RU2626792C1 - Method of payload delivery to celestial body soil, provision for soil and celestial body exploration and device for its implementation (versions) - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to methods of payload delivery - of a scientific package to celestial bodies (planets, asteroids, comets, etc.) for their exploration and penetrator-device with payload, separated from the main space vehicle and representing an impact penetrating probe, penetrating into the soil of the celestial body for the exploration of the body and soil parameters. The invention provides a method for delivering payloads to a celestial body and a device for its implementation, according to which a payload is placed inside a ballast serving as an additional protective body for the payload, and high-strength ice modifications, such as ice-VII or ice-VIII, or ice-X, are used as the ballast material. After the impact penetration of the penetrator into the soil, the ballast and the scientific package in it are freed out of the protective casing, the ballast is removed, releasing the payload, and the soil of the celestial body is explored.

EFFECT: increased impact resistance of the payload and higher measurement accuracy of the soil and celestial body parameters.

10 cl, 5 dwg

Description

The present invention relates to rocket and space technology, namely to penetrators - devices with payload, separated from the spacecraft and representing a penetrating penetrating probe that penetrates into the soil of a celestial body (hereinafter referred to as the soil) to study its parameters and its parameters soil and the influence of cosmic events on them.

The celestial bodies studied include, first of all, the celestial bodies of the solar system: planets (Venus, Mars, etc.), their satellites (Moon, Io, Europe, Ganymede, etc.), asteroids, comets, etc.

To study the parameters of the soil and the celestial body as a payload, immersed in the soil, use a complex of scientific equipment (KNA), as a rule, in the following composition:

- a gravimeter for measuring the mass of a celestial body;

- a gyroscope for determining the parameters of its rotation;

- a seismograph for sounding its internal structure by acoustic methods;

- mass spectrometer to determine the composition of the rocks;

- instruments for measuring the strength and porosity of rocks, the presence of a magnetic field, temperature at different depths, conductivity, radioactivity, etc.

A second KNA unit with a similar composition and a navigation sensor for recording space events can also be introduced. They strive to ensure that this KPA block during research is not completely submersible and has the ability to view the starry sky. Moreover, cosmic events are understood as the passage of a comet or an asteroid, certain positions of one or more celestial bodies, changes in the flow of the solar wind, etc.

When developing new and promising methods and devices, several conflicting problems must be solved, including:

- low impact resistance of the KHA during impact penetration of the penetrator into the soil of a celestial body with velocities in the range from 300 m / s to ≈4500 m / s (average speed of sound in solid materials) that can completely destroy the KNA;

- the need to improve the accuracy of measurements by ensuring mechanical contact of the KNA with the soil and minimizing the impact of the penetrator itself and its blocks on the results of these measurements;

- the need to ensure long-term stable radio communication with the Earth and / or spacecraft for transmitting the obtained research results from a penetrator immersed deep into the celestial body;

- the need to ensure guaranteed communication between two KNA units with the ability to synchronize their work;

- the short duration of the KNA due to the decrease in battery life after a long flight to the selected celestial body. For example, the Rosetta probe launched in March 2004 with Phil's descent vehicle arrived at its final destination - to comet Churyumov-Gerasimenko in November 2014, i.e. after 10 years. The flight time to the moons of Jupiter: Ganymede, Io, etc. can also be about 10 years.

Therefore, almost all existing methods of delivering payload to the soil of a celestial body differ depending on the compromises in solving these problems.

A well-known analogue is a penetrator for studying the surface of celestial bodies, developed at FSUE NPO im. S.A. Lavochkin "(patent RU 2111900, IPC B64G 1/00, publ. 27.05.98). This penetrator contains a shared bow, embedded in the soil, and tail, remaining on the surface, elements with instrument compartments placed in them with experimental and service equipment, interconnected by cable, brake means for the tail element, made in the form of a cavity between the shared elements of the penetrator, in communication with the container with gas under pressure, and the tail element includes a cylindrical part for accommodating the instrument compartment and an aerodynamic surface made in the form of a truncated cone, and the cylindrical part of the tail element is made in the form of a shell rigidly connected to the smaller base of the truncated cone, the instrument compartment and the nose element of the penetrator are placed in the shell of the tail element with axial movement with the formation of a cavity between them, the penetrator is equipped with a piston placed in the specified cavity and interacting with the nasal element, the cavity being in communication with the container with gas through a channel made in the wall of the shell, and the shell is equipped with faceting chitelyami turn the instrument compartment and the piston.

The method implemented by this penetrator consists in delivering the penetrator from the Earth to the selected celestial body and launching it, impacting the penetrator with the surface of the celestial body, as a result of which they begin to introduce it into the ground of the celestial body, and then the penetrator is touched with the surface of the celestial body contact device and create a signal for them, which is applied to control the movement of the piston, forming its movement, when introduced into the soil of a celestial body, the nose part is introduced into the soil of the celestial bodies, from the tail, remaining on the surface of the celestial body and electrically connected to the nose by the cable, due to the movement of the movable piston, the instrument compartment is braked when the nose is introduced into the soil of the celestial body until it stops completely, the above devices from the instrument compartment are used to study the heavenly soil body, using a cable exchange electrical signals between the nose and tail, with the possibility of exchanging signals between the tail with the Earth.

The disadvantages of these devices and methods can be considered the following: low speed of the movable piston, effectively absorbing the shock load only for low penetration rates of the penetrator into the celestial body, not more than 100 m / s;

- short research time after penetrator penetration into the soil due to the small battery life after a long flight to it;

- the lack of wireless radio in the event of a cable break for the transmission of signals and energy between the nose and tail parts after separation.

There is also known a device for delivering payload to an array of soil of celestial bodies (RF patent No. 2480385, IPC B64G 1/10, publ. 04/27/2013, Bull. No. 12), using braking by dumped engines with subsequent depreciation.

One embodiment of this device comprises a hollow power body made with a head and a cylindrical tail, the length of the cylindrical tail being 8-15 diameters, in which ballast with an average density exceeding the density of the power body is sequentially placed, payload in the head part of the hole, communicating through its channels with the internal cavity of the power housing, in which the said ballast and payload are located, while the ballast or part of the ballast ying of materials capable under the effect of inertial forces squeezed out of the cavity through these openings into the external medium as a lubricant.

In addition, the device for delivering payload to the soil mass of celestial bodies has resettable braking motors, orientation motors in space and lateral thrust, a laser range finder and an apparatus unit with a ballistic computer.

A method for delivering a payload to the soil mass of celestial bodies, based on the use of this penetrator, is implemented as follows. Under given flight conditions, the penetrator is separated from the spacecraft. The hardware unit with a laser range finder, using braking and spatial orientation engines and lateral thrust engines, provides the specified longitudinal speed, lateral speed and contact angle with the celestial body depending on the rocks of its components, their structure and terrain. After this, before the collision, the hardware unit and engines are disconnected from the device for delivering the payload to the soil mass of celestial bodies and continue to perform their own braking. The power body makes contact with the soil of the celestial body. The first cone in contact is an additional cone made of aluminum, as a result of which it is flattened, adheres to solid rocks of the soil and provides a counter-bounce at the initial moment of penetration of the power housing into the soil. Then cones of the head part penetrate successively into the ground, providing the least tipping moment. Upon penetration, a sequential stepwise separation of the soil from the lateral surfaces of the cones and the formation of a single cavitation cavity occur. The geometric characteristics of the cones and cylinders are optimally selected to solve the problem of penetration into the ground of a celestial body. The device continues to move in an inertially expanding array of soil along a predictable rectilinear trajectory. Through the holes communicating through their channels with the internal cavity of the power housing and made on the second and third cylinders and on the tail cylindrical part between the base of the fourth cone and the first radial groove, lubricant is squeezed out of the internal cavity of the power housing under the action of inertial forces. The aluminum pads installed in the grooves at first play the role of additional lubrication, after which, in the process of penetrating deep into the celestial body, the radial grooves and the corresponding faces develop and calibrate the punched hole, preventing the power case from jamming in the soil mass, and the longitudinal grooves following them provide reduced friction on the centering cylindrical tail and optimize its axial rotation.

These method and device have the following disadvantages:

- effective shock absorption for only small penetrator penetration rates into the celestial body, not more than 100 m / s;

- low measurement accuracy due to the influence of the released grease on their results;

- short research time after penetrator penetration into the soil due to the small battery life after a long flight to the celestial body selected for research.

The closest in technical essence to the prototype device can be considered the design of a monolithic penetrating penetrator (US patent No. 6186072, Monolitic balasted penetrator, JP Hickerson, FJ Zanner, MD Baldwin, MC Maguire IPC, F42B 30/00, publ. 13.02.01), which can be used to deliver payload to an array of celestial bodies.

The design of a monolithic penetrating penetrator contains a hollow front-pointed power protective case made of high-strength steel alloy, including two cavities: a front pointed one, in which a ballast-filler is placed, which is superior in strength to the material of the power case, and a rear cylindrical cavity in which it is mounted this part of the hull is a payload. The body is molded around the ballast-filler, connecting both cavities together, in such a way as to prevent the possibility of movement of the ballast-filler with respect to the body during impact with the target. The ballast filler may contain concentric grooves or protrusions that improve the strength of the connection between the housing and the filler.

The prototype method implemented by this device includes the use of a hollow power casing, the sequential placement of ballast-filler and payload inside it, the delivery of this device from the Earth to the selected celestial body and the implementation of shock introduction into the soil mass of this body.

This method and device can potentially be used to deliver a payload from the Earth by a spacecraft into the soil of a celestial body when the KPA is placed inside the ballast-filler, which in this case would be an additional protective body.

This would increase the maximum level of withstand overload of devices placed inside the ballast-filler, primarily due to rigid fixation and elimination of unacceptable displacements of elements, assemblies and parts, including and movable, each device relative to each other; running longitudinal shock waves arising from the impact are distributed in this case evenly over the entire cross-section of the ballast-filler and therefore act only in proportion to the area of the devices.

However, a significant drawback of this technical solution is the limited functionality:

- due to the impossibility of removing this ballast filler after impact introduction into the soil of a celestial body to ensure mechanical contact of the KNA with the soil,

- due to the lack of a second KPA with a navigation sensor with an overview of the starry sky for fixing space events.

The technical result of the invention is:

- increase the impact resistance of the payload when delivering it to the soil of celestial bodies with penetration speeds in the range from 300 m / s to ≈4500 m / s;

- expansion of functionality.

The specified technical result is ensured by the fact that in the method of delivering the payload to the soil of the celestial body, providing research on the celestial body and its soil, in which the payload, placed in the frontal protective body and containing ballast, is delivered by spacecraft from the Earth to the selected celestial body with the implementation of the collision of the device with the surface of the celestial body and shock introduction into its soil, according to the claimed invention, use two sets of scientific equipment for research parameters of the soil and celestial body, the second of which with the additional capabilities of fixing space events when viewing the starry sky and bidirectional radio signal reception with the Earth and / or the spacecraft, in this case, an electronic unit and a communication unit are introduced and placed in a protective housing, using the tail an element into which a second electronic unit, a second communication unit and a second set of scientific equipment are inserted and attach this tail element to the back of the protective housing with the possibility of separation at higher mentioned shock introduction, and between the communication units, a cable is introduced with the capabilities of wired and wireless communications, respectively, for the whole and torn cable, while the first set of scientific equipment in the form of a payload is placed inside the ballast, which serves as an additional protective body, and the protective power case is performed with the possibility of its separation from the additional protective body before, during or after the aforementioned shock introduction or from mechanical destruction during the aforementioned shock introduction and, and as the material for ballast, which serves as an additional protective body for the payload, use material with the possibility of solidifying it during the delivery of the payload and its removal after the aforementioned shock introduction into the ground, while shock activated batteries are used in the electronic units for power supply with passive, during the flight to the selected celestial body, and active modes of operation and the possibility of transferring them from passive to active modes of operation from the aforementioned shock introduction, moreover, the tail element is separated and fixed by the surface of the celestial body with the possibility of viewing the starry sky with the second complex of scientific equipment, and the batteries activated from the shock are transferred from passive to active mode during the aforementioned shock introduction, while ballast with the first scientific complex contained in it is released equipment from the power protective case, remove the ballast, freeing the payload, and determine the integrity of the cable and depending on this use a wired connection between the unit communications or create a wireless connection between the ends of the cable by creating an electromagnetic connection between them, and with the help of both sets of scientific equipment they conduct research, synchronize these studies with each other, record the space events with the second set of scientific equipment and, depending on this, control the synchronization parameters of the scientific complexes instruments and determine the parameters of the soil and the celestial body, as well as the influence of cosmic events on them, while monitoring the current value of the accumulated energy Two sets of batteries are set and set their minimum permissible levels, after which they transfer electricity to the discharged set of batteries from the other due to the connection between the communication units of the tail element and the protective casing, and they monitor the current load of electronic units by the computing operations and ensure their equal values by redistributing computing operations between electronic units.

According to the invention, this result is also achieved in that the ballast, which serves as an additional protective body for the payload, is a modification of ice-VII or ice-VIII or ice-X from solid phase states of a liquid or vapor.

Another difference is that water or naphthalene or solutions based on them are used as the material for creating ice modifications.

Another difference is that the removal of ballast is carried out due to its heating and evaporation by heating and / or mechanical destruction.

The next difference is that in the method of delivering the payload to the soil of the celestial body, providing research on the celestial body and its soil, in which the payload is placed in a frontal protective housing containing ballast and delivered by a spacecraft from the Earth to the selected celestial body with the implementation of the collision of the device with the surface of the celestial body and its shock introduction into the soil, a payload in the form of a set of scientific equipment for studying the soil of the celestial body is placed inside the ballast serving for the payload as an additional protective body, wherein the protective body is configured to separate from the additional protective body before, during or after the aforementioned impact introduction or from mechanical destruction during the aforementioned impact introduction, and as a material for ballast serving as an additional protective body body for the payload, use material with the possibility of solidification for the time of delivery of the payload and its removal after the aforementioned shock introduction into the ground, release the ballast with the complex of scientific equipment contained in it from the protective housing, remove the ballast, freeing the payload, and conduct research on the soil of the celestial body.

Another difference is that the ballast, which serves as an additional protective body for the payload, is a modification of ice-VII or ice-VIII or ice-X from solid phase states of a liquid or vapor.

And another difference is that water or naphthalene or solutions based on them are used as the material for creating ice modifications.

Another difference is that the removal of ballast is carried out due to its heating and evaporation by heating and / or mechanical destruction.

The specified technical result is also achieved by the fact that in the first embodiment of the device for implementing this method, comprising a hollow front-pointed power protective housing comprising two internal cavities: a front, pointed in the bow and a rear cavity, a ballast is placed in the front cavity, the ballast is formed from modifications of ice-VII or ice-VIII or ice-X from solid phase states of a liquid or water vapor or naphthalene or solutions based on them, a payload is placed in the front cavity inside the ballast, representing a complex of scientific equipment for studying the celestial body and its soil, and an ice remover, and in the back cavity of the protective case there is an electronic unit, also containing a set of accumulator, shock-activated accumulator, and a communication unit, in addition, the device additionally contains a tail an element made in the form of a cylindrical shell paired with a skirt at the end, while in the cylindrical shell of the tail element there is a second electronic unit containing another set, similar to the above cushioned from the accumulator, the shock-activated accumulator, and the communication unit, the device protective housing with the payload placed in its front and rear cavities and the electronic unit with the communication unit, respectively, is also partially located in the cylindrical shell of the tail element with the possibility of axial movement in it and the formation between the electronic unit located in the shell of the tail element and the rear wall of the protective housing, the cavity in which the cable is placed with the possibility of wired communication between the blocks with ides with the whole cable, or if it is broken wireless communication between its ends.

In the second embodiment of the device for implementing this method, comprising a hollow front-pointed power protective case comprising two internal cavities: a front, pointed in the bow and a rear cavity, a ballast is placed in the front cavity, according to the claimed invention, the ballast is formed from ice-VII modification or ice-VIII or ice-X from solid phase states of a liquid or water vapor or naphthalene or solutions based on them, a payload is placed in the front cavity inside the ballast, in the form of a set of scientific instruments for investigating the celestial body and the ground and ice remover, and in the posterior chamber of the protective cover are arranged electronics unit and the communication unit.

The invention is illustrated by drawings, where

- in FIG. 1 - a device that implements the proposed method with the separation of the bow and tail parts (hereinafter - device No. 1);

- in FIG. 2 - a device that implements the proposed method, without separation (hereinafter - device No. 2);

- FIG. 3, 4 - device No. 1 after shock penetration into the ground and removal of ballast when viewing the starry sky, radio communication with the Earth and / or spacecraft and wireless communication between parts of a broken cable (Fig. 3) or communication units (Fig. 4).

- FIG. 5 - device No. 2 after impact introduction into the ground and removal of the ballast-filler during radio communication with the Earth and / or spacecraft.

Device No. 1 is designed for flight speeds (initial penetration rate into the ground) from ≈300 m / s to ≈700-900 m / s. Device No. 2 can be used at higher flight speeds, up to ≈4500 m / s.

Device No. 1 (Fig. 1) contains a power protective case 1, pointed at the front, with a front cavity 2 filled with ballast 3 made of ice, with KHA 4 inside and ice remover 5, and a rear cavity 6 with electronic unit 7 located inside it consisting of a control system 8, a battery 9 and a shock activated battery 10. A communication unit 11 is attached to the control system 8, partially protruding beyond the back of the rear cavity 6.

The device No. 1 also contains a tail element 12, consisting of a skirt 13 with a shell 14, while the power protective housing 1 at the rear is partially inserted into the shell 14 with the possibility of axial movement along it. A communication unit 15, a cable 16 and an electronic unit 17, consisting of a control system 18, a battery 19 and a battery 20 activated by shock, are installed in the shell; KPA 21.

The power protective housing 1, in the part forming the front cavity, is disclosed and / or removable or with the possibility of separation from the ballast 3 before, during or after the shock introduction. It can also be made in terms of strength, material thickness and other parameters so as to be destroyed upon introduction into the ground. As a result, this will enable mechanical contact of KHA 4 with the soil after removal of ice ballast 3.

Blocks KNA 4 and KNA 21 contain equipment for studying the parameters of the celestial body and its soil. In this case, KNA 4 after impact introduction is immersed in the ground. The KNA block 21 additionally contains a navigation sensor, before the shock introduction, this block partially protrudes in the conical cavity 13, and after the shock introduction, it should be near the surface with an overview of the starry sky to record cosmic events.

The communication unit 15 may partially protrude both in the conical cavity formed by the skirt 13 for radio communication with the spacecraft and / or the Earth, and in the cavity between the electronic unit 17 and the rear wall of the power protective housing 1 for wired communication via cable 16 and / or wireless communication unit 15.

The cable 16 is located inside the shell 14 in the folded and / or coiled state with the possibility of pulling it, located in the cavity between the electronic unit 17 and the rear wall of the protective housing 1.

Control systems 8 and 18 control the operation of all units of device No. 1 at all stages of its operation, namely: they control the removal of ballast 3 using an ice remover 5, the preparation for work and scientific research using KNA 4, the process of exchanging information and electricity between electronic blocks 7 and 17, the transfer of scientific information to Earth, etc.

Due to the possibility of separating the power protective housing 1 from the tail element 12 when introduced into the ground, communication units 11 and 15 are used to organize communication both among themselves (via cable 16 and / or wirelessly), and with the Earth and / or spacecraft.

From the moment of starting from the Earth and before the introduction of device No. 1 into the ground, the front cavity of the protective housing 1 is filled with ballast 3, which covers KHA 4 and the ice remover 5, filling all the voids between them and forming a single additional protective body of ice. This ice is a solid phase state of a liquid or gaseous substance. When using distilled water, this ice is one of the well-studied high-strength ice modifications: ice-VII, ice-VIII, ice-X.

So, an additional protective body of ice-VII can be created from distilled water under certain combinations of pressure and temperature, for example, when exposed to high pressure P≥2.216 GPa at a temperature T≥ + 82 ° C. Storage of the created solid body and its use (work with him), including during the flight to the chosen celestial body, it is possible due to the subsequent decrease in pressure and cooling to cryogenic temperatures, for example, the temperature of liquid nitrogen T <-195 ° C.

In addition to distilled water, naphthalene, solutions based on them, and other liquids can also be used to create ballast. The technology for creating this ice body consists of standard operations in chemistry, press equipment, cryogenic technology, etc., corresponding to the current technological level.

The ice remover 5 is a device for removing ice, consisting of different blocks, the work of which actively helps, promotes and accelerates the removal of solid ice ballast 3, to free KNA 4 for research. Variants of removal can be evaporation due to active sublimation, i.e. the transition from the solid phase (ice) directly to the gaseous (water vapor), as well as mechanical cracking and removal (in the final stages of sublimation with thin / small ice), like peeling. Therefore, these blocks can be sources, signal and radiation generators:

1) for heating and evaporation (active sublimation):

- electric heaters for contact and / or non-contact (microwave radiation) heating,

- emitters in the infrared range with a wavelength in the wavelength range of the absorption of ice, heating solid ice ballast 3;

- a generator of high-frequency alternating electric current for passing it through a solid ice ballast 3 and heating by using the intrinsic conductivity of ice (Muchnik V.M. Thunderstorm Physics, p. 167, http://www.ngpedia.ru/id614075р1.html);

2) for heating, active sublimation, mechanical destruction (cracking) and removal:

- ultrasonic emitters forming vibrational vibrations and waves (running and / or standing) in the solid ice ballast 3 for heating and cracking the ice and cleaning it of its residues;

- metal-based heaters with shape memory, for example, nitinol (an alloy of nickel and titanium) and among them the so-called “Smart” materials that have several spatial forms for different temperatures and are similar to electrically controlled manipulators (http://zoom.cnews.ru/rnd/news/line/metall_s_pamyatyu_mozhet_hranit_neskolko_form). Their use can be quite effective, because allows you to combine heating (by transmitting current) and mechanical impact on ballast 3 (due to the memory of different shapes for different temperatures), allowing it to evaporate and / or crack, peel like puzzles or shell cells. One of the options for such materials may be bimetals, the deformation of which depends on the transmitted current and is widely used in thermostats.

Batteries 9 and 19 can be rechargeable power supplies for space applications with high impact resistance.

Batteries 10 and 20 are rechargeable power supplies for space applications with high impact resistance and with two operating modes (states): passive, "sleeping", during the flight to the selected celestial body, and active, working after shock introduction. The transition from passive to the second state is carried out from shock introduction into the ground. In the sleeping state, these batteries can be stored for a long time without loss of capacity (or with its minimum loss), and in the working state they can be operated with the possibility of recharging. Such batteries have already been created by mPhase Technologies (http://www.mphasetech.com, http://www.ixbt.com/news/hard/index.shtml?14/61/44).

Cable 16 electrically connects the electronic units 7 and 17 and can be a set, a loop of flexible conductors to ensure:

- (with the integrity of at least one core) wired connection;

- (in case of cable break 16) wireless communication (inductive and / or radio communication and / or waveguide) between the electronic units 7 and 17 (Fig. 3).

Alternatively, each such core can be a flexible metal waveguide (or high-frequency antenna), which is intact and unbroken is a conductor, and with torn parts it can form a wireless bidirectional signal transmission.

The first output of the control system 8, which is the first output of the electronic unit 7, is connected to the KNA 4 and the ice remover 5. The battery 9 and the battery 10, activated by shock, are connected to the first and second inputs of the control system 8, and its second output, which is the second output the electronic unit 7 is connected to the communication unit 11, to which the cable 16 is connected. The other end of the cable 16 is connected to the communication unit 15.

In the electronic unit 17, the battery 19 and the shock activated battery 20 are connected to the first and second inputs of the control system 18. And its output, which is the output of the electronic unit 17, is connected to the electrical input of the communication unit 15. The output of the KNA 21 is connected to the third input control system 18, which is the input of the electronic unit 17.

The tail element 12 can be made of aluminum to eliminate (or minimize) rebound in a collision with the surface of a celestial body. The cavity formed by the skirt 13 has the shape of a truncated cone, the smaller base of which is connected to the rear end side of the shell 14, inside which the communication unit 15 and the electronic unit 17 are located.

Device No. 2 (Fig. 2) contains a protective case 1, pointed at the front, with a front cavity 2 filled with ballast-filler 3 made of ice, with KHA 4 inside and ice remover 5, and a rear cavity 6 with an electronic unit located inside it 7, consisting of a control system 8 and a battery 9; partially protruding communication unit 11.

The mechanical and electrical connection of all elements and blocks making up device No. 2, their functions and use, as well as the properties of ballast filler 3, are completely similar to device No. 1.

The proposed method is implemented by device No. 1 in the following sequence of steps:

1) The preparatory stage in terrestrial conditions: the creation of a ballast in the form of an ice body with KHA 4 and an ice remover 5 located inside it.

2) Flight phase: launch from Earth, launch into space with the subsequent flight to the studied celestial body.

3) Impact penetration into the ground of a celestial body.

4) The preparatory stage in the soil of the celestial body is to remove ice ballast 3, release KHA 4 and prepare for research.

5) Research phase: KPA 4 and KPA 21 scientific research with an overview of the starry sky and the fixation of cosmic events.

The preparatory phase in terrestrial conditions.

Next, we consider the option of using distilled water to create ballast and create on its basis a high-strength modification of ice: ice-VII.

Before being sent into space, the first device is created by forming an ice body based on ice-VII from distilled water in the form of ballast 3 with KHA 4 built in and an ice remover 5. For this, at a temperature of T≈ + 27 ° С to the water tank with submerged, inoperative KHA 4 and an ice remover 5, pressure is applied up to P≥1.1 GPa and a solid is formed with a ballast and a covering shell of ice VI. Then, at the same temperature, the pressure applied to this protective body is increased to a level of at least P ≥ 2.216 GPa, which transfers ice-VI to a higher-strength phase state of ice-VII. And then the pressure is gradually reduced to normal atmospheric pressure, and the created body is cooled to the temperature of liquid nitrogen (<-195 ° C), at which it can maintain its strength parameters.

During these technological operations, inoperative KHA 4 and ice remover 5 are mechanically fixed in water, as an option, with a mechanical frame and prepared for subsequent placement of the formed ice body in the inner front cavity 2 of the power protective housing 1.

To date, technologies and devices with ultrahigh pressures up to 15-20 GPa and above have already been developed (Shatalov R.L. History and Philosophy of Metallurgy and Metal Processing, Publishing House “Teplotehnik”, 2011, Lugovskoy V.M., Danilov G.D. New methods of processing materials with ultra-high pressure liquid, http://www.elektron2000.com/article/1188.html).

Flight stage.

The flight phase begins when the device is launched from Earth into space with a spacecraft and sent along the trajectory to a selected celestial body, providing conditions for maintaining high strength properties of the created ice body (or their minimum and / or pre-considered reduction) in space conditions: protection against radiation: solar and ionizing, maintaining the temperature and pressure / vacuum during the flight.

Impact penetration into the ground of a celestial body.

After approaching the selected celestial body, the device, hitting its surface, is introduced into the ground and immersed in it. In this case, the part of the protective housing 1 forming the front cavity is removed by opening and / or shooting (immediately before or after) or is destroyed, violating its tightness, by a strong ballast 3 during impact penetration into the ground.

During impact penetration, the shock load is distributed over the entire volume of the ice body, significantly reducing the specific pressure on the rigidly fixed KHA 4 and ice removers 5, protecting them from destruction. After hitting the ballast 3 with the rear cavity 6 of the protective housing 1 continue to move in the ground and pull the cable 16, plunging into the ground to a complete stop. After stopping, the ballast 3 with KHA 4 located inside and ice removers 5 is immersed in the ground.

A skirt 13 made of soft metal, for example aluminum, collapses upon impact against the surface, taking the form of a curved tail (Fig. 3), minimizing rebound and shift relative to the entry point, and detaches from the protective housing 1, fixing the KHA 21 block near the surface with a view starry sky and fixing space events.

A strong shock leads to the activation of the batteries 10 and 20, which switch from the "sleeping" state to the working one, starting to power the second inputs of the electronic units 7 and 17. This shock effect is also detected by the control systems 8 and 18, which start the preparatory stage the soil of a celestial body.

The preparatory stage in the soil of the celestial body.

At the beginning of this stage, the integrity of the cable 16 is determined, and depending on the results of this, a communication channel is formed between the electronic units 7 and 17 for the exchange of signals and electricity:

- with a whole cable 16 in a wired way (wired connection);

- with a torn cable 16 wirelessly (wireless communication) due to the creation of electromagnetic coupling between its broken ends: inductive coupling similar to antennas (waveguides) and / or radio communication directly between communication blocks 11 and 15.

Next, from the first output of the control system 8, a signal is sent to the ice remover 5, its component blocks are turned on and various physical effects (heating, radiation, vibration, mechanical impact, etc.) begin to apply to the ice ballast 3, leading to its removal due to: heating and evaporation (sublimation), cracking and exfoliation. Removing ice ballast 3 releases the payload in the form of KHA 4 and provides free access to the soil and readiness for scientific research.

Research phase.

After the release of KPA 4 from ice, the research phase of scientific research begins.

Effective provision of soil research may consist, as an option, of maximizing the duration of the scientific mission and the number of scientific studies. This may depend on the economical use of accumulated energy and the elimination of battery discharge, as well as maximum performance and equal loading of electronic units by computing operations, including synchronous operation of KNA 4 and KNA 21 and other operations, some of which are presented below.

Mutual recharge of batteries.

Periodically at different stages of this stage, the energy consumption of individual blocks can reach high values for large distances both from the Earth to the Jupiter Ganymede satellite, for example, for KNA 4 and KNA 21 when conducting scientific research up to 100-150 W or more, for communication units 11, 15 during radio transmission up to 150-250 W or more and in other cases.

Due to the fact that the state of all batteries after a possible long flight and powerful impact is difficult to predict, it is important to monitor and maintain the current value of the accumulated electricity (capacity, charge, resource) of batteries 9, 10 and 19, 20 in order to prevent any or a pair of them to the full discharge and stop the scientific mission. Therefore, the possibility of mutual recharging due to the transfer of electricity to the most discharged pair of batteries from another pair with a large stock of stored energy was introduced.

For this, control systems 8 and 18 monitor the current value of the accumulated energy of two sets of batteries 9.10 and 19, 20 and set their minimum acceptable levels, upon reaching which they transfer electricity to the discharged set of batteries from another set (with the possibility of its redistribution between the batteries) due to the connection (wired or wireless) between the communication units 11 and 15. At the same time, at different points in the scientific mission, each set of batteries can be either a source or a receiver (receive Telem) the accumulated electric power.

Conducting research.

According to the control signals from the first output of the control system 8 supplied to the KNA 4, a program of scientific research is set, their management and a survey of measured values. Then, according to the signal from the second output of the control system 8 to the communication unit 11, the received information and the result of its processing is transmitted (via cable 16 or wirelessly) to the communication unit 15. This information is interrogated by the signal from the first output of the control system 8 for possible additional processing and / or subsequent relay to the Earth and / or spacecraft.

Conducting research to determine the effect of external influences on the studied celestial body.

To determine the influence of external influences, for example, the gravitational, magnetic fields of other celestial bodies or cosmic events (supernova burst) on the studied celestial body, scientific research, including and similar to those described above, can be synchronized by a signal from the block KNA 21.

Using the KNA 21, one or more celestial bodies are selected, one or more sets of their positions are set, the current spatial position of these selected celestial bodies in the starry sky is determined, and when they coincide, a synchronizing signal is generated at the output of this block. This signal captures the onset of a cosmic event in the form of a specific position of selected celestial bodies and is used to synchronize scientific measurements. It is transmitted sequentially to the input of the electronic unit 17 (third input of the control system 18), from the output of which to the input of the communication unit 15 and further (cable 16 or wirelessly) to the communication unit 11. The signal of the latter arriving at the input of the electronic unit 7 (third input of the system control 8), from the output of which scientific measurements are made according to the signal arriving at KNA 4. The influence of external influences (value, directional vectors, time of action, consequences, etc.) on the studied celestial body is calculated by one dimension or their combination.

Conducting research KNA 4 and KNA 21 with their mutual synchronization.

For certain scientific tasks, for example, determining the structure of the soil, identifying the objects contained in it, their shape, position in three-dimensional space, it is necessary to conduct a two-position ultrasonic location: from two different points displaced in space.

This can be done by ultrasonic locators installed in KNA 4 and KNA 21, the first of which is immersed in the ground, and the second near the surface of the celestial body and which should be synchronized with each other: with their simultaneous operation or with a time delay relative to each other (phased) .

Such synchronization is carried out using communication (cable 16 or wirelessly) between communication units 11 and 15. In one embodiment, the control system 18 generates at its output a signal passing through communication unit 15 onwards (cable 16 or wirelessly) to communication unit 11 The signal of the latter goes to the input of the electronic unit 7 (the third input of the control system 8), the output of which forms a signal, the next to KNA 4. As you can see, this signal is synchronized with respect to the output signal of the control system 18 and, as a result, the sequence signals can synchronize and research carried out by using 4 KPA and 21 KPA.

Optimization of loading by computing operations of electronic blocks and duplication of data in memory.

In the process of a scientific mission, to improve performance and other purposes, the electronic load of the electronic units 7 and 17 (and their control systems 8 and 18) is optimized for the current load by parallelizing the execution of these operations between these units. And to increase the reliability of data storage, they are duplicated.

The proposed method can also be implemented with device No. 2 (Fig. 2) and at all the above steps is basically similar to the above. The difference lies in a simpler design and correspondingly less functionality. Moreover, in the process of shock introduction, device No. 2 is completely immersed in the soil mass of the celestial body, like a pool, until it is completely inhibited, creating a passage. After diagnosing the health of all units by a signal from the first output of the control system 8, which is the first output of the electronic unit 7, the ballast 3 is removed to the ice remover 5 and KNA 4 are released for scientific measurements. Then, according to another signal from the first output of the control system 8, the scientific measurement process is controlled and KNA 4 is interrogated, and the information received by the signal from the second output of the control system 8, which is the second output of the electronic unit 7, is transmitted to the communication unit 11 for transmission by the radio signal to Earth and / or spacecraft.

Device No. 2 has minimal weight and size parameters due to the lack of various connecting elements, cables, etc., and can be used at higher penetration rates into the ground, up to ≈4500 m / s, corresponding to the average speed of sound in solids.

Thus, the essence of the proposed technical solutions is as follows.

1. The basis of the invention is as follows:

- (when impact penetration into the ground) increase the impact resistance of the payload in the form of KHA 4 due to its placement inside high-strength ice ballast 3, which serves as an additional integral single protective body;

- (after impact penetration into the ground) improving the accuracy of measurements of the parameters of the soil and celestial body due to the release of KPA 4 by removing this ice ballast 3 to ensure good mechanical contact with the soil.

Moreover, the increase in impact resistance is due, first of all, to the following:

a) the exception of the displacement of the layers of high-strength ballast 3 and the rigid fixation of the payload;

b) a decrease in shock specific pressure due to:

- its uniform distribution over the entire cross-sectional area of this body, pointed in front “under the cone” or “under the pyramid”. This is actively used by construction to increase the impact resistance of reinforced concrete piles (Tsoi LB Creating designs of reinforced concrete piles with increased impact resistance and the introduction of research results into the practice of building production. / Abstract of the dissertation of the candidate of technical sciences, 05.23.01, Chelyabinsk, 1992.);

- due to the peculiarities of loading bodies immersed in a solid ballast 3, distributing the external impact depending on the angle of incidence. This allows you to reduce the load on the KHA special forms with a small frontal area of shock wave, for example, elongated and / or rounded (cigar-shaped, round, etc.) forms of KNA. This is used by the military: to create rounded tank towers, helmets, which reduce the likelihood of penetration by a projectile or bullet.

d) the conversion of part of the kinetic energy from shock penetration into heat dispersed throughout the body.

A similar increase in impact resistance of objects is widely known on the example of the so-called inclusions - insects, frozen in resin, turned into amber. The impact resistance of such an individual insect is minimal, but, being immured into a single body, it approaches the impact resistance of amber.

Another example is based on the dynamics of bodies immersed in materials, in particular in a liquid, which is realized, for example, by the widespread hydraulic filling of pressure gauges. So the external impact is substantially suppressed, decreases due to the volume of liquid, and with an increase in its density and volume, the values of this decrease also increase (Pavlyuk Yu.S., Sakulin V.D. Dynamics of bodies immersed in liquid / Vestnik SUSU, Series “Engineering ", Issue 8, pp. 15-20.).

To create such an integral single protective body, it is proposed to use distilled water or naphthalene, or solutions based on them. So, three modifications of ice (ice-VII, -VIII, -X) with well-studied properties can be formed from distilled water for both creating ballast 3 and its subsequent removal. The ballast 3 created from distilled water based on such ice will have high strength, protect the payload during impact penetration into the ground, and at the same time it is quite easy to remove, primarily due to heating and active sublimation, without polluting outer space by international agreements.

2. In the device No. 1 it is also proposed to use batteries activated by the transition from the so-called “sleeping” to the operating mode by impact when the device is introduced into the ground. This allows you to significantly save the battery life for the time from the start from Earth to the introduction of the studied celestial body into the ground, which can be about 10 years when studying the moons of Jupiter, Ganymede or Io.

3. In the device No. 1, to increase the duration of work after the penetrator is introduced into the ground, as well as expand the functionality, it is proposed to use cable 16 with the following capabilities:

- (if it is intact) wire communication;

- (if it is broken), a wireless electromagnetic connection between its ends with inductive coupling and / or radio communication and / or waveguide coupling, using its ends as antennas and / or waveguides.

This can minimize the consequences of cable breakage 16, the maximum possible extension of the scientific mission, as well as the optimal use of its resources: the residual capacity of all batteries, processing performance and data storage capacity of control systems 8 and 18, etc.

Assessment of the manufacturability of ballast 3 based on ice-VII and its strength.

Ice-VII can be created by currently existing equipment, for example, the Institute of Nuclear Physics in Heidelberg (Germany), the Institute of High Pressure Physics, Russian Academy of Sciences L.M. Vereshchagin (Moscow), Institute of Spectroscopy of the Russian Academy of Sciences (Moscow), Technological Institute of Superhard and New Carbon Materials (Troitsk) in two versions (https://ru.wikipedia.org/wiki/ Лед_VII, Martin Chaplin. Water Structure and Science, http://www1.lsbu.ac.uk/water/water_strucrure_science_html):

- option 1 (directly):

water compression (at Т≥ + 82 ° С and Р≥2,216 GPa) and ice-VII formation,

- option 2 (in two stages, through the intermediate phase in the form of ice-VI):

water compression (at Т≈ + 27 ° С and Р≥1,1 GPa) and ice-VI formation, ice-VI compression (at Т≈ + 27 ° С and Р≥2,216 GPa) and ice -VII formation.

Ice-VII is formed in the pressure range from 2.216 GPa to ≈70 GPa, therefore, the minimum value of ice strength can also be estimated at 2.216 GPa. In terms of compressive strength, this value is higher than that of high-strength concrete Ml000 (100 MPa), steel (≤1 GPa), diamond (≈2 GPa), slightly inferior to silicon carbide (SiC, carborundum) ~ 2.3 GPa, self-bonding carbide silicon (~ 2.5 GPa) (https://ru.wikipedia.org/wiki/Karborund), but lower than that of trip steel (3 GPa), nickel-graphene composite (4 GPa) or fullerite (150- 300 GPa).

The practical implementation of the invention proposed does not contradict, but is based on the use and is a continuation of the current, already achieved level of development of methods and means in the following fields of technology and technologies: cryogenic technology, space rocket technology, radio engineering, materials science, high pressure technology, etc. .

For electronic systems, the level of maximum overload up to 100000g has been reached by now (the Generator for high-precision ammunition systems can withstand overloads up to 100000g, http://www.iqdfrequencyproducts.com, http://national-semiconductor.datasheet.su/news/2339:2013 -07-11). Therefore, the possibility of using such electronic equipment in electronic units that can withstand large overloads is beyond doubt.

Thus, as can be seen from the entire description, the proposed invention improves the impact resistance of the payload when it is delivered to the soil of celestial bodies with penetration speeds in the range from 300 m / s to ≈4500 m / s; to increase the accuracy of measurements due to direct contact with the soil during the measurement process and the duration of operation after penetrator penetration into the soil, and also extends the functionality due to the possibility of wireless communication for the exchange of signals and electricity between the electrical parts of the device when the cable is broken (for device No. 1).

This invention can be practically implemented in a slightly different way than specifically described, without departing from the essence and in the scope of the claimed formula.

Claims (10)

1. A method of delivering a payload to the soil of a celestial body, providing research of the celestial body and its soil, in which the payload, placed in a protective body pointed at the front and containing ballast, is delivered by the spacecraft from the Earth to the selected celestial body by impacting the device with the surface of the celestial body and shock introduction into its soil, characterized in that they use two sets of scientific equipment to study the parameters of the soil and celestial body, the second of which with additional the capabilities of fixing space events when viewing the starry sky and bidirectional radio signal reception with the Earth and / or the spacecraft, while introducing an electronic unit and a communication unit and placing them in a protective housing, using the tail element into which the second electronic unit is inserted, the second communication unit and a second set of scientific equipment, and attach this tail element to the back of the protective housing with the possibility of separation during the aforementioned shock introduction, and a cable is inserted between the communication units with the possibility of wired and wireless communications, respectively, for the whole and torn cable, while the first set of scientific equipment in the form of a payload is placed inside the ballast, which serves as an additional protective body, and the protective housing is configured to separate it from the additional protective body before, during or after the aforementioned impact penetration or from mechanical destruction during the aforementioned impact penetration, and as a material for ballast, which serves as an additional protective body for the floor of a cargo, use material with the possibility of solidification during the delivery of the payload and its removal after the aforementioned shock penetration into the ground, while in the electronic blocks, batteries are used for power supply, activated by impact with passive, for the time of flight to the selected celestial body, and active operating modes and the possibility of transferring them from passive to active operating modes from the aforementioned shock introduction, and the tail element is separated and fixed with the surface of the celestial body with By reviewing the starry sky with the second set of scientific equipment, the batteries activated from the shock are transferred from passive to active mode during the aforementioned shock introduction, while the ballast with the first set of scientific equipment contained in it is released from the protective housing, the ballast is removed, releasing the payload, moreover, they determine the integrity of the cable and, depending on this, use wired communication between the communication units or create a wireless connection between the ends of the cable by creating an electromagnetic connection between them, and with the help of both sets of scientific equipment, they conduct research, synchronize these studies with each other, record the space events with the second set of scientific equipment and, depending on this, control the synchronization parameters of the complexes of scientific equipment and determine the parameters of the earth and celestial body, as well as the influence space events on them, at the same time they monitor the current value of the accumulated energy to two sets of batteries and set their minimum acceptable levels, upon reaching the cat They transfer electricity to the discharged battery pack from another due to the connection between the communication units of the tail element and the protective casing, moreover, they monitor the current load of the computing operations of the electronic units and ensure their equal values by redistributing the computing operations between the electronic units. 2. The method according to p. 1, characterized in that the ballast, which serves as an additional protective body for the payload, is a modification of ice-VII, or ice-VIII, or ice-X from solid phase states of a liquid or vapor. 3. The method according to p. 2, characterized in that as the material for creating ice modifications use water or naphthalene or solutions based on them. 4. The method according to p. 2, characterized in that the removal of ballast is carried out by heating and evaporation by heating and / or mechanical destruction. 5. A method of delivering a payload to the soil of a celestial body, providing research on the celestial body and its soil, in which the payload is placed in a protective body containing ballast that is pointed at the front and delivered by the spacecraft from the Earth to the selected celestial body by impacting the device with the surface of the celestial body and its shock introduction into the soil, characterized in that the payload in the form of a complex of scientific equipment for studying the soil of the celestial body is placed inside the ballast, which serves for useful cargo additional protective body, while the protective body is configured to separate it from the additional protective body before, during or after the aforementioned shock introduction or from mechanical destruction during the aforementioned shock introduction, and as a material for ballast, which serves as an additional protective body for the payload , use the material with the possibility of solidification at the time of delivery of the payload and its removal after the aforementioned shock introduction into the ground, release ballast with holding in it a complex of scientific equipment from the protective housing, remove the ballast, freeing the payload, and conduct soil research of the celestial body. 6. The method according to p. 5, characterized in that the ballast, which serves as an additional protective body for the payload, is a modification of ice-VII, or ice-VIII, or ice-X from solid phase states of a liquid or vapor. 7. The method according to p. 6, characterized in that as the material for creating ice modifications use water or naphthalene or solutions based on them. 8. The method according to p. 6, characterized in that the removal of ballast is carried out by heating and evaporation by heating and / or mechanical destruction. 9. A device for delivering a payload into the soil of a celestial body, providing studies of the celestial body and its soil, containing a hollow front-protective body, including two internal cavities: a front, pointed in the bow, and a rear cavity, a ballast is placed in the front cavity, characterized in that the ballast is formed from a modification of ice-VII, or ice-VIII, or ice-X from solid phase states of a liquid, or water vapor, or naphthalene. or solutions based on them, a payload is placed in the front cavity inside the ballast, which is a set of scientific equipment for studying the celestial body and its soil, and an ice remover, and in the back cavity of the protective case there is an electronic unit also containing a set of battery, accumulator, activated from impact, and the communication unit, in addition, the device further comprises a tail element made in the form of a cylindrical shell mated to a skirt at the end, while in the cylindrical shell of the tail The second electronic unit containing another set, similar to the aforementioned one, of a battery, a shock activated battery and a communication unit, a device protective housing with a payload placed in its front and rear cavities and an electronic unit with a communication unit, respectively, is also partially located in the cylindrical shell of the tail element with the possibility of axial movement in it and the formation between the electronic unit located in the shell of the tail element and the rear wall of the shield a solid housing, the cavity in which the cable is placed with the possibility of wired communication between communication units with the whole cable or when it breaks the wireless connection between its ends. 10. A device for delivering a payload to the soil of a celestial body, providing research of the celestial body and its soil, containing a hollow front-protective body, including two internal cavities: a front, pointed in the bow, and a rear cavity, a ballast is placed in the front cavity, characterized in that the ballast is formed from a modification of ice-VII, or ice-VIII, or ice-X from solid phase states of a liquid, or water vapor, or naphthalene, or solutions based on them, a payload is placed in the front cavity inside the ballast in the form of a complex of scientific equipment for studying the celestial body and its soil and an ice remover, and an electronic unit and a communication unit are located in the back cavity of the protective case.

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