本文選題：火星探測 + 可觀測性��； 參考：《哈爾濱工業(yè)大學(xué)》2015年碩士論文

【摘要】：自主導(dǎo)航以其相較于其他導(dǎo)航方式的實(shí)時(shí)性、可靠性等特性發(fā)展為深空探測的重要技術(shù)之一,而且其在國外的深空探測系列活動中已經(jīng)成功驗(yàn)證并逐步開始應(yīng)用在實(shí)際任務(wù)中。在我國的深空探測規(guī)劃中,發(fā)展自主導(dǎo)航技術(shù)已成為重要研究方向。本文以火星探測為背景,重點(diǎn)研究了深空探測器在火星環(huán)繞段的自主導(dǎo)航方法。本文首先建立了所需的時(shí)空系統(tǒng),并給出不同坐標(biāo)系之間的轉(zhuǎn)換關(guān)系,同時(shí)計(jì)算了太陽和火星天然衛(wèi)星在火星慣性系下的星歷,然后綜合考慮火星形狀、大氣阻力、太陽光壓、太陽引力以及火星天然衛(wèi)星等主要攝動因素的影響,在火星赤道慣性系下建立探測器的軌道動力學(xué)模型,并分析了攝動力對探測器軌道的影響。同時(shí)與STK仿真模型進(jìn)行對比,給出了相比于參考模型的誤差,驗(yàn)證了所建立動力學(xué)模型的精確性。為更真實(shí)地模擬探測器的測量數(shù)據(jù),具體分析了影響探測器觀測火星天然衛(wèi)星以及火星路標(biāo)的因素:火星遮擋條件、火星陰影條件以及太陽逆光條件,并給出了造成不可見條件的具體方程,并對不同任務(wù)軌道的可觀測弧段進(jìn)行了對比仿真,結(jié)果顯示對于不同高度的任務(wù)軌道,雖然對衛(wèi)星與路標(biāo)可見性的主要影響因素各不相同,但最終都可歸結(jié)為目標(biāo)、火星以及太陽間的位置關(guān)系。在探測器環(huán)繞火星飛行段,首先針對導(dǎo)航系統(tǒng)是否可觀測的問題,通過分析觀測模型對狀態(tài)量的偏導(dǎo)數(shù)方程之間的獨(dú)立性來判別,并利用觀測矩陣的條件數(shù)分析了可觀測度。對以導(dǎo)航信標(biāo)視線矢量為觀測量的導(dǎo)航系統(tǒng),利用最小二乘算法對多組測量數(shù)據(jù)進(jìn)行批處理,然后利用牛頓迭代計(jì)算出探測器在環(huán)繞段的軌道要素,同時(shí)對利用火星表面上已知位置特征的路標(biāo)的導(dǎo)航方法進(jìn)行仿真分析。最后,通過對比仿真分析了軌道高度、采樣周期、采樣點(diǎn)個數(shù)、測量噪聲以及導(dǎo)航信標(biāo)的選取對軌道確定精度的影響,并以初定軌結(jié)果作為軌道初值進(jìn)行軌道預(yù)報(bào),分析誤差傳遞情況。
[Abstract]:Compared with other navigation methods, autonomous navigation has developed into one of the most important deep space exploration technologies for its real-time and reliability characteristics. Moreover, autonomous navigation has been successfully verified and gradually applied in practical missions in a series of deep space exploration activities abroad. In the deep space exploration planning in China, the development of autonomous navigation technology has become an important research direction. In this paper, based on the background of Mars exploration, the autonomous navigation method of deep space rover in the orbit of Mars is studied. In this paper, the necessary space-time system is first established, and the transformation relations between different coordinate systems are given. The ephemeris of the sun and the Martian natural satellites under the inertial system of Mars are calculated at the same time, and then the shape of Mars, atmospheric resistance and solar pressure are considered synthetically. Under the influence of the main perturbation factors such as the solar gravity and the Martian natural satellite, the orbital dynamics model of the probe is established under the Martian equatorial inertial system, and the influence of the perturbation force on the orbit of the probe is analyzed. At the same time, compared with the STK simulation model, the error compared with the reference model is given, and the accuracy of the established dynamic model is verified. In order to simulate the measured data of the probe more realistically, the factors that affect the observation of the natural Mars satellite and the Mars signpost are analyzed in detail: the condition of the occlusion of Mars, the condition of the shadow of Mars and the condition of the inverse light of the sun. The specific equations of the invisible conditions are given, and the observable arc segments of different mission orbits are compared and simulated. The results show that for different mission orbits at different heights, Although the main factors affecting the visibility of satellites and landmarks are different, they are ultimately attributed to the location of the target, Mars and the sun. In the spacecraft flight around Mars, the observability of the navigation system is first analyzed by analyzing the independence of the partial derivative equations of the observation model to the state variables, and the observable measure is analyzed by using the condition number of the observation matrix. For navigation system with navigation beacon line of sight vector as observation, the least square algorithm is used to batch process multiple sets of measurement data, and then Newton iteration is used to calculate the orbital elements of the detector in the circumferential section. At the same time, the navigation method based on the known position features on Mars surface is simulated and analyzed. Finally, the influence of orbit height, sampling period, number of sampling points, measurement noise and the selection of navigation beacon on the orbit determination accuracy is analyzed by comparison and simulation, and the orbit prediction is carried out with the initial orbit determination result as the initial orbit value. Analyze the error transmission.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V448.2

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本文編號：1979815