WO2014062092A1

WO2014062092A1 - Device for ensuring levitation of a craft and method for implementing same

Info

Publication number: WO2014062092A1
Application number: PCT/RU2013/000900
Authority: WO
Inventors: Борис Михайлович СОЛОДОВ
Original assignee: Solodov Boris Mikhailovich
Priority date: 2012-10-17
Filing date: 2013-10-11
Publication date: 2014-04-24
Also published as: RU2012144333A

Abstract

The technical field is that of aviation technology, in particular devices and methods for the levitation of an aircraft above the Earth's surface. What is proposed is: a device for ensuring levitation, said device comprising a superconducting shell (3), within which the concentrated magnetic field of the Earth (14) is arranged. Furthermore, in order to produce a concentrated field (14) in the shell (3) with a cooling system (4), the aircraft (1) is raised to an initial height by a hoist (7), whereupon lowering of the aircraft (1) is begun when the flow of the Earth's magnetic field (8) enters the shell (3) with concentration of this field (14). And when the force from the aircraft (1) being lowered and the force of the pressure of the deformed concentrated magnetic field of the Earth (14) are equal in the shell (3), the aircraft (1) ceases to fall and is suspended at the levitation height, whereupon the magnetic field (8) ceases to be admitted into the superconducting shell (3).

Description

Device for providing levitation of the apparatus

and method for its implementation

The invention relates to transport equipment, in particular to aviation, to devices and methods for providing levitation of aircraft above the surface of a celestial body such as the Earth, which has a magnetic field.

The current level of technology is characterized by a device and method for holding the aircraft in a suspended state above a certain point on the earth's surface, including holding the aircraft by supplying energy from an external energy source and converting it into force on this device, described, for example, in U.S. Patent No. 5,074,489, MKI B 64 C 37/02, NCI 244-2, publ. 12.24.1991, Volume 1 133, 4. ^~

Such a device and method provide levitation of the aircraft, allowing various scientific and technical projects to be determined by the payload on the device. This requires a significant supply of energy from an external source, as well as the introduction of devices that receive energy from such a source, and then convert this energy by virtue of traction to the aircraft.

However, there is a problem of using constant magnetic fields for levitation, which has not found its solution in this device and method.

A device for levitation of an apparatus is known in the art, including a superconducting disk suspended in a constant magnetic field of a magnet, described, for example, in the book of V. Bukkel. Superconductivity. M. Mir, 1975, p. 282-283.

Such a device provides levitation of superconducting disks, which makes it possible to create various technical devices (such as bearings) based on them. This is achieved through a powerful permanent magnet placed on the surface of the Earth.

However, there is the problem of organizing the levitation of a device above the Earth’s surface at high altitude, up to tens of kilometers, which is necessary for many scientific studies that have not found their solution in this known device. A device is known in the art for levitation of an aircraft, taken as a prototype, including an aircraft engine that interacts with the external environment, for example, levitation due to the force when the magnetic field of the apparatus interacts with the surrounding space, described, for example, in book of V.P. Burdakov, Yu.I. Danilov. External resources and space. M. Atomizdat, 1976, p. 444.

Fundamentally, such a device ensures the levitation of an aircraft in a near-Earth magnetic field, which makes it possible to create, for example, scientific and technical laboratories that are stationary relative to a given point in space. At the same time, the real characteristics of the device are low, and the lifting force of a disk-shaped ship with a diameter of 600 m and for 1000 turns with a current of 10 ⁵ A in each turn is only 5.9 N. And only a special construction of diamagnetic sites on the surface of the Earth can dramatically increase the lifting force However, such construction of sites sharply limits the operational capabilities of the device due to the impossibility of rapid deployment of levitation devices in case of need.

A technique is known in the art for providing apparatus levitation, adopted as a prototype, including creating a magnetic field with a permanent magnet, while the pressure of the magnetic field balances the weight of the apparatus, for example, a superconducting disk (serving as a device for providing levitation), described, for example, in book of V. Bukkel. Superconductivity. M. Mir, 1975, p. 282-283.

This method provides the levitation of superconducting disks, which allows the creation of various technical devices (such as bearings) based on them. In this case, a powerful permanent magnet located on the Earth's surface is required.

However, there is a problem of using the apparatus of the earth’s Earth’s magnetic field for levitation, without using other magnets, which has not found its solution in the prior art — devices for organizing levitation.

The present invention solves the problem of achieving the levitation of the apparatus above the Earth’s surface, which leads to a technical result in the form of ensuring the levitation of the apparatus in the Earth’s magnetic field at any height above the surface and reducing the mass of devices that create levitation.

The problem posed is solved by the fact that in the known device for providing levitation of the apparatus, including a device for creating a force of interaction with the environment, the device contains a superconducting shell, inside which the Earth’s concentrated magnetic field is placed, also has a cooling system for this shell. located in the apparatus. The superconducting shell is equipped with a system for opening and closing access of the Earth's magnetic field inside this shell, in short - a field access system.

The superconducting shell is made in the form of a pipe of arbitrary shape, and the applied superconductor layer uses the Meissner effect.

The device, together with the device for providing levitation, is lifted to the initial height by a lifting device, optimally by an aerostat, an airship, an airplane, a rocket, after which the device is launched from an initial height, and at this time the superconducting shell of the device is open for the Earth's magnetic field inside the shell, and when descending to the surface of the Earth, the flux of the Earth’s magnetic field enters the inside of the superconducting shell, and the magnetic flux and deformations are automatically accumulated and concentrated the field of its magnetic lines of force, and when the equality of the force from the descending apparatus and the pressure force of the deformed concentrated magnetic field of the Earth in the envelope is reached, the apparatus stops falling and freezes at a levitation altitude of 0.1 km to 70,000 km above the Earth’s surface .

At the height of levitation, the field access system terminates the Earth's magnetic field access into the superconducting shell of the device to provide levitation.

The apparatus is lowered from the initial height together with the lifting device, and when the levitation height is reached, the lifting device is uncoupled and sent to the surface of the Earth.

The device is uncoupled at the initial height from the lifting device, and the device falls to the surface of the Earth, while the device is equipped with a smooth descent system, optimally with a parachute or engines.

The field access system is made in the form of a section of the shell made of superconducting material, and at the initial height this section of the shell is heated above the critical temperature and is in a normal state, not hindering the access of the Earth’s magnetic field, and when the levitation height is reached, this section is cooled below the critical temperature and translate into a superconducting state, and for this they have a heating and cooling unit of such a section.

The field access system is made in the form of a screen, which is set at an initial height in a position that does not interfere with the access of the Earth’s magnetic field into the shell, and at the levitation height, the screen is set to a position that closes the section between the ends of the superconducting shell and the magnetic field is no longer accessible inside the shell the screen itself has a superconductor layer or a layer of a ferromagnetic alloy, and the screen is displaced by the locking mechanism of the field access system. Here, for the apparatus levitation (includes a payload, control systems, a device for providing levitation, etc. systems), the energy of the Earth’s concentrated magnetic field is applied, the flux of which is collected and placed in the superconducting shell of the device for providing levitation. In this case, the pressure (tension) of the deformed magnetic field lines of the concentrated field holds the superconducting shell, and, accordingly, the apparatus itself (any design) in the Earth’s magnetic field above its surface. And to ensure long-term operation of the superconducting shell and levitation of the apparatus, this shell has a cooling system located in the apparatus (one of the apparatus systems).

The superconducting shell is equipped with a system for opening and closing the access of the Earth's magnetic field inside this shell, in short - a field access system that first provides the necessary access to the field inside the shell and field concentration, and then, if necessary, closes the field’s access, providing the constancy of the concentrated field inside the shell during prolonged levitation.

The superconducting shell is made in the form of a pipe of arbitrary shape, for example, rectangular, ellipse, etc., and the superconductor layer used uses the Meissner effect, which expels the magnetic field from the bulk of the superconductor and holds this field inside the pipe.

The apparatus, together with the device for providing levitation, is lifted to the initial height by a lifting device, optimally by a balloon, airship, airplane, rocket. At the same time, a balloon, an airship and an airplane are used to lift to a height of 10 ... 40 km, and a rocket - to any height (theoretically), for example, hundreds of kilometers using a geophysical rocket. Then, at this initial altitude, the alpine begins to fall, descent to the surface of the Earth. Moreover, at this time, the superconducting shell is open for access of the incident magnetic field inside the shell, and when the apparatus is lowered into the shell, the flux of the Earth’s magnetic field enters. In this case, the magnetic field flux is automatically accumulated and concentrated, and its magnetic field lines are deformed. And when the force is equal between the descending apparatus and the pressure (tension) force of the deformed concentrated magnetic field inside the shell, the apparatus stops falling and freezes at the level of levitation (the point of equal forces). In this case, the levitation altitude, depending on the initial elevation and requirements for the operation of the apparatus, ranges from 0.1 km = 100 m (lower limit) to 70,000 km, which is a theoretical upper limit equal to the boundary of the Earth’s magnetosphere ( topause), and the optimal real range is from 1 km to 500 km. At the height of the device’s levitation, the access system of the device’s field to ensure levitation terminates the Earth’s magnetic field access into the superconducting shell, closes the shell (makes it closed). And this provides a stable concentrated field inside the shell during prolonged levitation.

The device is lowered from the initial height together with the lifting device, and when the levitation height is reached, the lifting device is uncoupled and sent to the Earth's surface, leaving the device at the levitation height.

In another embodiment of the descent, the apparatus at the initial height is disconnected from the lifting device, and the apparatus falls to the surface of the Earth, while the apparatus is equipped with a smooth descent system, optimally with a parachute or engines, which reduce the descent speed of the apparatus.

The field access system (shortened version, fully - the system of opening and closing the Earth’s magnetic field access inside this shell) is made in the form of a section of the shell (the lower plane of the shell during descent) of superconducting material, and at the initial height this section is heated above the critical temperature and is in a normal state, without preventing the Earth’s free magnetic field from going inside the superconducting shell (the “heat key” principle in the superconducting technique). Upon descent and reaching a levitation altitude with the apparatus freezing, this part of the shell is cooled below the critical temperature and transferred to the superconducting state, thereby obtaining a closed superconducting shell and locking the concentrated magnetic field inside this shell. For thermal effects on the regulated section of the shell in such an access system there is a heating unit (heater) and a cooling unit (source of liquid helium) of such a section.

In another embodiment, the field access system is made in the form of a screen, which, at the initial height and the descent stage, is set to a position that does not interfere with the access of the Earth's magnetic field inside the shell. And at the height of levitation, such a screen is installed in a position that closes the area between the ends of the superconducting shell (the shell becomes closed), and such a screen prevents the concentrated field from leaving the shell. Such a screen is made either with a layer of superconducting material, which is transferred to the superconducting state at the initial or levitation altitude (optimal variant), or the screen is made of a ferromagnetic alloy (soft magnetic alloys for ferromagnetic screens).

A comparative analysis with the current level of technology shows that the concentration of the earth's magnetic field and its use for levitation of the aircraft is provided by considered elements of the device and manipulations with them, as well as the considered operations in the method. Thus, the claimed device and method for its implementation meet the criterion of "novelty". Also, a comparison of the parameters and elements of the proposed solution with those known in the art allowed us to conclude that the criterion “inventive step” was met. In addition, all applicable elements correspond to the current state of the art, and the Earth’s magnetic field itself occupies all the space above the Earth’s surface; therefore, the proposed solution is feasible in any place and region of the Earth, which allows us to conclude that the criterion is “industrial applicability”.

The proposed device for ensuring the levitation of the apparatus and the method for its implementation are illustrated by the drawings in FIG. 1, FIG. 2, FIG. 3, FIG. 4 and FIG. 5.

In FIG. 1 shows the position at the initial height, in which the apparatus 1 includes a device for providing levitation 2, containing a superconducting shell 3 with a cooling system 4, an access system for the field 5 and a smooth descent system 6, transported by the lifting device 7, located in a magnetic field Earth 8 above the surface of the Earth 9.

In FIG. 2 shows a cross section of a superconducting shell 3 with an access system of field 5 with a section of superconducting material 10 and a heating and cooling unit 11.

In FIG. 3 shows a cross section of the superconducting shell 3 and the access system of field 5 with various options for the initial position of the screen 12 and the locking mechanism 13 at the initial height.

In FIG. 4 shows the final position at the height of levitation, in which the apparatus 1 includes a device for providing levitation 2, containing a superconducting shell 3 with a cooling system 4 and an access system of field 5, holding a concentrated magnetic field 14 captured during descent, located above the Earth’s surface for 9 s Earth's magnetic field 8.

In FIG. 5 shows a cross section of the superconducting shell 3 and the access system of the field 5 at the height of levitation with the final position of the screen 12, regulated by the locking mechanism 13.

In operation according to FIG. 1, at the first stage, the apparatus 1, together with the attached levitation device 2, containing a superconducting shell 3 with a cooling system 4, a field access system 5 and a smooth descent system 6 are transported by a lifting device 7 to an initial height with a magnetic field 8 relative to the Earth’s surface 9. After that, the lifting device 7 is disconnected from the device 1 with the device 2 and sent to the destination on the surface of the Earth 9. In this case, the device 1 with the device 2 using smooth descent systems 6 begin descent, a smooth fall to the surface of the Earth 9 in the Earth’s magnetic field 8. And when descent inside the superconducting shell 3 through the access system of field 5, the magnetic field of Earth 8 automatically enters, and accumulation and concentration occurs magnetic field 8.

In another variant of the method, the apparatus 1 with the device 2 is lowered to the surface of the Earth 9 with the help of a lifting device 7, in which the lifting force is changed, and when they are combined smoothly falling inside the superconducting shell 3, the Earth’s magnetic field 8 automatically enters through the field 5 access system, this leads to the accumulation and concentration of the magnetic field 8. Upon reaching the height of levitation, the lifting device 7 is disconnected from the apparatus 1 and sent to the destination on the surface of the Earth 9.

At the same time, at the initial height, according to FIG. 2, the superconducting shell 3 with the field 5 access system has a section of superconducting material 10, heated above the critical temperature and in a normal state, freely passing the magnetic field 8 into the shell 3, and heating of the section 10 provides a heating and cooling unit 11 .

In another embodiment, at an initial height according to FIG. 3, the superconducting shell 3 has a field tolerance system 5 comprising a screen 12 of superconducting material or a ferromagnetic alloy with the possibility of moving the screen 12 by the locking mechanism 13. Moreover, at the initial height, the screen 12 is located so that it does not interfere with the passage of the magnetic field 8 inside the shell 5, including for different options a) and b) the position of the screen 12, and where, according to option b) the screen of two planes 12 is located at an angle to the surface of the shell 3.

The descent of apparatus 1 with device 2 continues to the final position at the height of levitation. And in FIG. 4 shows the final position of the apparatus 1 and device 2. Here, the apparatus 1 is connected to a device 2 containing a superconducting shell 3 with a magnetic field 14 captured during descent, and for this, a cooling system 4 for the shell 3 is provided for long-term levitation. the apparatus 1 with the device 2 hangs at a height of levitation above the surface of the Earth 9 with the magnetic field of the Earth 8. In this case, the access system of the field 5 stops access of the magnetic field 8 into the shell 3 and at the same time holds the captured concentra This field 14 inside the shell 3.

At the height of levitation, in the final position, according to FIG. 2, the portion of the superconducting material 10 is cooled below the critical temperature by means of the heating and cooling unit 11 and transferred to the superconducting state in which the access system of the field 5 with the superconducting section 10 does not pass the magnetic field 8 inward shell 3 and at the same time does not release the magnetic field 14 from the shell 3.

In FIG. 5 shows another embodiment of the access system 5, in which, at a levitation altitude, the screen 12 is moved and closed between the ends of the superconducting shell 3 by means of the locking mechanism 13. Thus, such a screen 12 closes the access to the inside of the shell 3.

Note that in the final position at the levitation altitude, the apparatus 1 and device 2 do not require a smooth descent system 6 according to FIG. 1, therefore, in FIG. 4 this system 6 is absent, and the smooth descent system 6 itself is removed to the surface of the Earth 9 after arriving at the levitation altitude and closing by the access system of field 5 of the concentrated magnetic field 14 inside the shell 3.

An embodiment of the invention.

Let us consider the levitation of an aircraft (hereinafter - LA) in the upper layers of the Earth's atmosphere using the Earth's magnetic field (hereinafter - MPZ).

During the concentration and deformation of the MPZ and its placement in the superconducting shell, a lifting force arises from the side of the magnetic field, which compensates for the gravitational force on the aircraft, which then hangs and levitates.

This is due to the fact that the mechanical forces acting in a magnetic field are reduced to tension T along the field and pressure P in the perpendicular direction. Tension and pressure, referred to the unit of area on which they act, are numerically the same and equal to the density of magnetic energy in the medium (GHS, SI - systems of units).

Such a magnetic field has a magnetic line tension force, and when this field is applied, the field lines become curved, and the corresponding magnetic force always turns out to be in the direction opposite to the field line curvature. Moreover, this tension force tends to return the lines of force to their original position and thereby compensates for the force of gravity — the weight of the aircraft, ensuring its levitation.

The main structural element is a superconducting shell made in geometry (section) in the form of a pipe of arbitrary shape (specified by the developers). Consider the design of such a shell, with its elements and materials.

Levitation requires reliable placement of the concentrated MPZ in a closed shell and long-term field retention in this shell. And this requires the use of a layer of superconducting material on the surface of a closed shell. The depth of penetration of the magnetic field into type 1 superconductors does not exceed 100 nm; therefore, it is sufficient to use films of a superconductor 1– ^ 50 μm thick deposited on a copper or aluminum foil. Of the superconductors providing the full Meissner effect, the most optimal are niobium with a critical temperature Tc = 9.3 K and a critical field H _C o ⁼ 1980 e; technetium with a value of T _c = 7.8 K and a critical field H _C o ⁼ 1410 Oe However, it is possible to use alloys of type 2 superconductors in which there is no complete Meissner effect in the entire range of parameters of the superconductor, and there is a complete effect in a limited range of parameters, but they have a high critical temperature of loss of superconductivity, which reaches T _c = 23 for films , 2 K. And also superconductors provide levitation in a certain range of magnetic field parameters, as well as due to the thick layer of the superconductor for a certain time. We note the promise of using multicore tapes and cables, consisting of many (up to thousands) of individual thinnest wires of superconducting alloy, which have excellent characteristics for use in time-varying magnetic fields. A combination of different types of superconductors is also possible, for example, a niobium or technetium foil with an NbN film or the like. alloy, or tape on foil, etc. combinations. Note that high-temperature superconductors that do not lose superconductivity in strong magnetic fields up to the level of 20 ° C T at a critical temperature T _with more than 30 K (cooling with liquid hydrogen) are also interesting. For example, these are superconducting magnesium diboride ribbons MgB ₂ with T _c = 35 ... 39 K, with a critical current density of about 220 A / mm ² , with a length of up to 10 m and more. Moreover, the nomenclature of high-temperature superconductors is already quite large, and their properties are constantly improving, so in the future it is realistic to use these superconductors in a closed shell.

However, here we consider a variant of traditional superconductors, combinations of different types, for use in a closed shell. For example, a combination of a foil made of niobium or technetium with an alloy of the 2nd kind - ribbons (of different composition). Considering the need for long-term operation of the closed shell, we assume that the average working field inside the closed shell is equal to H _M o ^~ 10,000 e = 8 · 10 A / m. In this case, the average pressure of the concentrated field inside the shell is P _M o = 4 10 N / m ² , and the energy density of such a field is ω _Μ0 = 4 - 10 J / m.

Note that the choice of the absolute values of the envelope area depends on the tasks being implemented and is determined by the specific structures of the levitating aircraft.

Ideal lift F

F = PMO 'SB (2) where P _m0 - pressure concentrated MPZ;

S _B is the area of the perceptual surface of the shell.

For example, at S _B = 10 m we have the value F = 10 N N, which corresponds to the weight of an aircraft with a mass of 4 · 10 ³ kg = 4 t, and for SB - 100 m ² we have F = 10 ⁵ N, which corresponds to the weight of an aircraft with a mass of 4 · 10 ⁴ kg = 40 t.

The shell design is similar to the known superconducting devices and includes a foil of aluminum or copper, 0.1 + 0.5 mm thick, on which a superconductor layer is deposited (on the one hand is niobium, on the other is an alloy of the 2nd kind) with a total thickness of 1 + 100 microns. This foil is enclosed in an airtight shell, which in turn is fixed inside the housing. At the same time, there is a gap between the surface of the foil with a superconductor and a sealed sheath, a gap that is a channel for a cooling agent - liquid helium. Moreover, between the surfaces of the sealed enclosure and the housing there is a vacuum, and in this space additional film heat-shielding intermediate screens can be installed that reduce heat transfer from the enclosure to the sealed enclosure.

It is from the requirements of thermal protection that the design of the outer surface of the casing of the sealed enclosure is revealed — aluminum foil 0.1-mm thick, to which a selective coating is attached, for example, 150 microns thick fiberglass is glued through a layer of silver or aluminum in 1 μm, and this coating provides the absorption coefficient of solar radiation is a $ ~ 0.06 with a surface emission coefficient for the infrared range of radiation ε ~ 0.90. Naturally, other designs of selective coating are possible, providing approximately the same parameters, but here for evaluating the parameters we accept a similar coating.

For the inner surface of the case with an electropolished surface, as well as for the niobium coating of the hermetic shell, we obtain a heat flux from the body to the hermetic shell of the order of 0.04 W per 1 m ² , which is still reduced by 1.5 + 3 times due to the introduction of intermediate heat-shielding screens. And taking into account the additional heat flux from the rarefied atmosphere and from the Earth, the real heat flux is about 0.04 + 0.06 W per 1 m ^{2 area} .

Estimation of the average weight of 1 m ^{2 of the} shell, including a foil body with a thickness of 0.5 mm, gives a mass of about 6 kg, and taking into account heat shields - about 7 kg, and taking into account a helium layer of 5 + 8 mm, medium - the net weight of the wire is about 8 kg for an area of 1 m ² . Given the range of applied design solutions, materials and technological capabilities of production, the real mass of the closed shell in the range of 5 + 15 kg per shell area of 1 m ² . As an example, consider a closed shell with a total area of S ₀ = 50 m. We accept this shell in the form of a rectangular pipe with two parallel long sides a = 6 m (length) and a shell width c - 3.5 m with side walls with a height of b ~ 1, 2 m. From the end faces with area a x b, this closed cavity is open for free placement of the lines of power of the MPZ. This design corresponds to the area of the receiving shell S _B = a x c = 21 m ² , then the ideal lifting force is F = 8.4 · 10 ⁴ N, which corresponds to the levitation of an aircraft with a mass of up to 8.4 · 10 kg = 8.4 t. For such a shell, its mass is 300 ... 750 kg, of which up to 50 kg is liquid helium. In this case, the heat flux to the shell with a superconductor is Qn— 2 W. For such a heat flux, 50 kg of liquid helium provide cooling of the shell for 400 + 900 hours ~ 15 + 40 days. Therefore, an insulated container with liquid helium reserves is additionally installed on the aircraft, for example, 500 kg is enough for 3 + 9 months. And at the end of this helium supply, a new tank with a new helium supply is delivered to the aircraft.

However, for prolonged levitation of an aircraft, it is more promising to use cooling with the help of a refrigerating machine, which currently has several varieties. For a chiller with a power of 2.1 W at a temperature of ~ 4.5 K, the power consumption of such plants is 3 + 3.5 kW with a mass of 250 + 400 kg, depending on the design and materials used.

For long-term power supply of such a refrigerating machine, it is optimal to use a solar battery on solar cells with a mass of 50 ^ -100 kg, depending on the type, efficiency and perfection of the design used. And taking into account the need for an electric battery to provide shade, other auxiliary electrical converters, power elements and thermal devices, the total mass of the power supply system of the refrigeration machine is about 300 + 500 kg.

So, for the total shell area Sc = 50 m ^{2, the} total mass of the superconducting shell together with the cooling system, including either a container with a supply of liquid helium or a refrigerating machine with an energy supply system, is 900 + 1700 kg, and depending on the structural perfection of all devices.

Immediately, we note that the aircraft is necessarily equipped with a parachute system for launching the aircraft in the event of an accident. In addition, there is also a power structure made of lightweight high-strength materials, such as carbon plastics, for mounting aircraft systems. And therefore, with the weight of the closed shell and the systems serving it up to 900 + -1700 kg, the total mass of the aircraft design will be 1200 + 2000 kg.

Thus, the capture and deformation of the field lines when concentrating the magnetic field allows using the obtained field for aircraft levitation. Here, the captured deformed MPZ, concentrated inside the superconducting shell, has a tensile force, which tends to return the lines of force to their original position. And this tension force compensates for the force of gravity - the weight of the aircraft, ensuring its levitation. Considering the capture of field lines from a large area and the rather complicated nature of the distribution of curved field lines in space, it is mathematically difficult to describe the tension force of magnetic lines for a given physical case with a simple formula. However, in a first approximation, it is possible to estimate the lifting force by the pressure gradient of the concentrated magnetic field, in particular, by the average field with pressure P _mo . Given the estimated nature of these physical calculations, in reality the mass of aircraft kept in the range from 7000 kg to 8400 kg , that is, up to 80-100% of the ideal value of the lifting force F for the magnetic field inside the shell.

Naturally, the actual retained mass of the aircraft depends on the optimization of the geometric dimensions of the closed shell, as well as on the shape and ratio of the dimensions of the shell, the position of the shell and its geometric elements relative to the Earth’s magnetic field, and the obtained field geometry inside the shell. The applied design of the closed shell also affects its perfection and refinement of the structural units.

Let us evaluate the parameters of the Earth’s magnetic field necessary to obtain a concentrated magnetic field inside a closed superconducting shell.

For a magnetic field, the law of constancy of the magnetic flux Ф ₀ = const, where Ф ₀ - BS, and J? = μμοΗ. Then, the ratio of the concentrated field in the shell to the free SCF (as for a magnetic pump, etc. systems)

where S3 is the area of the taken and concentrated flux of the free earth's magnetic field with intensity Нз,

S _K is the cross-sectional area of the open end of the shell with a x b geometry with a concentrated field N _mo .

Actually, dependence (3) is similar to the dependence for a magnetic pump concentrating a weak magnetic field into a strong one (difference in scale).

Undoubtedly, levitation of aircraft over a region with a magnetic anomaly is very promising, for example, in the region of the Kursk magnetic anomaly, where the magnetic field exceeds 100 A / m. However, here we consider a real version of the Earth’s average magnetic field, which ensures the levitation of aircraft. For the magnetic field, the magnetic equator is about 27, 1 A / m, and at the magnetic poles is about 52.5 A / m, then the average Earth’s magnetic field is assumed to be equal to H ₃ = 40 A / m (near the Earth’s surface )

Then the ratio of the magnetic fields inside the shell with the average And mo - 8 · 10 ⁴ A / m and the average Earth’s H ₃ = 40 A / m is ~ 2000, respectively, and the ratio of the areas of free MPZ S ₃ to the area of the concentrated field S _K is ~ 2000 (more precisely, 1999).

Then the necessary height of the fall of the aircraft (in a first approximation) AN _p is

ДЯ „= - - ^ (4)

"λ H ₃

where b is the height of the side surface of the shell;

λ is the ratio of the area of the free MFZ S _3M field passing through the access system to the area of the field S _B ^~ x c concentrated in the shell.

For the variant H = 1, 0 and the example of a rectangular shell with b = 1, 2 m, we obtain

AN = \, 2 ~ (5)

And for N _m0 1 H ₃ = 2000 we get AN _p = 2400 m = 2.4 km, that is, the height of the aircraft fall will be 2.4 km. This means that the initial elevation of the aircraft (with the help of a lifting device) must exceed the levitation height of the aircraft by 2.4 km. The value of H ₃ ~ 40 A / m corresponds to a relatively low level of levitation altitude - up to 100 km from the Earth's surface.

For large heights of levitation, more than 10,000 km, the free MPZ drops significantly to the level of H ₃ ~ 1 ... 0.02 A / m, then the required height of the aircraft’s fall increases to the level of 100 ... 1000 km, which is quite real.

Thus, the initial height of the Nile of the aircraft lift is equal to the sum of the required levitation height N _l plus the required drop height AN „, which ensures the capture and concentration of the required MPZ value:

N _nl = N _l + AN _p (6)

We emphasize that the fall of the aircraft continues right up to the point in time when an equilibrium is established between the tension force of the captured concentrated MPZ and the weight of the aircraft. This ensures the levitation of the aircraft in the MPZ (at a height close to the calculated one according to formulas (5) and (6)) · However, in the general case, the access system of the envelope field may have a site for free passage of the SMF with a smaller or larger cross-sectional area than SB, THEN there are possible options I <1 or I> 1.

For the design of the shell with the “heat key”, when the lower plane of the shell has sections both in the normal state and in the superconducting state, the surface area that allows free MFL is smaller than the area S _B , then we have the value of R <1 up to I ~ up to 0.5 ... 0.9. However, of course, the optimal variant of the shell is Я = 1, 0 (the entire lower plane of the shell is in a normal state).

For a variant of a shell with a screen, it is possible to obtain a value of H> 1. In this case, the screen in the initial position is set in the form of a conical surface, while the total area between the edges of the 2 halves of the screen can exceed the area S _B , and this is relative I ~ 1, 5 ... 3.0. This option is interesting for the organization of aircraft levitation at high altitudes, with a levitation altitude of H _L > 100 km, where the atmosphere is practically negligible, there is a vacuum, and there is no air resistance to the fall of the shell from the aircraft. This ensures a decrease in the height of the fall of AN _{P by a} factor of 1.5–3, which is of interest, since it is possible to reach the initial height by a geophysical rocket or the like. a device that has restrictions on lifting height and lifting capacity.

There is also a system for organizing a smooth descent of an aircraft from an initial altitude, with the descent speed reaching a levitation altitude of V _C n ~ 0.1 ... 1 m / s. This ensures a decrease in the amount of movement of the aircraft during a fall, which also needs to be compensated for by a concentrated MPZ (it is the inertia of the falling aircraft that increases the height of the aircraft’s fall compared to the calculated height according to formula (4)).

An ideal variant of launching an aircraft is that the lifting device, after climbing to its initial height, begins to descend to the Earth’s surface, together with the aircraft mounted on the lifting device. And after the descent to the levitation altitude, when the necessary concentrated MPZ accumulates in the shell, the lifting device detaches from the aircraft, which remains levitated, and the lifting device continues to descend to the Earth's surface. In this embodiment, the use of a high-altitude balloon (lift altitude up to 30 ... 35 km) or an airship is optimal. The advantage of this option is full control of the aircraft descent process, the ability to control the speed of the aircraft fall using an aerostat or an airship, up to the possibility of a complete stop at the levitation altitude, and measurement of the field inside the shell over the entire area of the fall.

Another option for organizing a smooth descent of an aircraft is the use of a parachute. This option is the only one when using the aircraft in as a lifting device. At the same time, at the initial altitude, the aircraft is simply unhooked from the aircraft, and at the beginning of free fall the aircraft is parachuted, which will ensure a smooth descent of the aircraft to the levitation altitude. And at the height of levitation, when the aircraft hangs, it begins to levitate, this parachute is shot, dropped to the surface of the Earth. In principle, the use of a parachute is also applicable to balloons and airships as a lifting device (which simplifies the requirements for them). As a parachute, well-known structures are used, for example, parachutes for dropping military equipment, high-altitude parachutes, etc., and optimally high-altitude parachutes for lowering spacecraft compartments (such as Soyuz, etc.).

Another option for organizing the launch of an aircraft is the use of brake rocket engines. This option is the only one when using rockets as a lifting device for lifting aircraft to a height of more than 50 km, theoretically - up to tens of thousands of kilometers. In this case, the aircraft is equipped with either one engine or a system of small engines that are switched on periodically (after 1 ... 100 sec), slowing down the aircraft’s fall and compensating for the inertia of the falling aircraft. At the height of levitation, the brake engines also work, practically stopping the movement of the aircraft, and then the aircraft levitates, while the concentrated MPZ in the shell compensates for the weight of the aircraft.

A variation of this option is a more complex method - a geophysical rocket rises vertically up to its initial height, and then begins to gradually descend on its engines to the aircraft levitation altitude.

Actually, it is the complexity of organizing the smooth descent of the aircraft at high altitudes that gives interest in creating a shell with a screen with a large coefficient> 2.0, since this simplifies the missile braking of the falling aircraft at high altitudes. For example, the time of filling the shell with concentrated MTF for λ = 2.0 decreases by ~ 2 times, and this accordingly reduces the operating time of the braking rocket engines and their used fuel.

Thus, the current level of technology provides a smooth descent of the aircraft from the initial height to the height of levitation. Well-known designs of airplanes, balloons, airships, rockets, etc. are applicable here. devices, with some modifications (for mounting an aircraft, etc.). Moreover, this is a simple operation for organizing aircraft levitation in an air atmosphere (up to altitudes of 20 ... 30 km), and a rather complicated operation for organizing aircraft levitation at high altitudes, outside the atmosphere, although it is technically feasible for an altitude of thousands of kilometers ( for modern rockets) and more. At the height of the aircraft levitation by the access system, the device’s fields terminate the MFD access into the superconducting shell, close it, and make the shell closed to the MFB.

The shell design is made in the form of a pipe, in the general case an arbitrary section (ellipse, square, etc.), and here, for example, a rectangular pipe with dimensions a x b x c. In this case, the shell has a field access system for the on-going free MPZ, and this system has different versions.

The first version of the design — the lower plane of the shell — allows us to implement the principle of the “heat key” (see the book by V. Bukkel. Superconductivity. M. Mir, 1975, pp. 290-292, 314). Here, in the initial position at the height of Nnl, the lower plane is in a normal state, at a superconductor temperature of 25 ... 40 K (for traditional superconductors). And after falling and stopping at the height of levitation N _l in the shell, a fast transition of the lower plane to the superconducting state is carried out. To do this, a cooling agent, liquid helium, is supplied through the gap (between the foil surface and the sealed shell), which quickly, in 0.1 ... 5 sec (depending on the intensity of the liquid helium flow) transfers the superconductor of the lower plane to the superconducting state. For this cooling (from 25 ... 40 K to 5 ... 9 K), a capacity with liquid helium of 5 ... 10 kg is sufficient, after which the lower plane becomes superconducting. And this will provide further long-term retention of the concentrated SCF inside a closed shell with superconducting coatings. In this case, the access of the MPZ to the inside of the shell from the outside, outside the volume of the shell, automatically stops.

This design of the shell field access system is extremely simple, including, in addition, only a container with helium for quick cooling of the lower plane. And also a heater can be installed, providing heating of the lower plane to a normal state at the initial height.

The second version of the design is more complicated, and the access system of the field is in the form of a screen, which at the initial height and the descent stage is set to a position that does not interfere with the access of the MPZ inside the shell. And at the height of levitation, such a screen is moved and installed in a position that closes the portion of the lower plane of the shell, providing a completely closed shell. Such a screen is performed, for example, with a layer of superconducting material that is in a superconducting state at a levitation altitude, moreover, this superconducting state is made either in advance - at an initial height (and the screen descends in this state), or at a levitation altitude it is cooled to superconducting state due to pumping of liquid helium. In another embodiment (for λ = 1, 0), given the rather weak concentrated magnetic core inside the shell and the tension of the magnetic core lines with pressure on the upper receiving plane of the shell, such a screen is made of a ferromagnetic alloy (soft magnetic alloys for ferromagnetic screens). Such a ferromagnetic screen is structurally simple, without requiring cooling to cryogenic temperatures.

Of these 2 screen options, the superconducting screen is optimal, allowing at high altitudes to obtain an expansion of the area S _{3M of the} captured free MPS and obtaining R> 1.0, while the screen is made superconducting already at the initial height and the descent stage (this ensures concentration free MPZ with a large area and more quickly). In addition, the superconducting screen guarantees the retention of the concentrated SCF inside the shell for a long time, up to several years. A ferromagnetic screen does not guarantee long-term retention of the concentrated MPZ, however, its use is quite possible in any use cases of the aircraft (for short-term operation of the levitating aircraft).

We note an interesting version of the design of the screen from 2 planes, when one plane is made of a ferromagnetic screen and the other plane is made with a layer of superconducting material. Such a screen is applicable for the case with λ = 1.0 (and not applicable for λ> 1, 0), when the screen does not interfere with the flow of the Earth’s magnetic field into the envelope, but does not allow an increase in the area S3 _M due to asymmetric interaction free flow field and screen planes from different materials.

Structurally, the screen is made in the form of one or two planes (for the considered example of a rectangular shell). In this case, for the option with H = 1, 0, the screen is made in the form of one plane (optimal option) or 2 planes.

For a design variant with H> 1.0, the screen is made in the form of 2 planes, and their sizes correspond to the dimensions of the receiving shell 5e = A x s, and for example we have a = 6 m and c = 3.5 m. For To estimate the parameters, we represent the screen in the form of 2 symmetrically located identical planes with dimensions a x c, located at an angle of 45 ° to the edges of the edges of the lateral planes of the shell. Then the size of the area of interaction with free MPZ is a = 6 m, and the value c '= c + c sin45 + c sin45 = 2.4 s. Thus, the area of the captured free MPZ S _3M = a x c '= 2.4 S _B. And after reaching the levitation altitude, these planes are alternately closed, laid on top of each other, and at the same time form the lower plane of the shell (from 2 planes of such a screen).

To close the screen (one or two planes (flaps) of the screen) there is a locking mechanism. The size of the plane a x c (here 6 x 3 m) and the small mass of the plane allow the use of various design of locking mechanisms. Of the similar structures, we note the numerous control mechanisms, in particular, locking devices for airtight doors of transport aircraft, open during cargo loading and hermetically closed before flight. At the same time, various types of drives and types of thrusts are used in airplanes (tubular - shafts, flexible in the form of cables, steel tapes, etc.), power motors, hydraulic boosters, and there are also automatic actuating mechanisms that allow changing the position of doors, closing Cove (plane), etc. Naturally, there are other designs of similar locking mechanisms used in the technique that can be used here as well.

We emphasize that the simple design of the screen (plane of small mass) does not require any new and original designs of locking devices, and quite well-known designs from aviation and other industries.

We will evaluate the possibilities of organizing the levitation of the apparatus using a rocket. Note that the kinetic energy Ek ⁼ mV ^2/2 and the potential energy of a body in a uniform field (in first approximation) by the Earth's gravitational E _n = rri _g h. Therefore, for example, the Soyuz rocket, which launches into a circular orbit with an altitude of 250-400 km, an apparatus weighing ~ 6 ... 6.5 tons with a circular speed of V ~ 8 km / s, for the option of use as a geophysical rocket (with a vertical flight path) with the same energy transferred to the device from the side of the rocket (that is, Е _к + Е „= Е _п ), it will be able to lift such a device to the initial height ~ 3 ... 3,5 · 10 ⁶ m = 3000 -3500 km. The energy of more powerful missiles will be able to further increase the initial elevation. Thus, depending on the rockets used, from geophysical rockets (Vertical type) with a lift height of ~ 500 km to more powerful rockets, a rocket lift height of ~ 3,000 km (for the Soyuz) and up to 10,000 km and more (“Proton”), theoretically - up to tens of thousands of kilometers. In this case, it is possible to start both from the land surface and sea launch (from the platform, from a submarine, etc.), and later on - an air launch (from a cargo plane, etc. devices), which allows you to create levitation devices (stations) in different places and at different heights.

Thus, the current level of technology provides for the creation of levitation apparatuses in a wide range of heights above the Earth's surface. Moreover, this is a simple operation for the levitation of an aircraft in the air (up to an altitude of 20 ... 30 km) and quite complicated for the organization of levitation of an aircraft at high altitudes, outside the atmosphere, up to hundreds, thousands of kilometers (and theoretically, tens of thousands of kilo- meters) above the Earth’s surface in the MPZ.

Thus, the proposed device and method solve the problem of organizing the levitation of devices in the Earth's magnetic field based on concentrated and deformed Earth’s magnetic field using a superconducting closed shell. Moreover, the method allows organizing the levitation of vehicles in a wide range of heights, from 0.1 km to thousands of kilometers (theoretically - to the boundary of the Earth’s magnetosphere ~ 70,000 km) above the Earth’s surface. Such levitating devices (stations for various purposes) will find application in scientific experiments, as well as in various branches of technology.

So, the proposed device for ensuring the levitation of the device and the method for its implementation are completely realistic for the modern level of industry, meeting the requirement of “industrial applicability”, and will find application in various fields of science and technology.

Claims

CLAIM

1. A device for providing apparatus levitation, including a device for creating a force of interaction with the environment, characterized in that the device contains a superconducting shell, inside which a concentrated magnetic field of the Earth is placed, also has a cooling system for this shell located in the apparatus.

2. The device according to claim 1, characterized in that the superconducting shell is equipped with a system for opening and closing access of the Earth's magnetic field into this shell, in short - a field access system.

3. The device according to claim 1, characterized in that the superconducting shell is made in the form of a pipe of arbitrary shape, and the applied superconductor layer uses the Meissner effect.

4. A method for implementing the device according to claim 1, characterized in that the apparatus, together with the device for providing levitation, is lifted to the initial height by a lifting device, optimally an aerostat, an airship, an airplane, a rocket; after which the device starts to descent from the initial height, and at that time the superconducting shell of the device is open for the Earth’s magnetic field to enter the shell, and when it descends to the Earth’s surface, the Earth’s magnetic field flows into the superconducting shell, and the automatic accumulation and concentration of the magnetic field flux, deformation of its magnetic field lines, and when the force from the descending apparatus and the pressure force of the deformed concentrated magnetic field Ze are reached If the device stops falling in a shell and freezes at a levitation altitude of 0.1 km to 70,000 km above the Earth’s surface.

5. The method according to p. 4, characterized in that at the height of levitation by the field access system, the Earth’s magnetic field is terminated from entering the superconducting shell of the device to provide levitation.

6. The method according to claim 4, characterized in that the apparatus is lowered from the initial height together with the lifting device, and when the levitation height is reached, the lifting device is uncoupled and sent to the Earth's surface.

7. The method according to claim 4, characterized in that the apparatus at the initial height is uncoupled from the lifting device and the apparatus falls to the surface of the Earth, while the apparatus is equipped with a smooth descent system, optimally with a parachute or engines.

8. The method according to p. 5, characterized in that the access system of the field is performed in the form of a portion of the shell of superconducting material, and at the initial height, this portion of the shell is heated above the critical temperature and is in a normal state,

SUBSTITUTE SHEET (RULE 26) without hindering the access of the Earth’s magnetic field, and when the levitation height is reached, this section is cooled below the critical temperature and transferred to the superconducting state, and for this they have a heating and cooling unit for such a section.

9. The method according to p. 5, characterized in that the access system of the field is made in the form of a screen, which is set at an initial height in a position that does not interfere with the access of the Earth's magnetic field into the shell, and at a levitation height, the screen is set to the position closing between the ends of the superconducting shell and stop the magnetic field from entering the shell, while the screen itself has a superconductor layer or a layer of a ferromagnetic alloy, and the screen is moved by the locking mechanism of the field access system.

SUBSTITUTE SHEET (RULE 26)