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WO2007084092A1 - Procédé permettant de générer une force de poussée à l'aide des forces de coriolis, dispositif gyroturbine destiné à sa mise en oeuvre et moyen de transport faisant appel à un dispositif gyroturbine - Google Patents

Procédé permettant de générer une force de poussée à l'aide des forces de coriolis, dispositif gyroturbine destiné à sa mise en oeuvre et moyen de transport faisant appel à un dispositif gyroturbine Download PDF

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Publication number
WO2007084092A1
WO2007084092A1 PCT/UA2007/000006 UA2007000006W WO2007084092A1 WO 2007084092 A1 WO2007084092 A1 WO 2007084092A1 UA 2007000006 W UA2007000006 W UA 2007000006W WO 2007084092 A1 WO2007084092 A1 WO 2007084092A1
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WO
WIPO (PCT)
Prior art keywords
axis
flywheel
precession
around
rotation
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/UA2007/000006
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English (en)
Russian (ru)
Inventor
Yuriy Makarovych Lykhovyd
Volodimir Viktorovych Skambrychiy
Olexandr Yurievych Lykhovyd
Oleksandr Vladimirovych Skambrychiy
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Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from UAU200600524U external-priority patent/UA15767U/uk
Priority claimed from UAA200600518A external-priority patent/UA80211C2/uk
Priority claimed from UAU200700295U external-priority patent/UA24572U/uk
Application filed by Individual filed Critical Individual
Publication of WO2007084092A1 publication Critical patent/WO2007084092A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
    • B64G1/286—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using control momentum gyroscopes (CMGs)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03G—SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR
    • F03G7/00—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for
    • F03G7/10—Alleged perpetua mobilia
    • F03G7/125—Alleged perpetua mobilia creating a thrust by violating the principle of momentum conservation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H99/00—Subject matter not provided for in other groups of this subclass

Definitions

  • 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.
  • KA spacecraft
  • 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 /.
  • gyro-moment gyroscopic moment
  • 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.
  • 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.
  • 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 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 ⁇ around e of the local axis are synchronized with the angular velocity ⁇ of the rotation of the flywheels around the common axis of the precession, and the angle of inclination ⁇ of each local axis relative to the common axis of the precession is kept constant and set in accordance with the expression ⁇ ⁇ ⁇ / 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.
  • 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 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.
  • 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.
  • 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.
  • a feature of the proposed vehicle is that the moment of inertia I ⁇ 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.
  • each flywheel is made in the form of a part of a hollow cone.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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 °.
  • 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 ⁇ ( 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 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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 ⁇ 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 ⁇ around the point Q of the intersection of the corresponding local axis and the axis of the forced precession.
  • the angular velocity vector ⁇ 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 ⁇ 'when it is rotated is shown in dashed line in Fig. 8).
  • the direction of rotation of the corresponding local axis 20 should coincide with the direction of rotation of the rotated angular velocity vector ⁇ ', and all the rotation vectors ⁇ of rotation of the flywheels 18 around the local axes 20 are centrifugal in nature.
  • 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.
  • the vector of the velocity V of the flywheel 18 is conditionally rotated 90 ° in the direction of rotation of the angular velocity vector ⁇ , as a result of which the direction of forces is determined Coriolis F k , which acts on the flywheel 18.
  • the local flywheel axes 20 shown in FIG. 8 can be located at any angle ⁇ relative to the common axis 10.
  • 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.
  • 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 ().
  • ⁇ 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.
  • the moment of inertia about its axis of symmetry of rotation is defined as
  • Ic kMr 2
  • M the body mass of the gyroscope
  • k 0.5 is a dimensionless coefficient reflecting the annular shape of the gyroscope body
  • g the average radius of the gyroscope ring.
  • 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 ⁇ .
  • equation (1) will have the following form: kiMA 2 ⁇ 2 cos ⁇ - k 2 Mr 2 ⁇ + AP-O (2) where Consequentlyi ⁇ 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.
  • 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.
  • 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%.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)

Abstract

La présente invention se rapporte à des systèmes de gyrostabilisation, qui sont destinés à servir d'unités de propulsion sans support pour des moyens de transport, en particulier pour des véhicules spatiaux. Le procédé selon l'invention consiste à faire tourner des volants autour d'axes locaux, à déplacer les volants selon une trajectoire circulaire autour d'un axe de précession commun, à synchroniser la vitesse angulaire de rotation des volants autour de leurs axes locaux avec la vitesse angulaire de précession. L'angle d'inclinaison de chaque axe local par rapport à l'axe de précession commun est maintenu à une valeur constante, non égale à 90°. L'invention concerne également une gyroturbine, qui comprend un corps, une plate-forme, qui est disposée de manière à pouvoir tourner par rapport au corps autour de l'axe de symétrie du dispositif (axe de précession commun), et un ou plusieurs volants, qui sont fixés avec les unités de propulsion sur la plate-forme de manière à être inclinés par rapport à cette dernière, lesdites unités de propulsion étant reliées par voie cinématique au corps. L'invention a également trait à un moyen de transport, qui comprend un corps, un module doté d'un ensemble d'alimentation en énergie et fixé sur ledit corps, une cabine d'équipage et un système de commande. Ledit ensemble d'alimentation en énergie contient moins deux gyroturbines selon l'invention. Le corps de la gyroturbine peut être placé de manière à pouvoir être dévié par rapport au module. Le présent groupe d'inventions a pour but de réduire les couples gyroscopiques et les vibrations agissant sur le moyen de transport, ainsi que de faciliter la construction de ce dernier et d'augmenter la force de poussée.
PCT/UA2007/000006 2006-01-20 2007-01-18 Procédé permettant de générer une force de poussée à l'aide des forces de coriolis, dispositif gyroturbine destiné à sa mise en oeuvre et moyen de transport faisant appel à un dispositif gyroturbine Ceased WO2007084092A1 (fr)

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
UAU200600524 2006-01-20
UAU200600524U UA15767U (en) 2006-01-20 2006-01-20 Gyro-turbine vehicle
UAA200600518 2006-01-20
UAA200600518A UA80211C2 (en) 2006-01-20 2006-01-20 Method for using coriolis acceleration for producing driving torque (variants)
UAU200700295 2007-01-12
UAU200700295U UA24572U (en) 2007-01-12 2007-01-12 Method for compensation of forces of gyroscopic moment

Publications (1)

Publication Number Publication Date
WO2007084092A1 true WO2007084092A1 (fr) 2007-07-26

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PCT/UA2007/000006 Ceased WO2007084092A1 (fr) 2006-01-20 2007-01-18 Procédé permettant de générer une force de poussée à l'aide des forces de coriolis, dispositif gyroturbine destiné à sa mise en oeuvre et moyen de transport faisant appel à un dispositif gyroturbine

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Country Link
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009102227A3 (fr) * 2008-02-12 2013-08-01 Dumitru Ionescu Principe d'accélération de direction, dispositifs d'accélération de direction et systèmes de dispositifs d'accélération de direction

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB344061A (en) * 1929-05-07 1931-03-02 Frank Anderson Hayes Improvements in or relating to variable speed power transmission
US4050652A (en) * 1976-07-26 1977-09-27 The Raymond Lee Organization, Inc. Gyro foil
RU2080483C1 (ru) * 1994-05-04 1997-05-27 Эдвид Иванович Линевич Гравиинерционный двигатель
US5713246A (en) * 1992-09-11 1998-02-03 Ccm Beheer B.V. Method for fixing an energy-storing flywheel with pretension on a support and unit comprising an energy storing flywheel
UA72830C2 (en) * 2003-05-15 2005-04-15 Anatolii Ivanovych Synelnyk Rotor-screw propeller

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB344061A (en) * 1929-05-07 1931-03-02 Frank Anderson Hayes Improvements in or relating to variable speed power transmission
US4050652A (en) * 1976-07-26 1977-09-27 The Raymond Lee Organization, Inc. Gyro foil
US5713246A (en) * 1992-09-11 1998-02-03 Ccm Beheer B.V. Method for fixing an energy-storing flywheel with pretension on a support and unit comprising an energy storing flywheel
RU2080483C1 (ru) * 1994-05-04 1997-05-27 Эдвид Иванович Линевич Гравиинерционный двигатель
UA72830C2 (en) * 2003-05-15 2005-04-15 Anatolii Ivanovych Synelnyk Rotor-screw propeller

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009102227A3 (fr) * 2008-02-12 2013-08-01 Dumitru Ionescu Principe d'accélération de direction, dispositifs d'accélération de direction et systèmes de dispositifs d'accélération de direction

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