【摘要】：攔截衛(wèi)星是空天攻防中的重要元素,其末段軌道控制問(wèn)題是完成攻擊任務(wù)的關(guān)鍵,伴隨著軌道不確定性、噪聲以及目標(biāo)衛(wèi)星的軌道機(jī)動(dòng)等因素,攔截衛(wèi)星在進(jìn)行軌道機(jī)動(dòng)時(shí)難以準(zhǔn)確獲得自己相對(duì)于目標(biāo)衛(wèi)星的位置以及速度。本文針對(duì)軌道信息不完備這一問(wèn)題,對(duì)攔截衛(wèi)星末段軌道控制系統(tǒng)進(jìn)行建模分析,并對(duì)攻防衛(wèi)星相互接觸和攻防衛(wèi)星相對(duì)位置保持兩種情況進(jìn)行控制器設(shè)計(jì)。本文主要研究?jī)?nèi)容為:(1)基于C-W方程建立了攔截衛(wèi)星相對(duì)運(yùn)動(dòng)動(dòng)力學(xué)模型,根據(jù)攻防衛(wèi)星相互接觸和攻防衛(wèi)星相對(duì)位置保持兩種情況進(jìn)行狀態(tài)空間表達(dá)式的建立,并引入非圓不確定性、能量有界噪聲和白噪聲等干擾。(2)利用動(dòng)態(tài)輸出反饋控制器建立閉環(huán)系統(tǒng),針對(duì)系統(tǒng)鎮(zhèn)定問(wèn)題、參數(shù)不確定性、能量有界噪聲、白噪聲和推力有限等限制條件,設(shè)計(jì)了可以滿足極點(diǎn)配置、H2性能指標(biāo)、H∞性能指標(biāo)和推力有限約束的多目標(biāo)動(dòng)態(tài)輸出反饋控制器。(3)引入狀態(tài)觀測(cè)器,利用狀態(tài)觀測(cè)器實(shí)現(xiàn)狀態(tài)反饋。針對(duì)系統(tǒng)鎮(zhèn)定問(wèn)題、參數(shù)不確定性、能量有界噪聲以及白噪聲等限制條件,設(shè)計(jì)了可以滿足極點(diǎn)配置、H2性能指標(biāo)和H∞性能指標(biāo)的多目標(biāo)控制器。并基于閉環(huán)系統(tǒng)的傳遞函數(shù)分離特性和極點(diǎn)配置分離特性,將原系統(tǒng)分成兩個(gè)子系統(tǒng)分別進(jìn)行控制器和觀測(cè)器的設(shè)計(jì)。(4)基于攔截衛(wèi)星采樣軌道狀態(tài)信號(hào),將連續(xù)系統(tǒng)轉(zhuǎn)換為采樣系統(tǒng)。再利用輸入時(shí)滯法將采樣系統(tǒng)等價(jià)變換為時(shí)滯系統(tǒng)形式,利用時(shí)滯系統(tǒng)的思想設(shè)計(jì)魯棒濾波器,并將設(shè)計(jì)方法拓展應(yīng)用到攔截衛(wèi)星以與目標(biāo)衛(wèi)星相對(duì)位置保持為目標(biāo)的魯棒濾波器設(shè)計(jì)。
[Abstract]:Intercepting satellite is an important element in space and space attack and defense. The control of its terminal orbit is the key to accomplish the attack mission, accompanied by the orbit uncertainty, noise and orbit maneuver of the target satellite, and other factors, such as the orbit uncertainty, the noise and the orbit maneuver of the target satellite, etc. It is difficult to obtain the position and velocity of the interceptor satellite in orbit maneuver. Aiming at the problem of incomplete orbit information, this paper models and analyzes the terminal orbit control system of intercepting satellite, and designs the controller for the contact between attack and defense satellites and the relative position of attack and defense satellite. The main contents of this paper are as follows: (1) based on the C-W equation, the relative motion dynamics model of the interceptor satellite is established, and the expression of the state space is established according to the contact between the attack and defense satellites and the relative position of the attack and defense satellite. The noncircular uncertainty, energy bounded noise and white noise are introduced. (2) the closed-loop system is established by using dynamic output feedback controller to solve the stabilization problem, parameter uncertainty, energy bounded noise, etc. A multi-objective dynamic output feedback controller, which can satisfy the pole assignment, H2 performance index, H 鈭，

本文編號(hào)：2341088