of gyroscopes correspondingly indicated by a gyroscope selection mark as alternative gyroscopes; acquiring a communication mark and a motor state mark of each alternative gyroscope; judging the effectiveness of each alternative gyroscope according to the communication mark and the motor state mark of each alternative gyroscope to obtain an effectiveness mark of each alternative gyroscope; determining a used gyroscope according to the validity mark of each alternative gyroscope; and performing attitude control on the satellite according to the angular velocity measured by using the gyroscope. According to the method, the safety problem of motor starting under the condition of short-time power failure of the three-floating gyroscope and the problem that error data is introduced into a control system when the gyroscope is not started completely are solved.

The invention belongs to the technical field of attitude control, and relates to an aircraft attitude adjustment path optimization method based on rotation. The invention provides an inertia/starlightcombined attitude adjustment star observation sequence aerial autonomous setting method. Rotation freedom degree constraints are divided into three types, namely single-freedom-degree posture adjustment, two-freedom-degree posture adjustment and three-freedom-degree posture adjustment, and aiming at the three types of freedom degree constraints, posture adjustment parameters based on the optimalplatform error angle observation matrix D, namely the optimal design criterion of the optimal rotation angle, are given respectively.

The invention provides a dynamic characteristic test method and device of an air spring with an altitude valve control for a vehicle. The method and the device can obtain dynamic characteristic data which more accord with the air spring in the running process of the vehicle and provide more accurate data for vehicle design, suspension and whole vehicle dynamic performance optimization and vehiclebody attitude control.

The invention relates to a solar sail spacecraft three-axis attitude control and execution mechanism which is divided into a sliding mass block and a moving small sail. The solar sail spacecraft three-axis attitude control and execution mechanism comprises a support rod, the sliding bock, the small sail, a telescopic rod and a support frame. The support rod supports the spacecraft sail face, and the sliding block is embedded on the support rod and can slide along the support rod. One end of the telescopic rod is connected with the small sail, and the other end of the telescopic rod is fixedly connected to the support frame. The telescopic rod can telescope and rotate, the length of the telescopic rod is adjusted through linear telescoping, and the small sail is driven to rotate through rotation of the telescopic rod. The bottom end of the support frame is fixed to the geometric center of the spacecraft sail face, and the top end of the support frame is connected with a spacecraft load. According to the solar sail spacecraft three-axis attitude control and execution mechanism, torque needed by solar sail three-axis attitude control, sunlight is completely utilized for supplying energy, the structure is simple, and unfolding of the spacecraft sail face is not affected. By means of the solar sail spacecraft three-axis attitude control and execution mechanism, rolling shaft torque can be provided rapidly, and adjustable range of amplitude of the torque is large.

A pan-tilt control method and device, a pan-tilt and a computer readable storage medium, the pan-tilt comprising a protective case, the method comprising: acquiring a measurement attitude of the pan-tilt, and acquiring an expected attitude of the pan-tilt at a previous moment (S101); determining a base attitude of the pan-tilt based on the measurement attitude (S102); according to the base attitude and the expected attitude at the previous moment, determining a rotation axis and a rotation angle corresponding to the plane constraint-based adjustment attitude of the pan-tilt (S103); according to the rotation axis, the rotation angle, and the expected attitude at the previous moment, determining an expected attitude at the current moment of the pan-tilt (S104); and controlling the pan-tilt to rotate according to the expected attitude at the current time, so that a field of view corresponding to a photographing device loaded on the pan-tilt does not contain the protective shell (S105).