【摘要】：衛(wèi)星重力測(cè)量、天基引力波探測(cè)等空間引力探測(cè)任務(wù)的成功實(shí)施有賴于對(duì)非引力作用的有效剔除或精確測(cè)量。通過(guò)構(gòu)造驗(yàn)證質(zhì)量塊的純引力軌道,內(nèi)編隊(duì)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(cè)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(duì)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(yàn)證質(zhì)量塊組成,利用驗(yàn)證質(zhì)量塊與腔體結(jié)構(gòu)的相對(duì)位移測(cè)量信息驅(qū)動(dòng)航天器緊密跟蹤驗(yàn)證質(zhì)量塊,來(lái)維持驗(yàn)證質(zhì)量塊的純引力飛行狀態(tài)。內(nèi)編隊(duì)引力參考敏感器無(wú)需對(duì)驗(yàn)證質(zhì)量塊施加懸浮控制力,更容易達(dá)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(cè)量任務(wù)為牽引,針對(duì)構(gòu)建內(nèi)編隊(duì)引力參考敏感器亟需解決的相對(duì)測(cè)量和維持控制問(wèn)題進(jìn)行了系統(tǒng)研究,主要內(nèi)容如下:對(duì)影響內(nèi)編隊(duì)引力參考敏感器性能的主要因素進(jìn)行了分析,建立了驗(yàn)證質(zhì)量塊非引力干擾的頻域指標(biāo)分配模型,分別針對(duì)基于絕對(duì)軌道攝動(dòng)的長(zhǎng)波重力場(chǎng)測(cè)量和基于長(zhǎng)基線相對(duì)軌道攝動(dòng)的中高階重力場(chǎng)測(cè)量任務(wù),進(jìn)行了內(nèi)編隊(duì)引力參考敏感器的指標(biāo)分解。針對(duì)驗(yàn)證質(zhì)量塊的初始狀態(tài)捕獲和長(zhǎng)波重力場(chǎng)測(cè)量任務(wù)需求,提出了基于光能探測(cè)陣列的相對(duì)測(cè)量系統(tǒng)概念,動(dòng)態(tài)量程與腔體間隙相當(dāng),可達(dá)cm量級(jí),精度優(yōu)于1mm。通過(guò)提取探測(cè)陣列的有效輸出單元中心坐標(biāo),給出了驗(yàn)證質(zhì)量塊的相對(duì)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(cè)量干擾在10-11m/s2/(?)量級(jí)。構(gòu)建了實(shí)驗(yàn)系統(tǒng)對(duì)研制的相對(duì)測(cè)量實(shí)驗(yàn)裝置進(jìn)行了性能測(cè)試,結(jié)果表明,在以驗(yàn)證質(zhì)量塊標(biāo)稱位置為中心,動(dòng)態(tài)量程不小于±10mm的相對(duì)運(yùn)動(dòng)空間內(nèi),基于測(cè)量輸出的最大定位誤差為0.38mm。針對(duì)長(zhǎng)基線相對(duì)軌道攝動(dòng)重力場(chǎng)測(cè)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(duì)位移測(cè)量方法�？紤]敏感器的幾何布局,建立了驗(yàn)證質(zhì)量塊三位移與敏感器輸出的關(guān)系模型。設(shè)計(jì)了可解析求解驗(yàn)證質(zhì)量塊位移的“三正交”和“兩平行”敏感器布局方式�？紤]測(cè)量光壓、靈敏度和動(dòng)態(tài)量程指標(biāo),推導(dǎo)了敏感器的主要設(shè)計(jì)參數(shù)約束�；陔娮由⒘Ｔ肼曉u(píng)估了掩光能量測(cè)量的極限精度,給出了極限精度為0.09nm/(?)的敏感器設(shè)計(jì)參數(shù)。建立了光斑尺寸變化、光功率波動(dòng)、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(duì)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(jìn)行誤差預(yù)測(cè)時(shí),準(zhǔn)確度不低于19%。構(gòu)建了掩光能量測(cè)量實(shí)驗(yàn)系統(tǒng),實(shí)驗(yàn)結(jié)果表明在5mHz～0.1Hz的任務(wù)頻段內(nèi),測(cè)量精度優(yōu)于1μm/(?)�？紤]驗(yàn)證質(zhì)量塊的球面波動(dòng)、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(cè)量信息的驗(yàn)證質(zhì)量塊質(zhì)心相對(duì)位移確定方法。基于球諧函數(shù)級(jí)數(shù)描述的驗(yàn)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(cè)量信號(hào)模型�；陬l率辨識(shí)與測(cè)量信號(hào)擬合的思想,給出了等慣量驗(yàn)證質(zhì)量塊的質(zhì)心位移確定方法,考慮到驗(yàn)證質(zhì)量塊較大的初始釋放偏差,設(shè)計(jì)了全控制過(guò)程的質(zhì)心位移確定方案。仿真驗(yàn)證了方法的有效性,結(jié)果表明在掩光能量測(cè)量精度為1nm/(?)、驗(yàn)證質(zhì)量塊轉(zhuǎn)動(dòng)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(jí)的球面波動(dòng)和100nm量級(jí)的質(zhì)心偏差影響。研究了維持控制下的內(nèi)編隊(duì)引力參考敏感器任務(wù)能力評(píng)估問(wèn)題。考慮航天器與驗(yàn)證質(zhì)量塊的耦合效應(yīng),建立了內(nèi)編隊(duì)飛行的動(dòng)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(biāo)要求。結(jié)合殘余非引力干擾大小和驗(yàn)證質(zhì)量塊相對(duì)位移測(cè)量精度,分析了內(nèi)編隊(duì)引力參考敏感器支持下的長(zhǎng)基線相對(duì)軌道攝動(dòng)重力場(chǎng)測(cè)量任務(wù)能力。提出了內(nèi)編隊(duì)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(duì)自主軌道預(yù)報(bào)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(jī)分量為1×10-11m/s2的條件下,內(nèi)編隊(duì)導(dǎo)航星的自主軌道預(yù)報(bào)可在三個(gè)月內(nèi)保持m級(jí)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(duì)引力參考敏感器可顯著降低維持控制對(duì)航天器的功率和推進(jìn)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(hào)：2253648