RU2491210C1 - Method of changing path of dangerous space body (versions) - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to protection of the Earth against collision with dangerous space body (DSB). Proposed method comprises detecting DSB and defining its characteristics to place carrier rocket in orbit of rendezvous therewith. Carrier rocket comprises delivery vehicle assembly with command module and set of hitting modules with self-guidance system. In compliance with the first version, carrier rocket equipped with gamma-laser is placed in said orbit. In approach to DSB said hitting modules are released and positioned in space in definite intervals. Before first hitting module meets the DSB high-energy gamma-laser beam is guided thereto to create high-temperature channel. Hitting modules are placed in turns into said channel. In said channel explosive of hitting module is blasted. Hitting modules trajectories and flight control are corrected with allowance for the results of previous attacks delivered to DSB and variations in current situation. In compliance with another version, spacecraft with gamma-laser is included in carrier rocket set to be delivered to maximum possible distance to DSB for hitting from minimum distance.

EFFECT: higher efficiency of attack, reliable process.

2 cl, 11 dwg

Description

This invention relates to the field of application of space technology to ensure the safety of the Earth from collision with a dangerous space body (OCT) (asteroid, comet) or the passage of this body in unacceptable proximity.

The elimination of the danger of collisions with OCT is recognized as a task of global importance and is discussed in the framework of the UN Committee on the Peaceful Uses of Outer Space.

To eliminate this danger, a system of observation and exposure to dangerous space objects is being created. Known project to create a planetary defense system "Citadel". It is assumed that after the detection of a dangerous space body by ground means, small reconnaissance spacecraft will be launched into space to clarify the trajectory of the asteroid. According to their target designation, space interceptors equipped with nuclear explosive devices will operate. The task of changing the trajectory of a dangerous cosmic body or in the extreme case of its destruction is being fulfilled.

There are various ways of influencing these objects in order to change their trajectory or destruction.

Known patent RU No. 2243621 IPC 7 H01S 4/00, author Motorin Victor Nikolaevich, "A method for producing directional and coherent gamma radiation and a device for its implementation." The invention relates to laser technology and can be used to obtain a directed pulsed beam of coherent gamma radiation. The method includes pumping an active medium in the form of a laser rod made of a single crystal in the form of an elongated cylinder, in the volume of which the nuclei of the uranium hydride isotopes and hydrogen atoms are uniformly placed, the crystal lattice of the single crystal contains crystalline planes parallel to each other and to the axis of the laser rod, which is simultaneously a fast neutron moderator, a neutron wave shaper, a pump source and an active medium, while the laser rod is sequentially enclosed in an aluminum shell made of a material that absorbs thermal neutrons, bearing a steel case with connecting flanges at its ends, a metal plug is hermetically and rigidly mounted conical on one of the ends of the body, and a steel cup closed from one end with an axial chamber and a shutter is rigidly installed consisting of adjacent symmetric radial chambers, in one of which the first TNT charge with a detonator is rigidly mounted, in the axial chamber of the glass and successively installed with the possibility of radial movement into the second radial chamber of the shutter a metal tube made of a neutron-absorbing material, made with the possibility of axial movement through the glass an external source of fast neutrons in the form of a monolithic cylinder and a piston, a second TNT charge with a detonator, which is placed near the closed wall of the glass, is rigidly fixed critical regime in a single crystal by initiating a chain reaction of fission of heavy uranium nuclei by thermal neutrons at the moment of contact of the end surface in an external source of fast neutrons with an end face of a single crystal, sequentially undermining the first and second TNT charges, as a result of which the tube is forced into the free radial chamber of the shutter by gas pressure, to the place of which an external source of fast neutrons and a piston are moved, which uniformly presses the contact along the entire surface the end face of the neutron source to the single crystal, form a neutron wave along the longitudinal axis of the single crystal with subsequent exit from the conical stub coherent and directional gamma radiation. A significant increase in flux density and radiation power.

In the publication “The system for protecting the Earth from an asteroid-comet hazard based on an ultra-powerful space gamma laser. Description of the project of a comprehensive study of the possibilities of implementing the concept of a promising device for generating directed and coherent gamma radiation of high power as an element of the Earth’s protection system from asteroid-comet hazard ”(Address of project information on the Internet: http://www.rufund.ru/?PROJECT = laser & LANG = RUS) the purpose of this invention is defined - exposure to a dangerous cosmic body. According to estimates, the impact is supposed to be carried out from a distance of up to 100 thousand kilometers. (“Technique-youth” No. 9/2008, article “Cosmic laser - good or evil of the Earth?”).

This invention according to patent RU No. 2243621 is an analogue of the invention.

This method is promising for high energy exposure, mass and size characteristics and provides high efficiency if necessary, the destruction of the OCT of a relatively small mass. However, changing the trajectory of the OCT using the radiation of a gamma laser according to this patent analogue has the following disadvantages.

Studies have shown that the destruction of the OCT is not always advisable, since the fragments of the OCT have the property, when moving further, to come together in a single formation, which can pose the same danger to the Earth as the OCT before destruction.

In the event that it is not required to achieve OCT destruction, and the purpose of the impact is to change the trajectory of the OCT, most of the energy received by the OCT from laser radiation is not used in a targeted way.

It is technically difficult to ensure that the laser beam is not just aimed at the target — OCT, but to a point on a straight line passing through the center of mass of the OCT.

With an eccentric effect on the OCT, the resulting reactive force will be directed to the spin and rotation of the OCT, which is useless for changing the trajectory of the OCT. On the other hand, the shock waves propagating in this case in the body of the object, destroying it from the inside, causing the surface layer of the dangerous space object to discharge, are also formed when the laser energy is misused.

Thus, despite the high radiation energy, the beneficial effect on OCT during laser irradiation, which consists in creating a high-temperature channel in OCT and the formation of reactive force, which has a component acting in the right direction of change in the OCT trajectory, will consume a small part of the energy received from gamma laser radiation.

The well-known "Method of changing the trajectory of a dangerous space body and a device for its implementation" patent RU No. 2369533 B64G 1/00, b64g 1/66 2009

A method for changing the motion path of a natural space body and a device for its implementation is that after detecting and determining the characteristics of the OCT, the launch vehicle is launched, consisting of a delivery unit with a command compartment and a set of shock units with a homing system for the target and an explosive compartment. The first block is equipped with a penetration device. When approaching the OCT, the shock blocks are alternately released from the spacecraft and positioned in space at the required intervals. The first block is guided by the homing system of the compartment at the aiming point on the surface of the OCT, at which it enters the calculated depth, where the explosive is detonated. The trajectory of the next strike block is corrected according to the results of the first collision and is guided after the debris is scattered by the processor of the command compartment and the homing system on the heat spot of the crater made by the first block. Subsequent shock blocks carry out corrections according to the results of the previous collision using the processor of the command compartment and direct the homing system to the thermal spot of the crater. The command compartment controls the movement of shock blocks at the stage of pointing at the OCT, monitors the results of hits of the shock blocks and the change in the movement of the OCT, implements a target impact program that takes into account possible factors of a change in the situation (failures, misses, loss of blocks, etc.). After reporting to the Earth about the results of the operation, the spacecraft is used as a shock block, directing it to the crater at the target.

The method of changing the motion path of a dangerous space body according to patent RU No. 2369533 is selected as a prototype.

The disadvantage of the prototype is that with kinetic effects on OCT it is difficult to create a recess of the required depth. For this, it was proposed that the first shock block be equipped with a penetrator for this purpose. This requires the use of special materials, an increase in the thickness of the walls of the shock block, imposes strict requirements on its shape during manufacture, and requires compliance with the design mode at the entrance to the surface of the OCT, the composition of the substance of which also significantly affects the efficiency of crater creation.

The technical result of the invention is to increase the effectiveness of exposure to a dangerous space body and the reliability of the implementation of this process with the control of the results and a flexible reaction to changing the situation while increasing the energy potential of exposure to a dangerous space body.

This is achieved by the joint application of advanced technology of high-energy laser exposure and the use of space technology of kinetic effects, equipped with high-precision guidance, the necessary computer technology and communication systems.

The essence of the invention lies in the joint coordinated use of technologies of laser and sequential shock controlled impact on the OCT, providing the necessary force effects for changing the trajectory of the OCT, eliminating the danger of collision with the Earth.

This is achieved by the fact that the composition of space means of influence on the OCT includes a spacecraft equipped with a gamma laser and at the moment of time, coordinated with the approach and deployment of shock blocks of the kinetic effect, orient it, direct it to the OCT, turn on the nuclear reaction process and create laser radiation in a dangerous space body, a high-temperature channel into which using a homing system directs the kinetic shock block at time intervals necessary to maintain an effective process while gassing in the high channel.

In this case, the maximum use of the OCT substance is achieved to ensure this force effect due to the creation and maintenance of reactive force from the gas stream flowing from the high-temperature channel.

According to the proposed method, after determining the trajectory and characteristics of the OCT using ground-based infrastructure, using ground-based methods and using small reconnaissance spacecraft, a launch rocket is launched and a spacecraft with kinetic impact blocks on the OCT coordinated according to a single program is brought into the trajectory of meeting with the OCT .

In accordance with this program, the impact on OCT into the near-Earth space orbit launches a spacecraft equipped with an optical guidance system on OCT and a high-energy nuclear-pumped laser. This spacecraft is placed in near-earth orbit quite distant from the conditions of ensuring safety for the Earth and the space segment from nuclear reaction factors.

When a spacecraft with shock blocks approaches the OCT, a spacecraft with a gamma laser in near-Earth orbit is brought into operation, captured by the OCT with an optical guidance system, and, upon a command coordinated with the movement of the shock blocks, the gamma laser is launched and a high-energy laser beam is applied to the OCT. As a result, OCT form a high-temperature channel with the emission of vaporized gas. The resulting reactive force from the outflow of the jet of this gas provides a vector of its force component, aimed at the desired calculated change in the trajectory of the OCT.

When the spacecraft is oriented with laser guidance on the OCT, the safety condition for the Earth and the space segment is fulfilled - the need for safe direction of radiation from the rear side surface of the gamma laser in the opposite direction.

An application of the proposed method is the inclusion of a spacecraft with a gamma laser in the form of a block in the expedition to OCT together with shock blocks, the block with a gamma laser being brought to the OCT first, its movement is being adjusted (for example, it is brought out to the plane of the orbit of the OCT) to the projection point on the surface of the center of mass of the OCT and include its nuclear pumping. This embodiment of the method of deflecting the OCT trajectory requires additional costs for the delivery of a spacecraft with a gamma laser to the OCT, but has an increased efficiency of impact on the OCT in accuracy and energy.

The result of the impact on the OCT is monitored from a spacecraft approaching the OCT with a command compartment and a set of shock blocks, which, when approaching the OCT, are released from the spacecraft, positioned in space at a given interval and direct the laser action on the OCT into the received channel using homing systems of the strike unit and command commands of the command unit. The impact on the OCT is carried out by a set of shock blocks, which are sent to the high-temperature channel alternately with a given time interval.

When it enters the channel, detonation of the explosive of the shock block is carried out. The explosive charge power in the shock blocks of the kit, depending on the program of sequential impact on the OCT, may vary. In the case of the use of nuclear charges for these purposes, charges with adjustable power are used.

So the last shock block can be equipped with a charge of increased power in order to be able to implement various types of impact, for example, the destructive action on the asteroid with insufficient amount of removal of the asteroid from orbit or the impact on the broken off piece of the asteroid.

Studies have shown the inappropriateness of the destruction of the OCT, since its fragments have the property of collecting again into a single formation.

At the same time, it is advisable to supplement the variant of the required change in the OCT trajectory due to the reactive force of the outflow of gases from the high-temperature channel while maintaining the temperature in it using channel shock blocks to increase the reliability of the OCT neutralization operation in the necessary controlled case.

The positive qualities of this method of exposure to OCT are that the physical effect of a series of accurate hits to the channel from the laser exposure provides a more significant result than a one-time exposure in which most of the explosion energy is dispersed in space, the fraction of the explosion energy incident on the OCT is used inefficiently and the process of destruction of the OCT is impossible to control.

The OCT impact program according to the proposed method ensures the creation of the necessary reactive force in the OCT changing its path in the direction of the most effective effect.

Ballistic analysis of the effects shows that it is most effective to change the trajectory of the OCT when exposed to it by force in the plane of the orbit of the OCT.

The interval between hit blocks in the resulting channel is calculated from the condition of the thermodynamic state of the OCT substance in the channel. The kinetic effect of the shock blocks is carried out after the gas flows out of the channel with a temperature higher than that acceptable for the shock blocks under the condition of passage into the channel.

Periodic kinetic effects of shock blocks in the channel support the process of gas formation with high temperature and effectively use the OCT substance to create the necessary reactive force that changes the trajectory of the OCT in the desired direction.

The second factor affecting the choice of the interval between hits of the shock blocks in the channel is the condition for providing the necessary time for the shock block to maneuver around the OCT to guide the shock block into the channel.

The command compartment of the spacecraft with an onboard control system, a processor provides control of the impact operation on the OCT, implementing a laid-down program that provides various options for the development of the situation, for example, a possible fracture of the OCT, its premature destruction, the need to take into account the increase in the speed of rotation of the OCT as a result of the error in the impact of the blocks when the trajectory deviates from the point of the center of mass of the OCT, loss of shock blocks and other factors.

Impact blocks can be equipped with charges of various sizes, depending on the calculation of the optimization of the program of impact on the asteroid.

Thus, the method for changing the trajectory of a dangerous space body using a spacecraft carrying shock blocks delivered to a dangerous space body and a spacecraft with a gamma laser in near-Earth orbit with X-ray guidance on the dangerous space body consists in that the shock blocks before by approaching a dangerous cosmic body, they are alternately released and positioned in space for sequential exposure to a dangerous cosmic body when they are guided with the help of systems homing into the channel of a dangerous space body, which is obtained as a result of exposure of a dangerous space body to X-ray radiation using x-ray radiation from a gamma-ray laser from near-Earth orbit at a point in time that is consistent with the movement of the shock blocks, and from the spacecraft control the guidance of the shock blocks into the channel and monitoring the results of sequential exposure to a dangerous cosmic body.

An embodiment of the proposed method for changing the trajectory of a dangerous space body using a spacecraft delivered to the dangerous space body carrying shock blocks and a block with a gamma laser is that a block with a gamma laser and shock blocks are alternately released before approaching a dangerous space body and positioned in space for sequential exposure to a dangerous space body when pointing them with the help of a homing system into the channel of a dangerous space body, which they are taught as a result of exposure to x-ray radiation by a gamma laser from a minimum distance at a point in time that is consistent with the movement of the shock blocks, and from the spacecraft, the guidance of the shock blocks into the channel is controlled and the results of successive exposure to a dangerous space body are controlled.

The invention is illustrated by graphic images:

figure 1 - optoelectronic methods for determining the characteristics of the motion of the OCT, the use of reconnaissance spacecraft, preparation for launching a launch vehicle with a spacecraft with shock units and a launch vehicle with a spacecraft with a gamma laser in near-Earth orbit;

figure 2 - the transition of the spacecraft with shock blocks on the trajectory of the meeting with the OCT, the conclusion of the spacecraft with a gamma laser in near-Earth orbit;

figure 3 - diagram of the device of the spacecraft with shock blocks (option with a gamma laser as part of the expedition to the OCT);

figure 4 - release of shock blocks and their positioning in space;

5 is a diagram of the radiation effect on the OCT of a gamma laser from near-Earth orbit, the motion and kinetic effect on the OCT of shock blocks in the final section;

6 is a diagram of the radiation exposure on the OCT of the gamma laser and the kinetic effect on the OCT of the shock blocks in the final section (option with a gamma laser as part of the expedition to the OCT);

Fig.7 - the formation of a high-temperature channel in the OCT from exposure to x-ray radiation of the gamma laser;

Fig - getting into the high-temperature channel of the first shock block;

Fig.9 - getting into the high-temperature channel of the i-th shock unit;

figure 10 - getting into the high-temperature channel of the n-th shock block;

11 is a diagram of the total force impact on the OCT.

The method of changing the trajectory of a dangerous space body is as follows.

Using astronomical optical 1 (Figure 1) and radio engineering 2 means determine the motion parameters of OCT 3 and its characteristics (content of substances, their structure). It is possible to use reconnaissance spacecraft 4 for this purpose. Carry out preparations for launching a launch vehicle 5 with a spacecraft with shock units and a launch vehicle 6 with a spacecraft with a gamma laser in low Earth orbit

Using known launch vehicles 5 (FIG. 2), the spacecraft 7 with shock blocks is put into orbit and, using the booster stage 8, are brought into the trajectory of the meeting with the OCT, the necessary intermediate corrections are performed, for example, using the gravitational field of the Moon 9.

A spacecraft 10 with a gamma laser is launched into near-Earth orbit using a launch vehicle 6.

The spacecraft 7 with the command compartment 11, the necessary service equipment 12, carries shock blocks 14 in the payload compartment 13 (Figure 3) (in the case of the implementation of the option of including a gamma laser as part of the expedition to the OCT, a block with gamma laser 15) ;.

When the spacecraft approaches the target — OCT, shock blocks 14 (FIG. 4) are alternately released from the payload compartment, which occupy a position on the trajectory in space at a given distance from each other through a given interval L _i . Impact blocks approach the OCT alternately.

By the time of the approach of the first shock unit 14 (Fig. 5), a spacecraft with a gamma laser 10 in near-earth orbit is optically directed to OCT 3 and at a time point coordinated with the movement of the shock blocks 14, the gamma laser 10 is nuclear-pumped and provides laser x-ray radiation 16 on the OCT 3. This effect creates a high-temperature channel 17 of depth h with a flowing stream of a gaseous substance 18 from the OCT. As a result of the reactive force arising from the flow of gaseous and solid OCT 3 products from the channel, the OCT trajectory changes by an angle α ₁ (Figure 5) and the OCT 3 receives a rotation pulse.

Suitable alternate strike blocks are guided into the high-temperature channel using control from the spacecraft 7 and a homing system with an infrared sensor.

Each impact of the impact block 14 No. i on the OCT 3 provides the appearance of a force that changes its trajectory by an angle α ₁ . In addition, the temperature regime supported by these influences in the high-temperature channel provides a constant reactive force of variable magnitude with constant gas formation.

The process is monitored from the spacecraft 7 by determining the change in the OCT motion parameters, for example, by the hodograph of the reactive force from the jet flowing from the high-temperature channel, the thermodynamic state of the process in the high-temperature channel is controlled and control commands are issued to the shock blocks to optimize their trajectory and the impact interval.

Figure 6 shows an embodiment of a method for deflecting OCT using a gamma laser as part of an expedition to OCT. A block with a gamma laser 10 is led first to the OCT 3, maneuvering is performed to take the desired position relative to the OCT, pointing to the desired point on the surface of the OCT includes nuclear pumping of the gamma laser and X-ray radiation creates a high-temperature channel in the OCT. Impact blocks 14 No. i from a set of N pieces are alternately guided into this high-temperature channel.

The total deviation of the OCT trajectory in a given direction is determined by the actual addition of deviations from all influences, as α _∑ = α ₁ + α ₂ + ... + α ₁ + ... + a _N.

Figure 7 shows the moment of exposure to x-ray radiation on the OCT 3 and the formation of a high-temperature channel 17 of depth h, where L is the error of the laser beam, as the deviation of the direct laser beam from the center of mass of the OCT Tsm. As a result, the reactive force F acts on the OCT and creates the OCT rotation moment, where J is the OCT rotation momentum obtained from the action of the reactive force F on the arm h. The concomitant effects of temperature exposure lead to the discharge of surface layers 19.

The first shock block 14 No. 1, using the control from the spacecraft 7 and the homing system, is guided into the obtained high-temperature channel 17 (Fig. 8) after a period of time necessary to create acceptable conditions in the high-temperature channel, taking into account the changing parameters of the OCT 3 motion, including angular velocity OCT rotation - ω.

After the first shock block enters the OCT to the calculated depth g ₁ , detonation of the explosive is carried out. This ensures the creation of a force of action on the OCT to change its trajectory.

ω _i - change in the angular velocity of rotation of the OCT from the influence of the i-th shock block.

The power of explosive charges is selected in the range from the conditions for ensuring the strength of the necessary impact, depending on the mass of the dangerous space body and ensuring the integrity of the dangerous space body until the angle of deviation of the OCT trajectory α _∑ is eliminated, eliminating the risk of collision with the Earth.

The phases of hit of subsequent shock blocks 0 14 No. i-No. N in the OCT are shown in figures 9, 10, where A is the phase of approach and correction of the trajectory of the shock block, B is the hit and detonation of the explosive charge at the corresponding depth gi-gN.

Prevention of premature splitting of a dangerous space body is a condition for ensuring the Earth's safety from collision with large fragments of a dangerous celestial body. The momentum of movement from the hit of the shock block and the reactive force from the ejection of the jet and debris of the OCT change the trajectory of its movement. Impact blocks are brought to the OCT after a period of time necessary for the expansion of the OCT fragments from the high-temperature channel and the exit of the primary gas stream.

The results of the impact on the OCT are monitored by the spacecraft equipment, including optical sensors, the processor, which processes the data and through the communication system, provides the correction of the trajectory of the shock block and the calculation of the trajectory of the next shock block, coordinating the control with the homing system of the shock blocks.

After getting into the high-temperature channel, the explosive charge of the shock block is undermined. This provides the creation of the power of Fi - impact on OCT.

The operation of adjusting the trajectory of the shock unit at the final stage by measuring the specified parameters of the OCT movement after the previous impact and calculating the hardware of the command unit of the spacecraft and homing the shock block to a heat spot in the high-temperature channel on the OCT is repeated for each shock block from the kit.

The number of shock blocks in the set N is determined based on the calculation of the probability of the operation, taking into account possible misses, their destruction in the cloud of debris and the failure of the block systems.

The command unit transmits the results of the impact on the OCT to the Earth and can be used as an additional shock unit, for which it is also equipped with a homing system for a heat spot to enter the crater.

The impact of all shock blocks F ₁ -F _n creates a total force F _∑ , which is defined as the vector sum of these forces.

The reactive forces from the action of laser radiation and each percussion device F _{i are} vectorially summed up and create a total vector F _{∑ of} action on the OCT by changing its trajectory of movement (Figure 11).

The spacecraft is used as a reserve of influence on the OCT and, if necessary, it is sent to the crater, using also as a shock block.

The proposed method can be implemented using several spacecraft carriers of shock blocks. The sequence of their impact on OCT is determined by a single program under centralized management.

With the high-speed impact of shock blocks on the OCT in which the collision energy with the OCT exceeds the internal energy of the explosive and the impact of the shock blocks on the OCT is determined by their passive mass, an embodiment of the design of shock blocks without explosive charges is possible.

The positive effect of the application of the proposed method is to increase the efficiency of exposure to OCT by increasing the channel depth in it using x-ray gamma-ray laser, creating high temperature in this channel and maintaining high-temperature processes in the channel using impact blocks.

The method with creating a high-temperature channel in the OCT provides a reduction in the mass and cost of the project to protect the Earth from OCT through the use of high-precision guidance systems and high-speed computing tools. With this method, the OCT substance is used to the maximum to create a reactive force: the momentum from the outflow of a jet of substance with OCT is added to the direct shock pulse of the shock block. The necessary impact is formed and adjusted in real time.

This method provides an increase in the reliability of changing the trajectory of a dangerous space impact, expands the possibilities for the mass of deflected dangerous bodies or their successful destruction.

The implementation of the proposed method reduces the risk of falling to Earth as OCT, and its fragments, which is a socio-economic effect.

Claims (2)

1. A method of changing the trajectory of a dangerous space body using a spacecraft carrying shock blocks delivered to a dangerous space body and a spacecraft with a gamma laser in near-Earth orbit with X-ray pointing to a dangerous space body, characterized in that the shock blocks before approaching to a dangerous space body, they are alternately released and positioned in space for sequential exposure to a dangerous space body when they are guided using the system the guidance in the high-temperature channel of a dangerous space body, which is obtained as a result of the action of x-ray radiation on a dangerous space body using x-ray radiation from a gamma laser from near-Earth orbit at a point in time that is consistent with the movement of the shock blocks, and from the spacecraft control the guidance of the shock blocks into the high-temperature channel and control of the results of sequential exposure to a dangerous cosmic body. 2. A method for changing the motion path of a dangerous space body using a spacecraft delivered to the dangerous space body carrying shock blocks and a block with a gamma laser, characterized in that the block with a gamma laser and shock blocks are alternately released before approaching the dangerous space body and positioned in space for sequential exposure to a dangerous space body when pointing them with the help of a homing system into the high-temperature channel of a dangerous space body, which receives They are emitted as a result of exposure to x-ray radiation by a gamma laser from a minimum distance at a point in time that is consistent with the movement of the shock blocks, and from the spacecraft, the guidance of the shock blocks into the channel and the control of the results of successive exposure to a dangerous space body are controlled.

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