【摘要】：衛(wèi)星重力測量、天基引力波探測等空間引力探測任務(wù)的成功實施有賴于對非引力作用的有效剔除或精確測量。通過構(gòu)造驗證質(zhì)量塊的純引力軌道,內(nèi)編隊引力參考敏感器有效剔除了非引力干擾的影響,為高精度的空間引力探測任務(wù)提供了關(guān)鍵支撐。位于航天器質(zhì)心附近的內(nèi)編隊引力參考敏感器主要由空腔結(jié)構(gòu)、安裝在腔體內(nèi)壁的位移敏感器和包含其間的球形驗證質(zhì)量塊組成,利用驗證質(zhì)量塊與腔體結(jié)構(gòu)的相對位移測量信息驅(qū)動航天器緊密跟蹤驗證質(zhì)量塊,來維持驗證質(zhì)量塊的純引力飛行狀態(tài)。內(nèi)編隊引力參考敏感器無需對驗證質(zhì)量塊施加懸浮控制力,更容易達到極低的非引力干擾抑制水平,是最為理想的純引力軌道構(gòu)造方式。本文以衛(wèi)星重力測量任務(wù)為牽引,針對構(gòu)建內(nèi)編隊引力參考敏感器亟需解決的相對測量和維持控制問題進行了系統(tǒng)研究,主要內(nèi)容如下:對影響內(nèi)編隊引力參考敏感器性能的主要因素進行了分析,建立了驗證質(zhì)量塊非引力干擾的頻域指標分配模型,分別針對基于絕對軌道攝動的長波重力場測量和基于長基線相對軌道攝動的中高階重力場測量任務(wù),進行了內(nèi)編隊引力參考敏感器的指標分解。針對驗證質(zhì)量塊的初始狀態(tài)捕獲和長波重力場測量任務(wù)需求,提出了基于光能探測陣列的相對測量系統(tǒng)概念,動態(tài)量程與腔體間隙相當,可達cm量級,精度優(yōu)于1mm。通過提取探測陣列的有效輸出單元中心坐標,給出了驗證質(zhì)量塊的相對位移確定算法。分析了光壓干擾的頻譜分布,結(jié)果表明在光源周期性發(fā)光的工作模式下,測量干擾在10-11m/s2/(?)量級。構(gòu)建了實驗系統(tǒng)對研制的相對測量實驗裝置進行了性能測試,結(jié)果表明,在以驗證質(zhì)量塊標稱位置為中心,動態(tài)量程不小于±10mm的相對運動空間內(nèi),基于測量輸出的最大定位誤差為0.38mm。針對長基線相對軌道攝動重力場測量的高精度任務(wù)數(shù)據(jù)獲取需求,采用了基于基掩光能量敏感的相對位移測量方法�？紤]敏感器的幾何布局,建立了驗證質(zhì)量塊三位移與敏感器輸出的關(guān)系模型。設(shè)計了可解析求解驗證質(zhì)量塊位移的“三正交”和“兩平行”敏感器布局方式�？紤]測量光壓、靈敏度和動態(tài)量程指標,推導(dǎo)了敏感器的主要設(shè)計參數(shù)約束�；陔娮由⒘Ｔ肼曉u估了掩光能量測量的極限精度,給出了極限精度為0.09nm/(?)的敏感器設(shè)計參數(shù)。建立了光斑尺寸變化、光功率波動、光束發(fā)散角、光束中心顫振和指向偏角的誤差傳遞模型,并分析了球形邊緣效應(yīng)和光束衍射效應(yīng)對誤差傳遞關(guān)系的影響,結(jié)果表明建立的誤差傳遞模型在進行誤差預(yù)測時,準確度不低于19%。構(gòu)建了掩光能量測量實驗系統(tǒng),實驗結(jié)果表明在5mHz～0.1Hz的任務(wù)頻段內(nèi),測量精度優(yōu)于1μm/(?)�？紤]驗證質(zhì)量塊的球面波動、質(zhì)心與形心偏差等球體加工誤差,研究了基于掩光能量測量信息的驗證質(zhì)量塊質(zhì)心相對位移確定方法�；谇蛑C函數(shù)級數(shù)描述的驗證質(zhì)量塊質(zhì)心到球面距離模型,建立了包含非理想球體特征的掩光能量測量信號模型�；陬l率辨識與測量信號擬合的思想,給出了等慣量驗證質(zhì)量塊的質(zhì)心位移確定方法,考慮到驗證質(zhì)量塊較大的初始釋放偏差,設(shè)計了全控制過程的質(zhì)心位移確定方案。仿真驗證了方法的有效性,結(jié)果表明在掩光能量測量精度為1nm/(?)、驗證質(zhì)量塊轉(zhuǎn)動頻率～10Hz的條件下,球體質(zhì)心位移確定精度在nm/(?),有效剔除了 10nm量級的球面波動和100nm量級的質(zhì)心偏差影響。研究了維持控制下的內(nèi)編隊引力參考敏感器任務(wù)能力評估問題�？紤]航天器與驗證質(zhì)量塊的耦合效應(yīng),建立了內(nèi)編隊飛行的動力學(xué)模型。提出了基于H∞回路成形的魯棒維持控制方法,能夠滿足任務(wù)頻段內(nèi)的非引力干擾抑制和球體質(zhì)心位移確定指標要求。結(jié)合殘余非引力干擾大小和驗證質(zhì)量塊相對位移測量精度,分析了內(nèi)編隊引力參考敏感器支持下的長基線相對軌道攝動重力場測量任務(wù)能力。提出了內(nèi)編隊引力參考敏感器在低軌導(dǎo)航衛(wèi)星方面的拓展應(yīng)用概念,分析了殘余非引力干擾對自主軌道預(yù)報誤差的影響。結(jié)果表明,在非引力干擾的常值分量得到充分抑制、隨機分量為1×10-11m/s2的條件下,內(nèi)編隊導(dǎo)航星的自主軌道預(yù)報可在三個月內(nèi)保持m級精度�；贚QR控制律的仿真結(jié)果表明nm精度的高性能內(nèi)編隊引力參考敏感器可顯著降低維持控制對航天器的功率和推進劑質(zhì)量需求。
[Abstract]:The successful implementation of space gravity detection tasks such as satellite gravity measurement and space-based gravitational wave detection depends on the effective elimination or precise measurement of the non-gravity effect. By constructing the pure gravitational track of the verification mass block, the influence of non-gravity interference is effectively eliminated by the inner formation gravity reference sensor, and the key support is provided for the high-precision spatial gravity detection task. The inner formation gravity reference sensor located near the center of mass of the spacecraft is mainly composed of a cavity structure, a displacement sensor mounted on the inner wall of the cavity and a spherical verification mass block containing the cavity structure, and utilizing the relative displacement measurement information of the verification mass block and the cavity structure to drive the spacecraft to closely track and verify the mass block to maintain the pure gravitational flying state of the verification mass block. The inner formation gravity reference sensor does not need to apply suspension control force to the verification mass block, it is easier to reach extremely low non-attraction interference suppression level, and is the most ideal pure gravitational track structure mode. Based on the satellite gravity measurement task, this paper systematically studies the relative measurement and maintenance control problems which need to be solved in the construction of the inner formation gravity reference sensor, and the main contents are as follows: the main factors affecting the performance of the inner formation gravity reference sensor are analyzed. A frequency domain index distribution model for verifying the non-gravity interference of mass block is established, and the index decomposition of the inner formation gravity reference sensor is carried out aiming at the long-wave gravity field measurement based on absolute orbit perturbation and the middle-order high-order gravity field measurement task based on the relative orbit perturbation of long baseline. The concept of relative measurement system based on optical energy detection array is put forward aiming at the initial state capture and long-wave gravity field measurement task requirement of the verification mass block. The dynamic range is comparable to the cavity clearance, which can reach the order of cm, and the precision is better than 1mm. By extracting the center coordinates of the effective output unit of the detection array, the relative displacement determination algorithm of the verification mass block is given. The spectral distribution of optical interference is analyzed. The results show that the interference is 10-11m/ s2/ (?) on the order of magnitude. The performance test of the experimental system was constructed. The results show that the maximum positioning error based on the measurement output is 0. 38mm in the relative motion space with the nominal position of the verification mass block as the center and the dynamic range is not less than 1.10mm. Aiming at the high-precision task data acquisition requirement of long baseline relative orbit perturbation gravity field measurement, a relative displacement measurement method based on the basis mask energy sensitivity is adopted. Considering the geometrical layout of the sensor, a model of the relationship between the three displacement of the verification mass block and the output of the sensor is established. The paper designs the 鈥渢hree-orthogonal鈥，

本文編號：2253648