RU97107921A - METHOD OF ANGULAR ORIENTATION OF OBJECTS FOR RADIO-NAVIGATION SIGNALS OF SPACE VEHICLES (OPTIONS) - Google Patents
METHOD OF ANGULAR ORIENTATION OF OBJECTS FOR RADIO-NAVIGATION SIGNALS OF SPACE VEHICLES (OPTIONS)Info
- Publication number
- RU97107921A RU97107921A RU97107921/09A RU97107921A RU97107921A RU 97107921 A RU97107921 A RU 97107921A RU 97107921/09 A RU97107921/09 A RU 97107921/09A RU 97107921 A RU97107921 A RU 97107921A RU 97107921 A RU97107921 A RU 97107921A
- Authority
- RU
- Russia
- Prior art keywords
- signals
- spacecraft
- measurements
- determining
- time interval
- Prior art date
Links
- 238000005259 measurement Methods 0.000 claims 16
Claims (2)
где i=1,...,n - текущий навигационный космический аппарат (НКА), сигнал которого принимается;
j=1,...,m - текущее измерение фазовых сдвигов сигналов n НКА;
cos*βxyz= B•cosβxyz- произведение неизвестной базы B (расстояния между антенно-приемными устройствами) на ее направляющие косинусы cosβxyz, подлежащие определению;
kxij, kyij, kzij - направляющие косинусы направлений потребитель - i-ный НКА;
λi - длина волны сигнала i-го космического аппарата;
φij - измеренное значение разности фаз сигналов i-го НКА, принятых антеннами потребителя в j-м измерении;
ΔΦi - систематическая погрешность измеренной разности фаз, обусловленная разным временем прохождения сигналов в каналах приемоиндикатора и неоднозначностью, вызванной тем, что расстояние между антеннами превышает длины волн принимаемых сигналов.A method for angular orientation of an object using the radio navigation signals of spacecraft, based on receiving signals from n spacecraft with two or more antenna-receiving devices located parallel to one or two axes of the object, extracting a signal with a Doppler frequency, determining the phase incursion for the measurement time interval and determining the angular the position of the object, characterized in that during the measurement time interval, m measurements of phase shifts between pairs of antenna receivers are made, and the angular position the object is determined by solving the following system of equations:
where i = 1, ..., n is the current navigation spacecraft (NSC), the signal of which is received;
j = 1, ..., m is the current measurement of the phase shifts of the signals n of the satellite;
cos * β xyz = B • cosβ xyz is the product of the unknown base B (distance between antenna receivers) and its cosines cosβ xyz to be determined;
k xij , k yij , k zij are the direction cosines of the consumer directions - the i-th NCA;
λ i is the wavelength of the signal of the i-th spacecraft;
φ ij is the measured value of the phase difference of the signals of the i-th satellite, received by the consumer’s antennas in the j-th dimension;
ΔΦ i is the systematic error of the measured phase difference, due to the different propagation time of the signals in the channels of the receiver-indicator and the ambiguity caused by the fact that the distance between the antennas exceeds the wavelengths of the received signals.
где
φ
3. Способ угловой ориентации объекта по радионавигационным сигналам космических аппаратов, основанный на приеме сигналов от n космических аппаратов двумя или более антенно-приемными устройствами, расположенными параллельно одной или двум осям объекта, выделении сигнала с частотой Доплера, определении набега фаз за интервал времени измерения и определении углового положения объекта, отличающийся тем, что в течение интервала времени измерения производят m измерений фазовых сдвигов между парами антенно-приемных устройств, вычисляют разности сумм фазовых сдвигов, накопленных в интервалах (1, . ..,m/2) и (m/2+1,...,m) измерений, а угловое положение объекта определяют путем решения следующей системы уравнений:
где
4. Способ угловой ориентации объекта по радионавигационным сигналам космических аппаратов, основанный на приеме сигналов от n космических аппаратов двумя или более антенно-приемными устройствами, расположенными параллельно одной или двум осям объекта, выделении сигнала с частотой Доплера, определении набега фаз за интервал времени измерения и определении углового положения объекта, отличающийся тем, что в течение интервала времени измерения производят m измерений фазовых сдвигов между парами антенно-приемных устройств, вычисляют разности фазовых сдвигов принятых сигналов в (m-j)-м измерении и j-м измерении, а угловое положение объекта определяют путем решения следующей системы уравнений:
где
φ
Where
φ
3. A method of angular orientation of an object according to the radio navigation signals of spacecraft, based on receiving signals from n spacecraft with two or more antenna-receiving devices located parallel to one or two axes of the object, isolating the signal with the Doppler frequency, determining the phase incursion for the measurement time interval and determining the angular position of the object, characterized in that during the time interval the measurements are made m measurements of phase shifts between pairs of antenna receivers, calculate the different the sum of the phase shifts accumulated in the intervals (1, ..., m / 2) and (m / 2 + 1, ..., m) measurements, and the angular position of the object is determined by solving the following system of equations:
Where
4. A method of angular orientation of an object according to the radio navigation signals of spacecraft, based on the reception of signals from n spacecraft with two or more antenna-receiving devices located parallel to one or two axes of the object, isolating the signal with the Doppler frequency, determining the phase incursion for the measurement time interval and determining the angular position of the object, characterized in that during the time interval the measurements are made m measurements of phase shifts between pairs of antenna receivers, calculate the different the phase shifts of the received signals in the (mj) th measurement and the jth measurement, and the angular position of the object is determined by solving the following system of equations:
Where
φ
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU97107921A RU2122217C1 (en) | 1997-05-15 | 1997-05-15 | Method of angular orientation of objects by radio navigation signals of spacecraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU97107921A RU2122217C1 (en) | 1997-05-15 | 1997-05-15 | Method of angular orientation of objects by radio navigation signals of spacecraft |
Publications (2)
Publication Number | Publication Date |
---|---|
RU2122217C1 RU2122217C1 (en) | 1998-11-20 |
RU97107921A true RU97107921A (en) | 1999-02-10 |
Family
ID=20192960
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU97107921A RU2122217C1 (en) | 1997-05-15 | 1997-05-15 | Method of angular orientation of objects by radio navigation signals of spacecraft |
Country Status (1)
Country | Link |
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RU (1) | RU2122217C1 (en) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2529649C1 (en) * | 2013-07-11 | 2014-09-27 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Сибирский Федеральный Университет" (Сфу) | Method for angular orientation of object based on spacecraft radio navigation signals |
RU2564523C1 (en) * | 2014-07-17 | 2015-10-10 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Сибирский Федеральный Университет" (Сфу) | Method of angular object orientation using spacecraft radio navigation signals |
RU2580827C1 (en) * | 2015-02-17 | 2016-04-10 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Сибирский Федеральный Университет" (Сфу) | Method for angular orientation of object |
RU2706636C1 (en) * | 2018-10-17 | 2019-11-19 | Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королёва" | Method of determining coordinates of a spacecraft based on signals of navigation satellites and a device for determining coordinates of a space vehicle from signals of navigation satellites |
RU2712365C1 (en) * | 2019-05-28 | 2020-01-28 | Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королёва" | Method of determining coordinates of a spacecraft based on signals of navigation satellites and a device for determining coordinates of a space vehicle from signals of navigation satellites |
RU2740606C1 (en) * | 2020-05-18 | 2021-01-15 | Общество с ограниченной ответственностью "Специальный Технологический Центр" | Method and device for determining angular orientation of aircrafts |
-
1997
- 1997-05-15 RU RU97107921A patent/RU2122217C1/en not_active IP Right Cessation
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