WO2007084092A1 - Method for producing a thrust force by coriolis forces , a 'gydroturbine ' device for carrying out said method and a transport means based on the 'hydroturbine device' - Google Patents

Abstract

The invention relates to gyrostabilising systems which can be used in the form of supportless propulsive unit for transport means, in particular for a spacecraft. The inventive method consists in rotating flywheels about local axles, in moving said flywheels along a steep trajectory around a common axis of precession and in synchronising the angular spin rates of the precession rate of rotation, wherein the angle of cant of each local axis to the common axis of precession is maintained in such a way that it is constant and unequal to 90°. The gyroturbine comprises a body, a platform which is positioned in such a way that it is rotatable with respect to the body about the device axis of symmetry (commomn axis of precession) and one or more flywheels which are fixed to the platform at an angle jointly with the propulsive units which are cinematically connected to the body. The inventive transport means comprises a body, a module which is fixed thereto and is provided with a power plant, a crew cabin and a control system. The power plant comprises one or several gyroturbines. The hydroturbine body is mountable in such a way that it is deflectable with respect to the module. The aim of said group of inventions is to reduce gyroscopic torques and vibrations having an effect on the transport means, to simplify the structural design thereof and to increase a thrust force.

Description

 METHOD FOR MAKING TRACTION EFFORT BY CORIOLIS FORCES, DEVICE FOR ITS IMPLEMENTATION OF "GYRO TURBINE" AND VEHICLE-BASED VEHICLE

GYROTURBINE DEVICES.

The present invention relates to gyro stabilization systems and can be used, in particular, as a supportless propulsion device for orientation and plane-parallel movement, for example, of a spacecraft (KA) by creating control accelerations in stabilization modes and programmed movements KA, as above the surface of planets, and in outer space without the use of jet engines.

A known method of creating traction by Coriolis forces, according to which a material body (for example, a flywheel) is untwisted around a local axis and at the same time move it with a corresponding speed in a direction perpendicular to the local axis / Sivukhin D. V. "General Physics Course" Tl. Mechanics. - M .: Matgiz - 1979.- S. 339, 348 p. 8 /.

With such a complex rotational-precession motion of the material body, Coriolis acceleration occurs, the orientation of which is perpendicular to the vectors of the linear precession velocity and the angular velocity of rotation, and the direction of the acceleration vector is determined by the well-known rule Zhukovsky / N. Zhukovsky. Kinematics, Statics, Point Dynamics. - M .: OboronGiz - 1939 - S. 67, 68 /. One of the side effects of the known method of generating traction by Coriolis forces is the appearance of the so-called gyroscopic moment (hereinafter referred to as gyro-moment), which occurs when, when the flywheel rotates around its local axis with a very high speed, it is simultaneously rotated at a lower speed around the second axis perpendicular to the local axis of the flywheel and passing through the center of mass of the flywheel.

The effect of the occurrence of a torque moment is used in power hydrodynamic gyroscopes / see, for example, the application of the Russian Federation JNa 95120281 for the invention "HYDRODYNAMIC GYROSCOPE", IPC G01C19 / 00, publication date - 1997.10.27 / and in gyrodynamics of spacecraft / cm. RF patent JYaI 839792 for the invention "GYROSCOPIC POWER DEVICE FOR MANAGING ORIENTATION OF SPACE VEHICLES", IPC 6 B64G1 / 28, GOl Cl 9/00, publication date 2005.05.10 /, where flywheels are installed, rotating at high angular speeds of more than 300 - per minute.

When the flywheel of such a power gyroscope rotates around the local axis while rotating it around the second axis, perpendicular to the local axis of the flywheel and passing through its center of mass, a force moment arises directed orthogonally to both axes. The magnitude of this force moment is proportional to the kinetic moment of the flywheel of the gyroscope and the magnitude of the angular velocity of rotation of the gyroscope around the second axis. The resulting gyroscopic moment acts on the vehicle (spacecraft) and turns it around, which in some cases is an undesirable phenomenon.

Closest to the proposed device by technical essence, is a gyroscopic device, which contains a housing mounted on it with the possibility of rotation on the axis of symmetry of the body of revolution equipped with a propulsion / US Patent N ° 5,024,112, "Gorosoris arraratus", IPC 7 F16H27 / 04; G01C19 / 06, publication date 06/18/1991 /. The specified device contains two disks mounted opposite each other in two L-shaped handles supporting the respective disks with the possibility of rotation in bearings in opposite directions and the cam mechanism L-shaped handles are mounted on a vertical shaft - movably connected to a pivot point located in the middle between flywheel disks. The drive of the drive provides rotation of the flywheel disks around two local axes in opposite directions while simultaneously rotating from a complex engine of flywheels and L-shaped handles around the second vertical axis of the forced precession, perpendicular to the plane of rotation of the local axes. The cam mechanism performs the function deflection of the disks in the vertical direction while rotating the disks around the local axes together with the forced precession of the disks around the vertical axis of the precession. Such a deviation of the rotating disks by means of a cam mechanism creates a forced nutation of the disks in the form of their swings in the vertical direction during the forced precession of these disks. As a result of the joint rotational, precession, and nutational movements of both disks, a low-frequency (up to 100 Hz) pulsating pulling force arises, directed upward along the precession axis. A disadvantage of the known gyroscopic device is the pulsating nature of the tractive effort created by it and the inability to use in practice more than two working bodies (disks) to increase the total thrust of such an apparatus due to the difficulty of creating forced nutational movement of a large number of disks. Low-frequency pulsations of the traction forces create significant vibrations affecting the vehicle, which uses the known traction method for driving, and the gyroscopic apparatus itself is characterized by low efficiency of converting the torque of the power plant to the traction force of its movement in the vertical direction. Closest to the proposed vehicle by the number of essential features is a vehicle containing a body consisting of two parts, a power plant, a support platform and bodies of revolution, made in the form of balls. Moreover, the balls are installed with the possibility of their movement under the action of solenoids along a complex path / RF patent N ° 2003 H 2472 for the invention, IPC 6 B64C1 / 00 from 2004.11.20 /. The described vehicle is an aircraft, which is a complex inertial system designed to obtain directional traction.

The disadvantage of the described vehicle is its complexity, as well as the insufficient level of traction forces created in it due to the lack of synchronization of the inertial motion of bodies in the aircraft. The basis of the proposed inventions is the task of creating such a method and devices for creating and using Coriolis traction to rotate the flywheels of power gyroscopes, which would increase the level of traction and at the same time reduce the level of vibration by creating conditions for synchronizing the rotation speeds of the flywheels and the possibility of useful use obtained when this unidirectional Coriolis forces.

The solution to this problem makes it possible to create a vehicle with a propulsion device that allows you to move devices in space, in particular in space, without the use of reactive energy.

The problem is solved by the proposed method, which, like the well-known method of generating traction by Coriolis forces, involves spinning the flywheel around the local axis and simultaneously moving it around the precession axis, and, according to the invention, at least two additional flywheels are used that rotate around the corresponding local axes, all flywheels move along a circular path around the common axis of precession, which is created behind the centers of mass of the flywheels, the angular velocity of rotation of each flywheel ω around e of the local axis are synchronized with the angular velocity Ω of the rotation of the flywheels around the common axis of the precession, and the angle of inclination ψ of each local axis relative to the common axis of the precession is kept constant and set in accordance with the expression ψ ≠ π / 2.

A feature of the proposed method is that the local axis of the flywheels are placed at the same angular distance from one another around the common axis of the precession.

In addition, the inclination angle ψ of the local axis relative to the common axis of the precession is consistent with the synchronization coefficient j = Ω / ω of the angular velocity of rotation of each flywheel ω around its local axis with the angular velocity Ω of rotation of the flywheels around the common axis of the precession as follows: ψ = arccos (Ic / Ij_ω / Ω), where Ic is the moment of inertia of the flywheel relative to the local axis; Iχ is the moment of inertia of the flywheel relative to the axis of forced precession.

The problem is solved by the proposed gyroscopic device, which, like the known one, contains a housing mounted on it with the possibility of rotation on the axis of symmetry of the body of revolution equipped with a propulsion device, and, according to the invention, the gyroturbine is supplemented with a platform in the form of a disk and a flywheel, which is mounted for rotation around the local axis, the platform is mounted in the housing with the possibility of rotation around the common axis of the precession and which is the axis of symmetry of the gyroturbine, and the flywheel is obliquely attached to the rotatable latform with a mover, which is kinematically connected to the body.

The problem is solved by the proposed vehicle, which, like the known one, contains a housing consisting of two parts, on which a module is mounted, in which the power plant, the crew cabin and the control system are combined, according to the invention, the power plant includes at least , two gyroturbines with bodies of rotation, to ensure the movement of the vehicle by attaching gyroturbines to the module.

Another feature of the proposed vehicle is that the first gyroturbine is located above the top of the module in the first part of the housing, the second gyroturbine is located under the bottom of the module in the second part of the housing, and the axis of symmetry of the gyroturbines coincide.

A feature of the proposed vehicle is that three gyroturbines are located under the bottom of the module in the second part of the housing, and the axis of symmetry of the gyroturbines form an isosceles triangle.

A feature of the proposed vehicle is the fact that each gyroturbine includes a housing, a disk-shaped platform, a mover and flywheels mounted for rotation around respective local axes, the platform is mounted in the housing for rotation around a common precession axis located outside the flywheel and which is the axis of symmetry of the gyroturbine, and the flywheels obliquely b attached to a rotatable platform together with a mover, which is kinematically connected to the body.

A feature of the proposed vehicle is that the local axis of rotation of the flywheels are placed at the same angular distance from each other.

A feature of the proposed vehicle is the fact that each flywheel is mounted for rotation and is equipped with a corresponding electric motor.

кlц де к - целое число.A feature of the proposed vehicle is that the moment of inertia Iχ of each flywheel relative to the axis of the forced precession is consistent with the moment of inertia Ic of the same flywheel relative to the local axis, so that the relation

klc de k is an integer.

A feature of the proposed vehicle is that each flywheel is made in the form of a part of a hollow cone.

A feature of the proposed vehicle is the fact that each flywheel made in the form of a part of the hollow cone is made as one unit with the rotor of the corresponding electric motor.

The proposed solutions allow you to create a more reliable than a prototype vehicle design with high efficiency, the operation of which is based on the known laws of inertia systems and uses highly reliable mechanical devices - flywheels, which are known and tested in gyroscopic engineering. At the same time, the vehicle uses directional traction force of inertial gyroscopic systems (hereinafter referred to as gyroturbines), which generate unidirectional Coriolis traction forces resulting from the corresponding synchronization of rotation of the gyroturbine flywheels.

There is a direct causal relationship between the task and the technical nature of the proposed solutions. So with a complex rotational-translational motion of a material point with an appropriate speed, there is an acceleration of Coriolis directed perpendicular to the linear and angular velocity vectors. In accordance with the proposal, the linear movement of the material point (flywheel), which rotates around the local axis of rotation, is supplemented by the movement of the flywheels with the corresponding speed V along a closed path around a common axis located outside the flywheel at an appropriate distance. Since the speed V of the flywheel’s movement along a closed path, for example, along a circle, has a linear component, in this case there is a Coriolis acceleration and a force moment that affects all flywheels in the same direction along the common axis. Moreover, in such a gyroscopic system - gyroturbine, which consists of two flywheels - there is a traction force of at least a pair of Coriolis forces directed along the common axis of rotation of the steam turbine flywheels, which is also its axis of symmetry.

On Fig shows in section the first embodiment of the proposed vehicle.

In FIG. 2 shows a top view along the line A-A.

Fig. 3 shows a sectional view of a second embodiment of the proposed vehicle.

Figure 4 shows a top view along the line B-B of the vehicle depicted in Fig.Z.

Figure 5 shows in section a gyroturbine of the proposed vehicle.

In FIG. b shows a top view along the line C-C of the gyroturbine shown in Fig.5. Figure 7 shows a fragment of the gyroturbine electric motor shown in figure 5.

On Fig shows a kinematic diagram that explains the essence of the proposed method, which is the basis of the gyroturbine.

The proposed vehicle in FIG. 1 and 2 contains a cabin for crew 1, a power plant 2 and a control system 3, which are combined in module 4 and equipped with two gyroturbines 5, which are attached to module 4 using brackets 6. The first gyroturbine 5 has the shape of a cylinder and is placed on top of the module 4 in the first part 7 of the housing. The first gyroturbine 5 is installed with the possibility of deviation relative to the module 4 around axis 8 using the actuator 9. The first gyroturbine 5 is made in the form of a body of revolution, which has an axis of symmetry 10. A part of the housing 7 is designed to protect the first gyroturbine 5 from atmospheric precipitation. The second gyroturbine 5 is identical to the first and is located under the bottom of the module 4 in the second part 11 of the housing. The second gyroturbine 5 is installed with the possibility of deviation relative to the module 4 around the axis 12 using actuators 13, 14, the design of which is similar to the structure of the actuator 9. The second gyroturbine 5 is made in the form of a cylinder, which has an axis of symmetry 10. The second part of the housing 11 is designed to protect bottom of the second gyroturbine 5. The axis of symmetry 10 of the corresponding gyroturbines 5 coincide. The axis 8 and 12 of the deviation of the corresponding gyroturbines 5 relative to the module 4 are located in planes parallel to the plane AA and form an angle of 90 °.

In the second embodiment of the vehicle shown in FIGS. 3, 4, three identical gyroturbines 5 are placed under the bottom of the module 4 in the second housing part 11, and the symmetry axes 10 of the gyroturbines 5 form an isosceles triangle. In the first part of the housing 7 may be located the cargo compartment. All three gyroturbines 5 are mounted stationary relative to the module 4 of the vehicle.

The gyroturbine shown in FIG. 5, 6 comprises a housing 15, a drive 16, a rotatable platform 17, and flywheels 18, made in the form of an annular truncated cone.

The flywheel 18 is made as part of a cone 19, which rotates around the corresponding local axis of rotation 20 in the bearings 21. The node for turning the flywheels around the common axis of the precession 10 is made in the form of a disk platform 17, which rotates around a common axis 10. The disk platform 17 is equipped with three flywheels 18 ( 6), the local axis of rotation 20 of which are located at an obtuse angle ψ (Figure 5) to the common axis 10, which located outside the borders of all flywheels 18. Flywheels 18 are mounted on bearings 21 in housings 22, which are mounted on a rotatable platform 17 together with the drive 16.

The angle of inclination ψ is selected as follows: ψ = arccos (Ic / Iiω / Ω), where Ic is the moment of inertia of the flywheel relative to the local axis; Iχ is the moment of inertia of the flywheel relative to the axis of forced precession.

The shaft 23 of the drive 16 is kinematically connected with the housing 15, for example, through a planetary gear train 24, 25. The local axis 20 of rotation of the flywheels 18 are located at the same angular distance (120 °) from each other around the vertical axis 10. The local axis 20 intersect with the common axis 10 at point Q (Figure 5). Axis 10 coincides with the axis of symmetry of the steam turbine (Fig. 1 ... 4).

Each flywheel 18 is made in the form of a part of the hollow cone 19 and rotates with a corresponding electric drive. In this case, the implicit vertex of the cone T is directed toward the point Q of the intersection of the local axis 20 of the flywheel and the general 10 axis of the gyroturbine.

The electric drive consists of a housing 22, a field winding 26 and a rotor 27 (see also Fig. 7). The rotor 27 is fixedly connected to the flywheel 18. The field winding 26 is fixedly mounted on the sleeve 28 of the electric drive. Flywheel 18 is installed in the housing 22 of the electric drive with bearings 21. As an electric drive, an asynchronous, collector or hysteresis motor can be used.

The platform 17 is mounted on bearings 29. The gyroturbine housing 15 can be attached to the vehicle module 4 (see Fig. 3) using the corresponding fastening elements 30.

To transfer electricity from the power plant 2 of the vehicle shown in Fig.l (Fig.Z), to the electric drives 16,

22, which rotate on the platform 17, it is possible to use a current collector 31 made, for example, in the form of collector current collector rings. Electric energy from the power plant 2 (Fig. 3) to the current collector is transmitted using the power cable 32.

Example. During operation of each gyroturbine 5, a Coriolis traction force F _k arises, which is always directed along the axis of symmetry 10. At the same time, a reaction torque M acts on each gyroturbine, which tends to rotate the gyroturbine around the axis of symmetry 10, and the thrust force of the gyroturbine 5 is controlled by a change in rotational speeds the flywheel 18 and the platform 17. With an increase in the speed of rotation of the flywheels 18, the thrust force F _{k of the} gyroturbine increases, and vice versa, with a decrease in the angular speed of rotation of the flywheels 18, the thrust force F _k decreases.

In FIG. 1, two gyroturbines are mounted coaxially so that the reaction moment Ma of the first gyroturbine 5 (Figure 2) is directed to the direction opposite to the reaction time Mb of the second gyroturbine 5. As a result of this arrangement of the gyroturbines 5, the reaction times are mutually compensated, and the direction of forces the thrust of the gyroturbines coincides, which is ensured by the corresponding synchronization of rotation of the flywheels 18 of the gyroturbine with the rotation of its platform. In this case, the module 4 (Fig. 1) together with the vehicle rises without rotation around the axis 10.

The forward movement of the vehicle (Fig. 1) (in the direction of arrow D) is provided by tilting the second gyroturbine 5 around its axis 12 in the direction of arrow E. The actuator 13 deflects the second gyroturbine 5 from module 4, and the mechanism 14 brings it closer to the module 4, the traction force F _{kb of the} second gyroturbine 5b is decomposed into a vertical and horizontal component, which propels the vehicle forward.

The backward movement of the vehicle shown in FIG. 1 is ensured by turning the second gyroturbine 5 against the arrow E about the axis 12. In this case, the traction force F ^ of the second gyroturbine 5 is decomposed into a vertical and horizontal component, which moves the vehicle in this direction. The movement of the vehicle to the left is ensured by tilting the first gyroturbine 5 around axis 8, in which the actuator 9 brings the front edge of the first steam turbine 5 closer to the module 4.

The movement of the vehicle to the right is ensured by tilting the first gyroturbine 5 around axis 8, in which the actuator 9 moves the leading edge of the first gyroturbine 5 away from module 4.

In these cases, the traction force of the first gyroturbine 5 is decomposed into a vertical and lateral component, which moves the vehicle in space in the corresponding direction.

In Fig. 4, all three gyroturbines 5 are set so that their total reaction moment M _{s of the} reaction is reduced to zero, due to the fact that the reaction moment M _{a of} the first gyroturbine 5 is directed, for example, counterclockwise, and the reaction moments Mb, M _{0 of} two other gyroturbines 5 are directed in the opposite direction, as shown in Fig.4. As a result of this arrangement of gyroturbines, the reaction times are quenched, that is, M _s = M _a + Mb + M _c = 0, and the direction of the thrust forces F _{k of} all gyroturbines 5 coincides, which is ensured by the corresponding synchronization of rotation of the gyroturbine flywheels with the rotation of their platforms. In this case, the module 5 together with the vehicle rises up without rotation.

The forward movement of the vehicle shown in FIG. 3, 4 (in the direction of arrow D) is achieved by increasing the traction force of two gyroturbines 5 at the same time. In this case, the traction force of the gyroturbines is decomposed into a vertical and horizontal component, which moves the vehicle forward.

The backward movement of the vehicle shown in FIG. 2 is ensured by increasing the traction force of one gyroturbine 5. In this case, the traction force of three gyroturbines is decomposed into a vertical and horizontal component, which moves the vehicle backward.

The movement of the vehicle to the left is provided by increasing the thrust of the third gyroturbine 5. The movement of the vehicle to the right is provided by increasing the thrust of the second gyroturbine 5 out of three. In these cases, the traction of three gyroturbines It is decomposed into a vertical and lateral component, which moves the vehicle in space and turns it around.

Vehicle gyroturbine 5 works like this. To increase the traction force F _{k, the} gyroturbine 5 is equipped with several flywheels 18, the number of which is not less than three, as shown in Figure 5 (6). The mover 16 rotates the output shaft 23 in a clockwise direction, which through a planetary gear 24, 25 is kinematically connected to the housing 15 of the gyroturbine. As a result of this, the platform 17 rotates around the axis 10 together with the flywheels 18 in the opposite direction. Each flywheel 18 rotates with a corresponding electric drive mounted in the housing 22. Such an electric drive contains an excitation winding 26 and a rotor 27 (see Fig. 5, 7), which is made, for example, short-circuited in accordance with the squirrel-wheel circuit. The rotor 27 of each electric drive rotates the corresponding flywheel 18 around the local axis 20 in the direction determined by the proposed rule, according to which the angular velocity vector Ω of the disk platform 17 conditionally coincides with the corresponding local axis 20 of rotation of the flywheel 18. The rotation direction of the flywheel 18 around the corresponding local axis 20 coincides with the direction of rotation of the rotated vector Ω around the point Q of the intersection of the corresponding local axis and the axis of the forced precession.

As a result of this direction, the Coriolis forces F _{k of} all the flywheels 18 coincide and turn out to be directed in the same direction along the axis 10, due to which there is a traction force of 3F _k and ensures plane-parallel movement of the vehicle in space.

The physical essence of the functioning of the proposed vehicle in space is explained using the kinematic scheme shown in Fig. In the proposed device, all the flywheels 18 rotate around the corresponding local axes 20, and simultaneously synchronously rotate together around a common axis 10, which is located outside the centers of mass 33 of the corresponding flywheels in the plane 34 parallel the plane of the platform 17 (see Fig. 5, b). The transport speed V of the flywheels 18 is defined as V = AΩ, where Ω is the angular velocity of rotation of the flywheels around a common axis 10; A is the distance of the center of mass 33 of the corresponding flywheel 18 from the axis 10. The direction of rotation of each flywheel 18 (see FIGS. 5, 6 and 8) around its local axis 20 is determined based on the proposed flywheel synchronization rule, according to which the angular velocity vector Ω of rotation around common axis 10 conditionally rotate, for example, along trajectory 35 and combine it with the corresponding local axis of rotation 20 of the corresponding flywheel 18 (the intermediate position of the angular velocity vector Ω 'when it is rotated is shown in dashed line in Fig. 8). In this case, the direction of rotation of the corresponding local axis 20 should coincide with the direction of rotation of the rotated angular velocity vector Ω ', and all the rotation vectors ω of rotation of the flywheels 18 around the local axes 20 are centrifugal in nature.

The application of the proposed rule ensures that each flywheel 18 is properly synchronized with its rotation around the local axis 20 with rotation around the common axis 10 and, thus, the unidirectional orientation of the acting Coriolis forces F] ₀ F _k ', F _k "along the axis 10. This can make sure by applying the Zhukovsky rule for each flywheel 18. In accordance with this rule, the vector of the velocity V of the flywheel 18 is conditionally rotated 90 ° in the direction of rotation of the angular velocity vector ω, as a result of which the direction of forces is determined Coriolis F _k , which acts on the flywheel 18. The Coriolis force F _k coincides with the direction of the velocity vector V thus turned and is defined as F _k = kMωV, where k is the dimensionless proportionality coefficient that takes into account the geometric dimensions of the flywheel, the conditions of its movement and synchronization with movement around a common axis 20, M - flywheel mass.

When the flywheel 18 rotates around axis 10, the Coriolis centrifugal force F _d also appears (see Fig. 8), directed to the intersection point Q. To determine the direction of its action, it is necessary to arbitrary point 36 of the flywheel ring 18, which rotates around axis 10 with an angular velocity Ω, apply the Zhukovsky rule, taking into account the fact that the portable speed of point 36 is V _m = ωr (g is the average radius of the flywheel ring). In this case, the transport speed vector V ₁₁₁ is conventionally rotated 90 ° in the direction of rotation of the vector Ω. As a result, the direction of the Coriolis force Fd coincides with the direction of the vector V _m thus rotated, as shown in Fig. 8. The local flywheel axes 20 shown in FIG. 8 can be located at any angle ψ relative to the common axis 10. In this case, the local axes 20 move along the conical surface 37, which is radially shaded in FIG. 8, and the circular path 38 of the centers of mass 33 the flywheel 18 is located on the conical surface 36 and simultaneously on the plane 34. Moreover, the radius A and the angles are α = β = γ = 120 ° and are located on the plane 34, and the point Q of intersection of the axes 20 is located above the point R of the intersection of the projections of the axes 20 on plane 34.

In the theory of gyroscopes, the problem of determining the angular velocity Ω of the free precession is known depending on the mass M of the gyro flywheel (18) and its rotation frequency ω. Such a problem has an approximate solution, which does not take into account the centripetal nature of the flywheel movement around its axis of precession; therefore, it does not make much sense to dwell on it.

The exact solution to the problem of a symmetric gyroscope is based on vector algebra, and therefore it would be tedious to give it completely here.

The final form of the equation that relates the frequency ω of the rotation of the gyro flywheel (18) and the angular velocity Ω of the precession (which must be determined) is presented below

IiΩ ² cosψ - IцΩω + AP = 0 (1) where Ii is the moment of inertia of the gyro flywheel relative to the vertical axis of the precession; Ic - moment of inertia of the gyro flywheel relative to its local axis; P is the weight of the gyro flywheel; A is the distance from the center of mass (33) of the gyro flywheel (10) to the vertical axis of the precession (). ψ is the angle of inclination of the axis of rotation of the gyro flywheel (local axis) to the axis of the gyro precession. The moment of inertia is a characteristic that reflects the ability of the body (for example, the flywheel of the gyroscope) to maintain a constant uniform rotational movement around the corresponding axis. Therefore, the same body (18) can have many moments of inertia.

For example, for an annular body, the moment of inertia about its axis of symmetry of rotation is defined as

Ic = kMr ² where M is the body mass of the gyroscope; k = 0.5 is a dimensionless coefficient reflecting the annular shape of the gyroscope body; g is the average radius of the gyroscope ring. For other cases, the expression I = IcMr ² for the moment of inertia of the same body (flywheel) has a similar structure but with different values of k and g.

Quadratic equation (1) has two solutions with respect to the angular precession velocity Ω.

Without going into details of solving quadratic equation (1) with respect to Ω, we consider the internal structure of equation (1), replacing the moments of inertia Ic and Ii with their dependences on the mass M and on the size of the gyro flywheel (18). In this case, equation (1) will have the following form: kiMA ² Ω ² cosψ - k ₂ Mr ² Ωω + AP-O (2) where кi ≠ Ic ₂ <1 are coefficients whose value depends on the shape of the body of the gyro flywheel; g is the radius of the body of the flywheel of the gyroscope relative to the local axis 2; A is the distance between the axis of the precession 4 and the center (33) of the mass of the body of the gyro flywheel.

On the other hand, the body weight P of the gyro flywheel is nothing but gravity acting on the mass M of the gyro flywheel body M, i.e. P = MG, where G = ^: 9.8m * sec ^{* 2} - acceleration of gravity on the Earth's surface. Given this fact, equation (2) will have a slightly different form, namely: lqMA ² Ω ² cosψ - Ic ₂ Mr ² Ωω + AMG = O (3)

Dividing equation (3) by the mass M ≠ O and the distance A ≠ O, and also transferring the first two terms to the right side of equation (3), we obtain a paradoxical, at first glance, relationship: G = k ₂ r ² / AΩω- ki AΩ ² cosψ (4)

Based on the expression (4), we obtain that the acceleration of gravity G does not depend on the mass of a rotating body. A similar fact was known from school when we were told how Galileo threw various objects from the Leaning Tower of Pisa to confirm his hypothesis and came to the conclusion that in practice the time of the fall of an object does not depend on its mass.

The second conclusion, which follows from expression (4), is that under certain conditions the value of G can have a negative value, since the second term in expression (4) has a minus sign.

However, a negative value of G means that it is possible to obtain "anti-gravity" (vertical thrust force) by means of the complex rotation of a group of flywheel bodies having the corresponding geometric dimensions and configuration.

The authors' studies showed that such a body should be a cone or a set of disks of different diameters as a working body of a gyroturbine with a conical external or internal surface.

Based on equation (1), it is possible to determine the angle of inclination ψ of the local axis of the gyroturbine: ssψ = (I cΩω - AP) / Ij_Ω ² .

During the operation of the gyroturbine IcΩω »AP, as a result of which the angle ψ is determined by the relation ψ = arccos (I c / Ij_ω / Ω). The performed calculations indicate that with the mass of the annular flywheel M = I Okg; k = l; angular speed of rotation of the flywheel 18 ω = 6000 об / xв = 2πЮ0 rad / sec; the angular velocity of the flywheel 18 around the common axis Ω = 2π * 50 rad / sec, you can get the pulling force of the gyroturbine flywheel, which at ψ = 75 °; A = O.5m r = 0.05m the value is 12528H Newton (in the SI system). If we take into account that each gyroturbine can contain m - 6 flywheels, then with N = 3 three steam turbines, they can create a traction force Fs = Fk * m * N = 12.5kN * 18 = 225kN. Such a gyroturbine vehicle, with its maximum mass of 10,000 kg, is capable of developing a total traction force of 22,500 kg of force, that is, to lift an additional 10,000 kg of cargo or 40 crew members with equipment on board. Moreover, the efficiency of such a vehicle is 80%.

Claims

Claim . one . A method of generating traction by Coriolis forces, which involves spinning the flywheel around the local axis and simultaneously moving it around the precession axis, characterized in that at least two additional flywheels are used that rotate around the corresponding local axes, all the flywheels move in a circular path around a common axis of the precession, which is created behind the centers of mass of the flywheel, the angular velocity of rotation of each flywheel ω around its local axis is synchronized with the angular velocity Ω of rotation of the flywheel in around the common axis of the precession, and the value of the angle of inclination ψ of each local axis relative to the common axis of the precession is kept constant and set in accordance with the expression ψ ≠ π / 2. 2. The method according to claim 1, characterized in that the local axis of the flywheels are placed at the same angular distance from one another around the common axis of the precession. 3. The method according to claim 1, characterized in that the inclination angle ψ of the local axis relative to the common axis of the precession is consistent with the synchronization coefficient j = Ω / ω of the angular velocity of rotation of each flywheel ω around its local axis with the angular velocity Ω of rotation of the flywheels around the common axis of the precession in accordance with the expression: ψ = arccos (Ic / Ij_ω / Ω), where Ic is the moment of inertia of the flywheel relative to the local axis; Ii is the moment of inertia of the flywheel relative to the axis of forced precession. 4. A gyroscopic device (GYROTURBINE), comprising a housing mounted on it with the possibility of rotation on the axis of symmetry of a body of revolution equipped with a propulsion device, characterized in that the gyroturbine is supplemented by a disk-shaped platform and a flywheel that is mounted to rotate around a local axis, the platform is installed in the housing with the possibility of rotation around the common axis of the precession and which is the axis of symmetry of the gyroturbine, and the flywheel is obliquely attached to the rotatable platform together with a mover, which is kinematically connected to the housing. 5. The vehicle for implementing the method according to paragraphs. 1,2,3, comprising a housing consisting of two parts, on which a module is mounted, in which the power plant, the cockpit for the crew and the control system are combined, characterized in that the power plant includes at least two gyroturbines with rotation bodies for ensuring the movement of the vehicle by attaching gyroturbines to the module. 6. The vehicle according to claim 4, characterized in that the first gyroturbine is located above the top of the module in the first part of the housing, the second gyroturbine is located under the bottom of the module in the second part of the housing, and the axis of symmetry of the gyroturbines coincide. 7. The vehicle according to claim 4, characterized in that three gyroturbines are located under the bottom of the module in the second part of the housing, and the axis of symmetry of the gyroturbines form an isosceles triangle. 8. The vehicle according to claim 7, characterized in that the gyroturbine casing is mounted with the possibility of deviation relative to the module. 9. The vehicle according to claim 7, characterized in that the local axis of rotation of the flywheels are placed at the same angular distance from each other. 10. The vehicle according to claim 7, characterized in that each flywheel is mounted for rotation and is equipped with a corresponding electric motor. 11. The vehicle according to claim 7, characterized in that the moment of inertia Ii of each flywheel relative to the axis of the forced precession is consistent with the moment of inertia Ic of the same flywheel relative to the local axis, with the possibility of fulfilling the relation U = klc, where k is an integer. 12. The vehicle according to claim 7, characterized in that each flywheel is made in the form of a part of a hollow cone. 13. The vehicle according to claim 7, characterized in that each flywheel is made in the form of a part of a hollow cone, made as a whole with the rotor of the corresponding electric motor.