本文選題：飛機磁干擾建模　切入點：磁補償算法　出處：《電子科技大學(xué)》2015年碩士論文

【摘要】：在航空磁異常探測中,飛機本身硬磁材料產(chǎn)生的固有磁場、軟磁材料磁化產(chǎn)生的感應(yīng)磁場以及飛機切割地磁場產(chǎn)生的渦流磁場,都會對磁力儀的測量產(chǎn)生干擾。要探測的目標(biāo)在飛機飛行高度處所產(chǎn)生的信號磁場可能比飛機產(chǎn)生的干擾磁場小很多,因此對飛機平臺進(jìn)行磁干擾補償是航空磁探測的關(guān)鍵技術(shù)之一。本文提出的補償算法是基于標(biāo)量磁力儀測量的總磁場和矢量磁力儀測量的地磁場方向,是一種軟補償方法。首先,通過分析飛機產(chǎn)生的各種磁干擾類型和特性,建立了干擾磁場數(shù)學(xué)模型,并對特征干擾函數(shù)之間的復(fù)共線性進(jìn)行了分析。為了獲得求解補償系數(shù)所需要的實測數(shù)據(jù),設(shè)定了校準(zhǔn)飛行路線,一般是一個沿順時針方向飛行的四邊形,飛機在四邊形的每條邊上飛行時,依次做搖擺、俯仰和偏航三組機動性動作,標(biāo)量和矢量磁力儀同步采集數(shù)據(jù)。然后,提出了利用加權(quán)匹配法和嶺估計技術(shù)求解補償系數(shù)的算法,當(dāng)加權(quán)函數(shù)選取為特征干擾函數(shù)時就是傳統(tǒng)的最小二乘法或迦遼金法,而嶺估計技術(shù)一般可以獲得比最小二乘法更好的結(jié)果。進(jìn)一步,提出了一種先對總場和特征干擾函數(shù)進(jìn)行濾波處理,再同時求解補償系數(shù)和背景磁場的循環(huán)迭代算法。大量仿真表明,這些算法可以獲得較好的補償效果最后,開展了大量的外場半實物仿真實驗,利用所獲得的實驗數(shù)據(jù)驗證了補償算法的可靠性和實用性,補償后的品質(zhì)因數(shù)一般能達(dá)到100pT以下的水平,可滿足一般的工程要求。論文闡述的磁補償數(shù)學(xué)建模、補償系數(shù)求解算法以及外場模擬實驗方法和結(jié)論,對下一步開展實際的飛機平臺磁干擾補償試驗有指導(dǎo)意義。
[Abstract]:In aeromagnetic anomaly detection, the inherent magnetic field produced by the hard magnetic material of the aircraft itself, the inductive magnetic field caused by the magnetization of the soft magnetic material and the eddy current magnetic field caused by the plane's cutting geomagnetic field, Will interfere with the measurements of the magnetometer. The signal magnetic field generated by the target at the altitude of the plane may be much smaller than the magnetic field generated by the aircraft. Therefore, compensation for magnetic interference on aircraft platform is one of the key technologies in aeromagnetic detection. The compensation algorithm proposed in this paper is based on the total magnetic field measured by scalar magnetometer and the direction of geomagnetic field measured by vector magnetometer. It is a soft compensation method. Firstly, by analyzing the types and characteristics of various magnetic disturbances produced by aircraft, a mathematical model of interference magnetic field is established. The complex collinearity between the characteristic interference functions is analyzed. In order to obtain the measured data needed to solve the compensation coefficient, a calibrated flight path is set up, which is generally a quadrilateral flying clockwise. As the plane flies on each side of the quadrilateral, it does three sets of maneuvering actions in turn: swing, pitch and yaw. Scalar and vector magnetometers synchronize data collection. Then, This paper presents an algorithm for calculating compensation coefficients by using weighted matching method and ridge estimation technique. When the weighted function is selected as the characteristic interference function, it is the traditional least square method or Galerkin method. The ridge estimation technique can generally obtain better results than the least square method. Furthermore, a new method for filtering the total field and the characteristic interference function is proposed. A large number of simulations show that these algorithms can obtain better compensation effect. Finally, a large number of hardware-in-the-loop simulation experiments are carried out. The reliability and practicability of the compensation algorithm are verified by the experimental data obtained. The quality factor after compensation can generally reach the level of 100pT, which can meet the general engineering requirements. The algorithm of calculating compensation coefficient and the method and conclusion of field simulation experiment can be used to guide the practical test of magnetic interference compensation for aircraft platform.
【學(xué)位授予單位】：電子科技大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：P631.222

【參考文獻(xiàn)】

相關(guān)期刊論文 前1條

1 伍東凌;陳正想;王秀;;基于遺傳算法的磁干擾補償方法[J];探測與控制學(xué)報;2012年06期

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本文編號：1658029