發射載具的入軌導引

Abstract

本文針對不同的第二節火箭燃燒結束後的位置、速度數據，提供一種入軌導引律，使火箭滿足入軌條件，進入目標軌道當中。火箭在第二節燃燒後，會進入一段滑行階段，期間會關閉火箭的引擎，使火箭只受到重力的影響，並隨著其所產生的橢圓軌道滑行。根據第二節燃燒結束後的位置、速度數據，我們能夠計算軌道參數，進而與目標軌道高度比較，設計目標滑行位置的高度，並計算到達滑行目標高度所需的滑行時間。當到達滑行目標高度後，即開啟第三節火箭，透過牛頓迭代法找尋線性正切導引律的參數，根據不同的軌道高度，產生不同的補償角，使火箭調整自身的速度、姿態，最終進入軌道當中。由模擬的結果可以得知，設計的導引律能將火箭送入不同高度的軌道當中，且離心率、軌道遠地點與近地點的高度相差甚小。

This thesis discusses different kinds of the location and velocity data that after second phase was burned and provide a guidance law for launch vehicles to achieve the orbit conditions, eventually insert the target orbit. After the second phase was burned, the launch vehicle will enter into Coast phase. During Coasting phase the engine will be closed .The launch vehicle will only be affected by gravity and will coast along the elliptical orbit it produces. According to the position and velocity data after the second phase was burned, we can calculate the orbital parameters, then compare with the target orbit height to design the coast target height and calculate the required coasting time.When the coast target height is reached, the third phase of the launch vehicle is opened. We will use Newton iteration method to find the parameters of the linear tangent guidance law. According to the different orbital heights, different thrust elevation compensation will be generated, so that the launch vehicles adjusts its speed and attitude eventually insert the target orbit.Results of the simulation show that the guidance can make launch vehicles insert different heights of the orbit successfully.