RU2013131386A

RU2013131386A - METHOD FOR DETERMINING A VECTOR OF THE STATE OF A PASSIVE SPACE OBJECT

Info

Publication number: RU2013131386A
Application number: RU2013131386/11A
Authority: RU
Inventors: Валерий Сергеевич Красоткин; Вера Васильевна Прокофьева; Петр Михайлович Жидков; Дмитрий Цезарьевич Литовченко; Екатерина Дмитриевна Безлепкина; Владимир Францевич Боровский; Владимир Леонидович Егоров; Виктор Степанович Пеляк; Андрей Васильевич Степовой; Владимир Леонидович Троицкий
Original assignee: Открытое акционерное общество "Корпорация космических систем специального назначения "Комета"
Priority date: 2013-07-09
Filing date: 2013-07-09
Publication date: 2015-01-20
Also published as: RU2542836C2

Abstract

Способ определения вектора состояния пассивного космического объекта (ПКО) на геостационарной орбите (ГСО) с активного космического объекта (АКО), движущегося по квазигеостационарной орбите, включающий дрейф АКО по квазигеостационарной орбите с наклонением, близким к нулю градусов, поиск и обнаружение ПКО оптико-электронной системой (ОЭС) АКО, после чего АКО выполняет серию измерений угловых координат ПКО в визирной системе координат АКО при нахождении ПКО в пределах поля зрения ОЭС АКО, одна ось визирной системы координат АКО направлена вдоль вектора скорости АКО, вторая ось расположена в экваториальной плоскости Земли и направлена в центр Земли по радиусу-вектору АКО, третья ось дополняет визирную систему координат до правой, а автономная инерциально-спутниковая система навигации АКО, включающая измерения систем ГЛОНАСС и/или GPS, осуществляет получение информации о положении и скорости центра масс АКО на орбите, отличающийся тем, что ОЭС АКО на каждом его витке после вхождения ПКО в пределы поля зрения ОЭС АКО и вплоть до момента выхода ПКО за его пределы измеряет угловые положения ПКО в своей визирной системе координат и запоминает их в бортовом компьютере, а при каждом пересечении траекторией ПКО координатной оси визирной системы координат АКО, расположенной в экваториальной плоскости Земли и соответствующей точке восходящего/нисходящего узла орбиты ПКО, бортовой компьютер АКО вычисляет соответствующие моменты времени и фиксирует в своей памяти положение АКО в инерциальной геоцентрической системе координат (ИГСК) в эти моменты времени, кроме того, после второго пересечения ПКО координатной оси виA method for determining the state vector of a passive space object (ASC) in a geostationary orbit (GSO) from an active space object (ASC) moving in a quasi-geostationary orbit, including a drift of the ASC in a quasi-geostationary orbit with an inclination close to zero degrees, search and detection of a FEL in optoelectronic AKO system (OES), after which the AKO performs a series of measurements of the angular coordinates of the ACS in the AKO visor coordinate system when the ACS is within the field of view of the AKO ECO, one axis of the AKO sighting coordinate system is directed along the AKO velocity vector, the second axis is located in the equatorial plane of the Earth and directed to the center of the Earth along the radius vector of the AKO, the third axis complements the sighting coordinate system to the right, and the autonomous inertial-satellite navigation system AKO, including measurements of GLONASS and / or GPS systems, provides information on the position and velocity of the center of mass of the AKO in orbit, characterized in that the AES AKO at each of its turns after entering the FFP within the field of view of the AEC AKO and up to the moment the FFP goes beyond it measures angles the position of the FFP in its target coordinate system and stores them in the on-board computer, and each time the FFT trajectory intersects the coordinate axis of the VFR coordinate system located in the equatorial plane of the Earth and the corresponding point of the ascending / descending node of the FBO orbit, the onboard FAC computer calculates the corresponding time points and fixes in its memory the position of the AKO in the inertial geocentric coordinate system (IGSC) at these points in time, in addition, after the second intersection of the coordinate axis of the axis

Claims

A method for determining the state vector of a passive space object (ASC) in a geostationary orbit (GSO) from an active space object (ASC) moving in a quasi-geostationary orbit, including a drift of the ASC in a quasi-geostationary orbit with an inclination close to zero degrees, search and detection of a FEL in optoelectronic AKO system (OES), after which the AKO performs a series of measurements of the angular coordinates of the ACS in the AKO visor coordinate system when the ACS is within the field of view of the AKO ECO, one axis of the AKO sighting coordinate system is directed along the AKO velocity vector, the second axis is located in the equatorial plane of the Earth and directed to the center of the Earth along the radius vector of the AKO, the third axis complements the sighting coordinate system to the right, and the autonomous inertial-satellite navigation system AKO, including measurements of GLONASS and / or GPS systems, provides information on the position and velocity of the center of mass of the AKO in orbit, characterized in that the AES AKO at each of its turns after entering the FFP within the field of view of the AEC AKO and up to the moment the FFP goes beyond it measures angles the position of the FFP in its target coordinate system and stores them in the on-board computer, and each time the FFT trajectory intersects the coordinate axis of the VFR coordinate system located in the equatorial plane of the Earth and the corresponding point of the ascending / descending node of the FBO orbit, the onboard FAC computer calculates the corresponding time points and fixes in its memory the position of the AKO in the inertial geocentric coordinate system (IGSC) at these points in time, in addition, after the second intersection of the coordinate axis of the axis of the AKO zircon system located in the equatorial plane of the Earth, its draconic period is determined and the position of the AKO in the IGSC, which, together with the AKO position point at the first turn, forms a stereo base in the IGSC, and if there are n measurement periods,

C_{n}^{2}

dynamic stereobases of observation of the ascending / descending node point, then from the points of the orbit of the ACS located at regular intervals before and after the point of the ascending / descending node of the orbit of the FSC, the on-board computer of the AKO uses the stereotriangulation method to calculate the coordinates of the points of the orbit of the FSC in the ISSC located at the same time intervals synchronously to the measurements of the point of the ascending / descending node of the orbit of the FFP, and then determines the velocity vector of the FFP near the point of the ascending / descending node using the coordinates of the AKO obtained from the cut tatam measurements autonomous inertial-navigation-satellite system ACH, then the measured parameters determines the state vector FFP.