RU2555247C1 - Method for simultaneous determination of six movement parameters of sv at performance of trajectory measurements with one tracking station and system for its implementation - Google Patents

Abstract

FIELD: measurement equipment.

SUBSTANCE: group of inventions relates to trajectory measurements using a tracking station (TS) for flight of a space vehicle (SV). At information exchange with SV via a radio channel TS makes a measurement of distance to SV and speed of its change. The main and additional TS antennas receive a signal response from SV and transmit it to an interferometric measurement unit (IMU) having a phase bearing finder. Azimuth angles and places of SV and speeds of their change are determined in IMU. In order to disclose ambiguity of angular measurements, they are additionally made on the frequency emitted from SV board and equal to 1/4 of the main one. This allows using no antennas on TS, which create shortened bases. All the six measured parameters (distance, angles and speeds of their change) are transmitted to a ballistic centre, where trajectory and forecast of SV movement is determined according to them.

EFFECT: simplifying a tracking network of SV flight at performance of trajectory measurements.

2 cl, 2 dwg

Description

Technical field

The invention relates to the field of astronautics, to systems for trajectory measurements of spacecraft (SC).

State of the art

, угол места КА (β) и скорость изменения этого угла $$\left(\dot{\beta }\right)$$

и азимутальный угол положения КА относительно СС (α) и скорость изменения этого угла $$\left(\dot{\alpha }\right)$$

. Измеряемые параметры могут быть другими, но их должно быть шесть.In the general case, to determine the spacecraft motion path, it is necessary to simultaneously measure six independent spacecraft motion parameters: the inclined range from the ground-based tracking station (SS) to the spacecraft (R), the radial component of the spacecraft’s speed relative to the SS

, space elevation angle (β) and rate of change of this angle $$\left(\dot{\beta }\right)$$

and azimuthal angle of the spacecraft relative to SS (α) and the rate of change of this angle $$\left(\dot{\alpha }\right)$$

. Measured parameters may be different, but there should be six.

) и фазовым пеленгатором (измерения α, β, $$\dot{\alpha }$$

, $$\dot{\beta }$$

).It is known [1] that to determine the trajectory of the orbital and interplanetary spacecraft and predict their further motion, the results of trajectory measurements performed by several SSs (3,4,5) and the spacecraft on-board transponder (1) in the system of sequential measurements of the parameters of spacecraft motion (see Fig. 1). To determine the standing point of geostationary spacecraft [2], the results of trajectory measurements carried out simultaneously by the tracking station (measurements R,

) and phase direction finder (measurements of α, β, $$\dot{\alpha }$$

, $$\dot{\beta }$$

)

, которые последовательно измеряются несколькими СС (3,4,5), территориально разнесенными в широтном и долготном направлениях.In practice, when conducting trajectory measurements of orbital spacecraft, only two spacecraft motion parameters are used - R and

, which are successively measured by several SS (3,4,5), geographically spaced in latitudinal and longitudinal directions.

The measurement results from all tracking stations (3,4,5) are transmitted to the Ballistic Center (25), where they determine the trajectory and forecast of further spacecraft motion.

₁ - измеряемыми СС1 (6,7,8,9,10), R₂,

₂ - измеряемыми СС2 (11,12,13,14,15) и R₃,

₃ - измеряемыми СС3 (16,17,18,19,20) (см. фиг. 1). Так как измерения указанных параметров производятся в разное время, это приходится учитывать при расчете траектории движения КА, что приводит к увеличению погрешностей определения траектории КА. Это является одним из недостатков указанного способа траекторных измерений КА.With this measurement scheme, in most cases, errors in determining the trajectory of the spacecraft are within the limits sufficient to solve the spacecraft control problems. In this case, six motion parameters are used to calculate the trajectory, measured successively by several SSs: R ₁ ,

₁ - measured CC1 (6,7,8,9,10), R ₂ ,

₂ - measured CC2 (11,12,13,14,15) and R ₃ ,

₃ - measured SS3 (16,17,18,19,20) (see Fig. 1). Since the measurements of these parameters are made at different times, this has to be taken into account when calculating the spacecraft motion path, which leads to an increase in the errors in determining the spacecraft trajectory. This is one of the disadvantages of this method of trajectory measurements of the spacecraft.

In addition, since several SSs are involved in the trajectory measurements, this leads to large expenses for the creation and operation of SSs participating in the trajectory measurements.

Disclosure of invention

The claimed method for the simultaneous determination of six parameters of the motion of the spacecraft during trajectory measurements by one tracking station and a system for its implementation are aimed at eliminating the disadvantages of the analogue.

The technical result of the claimed invention consists in the simultaneous measurement of six parameters of the motion of the spacecraft during trajectory measurements by one tracking station, which reduces the errors in determining the trajectory of the spacecraft.

КА, и с помощью сигналов, принятых основной, первой и второй дополнительных антенн в блоке интерферометрических измерений, производят угломерные измерения $$\alpha ,\beta ,\dot{\alpha },\dot{\beta }$$

, где ( $$\alpha$$

) - азимутальный угол положения КА относительно СС, ( $$\beta$$

) - угол места КА, ( $$\dot{\alpha }$$

) - скорость изменения угла ( $$\alpha$$

), ( $$\dot{\beta }$$

) - скорость изменения угла ( $$\beta$$

), дополнительно формируют сигнал для раскрытия неоднозначности угломерных измерений блока интерферометрических измерений с частотой $$\frac{1}{4}$$

от частоты ответного сигнала, передают этот сигнал на антенну КА, и после преобразования сигнала излучают с борта КА, принимают основной, первой и второй дополнительными антеннами СС сигнал с частотой $$\frac{1}{4}$$

от частоты ответного сигнала, на которой производят фазовые угломерные измерения, используемые для раскрытия неоднозначности угломерных измерений $$\alpha ,\beta ,\dot{\alpha },\dot{\beta }$$

на основной частоте.The technical result is achieved by the fact that the method for simultaneously determining six parameters of the motion of the spacecraft during trajectory measurements by one tracking station (CC), which consists in generating a request signal from the tracking station (SS) measuring six parameters of the motion of the spacecraft, transmit a signal through the main antenna SS to the SC antenna, a response signal is formed to the SC, simultaneously transmit it to the main, first and second additional antennas of the SS, which measures six parameters of the SC motion, measure the range R and the radial composition yayuschuyu speed

SPACECRAFT, and using signals received by the main, first and second additional antennas in the block of interferometric measurements, goniometric measurements are made $$\alpha ,\beta ,\dot{\alpha },\dot{\beta }$$

where ( $$\alpha$$

) is the azimuthal angle of the spacecraft relative to the SS, ( $$\beta$$

) - spacecraft elevation angle, ( $$\dot{\alpha }$$

) - rate of change of angle ( $$\alpha$$

), ( $$\dot{\beta }$$

) - rate of change of angle ( $$\beta$$

), additionally generate a signal to reveal the ambiguity of the goniometric measurements of the block of interferometric measurements with a frequency $$\frac{\mathrm{one}}{\mathrm{four}}$$

from the frequency of the response signal, this signal is transmitted to the SC antenna, and after the signal is converted, they are radiated from the SC, the main, first and second additional CC antennas receive a signal with a frequency $$\frac{\mathrm{one}}{\mathrm{four}}$$

from the frequency of the response signal at which the phase goniometric measurements are made, used to reveal the ambiguity of the goniometric measurements $$\alpha ,\beta ,\dot{\alpha },\dot{\beta }$$

at the fundamental frequency.

The system for the simultaneous determination of six spacecraft motion parameters during trajectory measurements by one tracking station (SS) includes a spacecraft (spacecraft), a spacecraft antenna, SS, measuring six spacecraft motion parameters, including the main, first and second additional antennas, the main one the first and second switches, the inputs / outputs of which are connected to the inputs / outputs of the main, first and second antennas, respectively, the CC transmitter, the output of which is connected to the main antenna through the second input of the main switch, the first, the second and third antenna synchronous guidance units, the main antenna auto-tracking system CC, the main antenna input / output is connected to the input of the main SS antenna system, the auto-tracking system of the main SS antenna is connected through the first input of the main switch and the first output of the main switch with the input of the second synchronous pointing unit antennas, the output of the first synchronous antenna pointing unit is connected to the input / output of the first antenna through the first switch, the output of the third synchronous pointing unit the antenna is connected to the input / output of the second antenna through the second switch, the first, second and third receiving devices, the second input of the first receiving device is connected to the input / output of the first antenna through the second output of the first switch, the second input of the second receiving device is connected to the input / output of the main antenna through the second output of the main switch, the second input of the third receiving device is connected to the input / output of the second antenna through the second output of the second switch, the trajectory measurement system, the first output to the second is connected to the input of the transmitter CC, the second output is connected to the first inputs of the first, second and third receivers, respectively, an interferometric measurement unit, the first and third inputs of which are connected to the outputs of the first and third receivers, respectively, and the second input to the first output of the second receiver , the first, second and third blocks of the disclosure of the ambiguity of the goniometric measurements, the input of the first block of the disclosure of the ambiguity of the goniometric measurements is connected to the input / output of the main antenna through as a result of the third output of the main switch, the inputs of the second and third blocks of the disclosure of the ambiguity of the goniometric measurements are connected to the inputs / outputs of the first and second antennas through the first outputs of the first and second switches, respectively, and the outputs of the first, second, and third blocks of the disclosure of the ambiguity of the angular measurements are connected to the first, second and the third inputs of the interferometric measurement unit, the output of the interferometric measurement unit is connected to the first input of the trajectory measurement system, the second input of the trajectory system of of measurements is connected to the second output of the second receiving device, the third and fourth outputs of the trajectory measurement system are the outputs of the system for simultaneous determination of six spacecraft motion parameters during trajectory measurements by one tracking station.

Brief Description of the Drawings

The features and essence of the claimed invention are explained in the following detailed description, illustrated by the drawings, which show the following.

In FIG. 1 is a structural diagram of a system of sequential measurements of spacecraft motion parameters (analogue), where:

1. The spacecraft (SC);

2. Antenna of the spacecraft;

3. The first tracking station (CC1);

4. The second CC2;

5. The third SS3;

6. Transmitter CC1;

7. Equipment for synchronous guidance of the CC1 antenna;

8. The receiving device CC1;

9. System of trajectory measurements CC1;

10. Antenna CC1;

11. Transmitter CC2;

12. Equipment for synchronous guidance of the antenna CC1;

13. The receiving device CC2;

14. Trajectory measurement system CC2;

15. Antenna CC2;

16. Transmitter CC3;

17. Equipment for synchronous guidance of the CC3 antenna;

18. The receiving device CC3;

19. Trajectory measurement system CC3;

20. Antenna CC3;

22. The response signal CC1;

21. The request signal CC1;

24. Request signal CC2;

23. The response signal CC2;

25. The response signal CC3;

26. Request signal CC3;

27. The signal of the local oscillator CC1;

28. Spacecraft control signals received by the CC1 antenna;

29. The signal of the local oscillator CC2;

30. Spacecraft control signals received by the CC2 antenna;

31. The signal of the local oscillator CC3;

32. Spacecraft control signals received by the CC3 antenna.

In FIG. 2 is a structural diagram of the claimed system for the simultaneous determination of six spacecraft motion parameters when conducting trajectory measurements by one tracking station, where:

33. The spacecraft (SC);

34. Aerial of spacecraft;

35. Tracking station (SS), measuring six parameters of the motion of the spacecraft;

36. Transmitter SS;

37. The first block synchronous guidance of the antenna;

38. The second block synchronous guidance of the antenna;

39. The third block synchronous guidance of the antenna;

40. The first receiving device;

41. The second receiving device;

42. The third receiving device;

43. Trajectory measurement system;

44. The main antenna of the SS;

45. The first antenna SS;

46. The second antenna SS;

47. The main switch;

48. The first switch;

49. The second switch;

50. Interferometric signals received by antennas;

51. Block interferometric measurements;

52. The signal of the local oscillator;

53. Spacecraft control signals received by antennas;

54. Results of angular measurements;

55. Latitudinal base;

56. Long-term base;

57. Auto tracking unit of the main SS antenna;

58. The first block receiving the signal disclosure of the ambiguity of the goniometric measurements;

59. The second block receiving the signal disclosure of the ambiguity of the goniometric measurements;

60. The third block receiving the signal disclosure of the ambiguity of the goniometric measurements;

61. A signal for revealing the ambiguity of the goniometric measurements of the block of interferometric measurements;

62. Request signal SS;

63. The response signal SS.

The implementation of the invention

The system for the simultaneous determination of six spacecraft motion parameters during trajectory measurements provides for the use of only one SS (35), similar to those used in the system, which is analogous, but differs in the following:

- two smaller antennas (45, 46) with receivers (40, 42) located at a certain distance from the main antenna of the SS (44) in the latitudinal and longitude directions in such a way that with the main antenna (44) are additionally introduced into the SS they form latitudinal (55) and longitude (56) bases of radio interferometric measurements;

- an interferometric measurement unit (51) was additionally introduced into the SS;

- the main SS antenna has a spacecraft auto-tracking system according to the received signal (57);

- using synchronous communication equipment (37-39), additional antennas (45, 46) are aimed at the spacecraft synchronously with the main SS antenna (44).

A tracking station via a radio channel exchanges information necessary for controlling a spacecraft (issuing control commands, receiving telemetric and other types of information).

).At the same time, the SS measures the range to the spacecraft (R) and the radial component of the speed of the spacecraft relative to the SS (

)

Additional antennas (45, 46) together with the main one (44) receive a response signal from the spacecraft (33) and transmit it to the CC unit of radio interferometric measurements (51), which measures the angular motion parameters of the spacecraft characterizing the angular position of the spacecraft:

- directional cosines of the angles of direction to the spacecraft from both bases (55, 56) of the FP;

- the difference of Doppler frequency shifts of the signals received by the antennas of each base, which characterize the rate of change of the magnitude of the directing cosines at each base.

.The data obtained are recalculated into the angular coordinates of the spacecraft in azimuth and elevation and the rate of change of the angular coordinates: $$\alpha ,\dot{\alpha },\beta ,\dot{\beta }$$

.

The accuracy of determining the angular parameters of the spacecraft motion depends on the length of the interferometric bases and the frequency range in which these measurements are made.

With a base length of 100 m, the error in angular measurements will be 3.5 cm when operating in the radio range, depending on the elevation angle, from 1 to 4 arc seconds for each base.

от частоты, на которой производятся фазовые угловые измерения, дополнительно излучаемый с борта КА и принимаемый наземными антеннами (44, 45, 46) с соответствующими блоками приема сигнала раскрытия неоднозначности угломерных измерений (58, 59, 60). По этому сигналу (61) так же проводятся фазовые угломерные измерения, используемые для раскрытия неоднозначности угломерных измерений на основной частоте (63). Это позволяет не применять в составе станции слежения дополнительные антенны, создающие укороченные базы для раскрытия неоднозначности угловых измерений на основных измерительных базах (55, 56).To reveal the ambiguity during angular measurements, a signal is used to disclose the ambiguity of the goniometric measurements of the block of interferometric measurements (61) with a frequency equal to $$\frac{\mathrm{one}}{\mathrm{four}}$$

the frequency at which phase angular measurements are made, additionally emitted from the spacecraft and received by ground-based antennas (44, 45, 46) with the corresponding signal reception units for the disclosure of the ambiguity of the goniometric measurements (58, 59, 60). This signal (61) also makes phase goniometric measurements used to reveal the ambiguity of goniometric measurements at the fundamental frequency (63). This allows not to use additional antennas as part of the tracking station, creating shortened bases for revealing the ambiguity of angular measurements at the main measuring bases (55, 56).

, $$\alpha ,\dot{\alpha },\beta ,\dot{\beta }$$

) передаются в баллистический центр (БЦ), где по ним определяется траектория и прогноз движения КА.All six measured SS parameters of spacecraft motion (R,

, $$\alpha ,\dot{\alpha },\beta ,\dot{\beta }$$

) are transmitted to the ballistic center (BC), where they determine the trajectory and forecast of the spacecraft.

, проводимыми СС, позволяют в БЦ определить траекторию движения КА с высокой точностью.These measurements, together with the measurements of R and

conducted by the SS, allow in the BC to determine the trajectory of the spacecraft with high accuracy.

The cost of creating and operating the inventive tracking station will be significantly lower than the cost of two stations used today: the spacecraft control station and the phase interferometer.

The inventive new method for simultaneously measuring six spacecraft motion parameters of one SS and the system for its implementation can most effectively be used:

- for trajectory measurements on the surface section of the flight path of interplanetary spacecraft;

- during the trajectory measurements of the spacecraft, the forecast of the trajectory of which is known with great errors, due to the abnormal operation of the engines during dynamic operations;

- when launching the spacecraft into the geostationary satellite orbit and maintaining it with the necessary accuracy at the point of standing;

- in cases where it is advisable to build a spacecraft crew according to a one-point scheme.

Bibliography

1. Molotov EP “Terrestrial radio engineering spacecraft control systems”, Moscow: FIZMATLIT, 2004, 256 pp.

2. Urlichich Yu.M., Yezhov S.A., Zhodzishsky A.I. and others. "Modern navigation technologies of geostationary satellites", M .: FIZMATLIT, 2006, 271 p.

Claims (2)

1. A method for simultaneously determining six motion parameters of a spacecraft (SC) during trajectory measurements by one tracking station (CC), which consists in generating a query signal CC measuring six motion parameters of a SC, transmit a signal through the main antenna CC to the SC antenna, form a response signal to the spacecraft, simultaneously transmit it to the main, first and second additional antennas SS measuring six parameters of the spacecraft’s motion, measure the range R and the radial velocity component

SC and using signals received by the main, first and second additional antennas, in the block of interferometric measurements, goniometric measurements are made (

), where

- azimuthal angle of the spacecraft relative to the SS,

- spacecraft elevation angle,

- rate of change of angle

,

- rate of change of angle

, additionally generate a signal for disclosing the ambiguity of the goniometric measurements of the block of interferometric measurements with a frequency

from the frequency of the response signal, this signal is transmitted to the SC antenna and, after signal conversion, is emitted from the SC, the main, first and second additional CC antennas receive a signal with a frequency

from the frequency of the response signal at which the phase goniometric measurements are performed, used to reveal the ambiguity of the goniometric measurements (

) at the fundamental frequency. 2. A system for the simultaneous determination of six parameters of the motion of a spacecraft (KA) during trajectory measurements by one tracking station (SS), which includes a KA, an antenna of a KA, SS, measuring six parameters of the motion of a spacecraft, including the main, first and second additional antennas , the main, first and second switches, the inputs / outputs of which are connected to the inputs / outputs of the main, first and second antennas, respectively, the CC transmitter, the output of which is connected to the main antenna through the second input of the main switch, p the first, second and third blocks of synchronous guidance of the antenna, the auto-tracking system of the main antenna of the SS, and the input / output of the main antenna is connected to the input of the auto-tracking system of the main antenna of the SS, the auto-tracking system of the main antenna of the SS is connected through the first input of the main switch and the first output of the main switch with the input of the second synchronous antenna pointing unit, the output of the first antenna synchronous pointing unit is connected to the input / output of the first antenna through the first switch, the output of the third sync block the antenna is connected to the input / output of the second antenna through the second switch, the first, second and third receiving devices, and the second input of the first receiving device is connected to the input / output of the first antenna through the second output of the first switch, the second input of the second receiving device is connected to the input / the output of the main antenna through the second output of the main switch, the second input of the third receiving device is connected to the input / output of the second antenna through the second output of the second switch, the system of trajectory changes the first output of which is connected to the input of the SS transmitter, the second output is connected to the first inputs of the first, second and third receivers, respectively, an interferometric measurement unit, the first and third inputs of which are connected to the outputs of the first and third receivers, respectively, and the second input to the first the output of the second receiving device, the first, second and third blocks of the disclosure of the ambiguity of the goniometric measurements, the input of the first block of the disclosure of the ambiguity of the goniometric measurements is connected to the input / output the main antenna through the third output of the main switch, the inputs of the second and third blocks of the disclosure of the ambiguity of the goniometer are connected to the inputs / outputs of the first and second antennas through the first outputs of the first and second switches, respectively, and the outputs of the first, second and third blocks of the disclosure of the ambiguity of the goniometric measurements are connected to the first , the second and third inputs of the interferometric measurement unit, the output of the interferometric measurement unit is connected to the first input of the trajectory measurement system, the second input trajectory measurement systems are connected to the second output of the second receiving device, the third and fourth outputs of the trajectory measurement system are outputs of the system for simultaneously determining six parameters of the spacecraft motion during trajectory measurements of one SS.

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