探月衛(wèi)星同波束干涉測(cè)量技術(shù)應(yīng)用研究

韓松濤; 陳明; 李翠蘭; 路偉濤

doi:10.11999/JEIT180914

探月衛(wèi)星同波束干涉測(cè)量技術(shù)應(yīng)用研究

doi: 10.11999/JEIT180914 cstr: 32379.14.JEIT180914

韓松濤^{1, 2, ,},
陳明¹,
李翠蘭¹,
路偉濤¹

1.
北京航天飛行控制中心航天飛行動(dòng)力學(xué)技術(shù)重點(diǎn)實(shí)驗(yàn)室北京 100094
2.
中國(guó)科學(xué)院國(guó)家天文臺(tái) ??北京 ??100012

基金項(xiàng)目: 國(guó)家自然科學(xué)基金(11603001, 11833001)

詳細(xì)信息

作者簡(jiǎn)介:
韓松濤：男，1982年生，博士后，研究方向?yàn)樯羁仗綔y(cè)軌道測(cè)量

陳明：男，1974年生，研究員，研究方向?yàn)楹教炱鳒y(cè)定軌技術(shù)

李翠蘭：女，1979年生，高級(jí)工程師，研究方向?yàn)楹教炱鳒y(cè)定軌技術(shù)

路偉濤：男，1985年生，助理研究員，研究方向?yàn)樯羁諢o(wú)線電測(cè)量

通訊作者:
韓松濤　justdoit_doing@126.com

中圖分類號(hào): TN961
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- 文章訪問(wèn)數(shù): 1968
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出版歷程
- 收稿日期: 2018-09-14
- 修回日期: 2019-01-28
- 網(wǎng)絡(luò)出版日期: 2019-02-18
- 刊出日期: 2019-08-01

Research on Application of Same-beam Interferometry in China Lunar Exploration

Songtao HAN^{1, 2
, ,},
Ming CHEN¹,
Cuilan LI¹,
Weitao LU¹

1.
National Key Laboratory of Science and Technology on Aerospace Flight Dynamics, Beijing Aerospace Control Center, Beijing 100094, China
2.
National Astronomical Observatories, Chinese Academy of Sciences, Beijing 100012, China

Funds: The National Natural Science Foundation of China (11603001, 11833001)

摘要

摘要: 探月工程嫦娥4號(hào)中繼星任務(wù)同時(shí)搭載月球軌道微衛(wèi)星，受地面測(cè)控資源分配限制，微衛(wèi)星的軌道測(cè)量由地基S/X頻段統(tǒng)一測(cè)控(TT&C)系統(tǒng)天線(USB)保障。該文通過(guò)分析地月轉(zhuǎn)移軌道段中繼星、微衛(wèi)星相對(duì)于跟蹤測(cè)站的幾何構(gòu)型，依托深空干涉測(cè)量系統(tǒng)設(shè)計(jì)實(shí)現(xiàn)對(duì)微衛(wèi)星、中繼星的同波束干涉測(cè)量(SBI)跟蹤；發(fā)揮中繼星測(cè)控資源豐富、軌道精度高的優(yōu)勢(shì)，獲取了微衛(wèi)星優(yōu)于1 ns的測(cè)角觀測(cè)量；并應(yīng)用于微衛(wèi)星短弧定軌，統(tǒng)計(jì)分析表明定軌精度由2 km提升至優(yōu)于1 km、預(yù)報(bào)精度由6 km提升至2 km，為微衛(wèi)星軌道機(jī)動(dòng)后的快速高精度軌道確定與預(yù)報(bào)提供了有力支撐。
- 同波束干涉測(cè)量 /
- 短弧定軌 /
- 深空測(cè)控干涉測(cè)量系統(tǒng) /
- 嫦娥4號(hào)
Abstract: Because of restricted earth-based tracking network, Tracking, Telemetry and Command (TT&C) for lunar orbit micro-satellite is depended on Unified S/X Band (USB) antennas in China Chang’E-4 lunar exploration. Based on analysis of the geometry between relay satellite, micro-satellite and earth-based antennas during earth-moon transfer orbit, an applicable method to acquire delay observable through Same-Beam Interferometry (SBI) tracking by China deep space network is discussed. Benefited from more kinds of tracking resources and high accuracy orbit of relay satellite, delay observable for angular position measurement of micro-satellite in the order of 1 ns is obtained, which improves the micro-satellite orbit determination accuracy from 2 km to less than 1 km and improves orbit prediction accuracy from 6 km to 2 km. SBI tracking plays an important role in short arc orbit determination of micro-satellite.
- Same beam interferometry /
- Short-arc orbit determination /
- Deep space Tracking Telemetry and Command Interferometric system /
- Chang’E-4

HTML全文

圖 1 SBI測(cè)量原理示意圖

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圖 2 跟蹤弧段內(nèi)兩目標(biāo)角距

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圖 3 喀什深空站接收兩目標(biāo)信號(hào)頻譜

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圖 4 基于先驗(yàn)引導(dǎo)模型的干涉相位及殘余時(shí)延

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圖 5 定軌殘差圖

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圖 6 定軌精度比較

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圖 7 預(yù)報(bào)比較結(jié)果圖

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