近年來，積體電路（IC）的發展一直是眾所矚目的焦點，其原因不外乎是因為它的微小、精密、運算快速，甚至價格便宜等優點，也因此越來越多在工業上、日常生活上、學術研究上的應用。吾人即因這些優點，將其運用在飛彈的控制上，以期達到飛彈自動駕駛微小化、晶片化的目的。飛彈的自動駕駛系統包含導航系統及控制系統，導航系統接收來自於感測器的資訊，即接收三個軸向的陀螺儀及三個軸向的加速儀訊號，經過DSP計算後輸出，可得到飛彈的 ；而控制邏輯則是根據這些飛彈的狀態變數，經過DSP運算後，輸出飛彈四片尾翼所要打的角度。
　　本論文利用德州儀器公司生產的DSP來實現飛彈的導航及控制電路。吾人使用MATLAB及Simulink來執行複雜的導航迴路及控制迴路計算，再利用RTW將此迴路編譯成C code，下載到DSP內，達到控制飛彈系統的目的。所以在程式設計方面，利用MATLAB軟體從一開始模型的建立、DSP的設計到電路的模擬驗証，都可在同一個設計環境下完成（system design on a chip），使得設計與修改的工作更有效率。而設計出的晶片架構可以當作飛彈系統上一個獨立的模組，可以輕易維修及管理，亦是設計此晶片的另一個重要目的。

　　Recently, the development of Integrated Circuit (IC) has accelerated the growth of every branch of industry, because of its smallness, preciseness, high speed, and cheapness. Due to these advantages, we think it comes the time to investigate the possibility of integrating the whole missile navigation and control system into a single chip. Based on this motivation, in this thesis we find it is very promising to employ the TI24xx DSP chip to implement the integrated circuit of missile navigation and control system. The designed DSP chip receives the information of translational and rotational motion from gyros and accelerators fixed on the body axes and then compute the state variables describing the motion of missile ; using these state variables as input, DSP controller determines the deflection angles of missile rear wings according to the implemented control law.
　　The missile navigation and control loops are modeled and simulated by MATLAB & Simulink, translated to C code by real-time workshop (RTW), and finally downloaded to DSP to produce a chip design of missile autopilot. What we have proposed in this thesis is the concept of system design on a single chip : control law programming, missile modeling, DSP implementation, and circuit testing, can all be done in the same environment and accomplished in a single DSP chip. The hardware-in-the-loop simulation will be employed to validate feasibility of the designed DSP chip.

[1] 李勁輪, “應用強健控制于大離軸角飛彈自動駕駛設計”, 國立成功大學航空太空工程研究所碩士論文,1998.
[2] 白鴻慶, “高攻角飛彈之強健性控制”, 國立成功大學航空太空工程研究所碩士論文,2000.
[3] 蘇宗志,“遙控直昇機飛行控制測試系統之建立”,國立成功大學航空太空工程研究所碩士論文,1996.
[4] 洪啟超,“遙控直昇機增穩系統設計與製作”,國立成功大學航空太空工程研究所碩士論文,1996.
[5] 于武強,“無人飛行載具導控迴路之硬體設計”,國立成功大學航空太空工程研究所碩士論文,1999.
[6] 郭承忠,“無人飛行載具導控系統之設計與測試”,國立成功大學航空太空工程研究所碩士論文,2000.
[7] 許東榮, “應用DSP、FPGA及GPS模組實現無人飛行載具之自動導航駕駛系統” 國立成功大學航空太空工程研究所碩士論文,2002.
[8] 楊憲東, “自動飛行控制原理與實務”,全華科技圖書股份有限公司,2002.
[9] Nesline, F.W. and Zarchan, P., “Robust Instrumentation Configurations for Homing Missile Flight Control”, Proc. of the AIAA Guidance, Navigation, and Control Conference, Danvers, MA, Aug. 1980, pp. 209-219.
[10] 楊憲東, “ 控制理論與應用”.
[11] LMI Control Toolbox User’s Guide, The MathWorks, 1995.
[12] Developer’s Kit for Texas InstrumentsTM DSP User’s Guide, The MathWorks, 2001.
[13] 鈦思科技股份有限公司 “視覺化建模環境-Simulink 入門與進階” ,鈦思科技股份有限公司, 2001
[14] Texas Instruments, “Code Composer User’s Guide”, 1999.
[15] Texas Instruments, eZdspTM LF2407 Technical Reference”, 2001.
[16] Texas Instruments, “Stateflow and Stateflow Coder” , 2002