艦載戰(zhàn)斗機(jī)進(jìn)場功率補(bǔ)償?shù)目刂坡裳芯?/H1>
發(fā)布時間：2018-10-30 13:49
【摘要】：艦載戰(zhàn)斗機(jī)是航空母艦武器系統(tǒng)中的重要作戰(zhàn)手段，為保證艦載機(jī)安全著艦，提出了進(jìn)場功率補(bǔ)償系統(tǒng)，按照進(jìn)場功率補(bǔ)償控制律對發(fā)動機(jī)推力進(jìn)行控制，以克服艦載機(jī)低速進(jìn)場時的速度不穩(wěn)問題，提高航跡控制精度。因此，研究并設(shè)計進(jìn)場功率補(bǔ)償系統(tǒng)具有重要意義。本文以國外某艦載機(jī)為例，展開了進(jìn)場功率補(bǔ)償控制律的研究和設(shè)計，主要研究內(nèi)容如下： 1.艦載機(jī)縱向運(yùn)動數(shù)學(xué)模型的建立和處理。根據(jù)牛頓運(yùn)動定律對艦載機(jī)縱向運(yùn)動受力分析，列出了其動力學(xué)方程，對其進(jìn)行小擾動和線性化的簡化處理，建立艦載機(jī)三自由度的縱向運(yùn)動模型，從而得到航跡角對俯仰角的一般響應(yīng)特性。 2.艦載機(jī)進(jìn)場功率補(bǔ)償?shù)目刂撇呗匝芯�。分別分析了速度恒定的進(jìn)場功率補(bǔ)償系統(tǒng)和迎角恒定的進(jìn)場功率補(bǔ)償系統(tǒng)，應(yīng)用PID理論進(jìn)行設(shè)計并比較其控制性能，結(jié)論是迎角恒定的進(jìn)場功率補(bǔ)償系統(tǒng)比速度恒定的進(jìn)場功率補(bǔ)償系統(tǒng)更能滿足艦載機(jī)著艦快速性、準(zhǔn)確性和安全性的要求。 3.艦載機(jī)進(jìn)場功率補(bǔ)償控制律的分析和設(shè)計。針對國外某型艦載機(jī)的具體要求，，采用引入了法向加速度和舵面信息的迎角恒定的進(jìn)場功率補(bǔ)償系統(tǒng)，并進(jìn)行控制律的分析和設(shè)計。通過仿真驗證表明，所設(shè)計的進(jìn)場功率補(bǔ)償控制律能夠良好的滿足該型艦載機(jī)的要求，保證其著艦的安全性和穩(wěn)定性。 通過分析和仿真驗證表明，本文所設(shè)計的自動油門指令算法和進(jìn)場功率補(bǔ)償控制律達(dá)到了該型艦載機(jī)的各項要求，具有一定的工程實際意義。
[Abstract]:Shipborne fighter is an important means of combat in aircraft carrier weapon system. In order to ensure the carrier aircraft to land safely, an approach power compensation system is proposed to control the engine thrust in accordance with the approach power compensation control law. In order to overcome the problem of velocity instability and improve the accuracy of track control. Therefore, it is of great significance to study and design the approach power compensation system. Taking a shipborne aircraft abroad as an example, the research and design of approach power compensation control law are carried out in this paper. The main research contents are as follows: 1. Establishment and processing of Longitudinal Motion Mathematical Model of Carrier-borne aircraft. According to Newton's law of motion, the longitudinal motion force of shipborne aircraft is analyzed, its dynamic equation is listed, the small disturbance and linearization are simplified, and the longitudinal motion model of shipborne aircraft with three degrees of freedom is established. The general response of track angle to pitch angle is obtained. 2. Research on Control Strategy of approach Power compensation for Carrier aircraft. The power compensation system with constant velocity and constant angle of attack is analyzed, and the control performance is compared by using PID theory. The conclusion is that the approach power compensation system with constant angle of attack can meet the requirements of speed, accuracy and safety better than the one with constant speed. 3. Analysis and design of power compensation control law for shipborne aircraft. According to the specific requirements of a shipborne aircraft abroad, a power compensation system with constant angle of attack with normal acceleration and rudder surface information is adopted, and the control law is analyzed and designed. The simulation results show that the proposed approach power compensation control law can meet the requirements of the aircraft and ensure the safety and stability of the ship landing. The analysis and simulation results show that the automatic throttle instruction algorithm and the approach power compensation control law designed in this paper meet the requirements of the shipborne aircraft and have a certain practical significance in engineering.
【學(xué)位授予單位】：沈陽航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V271.492
【參考文獻(xiàn)】
相關(guān)期刊論文 前10條
1 張明廉，徐軍;艦載飛機(jī)自動著艦系統(tǒng)的研究[J];北京航空航天大學(xué)學(xué)報;1994年04期
2 金長江,車軍;斜板滑跳起飛動力學(xué)特性研究[J];北京航空航天大學(xué)學(xué)報;1997年03期
3 袁鎖中,楊一棟;艦載飛機(jī)著艦精確軌跡跟蹤控制研究[J];飛行力學(xué);2000年01期
4 張玉潔;楊一棟;;保持飛行迎角恒定的動力補(bǔ)償系統(tǒng)性能分析[J];飛行力學(xué);2006年04期
5 朱齊丹;李新飛;呂開東;;基于滑模變結(jié)構(gòu)控制的艦載機(jī)動力補(bǔ)償系統(tǒng)設(shè)計[J];飛行力學(xué);2012年03期
6 勵纓，溫瑋，金長江;艦載飛機(jī)逃逸復(fù)飛動力學(xué)特性研究[J];飛行力學(xué);1994年02期
7 李忠東;;自動油門控制技術(shù)在艦載機(jī)上的應(yīng)用[J];飛機(jī)設(shè)計;2012年04期
8 林國鋒;高浩;;直接升力控制對飛機(jī)著艦穩(wěn)定性的改善[J];飛行力學(xué);1992年01期
9 田寶林;艦載飛機(jī)對動力裝置特殊要求的分析(上)[J];航空發(fā)動機(jī);1997年02期
10 金長江,洪冠新;艦載機(jī)彈射起飛及攔阻著艦動力學(xué)問題[J];航空學(xué)報;1990年12期
本文編號：2300177
本文鏈接：http://sikaile.net/kejilunwen/hangkongsky/2300177.html
[Abstract]:Shipborne fighter is an important means of combat in aircraft carrier weapon system. In order to ensure the carrier aircraft to land safely, an approach power compensation system is proposed to control the engine thrust in accordance with the approach power compensation control law. In order to overcome the problem of velocity instability and improve the accuracy of track control. Therefore, it is of great significance to study and design the approach power compensation system. Taking a shipborne aircraft abroad as an example, the research and design of approach power compensation control law are carried out in this paper. The main research contents are as follows: 1. Establishment and processing of Longitudinal Motion Mathematical Model of Carrier-borne aircraft. According to Newton's law of motion, the longitudinal motion force of shipborne aircraft is analyzed, its dynamic equation is listed, the small disturbance and linearization are simplified, and the longitudinal motion model of shipborne aircraft with three degrees of freedom is established. The general response of track angle to pitch angle is obtained. 2. Research on Control Strategy of approach Power compensation for Carrier aircraft. The power compensation system with constant velocity and constant angle of attack is analyzed, and the control performance is compared by using PID theory. The conclusion is that the approach power compensation system with constant angle of attack can meet the requirements of speed, accuracy and safety better than the one with constant speed. 3. Analysis and design of power compensation control law for shipborne aircraft. According to the specific requirements of a shipborne aircraft abroad, a power compensation system with constant angle of attack with normal acceleration and rudder surface information is adopted, and the control law is analyzed and designed. The simulation results show that the proposed approach power compensation control law can meet the requirements of the aircraft and ensure the safety and stability of the ship landing. The analysis and simulation results show that the automatic throttle instruction algorithm and the approach power compensation control law designed in this paper meet the requirements of the shipborne aircraft and have a certain practical significance in engineering.
【學(xué)位授予單位】：沈陽航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V271.492
【參考文獻(xiàn)】
相關(guān)期刊論文 前10條
1 張明廉，徐軍;艦載飛機(jī)自動著艦系統(tǒng)的研究[J];北京航空航天大學(xué)學(xué)報;1994年04期
2 金長江,車軍;斜板滑跳起飛動力學(xué)特性研究[J];北京航空航天大學(xué)學(xué)報;1997年03期
3 袁鎖中,楊一棟;艦載飛機(jī)著艦精確軌跡跟蹤控制研究[J];飛行力學(xué);2000年01期
4 張玉潔;楊一棟;;保持飛行迎角恒定的動力補(bǔ)償系統(tǒng)性能分析[J];飛行力學(xué);2006年04期
5 朱齊丹;李新飛;呂開東;;基于滑模變結(jié)構(gòu)控制的艦載機(jī)動力補(bǔ)償系統(tǒng)設(shè)計[J];飛行力學(xué);2012年03期
6 勵纓，溫瑋，金長江;艦載飛機(jī)逃逸復(fù)飛動力學(xué)特性研究[J];飛行力學(xué);1994年02期
7 李忠東;;自動油門控制技術(shù)在艦載機(jī)上的應(yīng)用[J];飛機(jī)設(shè)計;2012年04期
8 林國鋒;高浩;;直接升力控制對飛機(jī)著艦穩(wěn)定性的改善[J];飛行力學(xué);1992年01期
9 田寶林;艦載飛機(jī)對動力裝置特殊要求的分析(上)[J];航空發(fā)動機(jī);1997年02期
10 金長江,洪冠新;艦載機(jī)彈射起飛及攔阻著艦動力學(xué)問題[J];航空學(xué)報;1990年12期
本文編號：2300177
本文鏈接：http://sikaile.net/kejilunwen/hangkongsky/2300177.html
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