Search

We present a real-time error-compensation method which is used to improve the measurement precision of a Scheimpflug range sensor. Based on this method a Scheimpflug range sensor is fabricated. It only takes 3.21 ms to complete one distance measurement in a hardware test. Furthermore, by using this range sensor, an altitude-holding application is performed on a proof-of-concept flight test platform in the lab environment. The hardware-in-loop (HIL) simulation result shows that approximately 10 mm control accuracy is achieved by implementing the error compensation.

A brief account of basic connotation and evaluation indexes system of harmonious leadership teams is gave. On this basis, a simulation model is built by using the ARENA simulation software and the quantified simulation is carried out for the factors of harmonization of aerospace enterprise leadership teams. Moreover, by taking the characteristics of aerospace enterprise leadership teams into consideration, this article lays emphasis on the comparison of harmonization quantified results of several typical leadership teams, especially on the comparative analysis of influencing degrees of moral characters and capabilities on the leadership teams overall harmonization. Finally, a conclusion is drawn.

For the missile with blended aero-fin and lateral impulsive thrust, a blended control autopilot is designed, which comprises an optimal controller and a control allocation module. The combined optimal/classical approach is applied to designing the optimal controller to determine the virtual controls, and the control allocation module is used to distribute the desired virtual controls onto the redundant control effectors. The autopilot holds some attractive characteristics, such as simple structure, good tracking performance and robustness; moreover the actual constraints of the control effectors can be taken into account. Based on this blended control autopilot, it is found that the conflict between stability and fast tracking performance is serious when using the total acceleration as feedback. In order to avoid this problem, the transient factors in total acceleration are eliminated, so the acceleration caused only by angle of attack is used as feedback, and obvious improvement is shown. Finally, how to get reasonable acceleration feedback is discussed, and conclusion is presented that after passing the low-pass filter, the total acceleration can also be used as feedback, and satisfied tracking performance can be obtained.