【摘要】：在衛(wèi)星導(dǎo)航接收機(jī)的應(yīng)用環(huán)境中,可用性容易受到各種環(huán)境因素的影響,比如高誤碼環(huán)境下電文校驗(yàn)出錯(cuò)糾正能力有限、可見(jiàn)星不足環(huán)境下無(wú)法按照傳統(tǒng)方法定位、弱信號(hào)環(huán)境下電文無(wú)法接收或更新等,都會(huì)導(dǎo)致可用性下降。針對(duì)上述問(wèn)題,本文從電文完好性、接收機(jī)鐘差建模和衛(wèi)星軌道外推三個(gè)方面展開(kāi)研究,研究了傳統(tǒng)處理方法的不足,提出優(yōu)化設(shè)計(jì)方法。本文的研究工作從以下三個(gè)方面開(kāi)展:(1)針對(duì)傳統(tǒng)BCH糾錯(cuò)方法存在只能對(duì)1比特誤碼進(jìn)行糾正的問(wèn)題,提出基于軌道限制的參數(shù)誤碼糾正方法。該方法結(jié)合電文參數(shù)的物理含義,分析參數(shù)的限制范圍,對(duì)誤碼的比特位進(jìn)行識(shí)別和糾正。仿真結(jié)果表明,提出的糾錯(cuò)方法對(duì)于部分參數(shù)范圍有限的電文高位誤碼情況可以糾正2比特以上的誤碼,最后以北斗系統(tǒng)星歷為例總結(jié)了各個(gè)電文參數(shù)的比特糾錯(cuò)成功率。(2)傳統(tǒng)多項(xiàng)式鐘差建模預(yù)測(cè)模型存在預(yù)報(bào)精度較差的問(wèn)題,通過(guò)對(duì)比AR模型和UC滑窗模型分別在短期和長(zhǎng)期預(yù)報(bào)情況下的精度分布規(guī)律,結(jié)合鐘差輔助三星定位的應(yīng)用背景,分析了鐘差預(yù)報(bào)誤差對(duì)定位精度的影響,得出的結(jié)論說(shuō)明UC滑窗模型適合短期預(yù)測(cè),多項(xiàng)式模型更適合于長(zhǎng)期預(yù)測(cè)。(3)針對(duì)星歷齡期較短接收機(jī)開(kāi)機(jī)后無(wú)法利用其計(jì)算衛(wèi)星位置的問(wèn)題,提出一種基于運(yùn)動(dòng)學(xué)定軌的衛(wèi)星位置外推算法。首先利用過(guò)期星歷擬合得到初始軌道,然后結(jié)合各類(lèi)攝動(dòng)力進(jìn)行軌道外推,并與IGS給出的軌道作比較,給出算法性能的研究結(jié)果。實(shí)測(cè)數(shù)據(jù)結(jié)果表明,使用12小時(shí)數(shù)據(jù)擬合初值預(yù)報(bào)的情況下,6天內(nèi)的徑向誤差在5m以內(nèi)。最后,對(duì)研究的成果進(jìn)行了總結(jié),并對(duì)下一步即將開(kāi)展的工作進(jìn)行了展望。
[Abstract]:In the application environment of satellite navigation receiver, the usability is easily affected by various environmental factors, for example, the error correction ability of message checking in high error code environment is limited. In weak signal environment, message can not be received or updated, which will lead to the decline of availability. Aiming at the above problems, this paper studies the message integrity, receiver clock error modeling and satellite orbit extrapolation, studies the shortcomings of traditional processing methods, and puts forward the optimization design method. The research work in this paper is carried out in the following three aspects: (1) aiming at the problem that the traditional BCH error correction method can only correct 1-bit error code, a parameter error correction method based on orbit limitation is proposed. This method combines the physical meaning of message parameter, analyzes the limit range of parameter, and identifies and corrects the bit of error code. The simulation results show that the proposed error correction method can correct the error of more than 2 bits in the case of high bit error with limited parameter range. Finally, taking the ephemeris of Beidou system as an example, the bit error correction success rate of each message parameter is summarized. (2) the traditional polynomial clock error modeling and prediction model has the problem of poor prediction accuracy. By comparing the accuracy distribution of AR model and UC sliding window model in short and long term forecast, combined with the application background of clock difference to assist Samsung positioning, the influence of clock error prediction error on positioning accuracy is analyzed. The conclusion shows that the UC sliding window model is suitable for short-term prediction, and the polynomial model is more suitable for long-term prediction. (3) aiming at the problem that the ephemeris receiver can not be used to calculate the satellite position after it is turned on, This paper presents an extrapolation method of satellite position based on kinematic orbit determination. First, the initial orbit is obtained by using expired ephemeris fitting, then the orbit extrapolation is carried out by combining various kinds of perturbation forces, and compared with the orbit given by IGS, the research results of the algorithm performance are given. The measured data show that the radial error within 6 days is less than 5m when the 12 hour data is used to fit the initial prediction. Finally, the research results are summarized and the future work is prospected.
【學(xué)位授予單位】：國(guó)防科學(xué)技術(shù)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2013
【分類(lèi)號(hào)】：P228.4

【參考文獻(xiàn)】

相關(guān)期刊論文 前1條

1 李輝;李隆;喬建新;;基于AR模型的GPS授時(shí)分析[J];測(cè)繪技術(shù)裝備;2012年01期

，

本文編號(hào)：2318764