發(fā)布時間：2018-05-27 16:39

  本文選題：旋轉(zhuǎn)彈體 + 彈體紅外輻射�。� 參考：《中國慣性技術學報》2017年04期

【摘要】：針對地球紅外輻射姿態(tài)測試方法中彈體表面紅外輻射干擾較大的問題,建立旋轉(zhuǎn)彈體自身紅外輻射補償模型,從而提高彈體姿態(tài)測量精度。首先,采用瞬態(tài)熱平衡微分方程推導出旋轉(zhuǎn)彈體表面溫度變化曲線,獲取彈體自身紅外輻射亮度。然后,根據(jù)地球紅外輻射及其在大氣中的傳播規(guī)律,建立了彈體自身紅外輻射補償數(shù)學模型。最終結合紅外傳感器輸出和所推導的補償模型,估算紅外輻射補償參數(shù)。結果表明補償后姿態(tài)角解算誤差顯著降低,俯仰角和橫滾角解算誤差最終分別保持在±0.2°和±0.4°以內(nèi)。本方法對姿態(tài)測量誤差的減小具有顯著效果,補償方法簡單有效,對旋轉(zhuǎn)彈體的紅外姿態(tài)測試技術的研究具有借鑒意義。
[Abstract]:The infrared radiation compensation model of rotating projectile is established to improve the precision of attitude measurement in view of the large interference of infrared radiation on the surface of the missile in the method of measuring the attitude of the earth's infrared radiation. Firstly, the surface temperature change curve of rotating projectile is derived by transient heat balance differential equation, and the infrared radiance of the projectile itself is obtained. Then, according to the infrared radiation of the earth and its propagation in the atmosphere, the mathematical model of the infrared radiation compensation of the projectile itself is established. Finally, the infrared radiation compensation parameters are estimated by combining the output of infrared sensor and the compensation model derived. The results show that the error of attitude angle calculation is significantly reduced after compensation, and the errors of pitch angle and roll angle are kept within 鹵0.2 擄and 鹵0.4 擄respectively. This method has remarkable effect on reducing the error of attitude measurement and is simple and effective. It is useful for the research of infrared attitude measurement technology of rotating projectile.
【作者單位】： 南京理工大學機械工程學院;
【基金】：國家自然科學基金項目(61675097)
【分類號】：TJ410;TN219

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本文編號：1942979