RU2281891C2 - Spacecraft steady global control system - Google Patents

Abstract

FIELD: information transmission systems; satellite communication systems; spacecraft control systems.

SUBSTANCE: proposed system includes spacecraft, mobile control member and global satellite navigational system 9GLONASS) including navigational satellites which are provided with onboard command-and-measuring system and inter-satellite communication system; spacecraft includes User's navigational equipment which is connected with onboard control system; User's navigational equipment operates in navigational fields of GLONASS system or GLONASS and GPS systems; onboard command-and-measuring system is used for connection with mobile control member which includes User's navigational equipment operating in navigational fields of GLONASS or GLONASS and GPS systems; it is connected with operation station performing function of spacecraft command post and flight control center; operation station is connected with command-and-measuring system establishing communication both with spacecraft and navigational satellites.

EFFECT: extended functional capabilities of system; enhanced stability of spacecraft control.

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Description

The invention relates to information transmission systems and can find application in satellite systems for controlling spacecraft in the mode of their normal operation and in special conditions.

Currently, control information is transmitted to low-orbit spacecraft either directly from ground stations (command and measurement points) or through special relay satellites. (See Krassner G.N. et al. Introduction to space communications systems. M: Communication, 1967, pp. 11 and 12. Kravets V.G. et al. Fundamentals of spacecraft control. M .: Mashinostroenie, 1983, p. 175-184. EP 0992429, B 64 G 1/10, 2000.)

Closest to the technical nature of the claimed invention is a method of transmitting information on a network with terrestrial and space subscribers, which consists in the fact that the information source generates an information signal to the recipient and the signals of its coordinates at the time of transmission, transmits them to the terrestrial subscriber, the terrestrial subscriber transmitting antenna to the region where the intermediate subscriber is located and transmits to him an information signal and coordinate signals of the recipient subscriber at the time of the start of transmission to the subscriber-recipient For example, the intermediate subscriber directs the transmitting antenna to the area of the subscriber-recipient and transmits to him an information signal at a predetermined point in time, characterized in that the information source generates the address signal of the subscriber-recipient, signals the length of the transmission time interval between each pair of intermediate subscribers, the maximum allowed signal the time of receipt of the information signal by the recipient subscriber, the ground subscriber receives the signals generated by the information source, and generates the research of the address signals of intermediate subscribers and the recipient subscriber, the time interval for transmitting the information signal to the recipient subscriber by means of which is minimal, generates a signal for each intermediate subscriber of the time when signals began to be transmitted to him and his coordinates at this point in time, sequentially transmits the generated signals to a predetermined moment of time by means of a transmitting antenna pointed to the zone of location of the first intermediate subscriber, which when receiving It determines the received sequence of address signals of intermediate subscribers and the recipient subscriber with its own address, if the own address does not match the address signal of the recipient subscriber, determines from the received signals the address signal of the next intermediate subscriber, the signal of the transmission start time to this subscriber and its coordinates to this moment of time and in accordance with these signals carries out the transmission of signals to the next subscriber. (RU 2070738, G 08 C 15/06, 1996)

The disadvantages of the known technical solutions include the need to launch additional spacecraft-transponders, as well as the need for a high-precision synchronization system. In addition, the known system according to the method does not provide the transmission of command and measurement information.

The technical result of the invention is to expand the functionality of the system, in particular increasing the stability of control of spacecraft.

To this end, a global control system for spacecraft - control objects, containing spacecraft, a mobile control link, as well as a GLONASS satellite navigation system (functionally), containing navigation satellites is proposed, while the new generation GLONASS navigation satellites contain an on-board command and measurement system connected with inter-satellite communications equipment that communicates between navigation satellites, spacecraft contain connected to the onboard a control system for consumer navigation equipment operating on the navigation fields of the GLONASS or GLONASS and GPS systems, and an on-board command and measurement system that communicates with the mobile control unit, and a mobile control unit that simultaneously functions as a command post, flight control center, and command and measurement system , contains the navigation equipment of the consumer, operating on the navigation fields GLONASS or GLONASS and GPS and connected to a workstation that performs the functions of a command punch and that the center of the space vehicle flight control, while the workstation is connected to a command-and-measurement system in communication with both the spacecraft and from navigation satellites.

The drawing shows a functional diagram of a global spacecraft control system.

The system includes spacecraft (SC) 1, which are the objects of control and containing an on-board command and measuring system (BKIS) 2, navigation equipment for consumers (NAP) 5, on-board control system (BSU) 6, the system also includes navigation satellites (NS) 9 GLONASS systems 8, containing inter-satellite communications equipment (AMS) 10 and an on-board command and measuring system (BKIS) 12, the system also contains a mobile control unit (MZU) 14, containing consumer navigation equipment (NAP) 15, a workstation (16) with remote control board and command and measuring system (KIS) 17, as well as two-way communication lines 4 (BKIS 2 - BKIS 12), 3 (BKIS 2 - KIS 17), 11 (AMC 10 - AMC-10) and 13 (KIS 17 - BKIS 12)

The global spacecraft control system works as follows:

KA 1 - the control object using NAP 5, coupled with BSU 6, continuously determines the parameters of the trajectory of its movement and transmits via BKIS 2 information to KIS 17 MZU 14 or via communication line 3 (if KA 1 is in range with MZU 14) or on NS 9 via communication line 4. The choice of NS is carried out autonomously by the criterion of the availability of the most favorable communication conditions. This information is distributed via inter-satellite communication lines 11 of the GLONASS system and transmitted to MZU 14 from one of those NS 9, which are located in the visibility zone via communication line 13.

In a similar way, generalized reports on the health of on-board systems of spacecraft 1, formed by BSU 6, are transmitted.

In the workstation 16 of the MZU 14, the spacecraft motion models 1 are updated, taking into account the own position of the MZU 14, determined by the NAP 15 located on it, as well as the state of its target and service systems.

With MZU 14 through KIS 17 plans for its targeted use are transmitted to KA 1, for example, in the form of macro-programs - “coordinate-action”. In this case, either communication lines 3 are used (if KA 1 is in the visibility zone with MZU 14), or they are relayed via communication lines 13, 11 and 4.

MZU 14 periodically exchanges information with operational controls, using both satellite and land lines. At the same time, new generation satellites are used as navigation satellites 9 of the GLONASS system, and the spacecraft is understood as low-orbit automatic satellites.

In the normal operation mode, spacecraft 1 should have a high degree of autonomy, at which the information exchange between spacecraft 1 and ground MZU 14 is reduced to the minimum level necessary and sufficient for spacecraft 1 to carry out its target tasks, which allows the use of narrow-band command-measuring and inter-satellite lines of GLONASS navigation systems.

In this case, the MZU 14 performs the functions of a command post, a flight control center and a command and measurement system.

Claims (1)

A stable global spacecraft control system containing spacecraft, a mobile control link, as well as a GLONASS satellite navigation system, functionally containing navigation satellites, while navigation satellites contain an on-board command and measurement system connected to inter-satellite communications equipment that communicates between navigation satellites, spacecraft contain user navigation equipment connected to the onboard control system, operating along the navigation fields of the GLONASS or GLONASS and GPS systems, and the on-board command and measuring system that communicates with the mobile control unit, and the mobile control unit contains consumer navigation equipment operating along the navigation fields of GLONASS or GLONASS and GPS and connected to a workstation performing functions of the command post and the flight control center of the spacecraft, while the workstation is connected to the command-measuring system that communicates with both the spacecraft and navigation satellites.