RU2704645C1 - System for cleaning outer space from objects of space debris - Google Patents

Abstract

FIELD: astronautics.

SUBSTANCE: invention relates to space engineering, and more specifically to spacecrafts, which can be used to combat space debris. Proposed system comprises spacecraft, solar charger and deployment system interconnected by assembly operations. Solar concentrator includes one or more optically conjugated mirrors which focus solar radiation at one point of the required diameter and connected to the deployment system. Spacecraft includes an autonomous control system, data transmission system, spacecraft stabilization and orientation system. Spacecraft accumulates solar energy and heat from solar concentrator for power supply of spacecraft.

EFFECT: elimination of small-size debris of space garbage in orbit.

1 cl, 2 dwg

Description

The invention relates to space technology, and more specifically to spacecraft that can be used to combat space debris in a given orbit.

There is a known space complex for cleaning near-Earth space from small-sized space debris according to patent RU 2612752 C2 (dated March 13, 2017), which is an orbital group - spacecraft for collecting and utilizing small-sized objects KM and spacecraft for measuring parameters of the orbits of small-sized objects KM, ground-based control complex and measurements (NKUI), a radio link for transmitting data on the parameters of the orbits of spacecraft objects between transmitting devices of the spacecraft of measurements and the receiving device of the NKUI to ensure the transmission of the outcome data on the detected CM objects and their orbital motion parameters, the radio link for controlling the collection of CM objects between the NKUI transmitting devices and the receiving and disposing spacecraft receiving devices in order to ensure the transfer of on-board control and target designation programs to the spacecraft for collecting and disposing small-sized CM objects. The spacecraft for collection and disposal is intended for the collection of small-sized objects of CM in a given sector of near-Earth space and their subsequent disposal. The solution to this problem is achieved by using a large-area screen and a certain shape, as well as the choice of the required orbit. Cleaning a given sector of near-Earth space is as follows. When space debris collides with the screen, the initial velocity of small-sized space debris is reduced, i.e., the orbit of the CM objects is braked, which leads to the descent of the CM objects from the original orbit, their further braking and disposal in the Earth’s atmosphere. Such a technical solution seems more costly due to the use of not just one spacecraft, but their grouping and a large number of subsystems in its composition. In addition, it should be noted that in the event of a collision with the screen, the KM fragment, while slowing down and changing the trajectory, exerts a physical effect on the apparatus itself, which can lead to the spacecraft withdrawal from a given orbit. This complex cannot be considered as close in design to the claimed system due to the different approach to solving the problem.

The invention is known "Spacecraft for cleaning the near-Earth space from debris" according to the patent of the Russian Federation No. 2492125 (IPC B64G 99/00 from 09/10/2013). A spacecraft for cleaning near-Earth space from debris contains a system for detecting bodies to be destroyed and a shot capsule with a magnetic suction cup connected to a boost unit to which a gas cylinder is attached, a braking ball, and a control unit. The control unit collects information from the GPS receiver and boost unit and transmits it through the antenna to Earth. It is possible to control the coordinates of the descent of space debris into the atmosphere, which eliminates the collision of other spacecraft with it. The spacecraft detects space debris using a system for detecting debris to be destroyed. After that, a shot capsule is released, which is attached to space debris using a magnetic suction cup. At the same time, the boost unit supplies information to the gas cylinder by inflating the braking ball. The braking ball is several times larger than the size of space debris, playing the role of a parachute, thereby causing a decrease in the speed of space debris, which leads to a decrease in the orbit of rotation of the CM around the Earth and its subsequent disposal. At the same time, it is possible to control the coordinates of the omitted space debris, which eliminates collisions with other spacecraft, as well as eliminating the problems associated with the twisting of the cable when using the cable system. The disadvantage of this technical solution is the limited possibility of using magnetic suction cups, since to capture objects with their help, surfaces with magnetic properties on the body of the capture objects with a sufficient area for adhesion and with minimal curvature are required. For spacecraft, in the design of the hulls of which non-magnetic composite materials predominate, the use of magnetic suction cups will be ineffective.

In addition, the disadvantage is the impossibility of collecting space debris with sizes up to 10 cm, which make up a huge amount in near-Earth space. It should also be noted that this invention differs from the claimed in another way of solving the problem.

The invention is known as “Space net” according to the patent of the Russian Federation No. 2046081 (IPC B64G 1/00, B64G 99/00 dated 03/27/2013). The essence of the invention lies in the fact that the space net contains a spacecraft (SC) and a screen associated with it, interacting with the external environment, made in the form of two surfaces of flexible film placed on opposite sides of the spacecraft and connected with it via cables of adjustable length moreover, the cables are oriented in space along the local vertical, a garbage collection container oriented along it is fixed at the free end of each cable, the inner end of which is made in the form of a funnel, with knitted with the edge of the film adjacent to it, and its end face external to the spacecraft is equipped with a hatch. When space debris interacts with the film material, the relative velocity of the particles is quenched, after which these particles under the action of centrifugal forces enter the containers for garbage collection. The space net is delivered to a given area of outer space and is deployed so that the cables are oriented along the local vertical. The disadvantage of this technical solution is the imperfection of the design of the device due to the cable system of the deployment of the screen, which is dangerous for the spacecraft itself, the impossibility of long-term maintenance of orientation and rigidity of the structure, as well as the limited ability to collect space debris (CM). This invention differs from the claimed method of solving the problem of cleaning outer space from space debris.

The closest in combination of essential features with the claimed invention is the high-temperature solar furnace according to patent 4706401/06 (IPC: F24J 2/00 of 01/30/1996), aimed at use in metallurgy, in the semiconductor industry for the production of ultrapure metals and semiconductors. The solar furnace contains a helioconcentrator, consisting of three optically conjugated mirrors focusing solar radiation on the plane of the output window of the focone, in which there is a light guide element made in the form of a bundle of optical fibers, the output ends of which are inserted into the spherical high-temperature chamber through through holes. It is proposed to use this invention to obtain ultrapure metals and semiconductors, other methods of use are not considered. A solar concentrator, consisting of three optically conjugated mirrors, is not considered as the only technical option for a part of the proposed spacecraft-solar furnace system and can be either one focusing lens or several, depending on the parameters and characteristics of the target fragments in orbit . This invention differs from the claimed purpose of use.

As purely theoretical, the problem of space debris arose in the fifties of the last century, when launches of the first artificial Earth satellites began. Debris and particles of space technology in orbit already pose a threat to existing spacecraft, especially manned ones. There are currently no particularly small debris protection measures. The smallest debris is most often paint or metal chips, but despite their size, these particles can reach speeds of more than 27 thousand km per hour. This may be enough to cause significant damage to existing spacecraft.

The issue of space debris is international in nature. In 2016, scientists at the Roskosmos Central Scientific Research Institute TsNIImash came to the conclusion that if we do not deal with this problem, then after 100 years the development of space activity may stop - the entire near-earth orbit will be strewn with fragments of space technology. The main danger of space debris is that its amount increases exponentially.

The task is to create a system, the design of which will allow you to effectively remove the elements of space debris in orbit without the need for their transfer to other orbits or descent into the atmosphere. At the same time, the tasks are set to ensure the safe operation of the system to combat space debris and economy.

The solution to the problem is achieved by the fact that the system proposed as an invention includes a spacecraft and a solar concentrator interconnected through assembly operations, the functional parameters of which are determined based on the parameters and characteristics of the debris that must be eliminated. In this case, the spacecraft is placed in orbit, on which satellites receive enough solar energy, for example, in the sun-synchronous orbit (MTR) of the Earth, which allows the satellite to never go into the shadow of the Earth, always staying in the sun near the border of day and night. Moreover, the spacecraft contains a control system and an orientation and stabilization system. In this case, the helioconcentrator may be one or more mirrors. Moreover, the system has one or more transformable mirrors, deployed in such a way that the solar radiation with a beam of a given diameter is focused on the target object.

The technical result of the claimed invention consists in the actual full or partial evaporation of small-sized debris of space debris in orbit, as well as in expanding the arsenal of available means of combating the clogging of outer space.

The advantages of this technical solution are as follows:

- The efficiency of cleaning small debris of space debris, while the debris is not diverted to a higher orbit, creating problems for future generations, but evaporates directly;

- Reduces construction costs due to the use of solar energy to eliminate debris;

- Improving the energy performance of the system, since solar energy is accumulated and used for the device itself;

- The location of the proposed system in a solar-synchronous or other orbits, in which the devices receive enough solar energy, allows the proposed technical solution to effectively deal with debris of space debris.

In fig. 1 and 2 schematically shows one of the possible examples of the implementation of the system for cleaning outer space from space debris.

The described system for cleaning outer space from space debris, which is a spacecraft with a solar concentrator, in general includes KA 1, one or more optically conjugated mirrors 2, focusing solar radiation at one point of the required diameter, control system 3 (in Fig. is not displayed), while the invention assumes the existence of a data transmission system 4 (not shown in the figure), while there is a stabilization and orientation system of the spacecraft 5 (not shown in the figure), the presence of device accumulation of solar energy and heat from a solar concentrator for additional power supply unit 6 (Fig. not shown).

After dropping the head fairing of the launch vehicle, the system for combating space debris enters a given orbit, and its deployment takes place. Then, using the detection system, which can be presented in the form of on-board technical vision or through data transmitted from the Earth, fragments of space debris are detected and data about objects is transmitted to the Earth. After receiving the task of eliminating the elements of space debris, the helioconcentrator is pointing at the element and on the Sun and the object of space debris is kept in focus until it is evaporated or melted.

The proposed system is highly economical due to the fact that it uses solar energy to remove debris from space debris, and also, if there is an accumulating device, it can provide itself with energy for functioning. The system can be composed of an MCA, for example, of the CubeSat class, which can contribute to the additional cost-effectiveness of the proposed technical solution due to the low cost of CubeSat relative to a standard-size spacecraft. The proposed system is reliable and does not require the use of complex devices to eliminate elements of space debris, for example, robotic. The availability and simplicity of the proposed solution allows you to use it everywhere.

Thus, the effectiveness of the implementation of the proposed technical solution consists in the actual elimination of small-sized debris of space debris in orbit, in expanding the arsenal of available means of combating space debris, as well as in the economics of the system due to the simplicity of design and the ability to use a small spacecraft. The proposed system is notable for its reliable functioning and does not require the implementation of complex action algorithms for eliminating debris, such as the actual capture of debris or moving fragments of debris to higher orbits, leaving the problem for future generations.

The above advantages of the proposed system make it possible to create not only a universal and highly efficient, but also a relatively simple system for eliminating space debris.

Claims (2)

1. A system for cleaning outer space from space debris objects, including a spacecraft (SC) interconnected through assembly operations, a solar concentrator and a deployment system, characterized in that the solar concentrator includes one or more optically conjugated mirrors focusing solar radiation at one point of the desired diameter and connected to the deployment system, while the spacecraft includes a control system installed in the apparatus through assembly operations, an update system space debris, a data transmission system, a spacecraft stabilization and orientation system, a device that accumulates solar energy and heat from a solar concentrator to power the spacecraft, fixed through assembly operations on the spacecraft's hull. 2. The system for cleaning outer space according to claim 1, characterized in that it is configured to place in orbit, for example, a solar-synchronous one, on which it receives enough solar energy and can function efficiently.

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