RU2668378C1 - Method for preventing contact of spacecraft with actively approaching object - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: invention relates to the space equipment. In a method for preventing a spacecraft (SC) from contacting an actively approaching object using reception sensors for detecting external radiation on the inside of the shell, made in the form of a body of revolution around the spacecraft, or its part, solid-state laser sources are installed in accordance with the receiving sensors of external radiation. Laser sources are emitted through an opening in the external radiation detection sensor on command from the control unit. Determine the direction of an actively approaching object by the result of comparative processing of the readings of the reception sensors for recording external radiation and set the mode of preventive laser radiation, and also issue commands to the engines of orientation to evasion from approaching the active object and transmitting equipment to a message to the ground control center about the effect on the space vehicle.EFFECT: technical result of the invention is to increase the stability and probability of performing a given SC program.1 cl, 6 dwg

Description

The invention relates to the field of monitoring or tracking the flight of spacecraft (SC) and can be used to prevent encounters with an active object deliberately approaching the spacecraft. An example of such possible situations is the unauthorized capture and withdrawal of an orbital reserve spacecraft into the burial zone or approaching the spacecraft for the purpose of unauthorized inspection, identifying its purpose, and evaluating technical characteristics.

Known technical solutions aimed at regulating the mutual position of spacecraft. Known invention protected by patent - analogue: application No. 2012104591/11, IPC B64G, 2012 "Method for the exact positioning and monitoring of moving objects" (V. Zarenkov, D. Zarenkov, V. Dikarev, B. Koynash). The method is based on the use of satellite navigation, allows you to determine the mobile coordinates of the object and control the object in flight. The method is implemented using a system of technical means, including navigation spacecraft, correction stations, hardware of a television center, hardware for space communications, hardware of a controlled moving object and space flight monitoring station. All of these tools operate simultaneously using specially designed algorithms. EFFECT: high reliability and accuracy of discrete signals exchanged between television centers and space objects, which, in turn, provides high accuracy of positioning and monitoring of moving objects. The disadvantages of the method include the high complexity of its implementation.

A technical solution is known analogous to the invention: application No. 2008133984/09, IPC B64G 4/00, 2007 “Device for monitoring the relative position (s) by measuring power for a spacecraft of a group of spacecraft during flight formation”, designed to control spacecraft when they move in formation. The device monitors the relative positions of the spacecraft in relation to each other and contains: a complex of at least three transceiver antennas mounted on at least three sides of different directions relative to the spacecraft and capable of emitting / receiving radio frequency signals; measuring instruments designed to determine the power of signals received by each of the antennas, and to issue sets of powers, each of which is associated with one of the spacecraft of the group located around the spacecraft; storage means for storing sets of cartographic data, each of which characterizes the normalized power of the signals received by each of the antennas depending on the selected transmission directions; processing means for comparing each set of capacities provided by measuring instruments with the totality of stored cartographic data.

As a result of the operation of the device, each of the directions of the transmission of signals emitted by other spacecraft of the group is determined with respect to the coordinate system attached to this spacecraft. The technical result of using the method is to ensure the positioning of a group of spacecraft relative to each other with the accuracy necessary for the joint execution of the task.

The invention is known "A method for determining the direction of an active object deliberately approaching a spacecraft" patent RU No. 2619168, according to which the signals emitted by the approaching active object are received, the amplitude is measured and the received signals are processed. To receive signals, flat-shaped detectors are used. The detectors are placed on the surface of the spherical shell orthogonally to the radius vector from the center of the spherical shell to the point of contact with the detector. Inside the spherical shell material is placed - an absorber of radiation. The direction of the active approaching object is determined by the radius vector directed to the detector with the maximum amplitude of the recorded signal.

Signals from an approaching active object are recorded simultaneously by all detectors, i.e. in accordance with the adopted geometric arrangement of the detectors, the data comes simultaneously from all possible directions of motion of the active object. The signals recorded in the region of the rear hemisphere with respect to the direction of movement of the active object have a lower amplitude than the signals from detectors located in the region of the front hemisphere, which is associated with the absorption of radiation in structural materials inside the spherical shell. With an equal detector area, the signal amplitude is proportional to the cosine of the angle of incidence of the detected radiation. One of the front hemisphere detectors will register a signal with maximum amplitude, which corresponds to the direction of the approaching active object. If necessary, this direction can be determined more accurately by the results of mathematical processing of the readings of detectors located in the vicinity of the detector with maximum amplitude. The speed of the proposed method is determined by the processing time of the electrical signals, so the method provides quick decision-making in controlled situations.

The invention according to patent No. 2619168 is selected as a prototype.

The disadvantage of the prototype method is the lack of response of the spacecraft when it detects the proximity of an active object with it, aimed at preventing negative consequences as a result of a collision with this object.

The aim of the invention is to prevent contact of the spacecraft with an actively approaching object.

The essence of the invention consists in making it possible for the spacecraft to perform retaliatory actions after determining the direction to an actively converging object using laser radiation, for example, a lidar locator, which consist of warning counterpropagating radiation of a given intensity and frequency, performing evasive maneuver by the engines of the spacecraft, and communicating to the ground control center about the emerging operational situation and the implementation of its commands.

The specified goal in the claimed method is achieved by performing these operations.

According to the method, the radiation of the active object is received by flat detectors (receiving sensors) located on the surface of the spherical shell. The control system for analyzing the reception readings by the sensor calculates the direction to the actively approaching object, determining the radius vector from the center of the spherical shell to the detector with the maximum amplitude of the recorded signal. Receiving sensors are manufactured with a central hole to ensure the emission of a beam of a laser radiation source located below it.

The way to prevent the spacecraft from contacting an actively approaching object using receiving sensors for detecting external radiation located on a shell made in the form of a body of revolution around the spacecraft, or part of it, is that on the inner side of the shell, in coordination with the receiving sensors of external radiation, set solid-state laser sources that emit through an opening in a receiving sensor for detecting external radiation on command from a control unit, in which determine the direction of an actively approaching object based on the results of comparative processing of the readings of the reception sensors for detecting external radiation and set the warning laser radiation mode, as well as give instructions to the orientation engines to avoid approaching the active object and the transmitting equipment to report to the ground control center about the fact of impact on the space apparatus.

The warning oncoming light of an actively approaching object, formed by laser pulses of pulses of pulses of various durations and intensities, serves to achieve the following goals:

informing an actively approaching object about the inadmissibility of the undertaken maneuver, for which they develop and publish a warning code known to an unlimited number of people;

opposition to optical systems of an actively converging object.

The spacecraft is equipped with a control program that takes into account various options for changing the situation and the behavior of an actively approaching spacecraft in the absence of its reaction to warning radiation. The program enables the spacecraft to turn on automatic commands for maneuvering to evade contact with an actively approaching object, transmit information to a ground control station and receive its control commands.

As a result of preventive measures on an actively approaching object and / or due to the simultaneous maneuvering of the spacecraft, the spacecraft is prevented from contacting this object.

The implementation of the proposed method is illustrated by the following figures:

FIG. 1 is a simplified diagram of a structural embodiment of a spacecraft for implementing the proposed method;

FIG. 2 - trajectories of the spacecraft and an actively approaching object;

FIG. 3 - inclusion of a lidar by an actively approaching object with radiation directed to the spacecraft;

FIG. 4 - determination by a spacecraft of a direction toward an actively approaching object by the characteristic of its laser radiation;

FIG. 5 - execution of the response laser warning radiation package in the direction of an actively approaching object and transmitting a message to the ground control center about the operational situation;

FIG. 6 - execution of an automatic maneuver command for avoiding contact with an actively approaching object, taking into account the received commands of the ground control point.

To implement the proposed method, the spacecraft 1 (Fig. 1) is equipped with a shell 2 made in the form of a body of revolution around the instrument and engine compartment 3 of the spacecraft with the necessary technological holes 4 in this surface, for example, for the operation of engines, antenna, optoelectronic devices.

On the surface of the shell 2 receive receiving sensors 5 of electromagnetic radiation are connected to the system 6 for measuring their readings and calculating the total result for issuing control commands.

In the center of each receiving sensor 5 (shown selectively), holes 7 are made for the output of the radiation of a solid-state laser 8, which is attached to the inner surface of the shell under the receiving sensors 5 and connected to the power supply and control systems of the instrument compartment 8 of the spacecraft 1.

In the process of performing a functional task by the spacecraft 1 in orbit 10 (Fig. 2), the appearance of an object 11 that is actively approaching the spacecraft 1 is possible, which is determined by the observation means for the maneuvering process 12 of this object near its initial orbit 13.

At the stage of approaching the spacecraft 1, to its security zone 14, the object 11 (Fig. 3) creates electromagnetic radiation 15 directed at the space object 1, for example, as a result of the operation of location tools.

The receiving sensors 5 on the shell of the spacecraft 2 record the radiation 15 and according to the intensity of the readings of these sensors i _n , the measurement system calculates the instantaneous direction vector R to the actively approaching object 11, in its own coordinates, where the unit vector r is located in the center of gravity M of the spacecraft 1 and is directed to the center of the receiving sensor 5 with the maximum value of the received signal.

Based on the results of evaluating the radiation intensity and determining the direction R to the actively approaching object 11 (Fig. 4), a command is issued to turn on the solid-state laser 8 located under the receiving sensor 5, through which the direction vector R passes to the actively approaching object 11, and generate radiation 17.

The command to execute the warning radiation package 17 (Fig. 5), provides the creation of a series of pulses of a given periodicity t in time T and intensity E.

From the spacecraft 1, information 18 is transmitted to a ground control station about the emerging operational situation using the radio channel of the transmitter-receiver unit.

In the case of continued active approach by object 11 (Fig. 6) and the absence of a reaction to warning radiation 17, the spacecraft 1 performs maneuvering 19 to avoid collision by turning on the propulsion system 20. The command to turn on the engines is provided in the program of the onboard control system or ground control team using the calculated ballistic data.

Such actions of the reaction of the spacecraft to the evolving situation, with possible necessary repetition, ensure the prevention of contact of the spacecraft with an actively approaching object.

The technical and economic effect of the invention is to increase the stability and likelihood of the execution of a given program by a spacecraft by ensuring the implementation of the regular term of active existence of the spacecraft when installing and using means of a response to the actions of an active object with the issuance of a warning signal by laser radiation, using evasive maneuvering of the spacecraft registration of the fact of impact on the spacecraft.

The proposed method does not require the use of an expensive optoelectronic guidance system for an actively approaching object.

Claims (1)

A method of preventing a spacecraft from contacting an actively approaching object using receiving sensors for detecting external radiation located on a shell made in the form of a body of revolution around the spacecraft, or a part thereof, characterized in that on the inner side of the shell, solid-state sensors are installed in accordance with the receiving sensors of external radiation laser sources that emit through an opening in a receiving sensor for detecting external radiation on command from a control unit in which determine the direction of an actively approaching object based on the results of comparative processing of the readings of the reception sensors for detecting external radiation and set the warning laser radiation mode, as well as give instructions to the orientation engines to avoid approaching the active object and the transmitting equipment to report to the ground control center about the fact of impact on the space apparatus.

Images