【摘要】：光纖陀螺儀作為全固態(tài)儀表,具有壽命長、質(zhì)量輕、體積小、動(dòng)態(tài)范圍大、精度應(yīng)用覆蓋面廣、抗沖擊等特點(diǎn),已成為新一代捷聯(lián)慣性導(dǎo)航系統(tǒng)及其它應(yīng)用中較理想的陀螺儀表。隨著光纖陀螺精度的提升,陀螺失準(zhǔn)角及其誤差的影響越發(fā)突出。例如:在地面靜態(tài)試驗(yàn)中,1.5角分的失準(zhǔn)角誤差將會(huì)導(dǎo)致光纖陀螺產(chǎn)生0.0066°/h的零偏測(cè)試誤差、0.0123°/h的零偏位置誤差與0.1ppm的標(biāo)度因數(shù)不穩(wěn)定性。這一失準(zhǔn)角誤差同樣會(huì)導(dǎo)致光纖慣組產(chǎn)生超過1角分的初始對(duì)準(zhǔn)誤差與隨時(shí)間成指數(shù)型增長的導(dǎo)航定位誤差。因此,為了能有效提升光纖陀螺的使用精度,有必要深入開展陀螺失準(zhǔn)角誤差機(jī)理的研究并尋找有效的技術(shù)解決措施。首先,論文理論推導(dǎo)了螺旋繞制的光纖環(huán)導(dǎo)致失準(zhǔn)角及失準(zhǔn)角誤差的產(chǎn)生原因。經(jīng)分析,理想的對(duì)稱繞法不會(huì)產(chǎn)生失準(zhǔn)角,諸多工藝問題是導(dǎo)致失準(zhǔn)角產(chǎn)生的主要原因。合理的改善工藝措施有利于在研制、生產(chǎn)過程中降低陀螺失準(zhǔn)角。當(dāng)前光纖陀螺常見的應(yīng)用環(huán)境因素中,溫度、應(yīng)力釋放、振動(dòng)、長期輻照均會(huì)引起難以補(bǔ)償?shù)氖?zhǔn)角變化(即失準(zhǔn)角誤差);短期輻照與磁場(chǎng)雖然會(huì)對(duì)零偏與標(biāo)度因數(shù)造成較大影響,但在光纖陀螺正常工作的范圍內(nèi)不會(huì)產(chǎn)生失準(zhǔn)角誤差。其次,論文分析了陀螺失準(zhǔn)角誤差對(duì)零偏漂移測(cè)試、多位置零偏測(cè)試(用于衡量陀螺零偏在不同空間位置的重復(fù)性)、標(biāo)度因數(shù)穩(wěn)定性、初始對(duì)準(zhǔn)、導(dǎo)航定位等性能指標(biāo)的作用機(jī)理及影響結(jié)果。通過分析可知,輸入軸失準(zhǔn)角及其誤差不僅會(huì)嚴(yán)重影響導(dǎo)航精度,對(duì)高精度光纖陀螺的其它性能指標(biāo)也會(huì)有較大影響。最后,論文開展了失準(zhǔn)角及失準(zhǔn)角誤差抑制的相關(guān)研究。本文在現(xiàn)有技術(shù)基礎(chǔ)上提出了失準(zhǔn)角溫度誤差的補(bǔ)償方法,對(duì)補(bǔ)償方法的物理意義、方法誤差、精確建模進(jìn)行了深入研究,通過試驗(yàn)證明了該補(bǔ)償方法的有效性與實(shí)用性。但是,該補(bǔ)償方法需要三個(gè)正交軸的角速度信息作為補(bǔ)償輸入,所以不適用于獨(dú)立應(yīng)用的單軸光纖陀螺。針對(duì)獨(dú)立使用的單軸速率陀螺,本文提出了一種利用尾纖傾斜繞制補(bǔ)償單軸陀螺失準(zhǔn)角的方法。在研究過程中不僅證明了該補(bǔ)償方法的可行性,也結(jié)合工程實(shí)際分析了可能遇到的問題。鑒于該補(bǔ)償方法的實(shí)現(xiàn)尚有諸多工藝問題需要考慮,本文僅進(jìn)行理論推導(dǎo)。本文研究表明,全面開展陀螺失準(zhǔn)角的研究工作,不僅可以有效地提高我們對(duì)失準(zhǔn)角產(chǎn)生機(jī)理與誤差影響的認(rèn)識(shí),也可以有效地抑制陀螺失準(zhǔn)角及其誤差,提升高精度光纖陀螺及慣組的應(yīng)用精度。
[Abstract]:As an all-solid-state instrument, fiber optic gyroscope has the characteristics of long life, light weight, small volume, wide dynamic range, wide precision application coverage, anti-impact and so on. It has become an ideal gyroscope instrument in the new generation strapdown inertial navigation system and other applications. With the improvement of the precision of fiber optic gyroscope (fog), the influence of gyroscope misalignment angle and its error becomes more and more prominent. For example, in the static test on the ground, the misalignment error of 1.5-angle will lead to the error of 0.0066 擄/ h, the error of 0.0123 擄/ h and the instability of the scale factor of 0.1ppm. This misalignment error will also lead to the initial alignment error of more than 1 angle and the exponential increase of navigation and positioning error over time in the optical fiber inertial system. Therefore, in order to improve the precision of fiber optic gyroscope, it is necessary to study the error mechanism of gyroscope misalignment and find effective technical solutions. Firstly, the paper theoretically deduces the causes of the error caused by the helically wound optical fiber loop. The analysis shows that the ideal symmetrical winding method can not produce the misalignment angle, and many technological problems are the main causes of the misalignment angle. Reasonable technical measures are beneficial to reduce the misalignment angle of gyroscope in the process of development and production. Temperature, stress release, vibration are the common environmental factors in the application of fiber optic gyroscope (fog) at present. Long-term irradiation will cause uncompensated misalignment (that is, misalignment error). Although short-term irradiation and magnetic field will have a great effect on zero bias and scaling factor, they will not produce misalignment error in the normal range of fog. Secondly, the paper analyzes gyroscope misalignment angle error to zero offset drift test, multi-position zero bias test (used to measure the repeatability of gyroscope bias in different space), scale factor stability, initial alignment, The action mechanism and effect result of the performance index such as navigation and positioning. The analysis shows that the misalignment angle of the input axis and its error will not only seriously affect the navigation accuracy, but also have a great impact on the other performance indexes of the high-precision fiber optic gyroscope. Finally, the paper studies the error suppression of misalignment angle and misalignment angle. In this paper, based on the existing techniques, a compensation method for the temperature error of misalignment angle is proposed. The physical meaning, method error and accurate modeling of the compensation method are deeply studied, and the validity and practicability of the compensation method are proved by experiments. However, the compensation method requires the angular velocity information of three orthogonal axes as the compensation input, so it is not suitable for single-axis fiber optic gyroscopes with independent application. In this paper, a method of compensating the misalignment angle of uniaxial gyroscope by tilting the tail fiber is proposed for the uniaxial rate gyroscope which is used independently. The feasibility of the compensation method is not only proved in the research process, but also the possible problems are analyzed in combination with the engineering practice. In view of the fact that there are still many technical problems to be considered in the realization of the compensation method, the theoretical derivation is only carried out in this paper. In this paper, it is shown that the research on the misalignment angle of gyroscope can not only effectively improve our understanding of the mechanism and error influence of the misalignment angle, but also effectively restrain the misalignment angle and its error of the gyroscope. Improve the application accuracy of high precision fiber optic gyroscope and inertial unit.
【學(xué)位授予單位】：中國航天科技集團(tuán)公司第一研究院
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：TN96

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