Launch Vehicle Design and Attitude Control

• Main Authors: Chen, Yi-Chi, 陳逸棋
• Other Authors: Lin, Ching-An
• Format: Others
• Language: zh-TW
• Published: 2012
• Online Access: http://ndltd.ncl.edu.tw/handle/tm5wev

碩士 === 國立交通大學 === 電控工程研究所 === 101 === This thesis discusses the mass configuration of rocket based on energy, we use optimization method to calculate the best mass distribution , and we found that the best distribution almost has the same result with theoretical analysis even under the influence of gravity and aerodynamic forces. Guidance law of this thesis can be divided into three stages. The first stage is gravity turn, we control the angle of attack to zero by using pitch angular velocity feedback, that avoid rocket damage due to aerodynamic forces. The second stage is linear tangent law, we use the angle which calculated in advance to make rocket turns, let the rocket is in level flight at Earth’s surface so that the rocket meet desired altitude and reduces flight path angle. The third stage is precise orbit injection, we use angle control and altitude feedback, angle control is to control the rocket is in level flight, this can made flight path angle to zero. Altitude feedback transfers altitude variation to angle compensation through look-up table, let the rocket fly at desired altitude. When the rocket speed meet the condition of orbit injection, the rocket separates and sends the payload into orbit. The most important is the error of altitude after orbit injection. Results of simulation show that the guidance can send the payload into orbit successfully.