RU2369533C1 - Method of changing motion trajectory of dangerous cosmic body and device to this end - Google Patents

Abstract

FIELD: physics.

SUBSTANCE: after detection of a dangerous body, a spacecraft is launched towards the body, carrying a set of striking units with explosive charge. The first unit is fitted with penetration apparatus. When approaching the dangerous body, the striking units are successively released from the spacecraft and positioned in space in required intervals. The first unit is directed at the target point on the surface of the body, into which it penetrates at a given depth. The explosive charge then explodes, resulting in formation of a crater. The next striking unit is directed at the crater, while adjusting its trajectory using results of the first impact. After fly-off of fragments, the block is directed onto the thermal spot of the crater using the processor of the command module of the spacecraft and a homing system. The next striking units are similarly adjusted using results of previous impacts. Not only is the movement of striking units controlled from the command module, but results of striking and change of movement of the dangerous cosmic body as well. After sending results of the operation to the Earth, the spacecraft can be used as striking unit to be directed into the crater on the surface of the dangerous body.

EFFECT: more efficient impact on a dangerous cosmic body, while reducing expenses on changing its trajectory.

2 cl, 10 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, meteor) or the passage of this body in unacceptable proximity.

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.

In accordance with US Pat. No. 6,726,153 VA, 2003, 7 B64G 1/64, NKI 244-158, 244-168 “Photon spacecraft for changing the orbits of asteroids, meteors and comets,” Campbell Jonathan W., NASA proposes to dock the spacecraft with Using a loop in the form of a dangerous asteroid, meteor, comet or other space object, pull the spacecraft and deploy a photonic device - a reflector filled with foam to use the pressure of sunlight to change the orbit of a dangerous object.

To combat asteroids, it was proposed to detonate them with a thermonuclear charge, displace it with a gravitational shift, strike with a heavy blank, and use laser radiation. In the case of impact destruction of the asteroid, there is a possibility that the fragments due to mutual attraction will have time to come together again.

A known method of deflecting dangerous comets from the trajectory of a collision with the Earth according to patent RU 0002266240 C2, 2003, 7 B64G 1/00. A.A. Maslennikov of RSC Energia im. S.P. Korolev. " In this method, the comet is exposed to the thermal effect of a nuclear energy source after cleaning the surface of the comet’s nucleus with several nuclear explosions at the pole from the rotation of the comet. A spacecraft with a nuclear power plant is planted on a cleaned surface to heat the comet's nucleus and create reactive thrust from the jet of the comet flowing from the surface.

In the case of using a heavy blank, it is necessary to launch an overly heavy spacecraft from the Earth.

There is an offer of astronomers from the French Space Research Center (CNES) to shoot down asteroids that threaten the Earth with other celestial bodies. For this, an asteroid of appropriate sizes is used, which is delivered to one of the five Lagrangian points. Before approaching a dangerous object from the outside, the “attached” asteroid is unbalanced so that its trajectory intersects with the dangerous cosmic body.

As a prototype of the present invention, the option of changing the trajectory of a dangerous space body by striking it with a spacecraft with an explosive is selected. Calculations for the implementation of this option are published in sources [1, 2, 3].

The disadvantage of this option is the need to use a significant power charge, in which a large fraction of the energy is spent not on changing the target’s trajectory, but on its destruction, in which the trajectories of the fragments are unpredictable.

The aim of this invention is to increase the effectiveness of exposure to a dangerous space body while reducing costs to change its trajectory. This is achieved by the use of high-precision guidance and use of the capabilities of computer technology and communication systems.

According to the proposed method, after determining the trajectory and characteristics of the OCT by known ground methods and using small reconnaissance spacecraft, a launch rocket is launched and a spacecraft with a program of impact on the OCT is brought into the trajectory of meeting with the OCT. The impact on the OCT is carried out using a spacecraft with a command compartment and a set of shock blocks, which, when approaching the OCT, are positioned in space at a given interval and point to a given point on the surface of the OCT, so that the trajectory of the shock block passes through the center of mass of the OCT along the direction vector optimal shift of the trajectory of the OCT.

The impact on the OCT is carried out by a set of shock blocks alternately with a given time interval.

The first block is equipped with a penetration system to penetrate the required depth into the asteroid, where it undermines its charge, which creates a crater or cavity in the asteroid in a shape that optimizes the creation of a jet stream, changes the path of the asteroid, in addition, ejected OCT fragments increase the effect of creating reactive force.

The penetration device includes a thickened block body and its shape, providing movement in a solid medium to the required depth.

Subsequent shock blocks are pointed at the crater using a heat spot guidance system in the crater and command commands from the command block.

The positive qualities of this method of impact on OCT are that the physical effect of a series of precise impacts provides a more significant result than a one-time effect, in which the majority of the explosion energy is dispersed in space, the fraction of the explosion energy that gets on the OCT is used inefficiently, and the process OCT destruction cannot be controlled.

The use of high-precision guidance tools using knowledge of the properties of the material of the asteroid and the characteristics of its movement allows you to create a crater in the OCT (cavity), the shape of which will optimize the use of the energy of explosive charges, and the process of exposure to a series of strokes is controlled and controlled by the command apparatus.

The command compartment of the spacecraft is equipped with an onboard control system, a processor, which 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 fault, premature destruction of the target, the need to take into account the increase in rotation of the dangerous space body as a result of impact error 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. So the last block can be equipped with a charge of increased power in order to be able to implement various options for exposure, for example, the destructive effect on the asteroid with insufficient amount of removal of the asteroid from orbit or impact on the broken off piece of the asteroid.

The invention is illustrated by drawings:

Figure 1 - the conclusion of the spacecraft;

Figure 2 - transition to the trajectory of a meeting with a dangerous space body;

Figure 3 - diagram of the device of the spacecraft;

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

5 is a diagram of the movement of the shock blocks in the final section;

6 is a diagram of the force effect on the OCT;

Fig.7 - hit the first shock block;

Fig - hit the second shock block;

Fig.9 - hit the i-th shock block;

Figure 10 - hit the n-th shock block.

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

Using (Figure 1) astronomical optical 1 and radio 2 means determine the motion parameters of the OCT 3 and the characteristics of its composition (content of substances, their structure). It is possible to use reconnaissance spacecraft 4 for these purposes.

Using known launch vehicles 5 (FIG. 2), the spacecraft 6 is put into orbit and, using the booster stage 7, is 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 8.

The spacecraft is equipped with a command compartment, a payload compartment containing shock blocks 9 (Figure 3).

When approaching the target, shock blocks 9 are released alternately from the carrier compartment (FIG. 4), which occupy a position in space at a predetermined distance from each other after a predetermined interval on the motion path to the OCT. Impact blocks approach the OCT alternately and as a result of each hit and detonation of the explosive charge, the OCT trajectory changes by an angle α _I (Figure 5). The total deviation of the OCT trajectory is determined by vector addition as α _∑ = α ₁ + α ₂ + α _I + α _N.

The first shock block is equipped with a penetrator 10 for penetrating a dangerous space body to the required depth.

The first shock block is pointed at the aiming point T (Fig. 6) on the surface of the OCT so that the trajectory of the first shock block passes through the center of mass of the target C _M in the direction of the vector of the necessary effect on the OCT.

ω is the angular velocity of rotation of the OCT.

After the first shock block enters the OCT to the calculated depth h, 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 condition of ensuring the strength of the required 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 shock blocks 9 No. 1-9 No. N in the OCT are shown in Figs. 7-10, 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.

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 shock impulse of movement from hitting the first block and the reactive force from the ejection of the jet and debris of the target change the trajectory of the target. The second strike block approaches the target after a period of time necessary for the debris from the target and the gas stream to fly from the crater.

The results of the impact on the OCT are monitored by the spacecraft equipment, including optical sensors, the processor that processes the data, and through the communication system provide the correction of the trajectory of the second shock block, so that the second shock block, using the homing system on the heat spot, enters the crater made the first shock block. After falling into the crater, the explosive charge of the second block is undermined. This provides the creation of force F ₂ - impact on the OCT. The shock impulse of movement from the hit of the second block and the reactive force from the ejection of the jet and debris from the crater (cavity) change the trajectory of the OCT.

The results of the impact on the OCT are monitored by the equipment of the command compartment of the spacecraft and through the communication system provide the correction of the trajectory of the third shock block, so that the third shock block, using the homing system on the heat spot, enters the crater and after the detonation of the explosive created a force F ₃ .

The operation of adjusting the trajectory of the shock block at the final stage by measuring the specified OCT motion parameters after the previous shock and calculating the equipment of the command block of the spacecraft and homing the shock block to a heat spot in a crater on a dangerous space body is repeated for each shock block from the kit.

The number of shock blocks in the kit 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.

A device for implementing the proposed method for changing the trajectory of a dangerous space body (option) is shown in the diagram of Fig. 4, where in the housing 11 of the spacecraft 6 there are provided on-board systems: a monitoring and targeting processor 12 with optical sensors 13, orientation engines 14 and motion 15 with cylinders of the working fluid 16 of radio communication with the earth control center and with shock blocks 17, the command compartment 18, the necessary service systems (temperature control, power supply, etc.)

The compartment with the shock blocks located in it has a device for fastening the shock blocks 19 and their release with hatches and covers 20.

The explosive charge compartment 21 is equipped with a detonation system.

The shock blocks have a homing system with optical sensors 22 in the infrared range and a control system from the processor and through a communication system with the command unit of the spacecraft 23. All shock blocks are equipped with a movement compartment with cylinders of the working fluid.

The first shock block is equipped with a penetration device, its shape and dimensions and the strength characteristics of the body are calculated from the conditions of motion in a solid medium for penetration into the OCT to the estimated depth h.

An example of using the device to implement the proposed method (option).

According to the results of determining the motion parameters and characteristics of the OCT, the device is equipped with a set for implementing the proposed method. The number of shock blocks, the size and volume of explosive charges, the layout of the command spacecraft-carrier of the shock blocks are selected, a program of impact on the OCT is made, and it is introduced into the onboard processor of the spacecraft.

The device is brought out in a known manner to near-Earth transitional orbit and transferred from it to the trajectory of the meeting with the OCT from a given direction.

The normal flight mode is provided by a complex of onboard systems of the spacecraft, based on well-known technical solutions.

When approaching the calculated distance to the OCT, the spacecraft opens the shutters 20, releases the first shock block 9 No. 1, and alternately through the time interval all the other 9 No. 2-9 No. N.

Blocks include propulsion systems and to clarify the positioning in the chain of building shock blocks. The spacecraft continues to close in the chain and maintains control communication with the shock blocks through radio communication systems

At the stage of approach to OCT with the help of optical sensors and the onboard processor of the spacecraft, the aiming point on the surface of the OCT is refined from the condition for determining the total vector of the optimal impact on the OCT, providing the necessary deviation of its trajectory. The direction vector of the movement of the first shock block at the aiming point should pass through the center of mass of the OCT in the direction of the specified action along the shift of the trajectory of the OCT.

In accordance with the data obtained in the direction of impact, the first strike unit performs a refinement maneuver and is guided on the OCT independently using a homing system.

The first shock block when it enters the OCT is separated, the service systems are destroyed on the surface, and the block with the explosive charge continues to move in the solid OCT medium until the specified depth is reached, where the detonation system initiates the explosive.

As a result of the explosion of explosives in the OCT environment, a crater or cavity is created with the release of gases and fragments and debris. Reactive ejection force creates a momentum of movement necessary to change the trajectory of the OCT.

The second shock block approaches the OCT after the time interval necessary for the fragments to disperse and the gas stream to escape, but no later than the crater cools from the explosion energy, receives data from the processor of the spacecraft, performs a refinement maneuver, and enters the crater obtained from the impact of the first shock block, detonation system initiates explosives. The reactive force of the ejection of gases, fragments and debris from the crater creates a second impulse of movement necessary to change the trajectory of the OCT.

The third and subsequent shock blocks perform similar actions, receiving clarifying data on the OCT situation from the processor of the spacecraft.

The reactive forces from the impact of each percussion device F _{i are} vectorially summed up and create the total vector F _{∑ of the} impact on the OCT by changing its trajectory of movement (Figure 6).

The spacecraft is used as a reserve of influence on the OCT and, if necessary, 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 and device is to increase the impact on OCT, reduce the mass and cost of the project through the use of high-precision guidance systems and high-speed computing tools. In this method, OCT substance is used to create 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.

The risk of large debris falling to the Earth from the affected OCT is reduced compared to the technical solution of the prototype.

Literature

1. Ivashkin VV, Smirnov VV Qualitative analysis of some asteroid hazard reduction methods. - Astronomical Bulletin. 1993. Vol. 27. No. 6. S.46-54.

2. Akhmetshin RZ, Ivashkin VV, Smirnov VV Analysis of the possibility of reducing the asteroid hazard for the Earth by the impact of the spacecraft. - Astronomical Bulletin. 1994.V. 28. No. 1 S.13-20.

3. Ivashkin VV, Zaitsev A.V. Analysis of the possibility of changing the orbit of an asteroid approaching the Earth by the impact of the spacecraft. - Space research. 1999.V. 37. Number 4. S.405-416.

4. Ivashkin V.V., Zaitsev A.V., Baum F.I. Analysis of optimal two-pulse flights of a spacecraft to an asteroid approaching the Earth. - M. Institute of Applied Mathematics. M.V. Keldysh RAS. 1999. Preprint No. 34.

5. Ivashkin V.A. Analysis of the possibility of using laser exposure on a celestial body approaching the Earth. - M. Institute of Applied Mathematics. M.V. Keldysh RAS. 2003. Preprint No. 89.

6. Ivashkin V.V., Baum F.I. Investigation of the gravitational maneuver near the Moon for the flight of a spacecraft to an asteroid approaching the Earth. - M. Institute of Applied Mathematics. M.V. Keldysh RAS. 2000. Preprint No. 97.

Claims (2)

1. The method of changing the trajectory of a dangerous space body by impact on its surface of an explosive delivered to a dangerous space body by a spacecraft using guidance aids, characterized in that the delivery of explosive is carried out by a spacecraft in shock blocks, which are alternately released from the spacecraft position in space when approaching a dangerous space body and alternately act on a dangerous space body at a point on its surface, corresponding to the passage of the trajectory of the shock block through the center of mass of the dangerous space body, while the explosive of the first shock block is blown up after it is deepened into the dangerous space body as a result of penetration, and the rest of the shock blocks are alternately directed to the resulting crater, in which they undermine their explosives, moreover, with the help of a spacecraft, they monitor the results of the specified exposure to a dangerous space body, adjust the traffic Ktorov shock blocks at the final stage of their motion transmission to earth information on the dangerous effect on the outer body, and then, if necessary, use the spacecraft to a dangerous impact on the outer body. 2. A device for implementing the method of changing the motion path of a dangerous space body, consisting of a spacecraft equipped with an onboard control system with a processor, communication systems, orientation, movement, homing, service systems, explosive charges and systems for their detonation, characterized in that the spacecraft has a compartment with shock blocks located in it, and this compartment is equipped with an ejection device for shock blocks, each of which is equipped with a communication system with space app with a homing system, homing system, orientation and movement system, fuel tanks, explosive charge and its detonation system, while the shape and material of the body of the first strike unit ensure its penetration into a dangerous space body to a given depth, and the spacecraft is equipped with a command compartment where it is located processor, optical sensors, communication system with shock units and homing system.

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