RU2546025C1 - Method of gas-dynamic action on dangerous space body and device for its implementation - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to cosmonautics and can be used for protection of the Earth against dangerous space objects (SO). Space vehicle (SV) with an explosive charge for gas-dynamic action on a dangerous SO includes primary explosive charge, a compartment with released blocks with additional explosive charge, a control system, a self-guidance system, movement and orientation units, a detonation system of the primary explosive charge, a time synchronisation unit, receiving-and-transmitting equipment of communication with blocks with additional explosive charge and a release and build-up programme of blocks with additional explosive charges to formation around SV. Blocks with additional explosive charge include a control system with a programme with relative coordinates of the block with additional explosive charge to formations and detonation time of additional explosive charge relative to detonation moment of the primary explosive charge. SV is brought to SO with released blocks with explosive charges, which are positioned in outer space, from SV with the primary explosive charge, prior to approach to dangerous SO, there released are blocks with additional explosive charge, blocks are positioned in outer space in the form of the specified spatial formation, coordinated detonation of the primary explosive charge of SV and additional explosive charges of blocks is performed, a high-temperature cumulative jet directed to the dangerous SO is formed in a cloud of explosion of the primary explosive charge.

EFFECT: invention allows increasing protection of the Earth against dangerous SO.

2 cl, 14 dwg

Description

This invention relates to the field of application of space technology to ensure the safety of the Earth in the event of a 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 extreme cases, its destruction is being fulfilled.

There are various methods of influencing OCT in order to change their trajectory or destruction.

In accordance with US patent 6726153 BA, 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 proposed 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 rejecting 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, RSC Energia im. S.P. Queen". 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 jet thrust from the jet flowing from the comet's surface.

Analogs of the invention are technical solutions using an explosion, preferably nuclear or thermonuclear, at a short distance in front of a dangerous space body.

The analysis showed that the disadvantage of this solution is the insufficient contribution to the impact on the OCT of the explosive wave factor under the conditions of the vacuum of outer space and during the formation of a spherical explosion cloud.

A known method of deflecting a dangerous space body according to patent RU 2369533 "Method of changing the trajectory of a dangerous space body and device for its implementation."

This method of changing the trajectory of the natural space body and the device for its implementation consist in the fact 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 blocks 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 using the command compartment processor and homing system at 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 disadvantages of the known invention are high technical and technological requirements for the design and equipment of the shock block performing penetration, i.e. penetration into the depths of a dangerous cosmic body. The body of the shock block requires special high-strength materials. High reliability requirements are imposed on the device for providing detonation of an explosive at the required time.

The invention according to patent RU 2369533 is selected as a prototype.

The aim of the invention is to increase the efficiency of exposure to a dangerous space body while reducing costs to change its trajectory.

The invention consists in positioning a spacecraft (leader) with a main explosive charge and surrounding spacecraft blocks with additional explosive charges in outer space in a spatial formation to realize consistent detonation of explosive charges, the main and additional, in such a way as to effectively form the front of the main blast wave explosive charge to obtain a high-temperature cumulative jet directed at a dangerous cosmic body.

The method of gas-dynamic impact on a dangerous space body with a charge of explosive delivered to it by a spacecraft with blocks with additional charges of explosives being released before approaching a dangerous space body is that the blocks released before approaches to a dangerous space body are positioned with an additional explosive charge in outer space in the form of a given spatial formation, for example, along the generatrices of a cylindrical surface whose axis n passes through the center of the main charge and is directed at the dangerous cosmic body, and at a distance of effective impact on the dangerous cosmic body, the detonation of explosive charges of the main charge of the spacecraft and additional charges of the blocks is coordinated detonating, forming a cumulative jet directed at the dangerous space body in the explosion cloud of the main charge .

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 launched onto the trajectory of meeting with the OCT. The impact on the OCT is carried out using a spacecraft having the necessary service systems and the main explosive charge carrying a set of blocks with additional explosive charges, which, when approaching the OCT, are positioned in outer space in the form of a given spatial formation, for example, along the generatrices of a cylindrical surface, the axis of which passes through the center of the main explosive charge, and at a distance of effective action on the OCT, consistent detonation is performed explosives of the main charge of the spacecraft and additional charges of explosive blocks, forming in the cloud of the explosion of the main charge a high-temperature cumulative gas-dynamic jet directed to the OCT.

The action of a gas-dynamic jet creates a momentum of force that changes the trajectory of the OCT to a level that excludes dangerous proximity to the Earth.

The implementation of the method is carried out using the spacecraft grouping delivered to the OCT or a single device made in the form of a spacecraft. In this case, the spacecraft contains the main explosive charge and a compartment with produced additional charge units equipped with communication systems and mutual accurate positioning in outer space based on equipment for exchanging navigation signals, measuring the mutual coordinates for installing additional charge units with the orientation system in the spatial configuration defined the control system program, and the system of coordinated detonation of the main charge and additional charges of the block from the device using time synchronization.

The principal feature of the formation’s group flight (formation - from Formation Flying) is the autonomous navigation of an individual device within the group and the management of their relative position in the group.

In order to ensure the formation of the spacecraft formation, in addition to the information support requirements for single missions, requirements are imposed on the information support for controlling the relative motion of the spacecraft in the group. These requirements are imposed on all three main types of information support: ballistic-navigational, command-software and information-telemetric. (Zaramensky Irina Evgenievna. The use of uniaxial control to maintain a relative trajectory in the satellite formation: the dissertation of the candidate of physical and mathematical sciences. Moscow, 2009, IPM named after MV Keldysh, RSL OD, 6109-1 / 1035).

An example of the formation of a formation in which the distance between spacecraft remains unchanged is the configuration of the LISA (Laser Interferometer Space Antenna) mission. In this mission, changes in the distance between spacecraft when moving around the Sun are minimized (Cosmos-magazine. Cosmos-jornal.ru. Satellite formations. V.S. Ivanov, IPM named after M.V. Keldysh. 06/13/2013).

The invention is illustrated by the following graphic materials:

figure 1 - delivery of the spacecraft to the OCT, pointing to the center of mass of the OCT, building a block formation and detonation of explosives;

figure 2 is a design diagram of gas-dynamic effects on OCT;

figure 3 - diagram of a spacecraft with the main explosive charge and compartment blocks with an additional explosive charge;

4 is a block diagram of a spacecraft with a main explosive charge;

5 is a block diagram with an additional explosive charge;

6 is a block diagram of a block with an additional explosive charge;

Fig.7 is the release of blocks with an additional explosive charge from the spacecraft compartment;

Fig. 8 shows the construction of a block formation with an additional explosive charge around the spacecraft;

Fig.9 - consistent detonation of the main explosive charge and additional explosive charges;

figure 10 - the impact of the high-temperature cumulative jet on the OCT;

11 - the impact of the front of the blast wave on the OCT;

Fig - reactive force from the products of the outflow from the crater on the OCT;

Fig - construction of the formation of blocks with additional explosive charges in the form of a cone (option);

Fig - construction of the formation of blocks with additional explosive charges in the form of a sphere (option).

Implementation of the proposed method is as follows.

After performing supporting operations on reconnaissance of the OCT parameters (its ballistic characteristics, composition and properties of the OCT substance, etc.) using ground-based infrastructure and the space segment, astronomical research, space reconnaissance directed to the OCT, and the necessary ballistic and technological preparation of the launch vehicle with it is used to deliver a spacecraft 1 (Fig. 1) with an explosive charge to change the trajectory of the OCT 2. The spacecraft is equipped with blocks 3 with additional explosive charges having their own navigational installations with a reserve of fuel components necessary for providing office communication systems, control.

When spacecraft 1 approaches OCT 2 (stage A), blocks 3 with additional explosive charges (stage B) are released from the spacecraft to the center of mass of Tsm OCT; they use their own propulsion systems and use strictly defined systems positions relative to each other - create formation 4 around the spacecraft with the main explosive charge in accordance with the program embedded in the onboard control system (step C).

Formation 4 of the spacecraft with the main explosive charge 1 and blocks 3 with additional explosive charges is united by a single spatial configuration using a system for maintaining the relative relative position of the formation participants using mutual navigation signals and connected by a synchronized single high-precision time reference system.

The spatial configuration of the formation is supported by each unit participating in the formation with additional explosive charges, which preserves the given spatial position using motion engines and block orientation system engines.

The options for constructing the formation are axisymmetric and can be based on various geometric surfaces: spherical, cylindrical, conical, etc.

When the formation approaches the OCT at the effective impact distance, a coordinated detonation of the main explosive charge 5 and all additional explosive charges 6 is carried out (stage D).

As a result of the formation of the total blast wave 7 of the explosion cloud, a high-temperature cumulative jet 8 is formed that acts on the OCT and forms a crater 9 with the subsequent outflow of a heated OCT substance from the crater.

This achieves a change in the trajectory of 10 OCT 2.

The detonation time of the main explosive charge T _o is determined as the moment of reaching the calculated distance to the OCT, which is determined from the conditions for obtaining a force pulse that is optimal for acting on the OCT.

The optimal effect on the OCT is determined from the conditions for creating the maximum pressure and temperature of the gas flow at the surface of the OCT in relation to the size of the area of the active effect of this flow on the OCT.

The calculated scheme of gas-dynamic effects on OCT is shown in figure 2,

where W is the detonation point of the main explosive charge;

L is the distance from the explosion to the center of mass of the OCT;

R is the radius of the OCT;

h is the distance from the detonation point of the main explosive charge to the surface of the OCT;

N is the projection onto the vertical axis of the force acting on the surface element of the OCT;

r is the distance from the point of explosion to the surface element dS OCT.

The total momentum I _Σ1 acting on the surface of the OCT is

Here S ₀ - part of the surface of the OCT, subjected to gas-dynamic effects;

ρ is the pressure of the gas stream;

u _ol - the projection of the gas flow velocity in the direction from the point of explosion to the center of mass Tsm OCT.

The solution to the optimization problem I _Σ1 allows us to go over to geometric aspect ratios with optimal effects on OCT. In particular, one of the options for the search calculation showed that the greatest effect of gas-dynamic effects is achieved when the ratio h / R = 0.1.

The detonation time of each additional explosive charge is defined as the shift ΔT = T _o -T _i and from the detonation time of the main explosive charge T _o (T _i is the delay or the advance of the detonation time of the additional explosive charge of the i-th block) and set i- in the control system program block in accordance with the plan for the formation of the surface of the total blast wave.

As a result, using the action of the total blast wave in the cloud of the main charge explosion, a high-temperature cumulative jet is formed, aimed at the center of mass of the CM OCT.

The impact of a high-temperature cumulative jet on the OCT creates a momentum of force sufficient to change the trajectory of the OCT until the threat of its collision with the Earth is eliminated.

To implement the proposed method, a device is used in the form of a spacecraft 1 (Fig. 3), which is equipped with the necessary service systems for functioning, movement, communication, control and contains the main explosive charge 5 with a detonation device for this charge 11, highly accurate in time. The spacecraft 1 has a compartment 12 with blocks 3 of an additional charge BB 6, having an exhaust system 13 of these blocks. The number of blocks 3 with an additional explosive charge is determined in accordance with a variant of the chosen formation for constructing these blocks and their layout. The spacecraft is equipped with motion systems 14, homing 15, power supply with solar panels 16, orientation 17, transceiver communications equipment 18, service supporting systems 19, on-board control system 20.

With the development of small satellite technology, it became possible to form a group of satellites moving at a small distance from each other and solving a single problem.

Figure 4 shows a simplified block diagram of the device of the spacecraft with the main explosive charge (leader), which has a compartment I of the navigation system, compartment II of storage and release of blocks 3 with an additional explosive charge, compartment III of the main explosive charge and detonation system, compartment IV control systems and transceiver communications equipment, compartment V movement and orientation.

The homing system 15 is electrically connected with the on-board control system 20 and provides a solution to the problem of determining the distance L to the OCT, optimal for obtaining the maximum impulse of impact on the OCT during detonation of explosive charges.

The on-board control system 17 is electrically connected with the exhaust system of the blocks 3, ensures the timely release of these blocks and their construction into the formation, then, according to the calculated distance L to the OCT, sets the time T _about detonation of the main charge of explosive 5, the value of which is via the communication channel, including the transceiver communication equipment 18, conversion unit 21, antenna 22, is transmitted to each block 3 with an additional explosive charge in the formation.

The on-board control system 20 is electrically connected to the detonation system 11 of the main explosive charge 5 and brings it into operation at time point T _o .

The time synchronization system of processes is equipped with a reference time block 23, which corrects the time errors of the equipment to the required accuracy.

Each block 3 (Fig. 5) of additional explosive charges 6 is unified in design and equipped with the following systems: providing movement in outer space 24, orientation 25 and maintaining a mutual spatial coordinated position in the formation, communication 26, control 27 and high-precision time synchronization, additional detonation 28 charge BB 6, service systems 29 ensure the functioning of block 3.

Figure 6 shows a simplified block diagram of block 3 with an additional charge of explosive 6. On-board control system 27 is connected to the communication system 26 with the spacecraft leader and solves the problem of mutual navigation of formation participants using the motion support system 24 and orientation 25, then includes a system detonation of 28 additional explosive charge 6.

Figure 7 shows the release of blocks 3 with an additional explosive charge 6 from the compartment 12 of spacecraft 1. Each block 3 includes the engines of the motion support system and, in accordance with the navigation signals, occupies and maintains its relative spatial position in the formation.

On Fig shows an example of building a formation of blocks 3 with an additional explosive charge 6 around the spacecraft 1 along the generatrices of a cylindrical surface, the axial line of which passes through the centers of the main charge and the center of mass CM OCT 2. The position of the block 30 with an additional explosive charge on the axial line forms the surface of the blast wave of the main charge in the rear hemisphere.

Figure 9 shows the moment of coordinated detonation of the main explosive charge of the spacecraft 1, additional explosive charges of blocks 3 and the formation of the total blast wave 8. As a result of the difference in the time of charge detonation in the formed cloud, a directed high-temperature cumulative jet of gaseous explosion products 7 directed to the center appears mass CM OCT 2.

The result of gas-dynamic effects on a dangerous space body according to the proposed method and the use of a device to implement this method provides the following factors aimed at changing the trajectory of the OCT 2.

1. The impact on OCT 2 with a high-temperature cumulative jet 7 from the front of the blast wave 8 (Fig. 10), after detonation of explosive charges, when interacting with the OCT 2 substance, creates a force F ₁ directed to the center of mass of the CM OCT 2, which changes the trajectory of the OCT.

Calculation of the force during the process simulation is based on a gas-dynamic description of the interaction of gas flows of a high-temperature cumulative jet and vapor from OCT.

2. The impact on the OCT (Fig. 11) of the front of the total blast wave 8 on the surface of the OCT 2, suitable after the cumulative jet, creates a force F ₂ .

Calculation of the arising force in the process simulation is performed by integrating the pressure of the blast wave on the surface sections of the OCT. In the total impact, there is a force vector aimed at changing the trajectory of the OCT.

3. As a result of exposure to a high-temperature cumulative jet on OCT 2 (Fig. 12), a crater 9 with a heated OCT substance arises. The gas jet 31 flowing from the crater 9 creates a reactive force F ₃ , which is additionally involved in changing the trajectory of the OCT. The parameters of the gas jet emitted from the OCT are determined by the composition of the OCT substance and the energy characteristics of the acting cumulative jet.

When choosing options for constructing block formations with additional charges for the selected type and mass of explosives, they solve the problem of choosing the relative coordinates for each element of the formation and calculating the detonation start time for each element of the formation. The ultimate goal of the optimization calculation is to obtain the maximum share of the contribution of explosive energy to the production of a cumulative jet as the most effective factor in influencing OCT.

In this case, options are used to build formations based on building the configuration of blocks 3 with additional charges along the generatrices of the conical surface (Fig. 13), forming a spherical surface (Fig. 14) (or other surfaces: parabolic, hyperbolic, etc.).

The technical result of the use of the invention is:

improving the impact on OCT due to:

increasing the degree of utilization of the energy of the main charge during the gas-dynamic effect on the OCT during the formation of a high-temperature cumulative jet of products of the explosive wave of the main charge directed to the OCT;

reducing requirements from the design of additional units and equipment for providing detonation of explosive compared with the option of impact in the depth of the OCT;

the integral impact on the OCT of the three phases of the explosive process - the impact of the high-temperature cumulative jet, the front of the total blast wave, the effect of the gas jet flowing from the high-temperature crater on the OCT after gas-dynamic impact, which ensures the creation of an effective effect for the necessary change in the path of the OCT.

Claims (2)

1. The method of gas-dynamic impact on a dangerous space body with a charge of explosive delivered to it by a spacecraft with blocks released before approaching the dangerous space body and placed in outer space with explosive charges, characterized in that from a spacecraft with the main explosive charge before approaching a dangerous space body release blocks with an additional explosive charge, position them in outer space in the form of a rear spatial formation, for example, along the generatrices of a cylindrical surface, the axis of which passes through the center of the main charge and is directed to a dangerous cosmic body, and at a distance of effective influence on the dangerous cosmic body, a coordinated detonation of the main explosive charge of the spacecraft and additional explosive charges of the blocks is produced, forming in the cloud of the explosion of the main explosive charge, a high-temperature cumulative jet directed at a dangerous space ate. 2. The device of a spacecraft with a charge of explosive to implement a method of gas-dynamic impact on a dangerous space body using released blocks, characterized in that the spacecraft contains the main charge of the explosive, a compartment with the released blocks with an additional charge of explosive, and the spacecraft is equipped with a system control electrically connected to the homing system, the unit of movement and orientation, the detonation system of the main explosive charge the unit, the time synchronization unit, transceiver communication equipment with blocks with an additional explosive charge, which contains a program for the release and construction of blocks with additional explosive charges into the formation around the spacecraft, and the blocks with an additional explosive charge are equipped with a control system associated with transmitting and receiving communication equipment, a block of movement and orientation, and a detonation system of an additional explosive charge, and in On the board, the relative coordinates of the block with the additional explosive charge in the formation and the detonation time of the additional explosive charge relative to the moment of detonation of the main explosive charge are introduced.

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