This paper presents the summary of the image processing of a vision-based three-axis attitude determination sensor, which observes a solar system oblate body such as a planet or a planet’s moon. From the observed image it is possible to extract two independent directions and, consequently, to estimate the three-axis spacecraft attitude. By measuring two independent directions, the sensor can op...

This paper proposes an approach for measuring the azimuth angle and tilt angle of underground drilling tools with a MEMS three-axis accelerometer and a three-axis fluxgate sensor. A mathematical model of well logging attitude angle is deduced based on combining space coordinate transformations and algebraic equations. In addition, a system implementation plan of the inclinometer is given in thi...

Space manipulators mounted on an on-o thrustercontrolled base are envisioned to assist in the assembly and maintenance of space structures. When handling large payloads, manipulator joint and link exibility become important, for they can result in payload-attitude controller fuel-replenishing dynamic interactions. In this paper, the dynamics model of an Nexible-joint space manipulator is develo...

An effective control scheme for three-phase three-wire active power filter is proposed in this paper. Conventionally, the majority of existing APF control strategies in literature adopts feed-forward control scheme, which results in switching notches (sharp-rising or falling ripples) in the source-side currents at conduction instants of diode/thyristor rectifier load. The proposed method utiliz...

In order to enhance the control stability and anti-interference ability of quadcopter, this paper presents a quadcopter based on double-layer PID control, designs with STM32 as main controller, simulates verifies its system attitude. Firstly, nonlinear attitude mathematical model aircraft is established by four-element method, relationship between angle angular velocity obtained solving, so tha...

In this paper, several attitude estimation designs are developed for the Tropical Rainfall Measurement Mission (TRMM) spacecraft. A contingency attitude determination mode is required in the event of a primary sensor failure. The final design utilizes a full sixth-order Kalman filter. However, due to initial software concerns, the need to investigate simpler designs was required. The algorithms...

In this paper, a closed-loop switching function for on-off thruster firings is proposed to provide good attitude control performance in the presence of modeling errors for single-axis slew maneuver of a rigid spacecraft and to eliminate double-sided thruster firings. The size of a single-sided deadband in the switching function provides the capability of a tradeoff between maneuver time and fue...