【摘要】：試飛檢驗是機載預警雷達在正式投入使用之前或維修之后必不可少的關鍵環(huán)節(jié)�，F(xiàn)行的機載預警雷達試飛檢驗的方法主要是參考地基雷達的相關規(guī)范,不能全面的反應機載預警雷達的真實性能。同時,試飛檢驗也是一項耗時長、耗資巨大的過程。對新型雷達的試飛檢驗往往會持續(xù)數(shù)年以上,這就會耗費大量的人力、物力和財力。因此,系統(tǒng)性的研究機載預警雷達試飛檢驗的方法就變得尤為重要。本文的主要內(nèi)容和工作如下:1.分析了機載預警雷達的探測性能。在具體安排某款機載預警雷達的試飛試驗前,需要先知道該雷達整體的探測能力。為此,研究了雜波回波功率模型,其中詳細介紹了劃分地面網(wǎng)格、后向散射模型、空間坐標系轉(zhuǎn)換和天線方向圖等模塊。之后,建立了目標回波和噪聲的功率模型,并給出了仿真結(jié)果。進而繪制了距離-速度盲區(qū)圖,該圖能夠全面的反映雷達的探測性能。2.編排了試飛測試方案。根據(jù)雜波回波功率圖,分析了試飛中所關心的檢飛地區(qū)的選擇問題。針對現(xiàn)行試飛試驗時只安排載機和目標機迎頭飛行的缺陷,提出分方位向的安排斜向飛行的航線設計原則。接著,依照距離-速度盲區(qū)圖按該原則以機載預警雷達在某些探測能力較弱的方位向上為例設計了試飛的航線。為了能夠在一次試飛中能夠盡可能多的找出雷達探測能力的薄弱區(qū)域,減少試飛所需的總時間,本文還設計了一條目標機對載機不可視的航線。3.研究了試飛實測數(shù)據(jù)的處理方法。本文建立了試飛實測數(shù)據(jù)處理的一系列流程,如先經(jīng)過時間配準、坐標轉(zhuǎn)換和野值剔除對數(shù)據(jù)進行預處理,接著按一定的距離采樣間隔對數(shù)據(jù)進行分割,進而評估探測威力和測量精度這兩項機載預警雷達的重要指標。在做數(shù)據(jù)分割時,根據(jù)用戶所關心的結(jié)果,將采樣點數(shù)的計算從發(fā)現(xiàn)概率統(tǒng)計可信度轉(zhuǎn)換到探測距離統(tǒng)計可信度,依此求出合理的距離采樣間隔。針對利用實測數(shù)據(jù)做精度分析時發(fā)現(xiàn)的載機拐彎時測量精度偏差較大這個問題,分析了偏差產(chǎn)生的原因并提出了解決方案。通過目標航跡修正后與修正前的對比證明了解決方案的可行性。4.制作了一款試飛仿真的小軟件。重點介紹了該軟件的組成框圖和具體的實現(xiàn)方法,并演示了載機和目標機的試飛仿真結(jié)果。該軟件具有友好的人機界面和良好的動態(tài)可視化效果。
[Abstract]:Flight test is an essential key link of airborne early warning radar before it is put into use or after maintenance. The current flight test methods of airborne early warning radar mainly refer to the relevant specifications of ground-based radar and can not fully reflect the real performance of airborne early warning radar. At the same time, flight testing is also a time-consuming and costly process. The flight test of the new radar will last more than a few years, which will cost a lot of manpower, material and financial resources. Therefore, the systematic study of airborne early warning radar flight test method becomes particularly important. The main contents and work of this paper are as follows: 1. The detection performance of airborne early warning radar is analyzed. Before arranging the flight test of an airborne early warning radar, we need to know the overall detection capability of the radar. In this paper, the clutter echo power model is studied, including ground grid division, backscattering model, spatial coordinate system transformation and antenna pattern. Then, the power model of target echo and noise is established, and the simulation results are given. Furthermore, the range-velocity blind area map is drawn, which can fully reflect the radar detection performance. 2. The flight test program was designed. According to the power diagram of clutter echo, the selection of detection area concerned in flight test is analyzed. Aiming at the defect that only onboard aircraft and target aircraft are arranged head-on in the current flight test, the principle of route design for inclined flight in azimuth direction is put forward. Then, according to the principle of range-velocity blind area map, the flight route of airborne early warning radar is designed as an example in some azimuth with weak detection ability. In order to find out as many weak areas as possible in a test flight and reduce the total time required for flight test, this paper also designs an invisible route of target aircraft to the carrier. The processing method of flight test data is studied. In this paper, a series of processes of flight test data processing are established, such as time registration, coordinate transformation and outliers elimination, data preprocessing, and then data segmentation according to a certain distance sampling interval. Then the detection power and measurement accuracy are evaluated as two important indexes of airborne early warning radar. In the process of data segmentation, according to the results concerned by the user, the calculation of the sampling points is transformed from the discovery probability statistical credibility to the detection distance statistical credibility, and the reasonable distance sampling interval is obtained. In order to solve the problem that the deviation of measurement precision is large when the load machine turns around, the cause of the deviation is analyzed and the solution is put forward. The feasibility of the solution is proved by the comparison between the target track correction and the correction. 4. A flight test simulation software is made. The composition block diagram and realization method of the software are introduced emphatically, and the flight test simulation results of the carrier and target aircraft are demonstrated. The software has friendly man-machine interface and good dynamic visualization effect.
【學位授予單位】：電子科技大學
【學位級別】：碩士
【學位授予年份】：2014
【分類號】：TN959.73

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本文編號：2267781