RU2704348C1 - Method of determining an object, which inspects a spacecraft in passive mode - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: invention relates to the field of spacecraft observation and tracking devices and can be used to determine the object inspecting the spacecraft in passive mode. In order to determine an object which inspects a spacecraft in passive mode, space viewing zones are recorded, an image of the viewing areas is formed on a multi-element radiation detector, and an inspecting object is determined from the data of the multi-element receiver. Vision areas are then recorded again at a constant exposure time. Inspecting object is determined by increasing brightness and decreasing length of the track in the multielement receiver.EFFECT: enabling determination of an object which inspects a spacecraft in passive mode, namely, in the absence of signals emitted by an approaching inspecting object without the need to place onboard additional equipment, which increases mass and dimensional characteristics of the spacecraft and requires additional onboard power engineering.1 cl

Description

The invention relates to the field of means of monitoring or tracking the flight of spacecraft (SC) and can be used to determine the object inspecting the spacecraft in passive mode. An example of such situations is the approach to the spacecraft in order to identify its purpose, evaluate technical characteristics or search for new technological solutions.

Known invention protected by patent - analogue: application No. 95115874/11, IPC B64G 9/00, 1995 “Method for the selection of space objects” (Atnashev AB, Atnashev VB, Dokukin VF, Zemlyanov A.B ., Chuev V.I.), intended for the selection of passive space objects and detection from the space station (SC) of fragments of particles moving along the trajectories of a dangerous approach. The essence of the invention lies in the fact that they conduct direction finding of space objects located near the CS (in the area of the direction finder). In this case, two parameters are measured: the current relative position of the CS and the bearing to be detected, as well as the relative radial velocity. Based on these data, a space object is identified. The disadvantages of the method include the need to use radar equipment onboard the CS, which leads to an increase in the mass and overall characteristics of the CS, as well as to an increase in onboard power.

Known invention protected by patent - analogue: application No. 2008133984/09, IPC B64G 4/00, 2007 "Device for monitoring the relative position (s) by measuring power for the spacecraft of a group of spacecraft during the flight system", designed to control space devices when they are moving in formation. The device monitors the relative positions of spacecraft in relation to each other and contains:

- a complex of at least three transceiving 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 the 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 designed to store 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 tools designed to compare each set of capacities issued 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 this 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 disadvantages of the device include the need to place on board the spacecraft radio transmitting equipment, which increases the mass and overall characteristics of the spacecraft and requires additional costs of onboard power.

Known invention protected by patent - analogue: patent No. 2658203 IPC B64G 3/00, 2017. “A method for registering the proximity of an active object to a spacecraft orbital reserve in the low Earth orbits” (authors: M. Yakovlev), according to which signals to the spacecraft, measure the level of signals, process and store signals, and the signals are recorded in series for equal intervals of time, and the approach of the active object is determined by the increase in the rate of change of the signal level s sequentially recorded in series. A disadvantage of the invention is the inability to detect an active object in the absence of signals emitted by it.

A patented invention is known as an analogue: Patent No. 2632792 IPC B64G 3/00, 2016. “Method for detecting inspection of a spacecraft” (authors: Yakovlev M.V., Yakovleva T.M., Yakovlev D.M.), according to which receive signals emitted by an active object approaching the spacecraft, measure the amplitude of the received signals, process and store the received signals, compare the amplitude of each next signal with the amplitude of the previous signal, and the inspection of the spacecraft is determined by the transition mode been consistent increase in the amplitude of the received signals to reduce the slew rate mode amplitude of the received signals and their subsequent stabilization at a constant level. A disadvantage of the invention is the inability to detect an active object in the absence of signals emitted by it.

A patent-protected invention is known as a prototype: Patent No. 2494415 IPC B64G 1/64 2011, “Method for detecting a passive space object when an active spacecraft approaches it” (authors: Starovoitov EV, Afonin VV), according to which they perform space scanning by turning the active spacecraft with a radar rigidly mounted on it along the pitch or course channel until a passive spacecraft is detected. The width of the radiation pattern of the probe radar radiation in the scanning direction is minimal, and in the perpendicular direction the angle of divergence is equal to the angular size of the viewing area. The detection of a passive spacecraft is carried out in the instantaneous field of view of a multi-element radiation detector. This field coincides with the radiation pattern of the radar. The technical result of the invention is to increase reliability by eliminating optical-mechanical scanning using moving parts. A disadvantage of the invention is the inability to detect an active object in the absence of signals emitted by it.

The aim of the proposed invention is to determine the object inspecting the spacecraft in a passive mode, that is, in the absence of signals emitted by the approaching inspecting object.

This goal is achieved in the claimed method for determining the object inspecting the spacecraft in a passive mode, according to which the space viewing zones are recorded on the spacecraft, the image of the viewing zones is formed on a multi-element radiation receiver, and the inspecting object is determined according to the multi-element receiver. Viewing areas are re-recorded at a constant exposure time. An inspecting object is determined by increasing brightness and decreasing track length in a multi-element receiver.

The rationale for the feasibility of the proposed method is as follows. To identify the purpose of the spacecraft, evaluate its technical characteristics or search for new technological solutions, a detailed examination of the spacecraft from a short distance is necessary. Therefore, the inspecting object must have a homing system that provides proximity to the spacecraft at the minimum allowable distance. Passive inspection mode means that approaching the inspected spacecraft is done by registering solar radiation reflected from the spacecraft or infrared radiation from its surface. Preliminary rapprochement of the inspecting object with the spacecraft is carried out according to the commands of ground-based control complexes until the level of the acting radiation is higher than the sensitivity threshold of the on-board surveillance equipment of the inspecting object. In connection with the approach of the inspecting object, the brightness of the received signals in a multi-element receiver monotonically increases. In this case, the track length of the inspecting object as it approaches the minimum allowable distance from the spacecraft gradually decreases and degenerates to a point.

Thus, the efficiency and practical significance of the proposed method for determining the object inspecting the spacecraft in passive mode is not in doubt.

Claims (1)

The method for determining the object inspecting the spacecraft in passive mode, according to which the space viewing zones are recorded on the spacecraft, forming the image of the viewing areas on the multi-element radiation detector, determining the inspecting object according to the multi-element receiver, the viewing areas being re-recorded at a constant exposure time, inspecting an object is determined by increasing brightness and decreasing track length in a multi-element receiver.