SU1764524A3 - Method of determining sign of phase difference of two sinusoidal signals - Google Patents

Abstract

A space module for disposal of radioactive waste comprises a transportation stage (1) and a detachable emergency rescue stage (2) between which is located a protective screen (19) connected with them with the possibility of separation from one of the stages. The casing (11) of the detachable stage (2) is hollow and open on the side of the protective screen (19) and is mounted on the said screen (19) by its open part so as to form, together with it, a sealed cavity (21) for placing in it the container (5) with radioactive waste. The detachable stage (2) is provided with a system (18) intended for active cooling of the container and comprising reservoirs (49) with a cooling agent interconnected to each other and located in an annular gap between the container (5) and the casing (11), as well as fueling (51) and drainage (52) units. One of the reservoirs (49) has an outlet valve (53) provided with a nozzle (54). <IMAGE>

Description

one

(21) 5005850/25

(22) 10/30/91.

(46) 09/23/92. Bul No. 35

(76) Yu.A. Bakanov, Yu., V. Bryzhinsky,

V.V.Ivanik, V.G.Kinelev, E.V.Oblonsky,

A.D.Parashin, V.F.Suranov, A.M. Khabarov,

B.V. Shagov and I.A.Klepikov

(56) Atomic technology abroad. № 4, April 1991, p. 8-15.

Atomic Engineering Abroad, No. 5, May, 1990, p. 35-37.

Astronautics and aeronautics, 1980, IV, v.18, p.26-35.

(54) SPACE MODULE FOR BURIAL OF RADIOACTIVE WASTES

(57) Uses: space disposal of radioactive waste. SUMMARY OF THE INVENTION: A space module for the disposal of radioactive waste comprises a transport stage and a separable emergency rescue stage, between which a protective shield is connected, connected with them, with the possibility of separation from one of the stages. The casing of the detachable stage is made hollow and open on the side of the protective screen and is installed on this screen with its open part, forming together with it a sealed cavity for placing a container with radioactive waste in it. The separable stage is equipped with a system of active cooling of the container, containing refrigerant tanks, interconnected and placed in the annular gap between the container and the housing, and the filling and drainage units. One of the tanks is equipped with an exhaust valve equipped with a nozzle. 13 il.

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The invention relates to protection against radioactive radiation by dumping radioactive waste of various origins in the space module.

In connection with the expansion of the use of nuclear power plants and devices with radioactive isotopes, the amount of radioactive waste increases, the elimination of which is a big problem.

Protection against radioactive radiation by dumping waste in the Earth, the ocean is widespread. For example, low-level liquid and gaseous wastes are dumped into open water bodies or sea currents or released into the atmosphere after they are first diluted with water or air.

Industrial radioactive waste with medium and high specific activity is pre-concentrated, and then placed in special sealed containers for long-term storage in stable geological formations at a depth of 2 km, for example, in salt mines. Sealed containers are made of stainless steel in the form of cylindrical canisters with a diameter of 0.61 m and a length of 3 m with a hollow mass of up to 350 kg, residual heat generation of waste from 60 to 150 kW, dose rates on the surface of the canister up to 40 Gy / h.

However, this method of disposal of radioactive waste does not exclude the possibility of

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their impact on the Earth’s biosphere during long-term storage requires significant costs for the construction and operation of underground storage facilities; reliable (for hundreds of thousands of years) disposal of radioactive wastes with high specific activity that generate more heat is not ensured, which leads to heating surrounding rocks and containers. Reheating can lead to a violation of the tightness of the containers and even to their destruction, which is unsafe for the environment.

Sealed Castor-type containers for transporting radioactive waste in the form of a hollow thick-walled cylinder with cooling fins on its outer surface are known. The moderator rods are installed in the wall of the cylinder (neutron protection). The ends of the containers are closed with lids on which dampers are installed. Inside the cylinder, there are aluminum segments with channels for capsules with waste. The segments are rigidly connected to the container body. The mass of the loaded container is up to 110 tons, the length is 5.8 m, the diameter is 2.5 m, the total mass of the installed capsules is 8.4 tons, including the mass of the radioactive waste itself is 1.9 tons. The heat sink to the outer space is 52 kW.

However, containers of this design are unsuitable for long-term disposal of radioactive waste due to the possibility of loss of tightness due to aging of the hull material during storage, as well as melting of the hull in the absence of the necessary heat exchange with the environment (in case of landslides, for example, in underground storage).

A known space module for the disposal of radioactive waste, which contains a transport stage equipped with a propulsion system, control system and communication with the Earth; a docking station; a detachable emergency rescue stage fixed at the transport stage and having jet engines on the casing; a radioactive waste container having a cooling means and a damping device.

The transport space stage is used as the transport stage (SOIS) (Solar Orbits Insertion Steig). The department of the emergency rescue stage is made in the form of a descent vehicle, which is docked with the booster and is equipped with cooling means for the container during launch, means for ensuring buoyancy (in case of

on the water). The container is placed in the front of the descent vehicle and after the removal of the space module in the payload compartment of the reusable vehicle

of a space shuttle of the Space Shuttle type to a near-earth orbit, the container is separated from the descent vehicle, after having unloaded the module from this compartment with the aid of an onboard manipulator. After

Separating from the descent vehicle the container is docked to the transport stage for subsequent transportation to space.

It is proposed to use a carbon-carbon composite for thermal protection of the descent vehicle, and a steel honeycomb structure for cushioning.

However, in case of accidents of the means of removing the module into orbit (in this case ships of the Space Shuttle type), especially in the initial part of the ascent after launch, the constructive implementation of the means of removal and the detachable stage does not ensure the rescue of the container with radioactive waste, which can lead to radioactive contamination of the area the module falls upon the destruction of the container as a result of a catastrophic failure (explosion) of the means

withdrawal. In addition, in the known device, there is no reliable cooling of the container with radioactive waste during an emergency return to the Earth and for the time required on Earth for the arrival of the search and rescue complex and the evacuation of the container from the crash site. Cooling of the container is not provided also in the area of its transportation.

transport stage to the place of burial in space. In the absence of cooling, the radioactive waste is heated, which can lead to the destruction of the container and the accidental leakage of the radioactive substance into the surrounding space.

The layout of the known module by the tandem scheme, when the container is docked with the descent vehicle, and that with the transport stage, reduces the reliability of the device as a whole, since it requires the container to be disconnected from the descent vehicle and the container is redocked to the transport stage after unloading the module from the payload compartment .

In addition, due to an increase in the dose of radiation acting on the transport stage, after it is attached to the container, the probability of a failure of the devices and equipment of the stage increases.

The need for container re-docking, as well as an increase in the radiation dose acting on the transport stage, require reducing the mass of the payload (radioactive waste) due to an increase in the fuel reserves of the stage during stabilization operations and orientation of the module during redocking, as well as due to the installation of additional backup (redundant) instruments and equipment on the stage and ensuring their increased radiation resistance due to the application of appropriate coating and increase in the mass of the enclosures of instruments and equipment,

The purpose of the invention is the creation of such a space module for the disposal of radioactive waste, the constructive implementation of which would ensure a highly reliable and environmentally safe implementation of the disposal of this waste in space at all stages of the module’s flight, and in the event of an accident when the module was removed from Earth to near-earth orbit and the next launch of this orbit - saving the container and preserving its integrity (non-destructible) in the interests of the Earth’s environmental safety,

In the proposed space module for the disposal of radioactive waste containing a transport stage equipped with a propulsion system, a control and communications system with the Earth, a separable emergency rescue stage having jet engines on the body and installed at the transport stage, a docking station and a container with radioactive waste, having a means of cooling and a damping device, a protective screen is placed between the transport stage and the separable emergency rescue stage; the possibility of separation from any of them and having devices for rigid fixation of the container and its centering, and the body of the emergency rescue stage is made hollow and open on the side of the protective screen and mounted on it with its open part, forming, together with the screen, a sealed cavity to accommodate the container radioactive waste, while the detachable emergency rescue stage is equipped with a system of external active cooling of the container and at least two of its jet engines are made in the form of solid fuel willow rocket engines, the nozzle outlets of which are turned in the direction of the transport stage.

Making the detachable emergency rescue means hollow and open from the transport stage and installing a protective screen that, together with the detachable emergency rescue means housing, forms a cavity for accommodating a container with radioactive waste, improves the reliability of the module by reducing the radiation impact on the transport step and simplify design and layout

0 schemes of the space module;

reduce the dose of radiation acting on the instruments and equipment of the transport stage;

increase the mass of payload (transportable radioactive waste).

Placing a container with radioactive waste on a protective screen, using a means of rigid fixation and centering of the container allows you to increase

0 the reliability of the space module and the safety of its flight, as well as to increase the mass of the displayed payload, which is achieved by simplifying the design and layout scheme of the module,

5 improve the controllability of the movement of the module due to a decrease in the eccentricity of the center of mass of the container relative to the center of mass of the module body.

The installation at the detachable stage of emergency rescue of the external active cooling system of the container eliminates the possibility of overheating and destruction of the container during emergency return to Earth and waiting for the arrival of funds from the search and rescue complex 5 and evacuation.

The presence of solid propellant rocket engines at the separated emergency rescue stage allows to realize

0 emergency withdrawal of the module to a safe distance in case of failure of the removal device or transport stage and transfer the module to the return trajectory to one of the selected areas on Earth or

5 to a low Earth orbit, if a catastrophic failure of the removal means occurs in the final phase of the flight to orbit.

Safety shield in the space module

0 contains a power shell and heat-shielding layers located on both sides of the power shell, at least one of which is made of a material with radiation-protective properties.

5 The presence of heat-shielding layers improves the safety of transporting the container to orbit by reducing the thermal loading of the power shell both from the heat flux coming from the container during orbit and the emergency return of the module to the Earth, and from external aerodynamic heating during an emergency descent of the module to the Earth . The use of a material with radiation-protective properties in the heat-shielding layer allows simultaneously with an increase in the module reliability (due to the weakening of the radiation effect on the transport stage) to reduce the module mass and, accordingly, to increase the mass of the payload due to the optimal combination of thermal and radiation characteristics of the material.

In the space module, each device for rigid fixation and centering of the container is advisable to make at least two rods of different lengths, of which the large is pivotally connected to the upper part of the container and to the protective screen, and the smaller one - to the lower part of the container and to the protective screen, each from the rods is equipped with a damping unit. This increases the reliability of the module design due to the ease of installation and centering of the container, as well as the possibility of modifying the size and configuration of the container. Supplying each of the rods with a damping unit reduces the magnitude of the shock load on the container body and, consequently, increases the module's environmental safety by eliminating its destruction during emergency descent and fall to the ground.

The protective screen can be made concave from the side of the container, while the damping device of the container is placed on its lower part facing the protective screen, and made in the form of a shock-absorbing cushion, the outer surface of which has a convex shape, which responds to the concave shape of the protective screen. This makes it possible to increase the reliability of the complex of means of depreciation of the container and, accordingly, its environmental safety due to duplication of the damping rods of rigid fixation rods and centering of the container. The cushion cushion is the second, safeguarding stage for the absorption of impact energy upon contact with the surface of the Earth. The concavity of the screen (its bulge outwards) ensures the centering of the shock load, its uniform distribution and reduction in the mass of the module's construction, increases the volume of the container placement cavity, increases the structural strength and the environmental safety of the module.

The system of external active cooling of the container consists of two parts, one of which is made in the form of containers with

the coolant located in the annular gap between the container and the case of the separated stage of emergency rescue and communicating with each other, and the other part

made in the form of filling and drainage units mounted in the casing of the separable stage, at the same time at least one of the tanks is equipped with an exhaust valve equipped with a nozzle. This makes it possible to ensure, by blowing the container, the fire and explosion safety and cooling of the container at the start, during start-up and during the withdrawal, as well as during the emergency return of the module to Earth.

5 The simplicity of the cooling system, its layout on the detachable emergency rescue facility and the possibility of replenishing refrigerant reserves at the start (up to the beginning of the autonomous movement of the derivation engine) increase the reliability of the cooling system and save a lot of refrigerant operating reserves, which ultimately aims at improving safety flight module and its environmental

5 security.

The space module container on the side opposite to the placement of the damping device has radiators of the thermal control system secured in the lid of the container made of thermally conductive material, while heat-exchange elements interacting with the lid are installed in the container filled with radioactive waste. Behind

5 due to this, the best conditions for cooling the container and its contents at all stages of the module’s flight are achieved: in preparation for launch, at launch, in the orbit and further

0 transportation to the place of disposal of radioactive waste in space. Such a solution of the problem provides an increase in the tightness of the container, flight safety and the environmental safety of Zem5.

The implementation of the radiators of the thermal regulation system in the form of zigzag plates makes it possible to increase the heat transfer surface area of the radio at a limited size of the internal cavity of the module where the container is located. On the protective screen from the side of the transport stage, it is advisable to place the means of approach and docking

5 knot, which will create the possibility of conducting rescue operations with a module in near-earth orbit, installing several space modules using a packet or packet-flow system on another vehicle carrying radioactive materials.

waste to the place of burial and that will increase the safety of the flight module, the ecological safety of the Earth and expand the functionality of the module part of the means used for its transportation in space.

Figure 1 schematically shows a general view of the space module; 2 is a schematic design-layout diagram of a space module; Fig. 3 is a view along arrow A in Fig. 2, the arrangement of the elements of the side surface of the module; figure 4 is a schematic fragment of the design of the module, node B; figure 5 is the same, the node; figure 6 is the same node G; Fig. 7 schematically shows a device for a damping rod unit for fastening a container; on Fig - placement of tanks with coolant relative to the container and the module housing; Fig. 9 is a schematic design-layout diagram of a container with radioactive waste; in fig. 10 is a schematic fragment of the container structure, node D in FIG. 9; figure 11 is a view along arrow E of figure 9; Fig.12 - bringing the module to the state of transportation from a near-earth orbit to space; on Fig - General view of the module during an emergency return from orbit and landing on Earth.

The space module for the disposal of radioactive waste contains a transport stage 1 (Fig. 1), a separable stage 2 emergency rescue, a transfer compartment 3, a docking station 4 (Fig 2) of known construction, a container 5 with radioactive waste, having cooling means 6 and depreciation device 7.

The transport stage 1 (Fig. 1) is equipped with a propulsion system having a main (sustainer) jet engine 8 and auxiliary control engines 9. The transport stage 1 is also equipped with the known system 10 for controlling and communicating with the Earth, as well as other onboard service systems for long-term autonomous space flight. Transport stage 1 can be performed, for example, according to the type of instrument-aggregate compartment of the Soyuz-TM spacecraft. At the transport stage 1, through the transition compartment 3, an emergency rescue stage 2 is fixed, having on the case 11 jet engines 12, at least two of which are made in the form of solid propellant rocket engines 13, and auxiliary control engines 14, the automation system 15 (Fig .2) and a tank 16 with reserves of fuel (working fluid) for auxiliary engines 14. The outlets of nozzles 17 of rocket engines 13 are facing in the direction of the placement of transport stage 1. At the same time, the angular position of the nozzles 17 of the engines 13 provides the largest possible value of the total th g in the longitudinal direction, taking into account the allowable thermal and gas-dynamic effects of the jets of these engines on the design of the space module and the means of its launch into the near-earth orbit.

The emergency department of the emergency rescue stage 2 is equipped with a system 18 for external active cooling of the container 5.

Docking station 4 may be of the androgynous-peripheral type, as, for example, in the famous Soviet-American project Apollo-Soyuz

Between steps 1 and 2 is placed a protective screen 19 connected to them with

0 the possibility of separation (connector) from each of them and having devices 20 for rigid fixation of the container 5 and its centering. The case 11 of the stage 2 is hollow and open from the side of the protective screen 19

5 and installed on its open part,

form together with a protective screen

19 sealed cavity 21 for placement

container 5 with radioactive waste.

The protective screen 19 is connected to the corpus 11 of stage 2 and with stage 1 in its transitional compartment 3 by means of detachable connecting nodes of known construction, for example pyrozamok, widely used in space technology and allowing, depending on the conditions, to separate from the protective screen 19 from steps (1 or 2).

The container 5 has cooling means 6 in the form of ribs 22 placed on the lateral surface of the housing, and a damping device 7.

On the housing 11 of the stage 2 mounted landing support 23 (Fig 2, 3) with retractable rods 24,

5 In the upper part of stage 2 (Fig. 2) are placed a container 25 with a draft parachute, a container 26 with a main and a reserve parachute, a container 27 with means for maintaining buoyancy (inflatable balloons), a radio system equipment 28, a flashing optical camera to 29, power supplies and automation system. Radio equipment may include the international COSPAS-SARSAT system.

The protective screen 19 contains the power shell 30 (figure 4), supported by a power frame 31 of the elements made in the form of profiled frames, and heat-shielding layers 32.33, located

on both sides of the power shell 30. On the outer surface of the screen facing the transport stage there is a thermal barrier layer 32 made of a carbon-carbon composite, which may consist of separate fragments-blocks fastened together with the shell 30. Similar coatings used on space shuttle spacecraft, Buran. The thickness of the coating is determined on the basis of the calculated conditions of aerodynamic heating and the necessary attenuation of the radiation dose acting on the instruments and apparatus. Note that the carbon thermal barrier coating also has radiation protective properties (in atomic reactors, graphite blocks are used as a reflector retardant). Some elements (e.g., boron) can be incorporated into the coating 32 to more effectively slow down neutrons and other radiation components.

The inner surface of the screen is covered with a glass-protective layer 33 for thermal insulation of the power shell 30 and the frame 31. This layer can be made, for example, of a polymeric material such as foam and can also contain the necessary element additives to improve the radiation-protective properties of the material of this layer.

The heat protection of the upper part and the side surfaces of the stage 2 and the engines 12 are similarly arranged. The heat-shielding coating of the upper part of the internal cavity of the stage 2 is made in the form of an internal porous heat-shielding layer 34 applied to the power shell 35 (FIG. 5).

The heat-shielding coating of the engine housing 12 and the upper part of the stage 2 is made in the form of a layer 37 deposited on the power shell 36 of the body housing (FIG. 6) of carbon-carbon composite blocks,

Each device 20 (FIG. 2) of rigid fixation and centering of the container is made of at least two rods 38, 39 of different lengths. A bar 38 of greater length is pivotally connected to the upper part of the container 5 and with a protective screen 19. A bar 39 of shorter length is pivotally connected to the lower part of the container 5 and with a protective screen 19. Each of the rods 38, 39 is provided with a damping unit 40 (Fig. 7 ), which can be made in the form of a cylindrical cup 41 coaxially with the rod. The closed end of the cup 41 is connected to the rod 42 of the rod with the possibility of axial rotation of the cup 41. The other end of the glass 41 has an aperture into which the rod 43 of the rod is attached, at the end of which is fixed piston 44, to ory has through longitudinal channels 45 and an outer thread cooperating with the thread on the inner surface of cup 41. In

the inner cavity of the cylindrical cup 41 is liquid 46. On the inner surface of the cup 41, there are protrusions 47. The turn of the cup 41 relative to the stem 42 is fixed by a locking screw

0 48.

The protective screen 19 from the side of the container 5 is made concave (figure 2). In this case, the damping device 7 of the container 5 is placed on its lower part facing the screen 19, and is made in the form of a shock-absorbing cushion, the outer surface of which has a convex shape, which responds to the concave shape of the surface of the screen 19, and which is separated from the screen 19 on

0 the stroke of the damping unit 40. The shock-absorbing cushion can be made in the form of a steel honeycomb structure, crushed when it hits the screen. External active cooling system 18

5 can be performed in a known manner used in space technology, for example, by supplying a refrigerant to the external surface of the container or inside it through special channels.

0 The system 18 for external active cooling of a container usually comprises two parts, one of which is made in the form of tanks 49 with a refrigerant (for example, liquid nitrogen) placed in the annular gap of the cavity 21 between the container 5 (Fig. 2) and the case 11 of the stage 2 and communicating between each other, the nozzles 50, and the other part, are made up of refueling 51 and drainage52 units, mounted in a housing 11 of stage 2, with at least one of the tanks 49 fitted with an exhaust valve 53 equipped with a nozzle 54 (FIG. 8).

Refrigerant from the filling station 51

5 (FIG. 2) is supplied to the tank 49 through conduit 55, and from the inner cavity 21 of step 2 leaves through the receiving funnel 56 and the pipeline 57 and further through the drainage assembly 52 into the surrounding space.

0 The presence of overpressure in cavity 21 makes it possible to increase the stability of the structure of stage 2 to a dynamic external effect, including in the case of the action of a shock wave during an explosion.

5 means of removal in the area of ascent into orbit.

The container 5 (Fig. 9) on the side opposite to the placement of the damping device 7 has radiators 58 of the thermal control system secured in the cover 59 of a heat-conducting material. In the container 5, filled with radioactive waste 60, heat exchange elements 61 are installed that interact with the cover 59 through the heat-conducting medium 62 (for example, lead). Elements 61 can be made in the form of well-known heat pipes installed in channels inside the waste 60. Top elements

61 is fixed by separator 63, which is also a separating element between the heat-conducting medium.

62 and waste 60 in the event of a melting of the material of the heat-conducting medium in case of emergency heating of the waste.

It should be noted that the container body 5 is multi-layered and consists of a power shell 64 (FIG. 10), made for example of steel, on which a cylindrical cup 65 is fixed on the outside, carrying ribs 22 (in some cases the power shell can have own ribs, then glass 65 is not placed on it). On the inner side, a layer 66 of protection against gamma radiation (for example, from lithium hydride), a layer 67 of protection against neutron flux (for example, from tungsten) are adjacent to the power shell 64. A layer of thermal protection 68, made, for example, of a carbon-carbon composite, is in direct contact with radioactive waste.

In the proposed embodiment, the design of the module ensures the best cooling conditions for the container and its contents at all stages of flight, improves the container tightness, flight safety and environmental safety of the Earth.

This is achieved as a result of using heat removal elements that do not have moving parts, operating under zero gravity and space vacuum conditions and transferring heat from sealed containers (compartments).

To increase the area of the radiating surface, radiators 58 (Fig. 11) are made in the form of zigzag-shaped plates, which allows to improve the cooling of the container with limited internal dimensions of the container housing cavity.

In the space module on the protective screen 19 (Fig. 2) from the transport stage I, or rather in the zone of the transitional compartment 3, are placed the means 69 of approaching and the docking assembly 4 of known construction.

This achieves the possibility of carrying out rescue and assembly and installation work in orbit and, consequently, increases safety

space module flight and adaptability to selectable means of interorbital (interplanetary) transportation.

The launch of the space module for the disposal of radioactive waste is carried out as follows.

Container 5 (FIG. 2) with radioactive waste 60 is rigidly mounted on a protective screen 19 using rods 38, 39, while adjusting the position of the center of mass of the container by rotating the cup 41 (FIG. 7) of the damping unit with the screw 48 released, which after installation, Z5 is screwed, fixing the cup 41 from turns. Prior to this, the docking station 4 and the approach means 69 are mounted on the screen 19. After installation of the container 5, the pre-assembled 2 emergency rescue stage is docked to the screen 19 (FIG. 2), and a refrigerant supply is immediately connected to the filling unit 51 of which

Next, stage 2 with container 5 is connected to transition compartment 3, with which it is connected to transport stage 1.

The assembled space module is mounted on a launch vehicle (carrier rocket, for example) and output to

0, a near-Earth orbit, from which the module is accelerated with the help of a booster rocket 70 (Fig. 12) (tug) to the flight path to the waste disposal site.

After reaching a predetermined increment of the speed of the module, the stage 2 is separated from its attachment points to the screen 19 and the stage 2 is withdrawn with the help of engines 12 and 14. Thereafter, the acceleration unit 70 is separated from stage 1,

0 which, together with the container 5 placed on the screen 19, is transferred to the autonomous flight mode along the flight trajectory to the burial site, providing the necessary trajectory corrections,

5 interorbital dynamic operations, orientation and stabilization of the module, radio communication with the Earth and exchange with it of command and telemetry information.

During the flight into the cavity 21 (figure 2), where

0 the container 5 is placed, the refrigerant is supplied which provides the inflation of the internal volume of the stage 2 to a predetermined level of overpressure, with an increase in which the refrigerant is discharged through the drainage unit 52, which ensures the cooling of the fins 22 and the radiators 58 of the container 5.

In the event of an accident of the removal means, an emergency separation of the stage 2 from the stage 1 is performed at the site of its ascent;

stages 2 with container 5 using solid-propellant rocket engines 13 to a predetermined area along the withdrawal route and landing on Earth a splash while active cooling of container 5 from system 18.

In case of failure of the transport stage 1 or the accelerating unit 70 (Fig. 12), the stage 2 can be descended from the orbit when the braking speed impulse is realized by the motors 13, and the angular position control during the descent is controlled by the control motors 14 (Fig. 13). When this occurs, the separation of stage 2 together with a protective screen 19 from the transition compartment 3 stage 1.

When landing stage 2 (carrier container 5), carried out using parachutes placed in containers 25, 26 (Fig: 2) and pulled out after opening the top cover of stage 2, the rods 24 of the landing bearings 23 are advanced, damping units 40 are triggered, and further, in the case of their full compression, a damping device 7. When landing on water, from a command from the sensors of the landing system, means of buoyancy 71 are inflated (Fig. 13) located in container 27. During descent, the radar system 28 is activated by parachute and includes n Robust optical mater to 29.

The descent of stage 2 to the Earth for its reuse in case of normal termination of the withdrawal section can be carried out autonomously with the help of engines 12, 13, 14, while at the aerodynamic deceleration section in the atmosphere stage 2 is stabilized by the upper part, and landing is carried out from the parachute mode on retractable supports 23 on the ground or on the water using inflatable means of buoyancy 71.

Claims (8)

Claim 1. Space module for disposal of radioactive waste containing a transport stage equipped with a propulsion system, a control and communications system with the Earth, a separable emergency rescue stage having jet engines on its body and installed at the transport stage, a docking station and a container with radioactive waste, having cooling means and a damping device, most importantly with the fact that between the transport stage and the separated stage of emergency rescue is placed protection An integrated screen connected to them with the possibility of separation from any of them and having devices for rigid fixation of the container and its centering, and the body of the detachable emergency rescue stage is made hollow and open on the side of the protective screen and installed on it, with its open part, forming, together with a screen, a sealed cavity for placing a container with radioactive waste, while the separable emergency rescue stage is equipped with 0 external active cooling of the container and at least two of its jet engines are made in the form of solid propellant rocket engines, nozzles of which are facing in the direction of 5 accommodation transport stage. 2. The module according to claim 1, characterized in that the protective screen comprises a power jacket and heat-shielding layers located on both sides of the power shell, 0 at least one of which is made of a material with radiation-protective properties. 3. The module according to claim 1, characterized in that each device for rigid 5 fixing and centering the container with radioactive waste is made of at least two rods of different lengths, one of which, having a greater length, is hinged to the top of the container 0 and a protective screen, and a friend, having a smaller length, is pivotally connected to the lower part of the container and to a protective screen, while each of the rods is provided with a damping unit. five 4. A module according to claims 1 and 2, excluding the fact that the protective screen on the container side is made concave, while the damping device of the container is placed on its lower part facing the protective screen, and in the form of a shock-absorbing cushion, the outer surface of which has a convex shape, corresponding to the concave shape of the surface of the protective screen. five 5. The module according to claim 1, 1 and 2 with the fact that the system of external active cooling of the container contains two parts, one of which is made in the form of tanks with a refrigerant, placed in the annular gap between the container and the case a detachable emergency rescue stage and communicating with each other, and the friend is made up of refueling and drainage assemblies built into the case of department e5 of my stage, with at least one of the tanks equipped with an exhaust valve equipped with a nozzle. 6. The module according to claim 1, characterized in that the container on the side opposite to the placement of the damping device has radiators of a thermal control system fixed in the lid of the container made of thermally conductive material, while in the container filled with radioactive waste the heat exchange elements are installed interacting with the lid. 2 eight p GLK | 1- n ; / Phage. / 29 7. Module according to claim 6, characterized in that the radiators are made in the form of plates having a zigzag shape, 8. The module according to claim 1, characterized in that on the protective screen from the transport stage is placed the means of approach and the docking station. R 12/7 FIG. one  --o - -o and 66 of FIG. ten 1764524