RU2659376C1 - Descending space objects or their devices coordinates monitoring in the earth atmosphere and their dispatching control system - Google Patents

Abstract

FIELD: radio equipment and communications.

SUBSTANCE: invention relates to the aviation, space equipment, traffic in the Earth's atmosphere dispatching and control systems radio equipment means and can be used in descending space objects or their vehicles, landing systems, traffic in the Earth's atmosphere control systems. Invention on-board equipment is added with the automatic dependent surveillance (ADS) module with the satellite navigation system additional differential correction data receiving means between the in-series connected on-board beacon with antenna and on-board navigation unit. Invention ground-based equipment, the automatic dependent surveillance system ground-based receivers are added with the time-synchronization means for their implementation as part of the multi-position surveillance system.

EFFECT: technical result is increase in the descending space object or its device coordinates determining accuracy in the Earth's atmosphere under various flight conditions.

1 cl, 2 dwg

Description

The present invention relates to radio-technical means of aviation, space technology, scheduling and motion control systems in the Earth’s atmosphere and can be used in descent space objects or their devices, landing systems, motion control systems in the Earth’s atmosphere.

From literature sources [4, 5, 6, 7, 8, 9, 11], definitions of an aircraft and a descent vehicle are known.

The Descent Vehicle (SA) is a part of the spacecraft for descent with braking and soft landing on the Earth or other celestial body. On manned spacecraft, the descent vehicle is the cockpit in which the crew is located; on automatic aircraft in the descent vehicles there are devices [9].

A space object is a body of artificial origin located in near-Earth space [11].

An aircraft (aircraft) is an aircraft maintained in the atmosphere by interacting with air other than interacting with air reflected from the earth's surface. Aircraft do not include rockets, spacecraft, hovercraft, ekranoplanes, ekranopleta, meteorological balloons, unmanned uncontrolled balloons without payload [8].

Based on the well-known definitions and classifications, spacecraft or their spacecraft are not related to aircraft, and the radio equipment and methods of approaching the landing of aircraft and spacecraft are different.

Considering the functioning aspects of airborne and ground equipment ensuring the landing of an aircraft, it is worth noting:

At most modern aerodromes, aircraft approach paths in horizontal and vertical planes are formed by equal-signal zones of electromagnetic radiation from ground directional (CRM) and glide path (GRM) radio beacons, the intersection of which represents the given horizontal and vertical approach paths. The current distance from the aircraft to the start of the runway (runway) is determined by the rangefinder radio beacon (DRM), which is part of the ground equipment. A detailed description of the processes and procedures for the formation of a given approach trajectory using the CRM, the timing and the DRM are given in section 5.6. The principle of operation of the landing and display channels in systems such as RSBN, chapters 7.8 of the manual [18], chapter 2 of the book [19], section 2.7 of the book [20].

A description of the features of the functioning of the flight navigation equipment during the approach is given in chapter 3 of the book [19], chapters 2 and 8 of the book [20]. In the process of implementing the automatic approach mode, the known laws of controlling the motion of the center of mass through the roll and pitch control of the aircraft are used. The book [20] gives examples of the laws of automatic aircraft control over roll and pitch, in which, along with other signals, signals are used to deviate the aircraft from a given path along the course εk and the glide path εr. To implement the manual approach mode on the corresponding indicating instruments, simultaneously, in the form of vertically and horizontally oriented bars of the signal, deviations from the given trajectory along the course εk and the glide path εr are indicated.

Unlike an aircraft, during regular descent at altitudes of 130-170 km, the separation field with the spacecraft SA, descent space objects without separation, under the influence of aerodynamic forces and control engines, the launching of the aircraft is oriented by the frontal shield towards the oncoming flow and at altitudes below 84- 82 km, the rolls take place on the roll in automatic (AUS) or manual (RUS) control modes, ensuring the landing of the SA in the calculated area.

In the event of automatic or manual descent control modes failure on board the SA, a ballistic descent (failure on the BS) can be formed, which is performed by spinning the SA relative to the velocity vector with an angular velocity of 13 ° / s. Depending on the time of transition to the ballistic descent mode, the SA landing point in the ballistic descent mode is separated from the calculated point at a distance from 0 to 450 km.

In addition, at an altitude of 90–40 km, intense aerodynamic deceleration of the SA occurs and the formation of a “plasma cavity” around the SA with temperatures up to 2000 ° C. During the formation of the "plasma cavity" for 5-6 minutes, radio communication with the SA is disturbed. Then, at an altitude of 8.5 km, the braking parachute fires away from the SA, removing the main parachute from the parachute container, which is fully filled within 11 seconds and at which the further reduction of the SA takes place.

To ensure the search for astronauts and two-way communication between astronauts and crews of search aircraft, helicopters and search and evacuation vehicles on the parachute descent site and after landing, on-board radio equipment of the KV-bearing and an emergency portable VHF radio station are used.

The KV-bearing radio equipment includes:

2 VHF transmitters (primary and backup) at a frequency of -121.75 (FM) / 121.5 MHz (AM), 2 VHF simplex receivers (main and reserve) at a frequency of -121.75 MHz 2 VHF duplex receivers (main) . and reserve.) at a frequency of -130.167 MHz, 2 HF transmitters at frequencies of 8.364 and 18.060 MHz. The output power of VHF transmitters is 3 W in FM mode and 1 W in AM mode. The output power of KB transmitters is 6 watts and 11 watts.

The receiving-transmitting slotted VHF antenna is mounted on the SA manhole. Up to an altitude of 10 km, the VHF transmitter operates at a frequency of 121.75 MHz, at an altitude of 10 km, the VHF transmitters transition to a frequency of 121.5 MHz. The transmitters operate alternately for 2 minutes each, emitting an amplitude-modulated signal, which is a 3-fold repetition of the letters "A N" Morse code (duration 5 seconds with 10 second intervals). VHF receivers at a frequency of 130.167 MHz go into amplitude modulation mode.

KB transmitters at 8.364 and 18.060 MHz operate continuously until the landing of the SA, emitting the letters "AN" in amplitude telegraphy mode.

HF beacons operating mode:

at a frequency of 8.364 MHz - 3 hours 12 minutes;

at a frequency of 18.060 MHz - according to the program: 2 minutes work, 6 minutes break.

After 3 hours, both beacons on the cyclogram are switched on simultaneously:

at a frequency of 8.364 MHz - 10 minutes work, 6 minutes break;

at a frequency of 18.060 MHz - 2 minutes work, 14 minutes break.

After landing, the crew can also use the Iridium portable satellite communications station and GPS device with autonomous power sources to communicate with search and rescue units.

A common problem of modern manned space exploration is the creation of a communication channel (radio channel) of a descent space object or its device in dense layers of the Earth’s atmosphere along a ballistic or calculated trajectory, as well as any other, especially in an emergency situation with the control center of the control center (the central control point is the control room control, monitoring the coordinates of the launched space objects or their devices in the atmosphere of the Earth). The difficulty is that around the descent space object or its spacecraft, due to the high speed of descent (up to 4 km / s), the frontal outer layers of thermal protection of the descent spacecraft are sublimated, i.e. evaporate, the high temperature in the created shock wave ionizes air molecules in the atmosphere - the effect of a “plasma cavity” arises. The “plasma cavity” covers a large part of the descent vehicle and, as a screen, closes the descent vehicle moving in the atmosphere, and thereby deprives the KB and VHF of the airborne-ground communication (between the SA and the control center). A similar picture occurs with external observation of SA, electromagnetic radar rays, reflected from the "plasma cavity", acquire turbulence, i.e. vortex state, therefore, it is practically impossible to determine the exact coordinates of the descent space object or its apparatus. Therefore, the descent vehicle flies in the radio silence mode until the speed is extinguished, i.e. almost before the opening of the brake parachutes.

The location of the center of mass (centering) of the descent vehicle provides a stable position of the descent vehicle in the air flow (bottom forward), as well as asymmetric flow around the descent vehicle.

Due to the described problems and based on the need to ensure the continuity of data on the coordinates of the SA, to minimize errors in determining the coordinates of the SA by ground-based means from reflections from the "plasma cavity", the problem of the invention is formulated - increasing the accuracy of determining the coordinates of a descent space object or its device in the Earth’s atmosphere.

Based on the known theoretical and practical aspects of the passage of radio waves with a frequency of 1 GHz ± 1 kHz, corresponding to the frequency range of automatic dependent observation, through plasma [16, 17], known systems and methods of automated dependent observation [12], a well-known complex of means for receiving and processing messages from Aircraft systems of automatic dependent observation [13] are not designed to receive data of automatic dependent observation of descent space objects or their devices in the atmosphere of Ze Is.

The closest claimed system is an automated dispatch control system for aircraft flights with the possibility of using information from an automatic dependent surveillance system [14], shown in FIG. 1 and containing a local area network (1), flight planning workstation (2), airspace usage control workstation (3), a set of data exchange tools with a ground-based data processing complex (4), a telephone and telegraph channel interface device (5), database server of flight routes and aircraft numbers (6), a pairing device (7) and a receiver of an automatic dependent surveillance system (8).

This system is not intended for supervisory control by the MCC over the flights of launched space objects or their devices and does not provide determination of the coordinates of a launched space object or its device in the Earth’s atmosphere.

The basis of the invention is the task of increasing the accuracy of determining the coordinates of a descent space object or its apparatus in the Earth’s atmosphere during a standard landing, during ballistic descent, during early (urgent) descent, under various flight conditions.

This task is achieved by introducing into the on-board equipment (on-board radio beacon with antenna, on-board navigation unit) descent vehicles maneuvering spacecraft in the Earth's atmosphere, an on-board automatic dependent observation module (abbreviation in English transcription ADS, abbreviation in Russian transcription AZN) with means for receiving additional differential data correction of the satellite navigation system and the introduction of time synchronization tools in the composition of ground-based receivers of the automatic independent observation for their implementation as part of a multi-position monitoring system (abbreviation in English transcription WAM, MLAT, abbreviation in Russian transcription MPSN).

In contrast to the ground-based means for receiving additional differential correction data of the satellite navigation system using the transmission of correction data via the VHF transmission line (108-117, 975 MHz) from the corresponding ground station evaluating the signals of the satellite constellation, the on-board systems use the correction data via geostationary satellites, which increases the likelihood of receiving corrective corrections and data processing by on-board CA systems in case of a radio communication failure with the SA while in the "plasma cavity".

In addition, on-board means for receiving additional differential correction data of a satellite navigation system, with a sufficient number of observed navigation satellites (at least 6) based on autonomous integrity control algorithms (RAIM), analyze information from satellites and exclude it when calculating navigation characteristics in case of failure of one of navigation satellites.

The stationary installation of the receivers of the automatic dependent surveillance system allows receiving, among other standard signals, the exact time signals of the satellite navigation system, and since the coordinates of the installation of the ADS receiver are precisely known and unchanged, receiving the true range to the satellite in the received data frame, signal delay during signal propagation from satellite to the receiver is calculated immediately and thus get the reference to time with very high accuracy.

The internal synchronization of the timelines of the ADS receivers as part of the MPSN consists in continuously checking the discrepancy between the internal clock of the ADS and the exact time signals on the device for receiving and adjusting the scales of the receivers of the ADS relative to the temporary server specified as a reference (also known as a time server). The time difference in the MPSN should not exceed 100 ms.

In FIG. 2 is a structural diagram of a system for monitoring the coordinates of descent space objects or their devices in the Earth’s atmosphere and their dispatch control.

The coordinate monitoring system for the launched space objects or their vehicles in the Earth’s atmosphere and their supervisory control consists of on-board equipment containing a serial beacon on-board with an antenna (9), an on-board module for automatic dependent observation (ADS) (10) with means for receiving additional differential correction data satellite navigation system and on-board navigation unit (11) and ground equipment containing interconnected ground-based radar stations (radar) (14), bearing beacons (12), ground-based AZN receivers with time synchronization facilities (13) and a system for collecting, processing and displaying information consisting of interconnected local area networks (1), devices and / or devices interfacing with local area networks of external sources information (15), automated workstations (AWS) of a flight management group and / or dispatchers based on a personal computer (16), a set of means for exchanging data with consumers with a device for interfacing with telephone, telegraph information exchange channels and fiber-optic communication lines (19), databases on the server (18) (static and dynamic), special mathematical software (17).

The proposed system works as follows.

The airborne AZN module with the means for receiving additional differential correction data of the satellite navigation system (10), the airborne beacon with an antenna (9) transmit in the established format and according to the established rules (procedures) data on the location and altitude of the launched space objects or their devices in the Earth’s atmosphere. The onboard AZN module at a frequency of 1090 MHz and / or 978 MHz, with an interval from 1 to 10 s, transmits location data as part of an extended squitter received by ground-based reception means, also, after leaving the “plasma cavity”, an on-board radio beacon with an antenna can transmit on the frequency band 406-406.037 MHz through the COSPAS-SARSAT system and / or at other frequencies, by a signal received directly by the receiving means.

Information from descent space objects or their vehicles in the Earth’s atmosphere, received by ground-based receivers of automatic dependent monitoring system with time synchronization means (13) and / or direction-finding beacons (12), and / or ground-based radar (14), via an interface unit with a local computing network of external information sources (15), enters the database (18) (static and dynamic) on the server of the system for collecting, processing and displaying information, where the search for the descent, flight path in the Earth’s atmosphere and additionally information on the descent capsule (reentry vehicle identification number, alarms and other signals, fuel residue (if the design suggests its presence on the board during the descent)).

If the information from the spacecraft or their spacecraft is present in the databases (18), then it, together with the additional information received from the receivers of the ADS system with time synchronization tools (13), goes to the local area network (1) to the workstation (16) )

If additional information about the descent vehicle or maneuvering spacecraft is not available in the databases (18), then only the information about the descent vehicle or maneuvering spacecraft received from the receivers of the AZN system with time synchronization means (13) is output to the local network (1).

The construction of the predicted track of the descent trajectory, flight in the Earth’s atmosphere of the descent vehicle or maneuvering spacecraft is carried out by special mathematical software (17) on the server and, according to the calculation results, enters the local area network (1) on the workstation (16). Data on the descent trajectory, flight in the Earth’s atmosphere, additional information, the forecast track of the descent trajectory, flight in the Earth’s atmosphere from the local network (1), through a set of data exchange tools with consumers (19), is supplied to interested consumers of information.

To ensure the descent trajectory, flight of spacecraft or their vehicles in the Earth’s atmosphere in areas exceeding the stable reception zone of one of the ground-based receivers of the ADS system with time synchronization facilities (13), ground-based receivers of the AZN system with time synchronization facilities (13) are implemented in the composition of the wide-gap multi-position monitoring system, and the time synchronization of the received signals of the airborne AZN module with the means for receiving additional differential correction data and satellite navigation system (11) is implemented on the means of time synchronization built into the ground-based receivers of the ADS system.

To ensure the observation of descent space objects in the area of the aerodrome, runway, specially prepared site, landing zone, and surface movement, the receivers of the automatic dependent observation system are implemented as part of an aerodrome multi-position observation system.

In order to increase the accuracy of determining coordinates, the GNSS on-board module included an on-board local control and correction station (LCC).

A local control and correction station is an airborne or ground-based differential correction system. The principle of differential correction and the differential mode of operation of a satellite navigation system are described in the literature [15]. Note that the geographical coordinates of the equipment by the local control and correction station are known in advance with a high degree of accuracy. By comparing the actual data from the on-board navigation unit (11) and the data from the satellite broadcasting frame of the LCC messages, data of differential corrections (differential correction) are generated.

Thus, the proposed monitoring system for the coordinates of the launched space objects or their devices in the Earth’s atmosphere and their supervisory control improves the accuracy and continuity of determining the coordinates of the launched space object or its device in the Earth’s atmosphere.

At the same time, the coordinate monitoring system of the descent space objects or their vehicles in the Earth’s atmosphere is aimed at working with all sources of information about the coordinates of the observed descent space objects or their devices both while they are in the “plasma cavity” and after leaving it. This allows, during the launching, to solve the urgent problem for modern manned space exploration of continuously determining the coordinates of spacecraft or their spacecraft at all altitudes in the Earth’s atmosphere, as well as to increase the intensity and information content of information provided to interested consumers.

The passage of AZN frequency waves (1 GHz ± 1 kHz) through the plasma forming the “plasma cavity” [16, 17] gives positive results for the on-ground transmission of the actual coordinates measured onboard the SA, which, in contrast to external radar observations of the coordinates descent space objects or their vehicles at all altitudes in the Earth’s atmosphere by turbulent reflections of radar signals has a greater error and less probability of reliable reception by radio means.

Also, the invention is relevant for search and rescue support. The ability to accurately determine coordinates during descent in the Earth’s atmosphere provides the possibility of more efficient dispatching of funds involved in search and rescue support and reduction of time and material costs for search and rescue support of launched space objects or their devices in the Earth’s atmosphere along a ballistic trajectory or their deviation from the calculated trajectory, as well as in case of emergency.

Sources of literature

1. Order of the Air Navigation Service of April 3, 2007 N 22.

2. Order of the Air Navigation Agency dated 11/21/07 No. 112.

3. http://oaoniikp.ru/prod2.php?id=71.

4. "Air Code of the Russian Federation" dated March 19, 1997 N 60-ФЗ (as amended on July 13, 2015) (as amended and supplemented; entered into force on July 24, 2015).

5. Dictionary of international civil aviation.

6. ICAO DOC 9713, Third Edition, 2007, pp. 1-55.

7. Space object // Cosmonautics: encyclopedia; Editor-in-chief V.P. Glushko. - Moscow: “Soviet Encyclopedia”, 1985 - S. 189.

8. Dictionary of international law (diplomatic academy of the Ministry of Foreign Affairs of Russia. 3rd edition, revised and supplemented. Edited by S. A. Egorov // "Statut", 2014.

9. The Great Encyclopedic Dictionary. 2000.

10. Code of the International Aviation Federation.

11. GOST R 25645.167-2005 Space environment (natural and artificial). A model of the spatio-temporal distribution of the flux density of technogenic matter in outer space.

12. “Automatic dependent surveillance systems and methods” (US 8072374 B2, publication date Dec 6, 2011).

13. “A complex of means for receiving and processing messages from aircraft of the system of automatic dependent monitoring” (patent 124408 (08.20.2012) Published: 01.20.2013).

14. “Automated system of supervisory control over aircraft flights with the possibility of using information from the automatic dependent surveillance system (patent 150701 (05/13/2014), published: 02/20/2015).

15. Dvorkin V.V. The principle of differential correction / V.V. Dvorkin // Gyroscopy and navigation. - 2011 - No. 5. - S. 62-78.

16. “Final technical report. Transmission of RF signals through plasma during hypersonic flight. " 2009 http://www.dtic.mil/dtic/tr/fulltext/u2/a518365.pdf.

17. Richard Van Der Prit, Ron Vincent “Simulation of the Reception of Automatic Dependent Surveillance-Broadcast Signals in Low Earth Orbit / Richard Van Der Pryt, Ron Vincent; www.hindawi.com/joumals/ijno/2015/567604/.

18. Aeronautical radio navigation. Directory. Edited by A. Sosnovsky. - M .: Transport, 1990, 264.

19. Belgorod S.L. Automation of aircraft landing control. - M .: Transport, 1972, 352.

20. Rogozhin V.O., Sineglazov V.M., Filsheshkin M.K. Sailing and navigating complexes of used ships. - K .: Knizhkov vidavnitstvo NAU, 2005, 316 (in Ukrainian).

Claims (1)

A monitoring system for the coordinates of the launched space objects or their vehicles in the Earth’s atmosphere and their supervisory control, comprising on-board equipment - an on-board radio beacon with an antenna, an on-board navigation unit, as part of ground-based equipment - interconnected ground-based radar stations, direction-finding beacons, receivers of automatic dependent observation (AZN) and a system for collecting, processing and displaying information, consisting of a local area network, a device for interfacing with external sources of information formations, workstations based on a personal computer, a set of means for exchanging data with consumers with telephone, telegraph information exchange channels and fiber-optic communication lines, a database, special mathematical software, characterized in that an onboard AZN module with additional receiving devices has been introduced the differential correction data of the satellite navigation system between the airborne beacon connected in series with the antenna and the airborne navigation unit and time means have been introduced variable synchronization to ground-based receivers of an automatic dependent monitoring system for their implementation as part of a multi-position monitoring system.

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