WO2005016746A1 - Objet volant en forme de disque - Google Patents

Objet volant en forme de disque Download PDF

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Publication number
WO2005016746A1
WO2005016746A1 PCT/YU2003/000025 YU0300025W WO2005016746A1 WO 2005016746 A1 WO2005016746 A1 WO 2005016746A1 YU 0300025 W YU0300025 W YU 0300025W WO 2005016746 A1 WO2005016746 A1 WO 2005016746A1
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WIPO (PCT)
Prior art keywords
flying
disc
axis
engines
engine group
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Ceased
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PCT/YU2003/000025
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English (en)
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Zoran Matic
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Individual
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Individual
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Priority to PCT/YU2003/000025 priority Critical patent/WO2005016746A1/fr
Priority to AU2003267324A priority patent/AU2003267324A1/en
Publication of WO2005016746A1 publication Critical patent/WO2005016746A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/001—Flying saucers
    • 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
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/411—Electric propulsion

Definitions

  • the invention belongs to the atmospheric and space aircrafts engineering field, i.e. the new, natural forms of aircrafts in the form of a disc with great stabilization in state of moving or steadiness in space, vertically ascending or lowering on Earth or some other heavenly body; with great maneuver abilities and radical changes in flying directions depending on space it moves through, with turbojet or rocket (classical or plasma reactive) engine drives or their combination, with small movement resistance, wide range of flying speed (under sound or over sound to 5 M, I and II cosmic speed and up to 0,6 c for plasma reactive engine ),with ability to transport heavy loads and fuels.
  • IPC international patent classification
  • TECHNICAL PROBLEM In what way to solve the problem of an aircraft having a natural disc form for flying through atmosphere or space, with small flying resistance coefficient during flying through atmosphere, with great surfaces and ascent coefficient, with ability for vertical ascent and descent and hovering in space, also having great maneuver ability in the course of moving and hovering with wide range of flying velocity depending on application of the aircraft; with a possibility to promptly change directions and courses of moving, to be able to function using the existing turbojet and rocket engines, and subsequently plasma reactive engines for accomplishing maximum speed in atmosphere and speeds required for closed or opened trajectories around the planet, with easy modifications of velocity and flying directions, for transport of heavy loads and fuel for departure and return to specific spots in space?
  • This invention with its natural form, great stability and aircraft drive in which, apart from new advantages, the ones of plane, rockets and partly of helicopters are united, solves all above mentioned and other problems concerning atmospheric or cosmic space as the disc flying object.
  • Plane speed depending upon the type and application is from few hundred km per hour to 3,5 M (Mach).
  • the drive is achieved with airscrews set to motion by piston or turbojet engines or by turbojet engines only. Their characteristic is that the ascent and stabilization is accomplished with wings containing the drive fuel, and in the fuselage is the useful load.
  • the control and stabilization elements ailerons, cover wings, flaps, vertical stabilization, trimmers
  • the supple wings ( ⁇ > 6) are subject to oscillations and easy fractures. With drive engine ceasing to work it abruptly dives. Long runways - from few hundred meters to ten kilometers are necessary for taking - off and landing.
  • Rockets are also highly developed nowadays, so that they are used for delivering artificial satellites around Earth, or to send cosmic devices to interplanetary space and some even to interstellar space with powerful multiple digress rockets. Rockets are characterized by the fact that they are used only once - after the power of rocket ceases to work it is discarded. Subsequently, the controls and service modules continue their independent flight and only the control module returns to Earth. Because of the impossibility to adjust the velocity and trajectory, the destination in space must be " aimed at ", i.e.
  • the first flying object similar to the disc is an aircraft on air cushion, better known as hovercraft. It is the aircraft that vertically rises from surface (of approximately 0,5 m) and then horizontally flies using small speed over flat surfaces (ground or water) or it hovers.
  • the disc flying object has the form of a disc -it is a circle in horizontal projection and ellipse in vertical projection.
  • the circle radius is the big semi-axis of the ellipse.
  • the ratio circle diameter and disc height (the ratio ellipse semi-axis a : b ) is ranging from 2 : 1 to 10 : 0 and it depends on application of the flying object. As a rule, this ratio is bigger for greater aircraft velocities, because the movement resistance coefficient is smaller.
  • the flying object can be composed of two discs in moving direction, or of three discs forming equilateral triangle with rounded angles.
  • the disc flying object is actually composed of armour and body, whereas the body is a smaller disc inside the armour and subdivided in two parts by horizontal plane- upper part for the aircraft staff, space for measuring, regulating and controls equipment, passengers, scientific equipment and so on; and the lower part is for stabilization, drive engines, fuel, useful load, undercarriage and other auxiliary equipment.
  • the flying disc armour together with top fuel reservoirs, can swivel in relation to the horizontal axis and also around the vertical axis of the object for a smaller angle using specific number of hydraulic cylinders (at least four pairs of them).
  • the swiveled armour in relation to the body keeping moving direction provides the ascent of the object or it's turning in a great angle, keeping passengers and the load in horizontal position.
  • the undercarriage as a rule, consists of four stands (three at least) that are telescopically bound hydraulic cylinders withdrawing inside the body after the take -off.
  • the drive of the flying object includes four engine groups of different application: for vertical ascend, landing and hovering in space, for flying forwards in projected speed, for sudden brake and flying backwards and for sudden lateral moving and rotation around the vertical axis.
  • the type of engine drives depends on application of the aircraft- turbojet, rocket (classical or plasma reactive), or the combination of the two. It is necessary to point out that this shape, or the ellipsoid, is ideal for plasma reactive engines that are to be expected in recent future.
  • the group of engines for vertical take-off, landing and hovering of the flying object is placed on the disc flange, or on the flange of the object composed of two or three discs.
  • the number of engines in this group depends on the weight of the object and the speed required for vertical movement. Generally, there are six of them and the half should have the buoyancy enough to maintain the object in flying position.
  • the group of engines for flying forwards provides the necessary velocity of the object, overcoming the resistance of atmosphere flying through it, or the appropriate velocity in cosmic space. For example, moving through the atmosphere requires at least three turbojet engines of the speed up to 2,5 M and for accomplishing the speed up to 5 M two or more rocket engines are added.
  • the group of engines for sudden brake and moving backwards are set on the disc flange on the side of the course of moving. They are used for prompt decrease of the velocity and stopping of the object, and subsequently for flying backwards.
  • the group of engines at the flanges of the flying object, under right angle in relation to the flying course, is used for abrupt lateral moving and prompt turning.
  • one engine is turned on at each side, opposite regarding the center, they form a couple for revolving the object around its vertical axis and thus quick turning of the object flying or in the state of hovering.
  • the stabilization is one of the most important elements for moving the disc flying object through space at all. Considering that, observed from above (or under) it is a circle, and in front (or from the side) is an ellipse, it does not have any other elements of stabilization. That is why the stabilization of the disc flying object is performed with specially constructed gyroscope. Beneath the floor bound to it is gyroscope stator, in which two rings rotate in opposite directions around the vertical axis of the disc.
  • the stator is I profile in the cut in which vertical is the drive of the rings, and the inner and outer rings rotate between the horizontal tracks.
  • Mechanical drive (gears or friction), fluid under pressure or inverse magnetic field can be used as the rings drive.
  • Mechanical drive is for very small and school aircrafts, compressed air is for moving through that space, and possible use of pressured liquid is also used for space aircrafts.
  • Inverse magnetic field accomplished with alternating polyphase currents has universal application and then the rings have the role of short- circuited electric motor's rotors.
  • the kinetic moment of gyroscope itself depends on outer forces trying to take the rotation axis from the direction of vertical axis of the disc, i.e. to swivel it.
  • the change of angular rotation speed of the rings is deduced by changing the number of revolutions of drive gear or friction wheel at mechanical drive, by changing the quantity and pressure of the fluid at such drive or by changing frequency of the polyphase electricity's at inverse magnetic field. Balancing of the object in space, causing it not to revolve around its own axis is achieved by opposite- direction ring_rotation. They should have the same value of their own kinetic moment that satisfies the condition of top stabilization.
  • the rings between the upper and lower stator arms can rest mechanically (on balls or cones), using fluid cushions or strong magnetic field.
  • the choice depends on size and application of the disc flying object.
  • flying and landing of the disc flying object other equipment is required which can be named auxiliary equipment.
  • auxiliary equipment For the start of the object a source of electrical energy is necessary and it depends on the application of the aircraft.
  • For smaller ones flying through the atmosphere accumulator battery is sufficient for turning the turbojet engines subsequently producing the required amount of electricity.
  • Great aircrafts require a special set of machines for electricity production and at the same time they are the spares.
  • the disc flying object for the safe flight of the disc flying object, a specific number of measuring, regulatory, control and telecommunication devices is required, such as altitude meter, speed indicator, the object position indication in relation to all three axis, engine performance parameters, stabilizator work parameters, auxiliary equipment, pressure indicator, also the audio and visual contact devices, radars, etc., depending on the application of the aircraft.
  • the disc flying object volume is very great and comparing disc diameter and the length or wingspan of airplanes; it surpasses volumes of other modern aircrafts in multiple ways.
  • the basic division of the disc space concerning the horizontal axis surface is on the upper and lower space.
  • the upper space above the floor, is a space for the staff of the flying object, controls, and passengers if applied for the transportation of the mentioned, or for laboratory and scientific equipment and for similar applications.
  • the space between the floor and the stabilizer is reserved for the drive group of engines.
  • the area inside the stabilizer rings and the lower fuel tank and beneath it is reserved for auxiliary equipment and useful load.
  • the space division is similar with the flying objects composed from two or three discs. However, according to the needs, this division of disc space can be different, that will be determined by the constructor depending on the application of the disk flying object.
  • Picture 1 - shows A-A cut of the disc flying object from picture 2.
  • Picture 2 - shows view A on the disc flying object from picture 1.
  • Picture 3 - shows view C on flying object composed of the two discs from picture 4.
  • Picture 4 - shows view D on flying object composed of the two discs from picture 5.
  • Picture 5 - shows view B on flying object composed of the two discs from picture 4.
  • Picture 6 - shows view F on flying object composed of the three discs from picture 7.
  • Picture 7 - shows view E on flying object composed of the three discs from picture 6.
  • Picture 8 - diagrammatically shows effect of forces on the disc flying object from picture 1 when the armour is swiveled for angle in relation to the body in the direction of flying.
  • Picture 9 - shows cut of the ring stabilizer 13 from picture 1.
  • Picture 10 - shows the position of the group of engines for vertical flying and hovering of the disc flying object on view G from picture 11.
  • the disc flying object is basically composed of the armour 1 and the body 2.
  • the floor 11 divides the disc body in two parts, the upper 10 for the crew, passengers or minor loads, controls area 4 for commands and regulatory devices, scientific devices etc., and the lower part 12 for drive engine groups 3, 9, 13, 16, 28, 29, stabilizer 15, fuel tanks 5, undercarriage 6, auxiliary equipment 8 and useful load.
  • engine groups 13 Under the floor 11, and on the disc flange bound to the floor are engine groups 13 for vertical ascend, engine group 16 for flying forwards, engine group 3 for prompt stopping and flying backwards and engine groups 9 and 29 for rapid lateral moving and rotating around z-axis during flying or hovering of the object.
  • the armour and the body of the disc flying object are linked with hydraulic cylinders 17, as well as with slide contacts 7, providing the swiveling of the object in relation to the body for a small angle up to maximum 10°, around x and y axis, i.e. in the floor plane. Observing the object from the front or from the side, from directions of x and y - axis, a form of the ellipse is perceived as shown in the A-A cut.
  • the big semi-axis of the ellipse a is equal to the radius R.
  • the minor semi-axis of the ellipse, b x and b 2 are 2 to 10 times smaller than the big semi axis, depending on the object size.
  • the bigger semi-axis a i.e. the radius R, the ratio of semi-axis is greater. With the ratio increase the movement resistance coefficient is smaller, meaning it is maximum for the ratio 2 and maximum for the ratio lO.The maximum movement resistance coefficient would be if semi-axis were equal, i.e. when the ball form would be obtained.
  • the values of movement resistance coefficient are to be measured experimentally in aerodynamic tunnels for all axis ratios.
  • the form of a disc has small resistance coefficients especially because the inductance is very small.
  • the pressure on the upper will be smaller than on the lower, and the basic ascent force F z occurs under the framework swiveling angle of 0°. This value of the ascend force will be sufficient for maintaining the flight direction but only over the specific velocity of the given profile.
  • the value of the ascent coefficient c z should be measured experimentally.
  • the movement resistance forces F x anct of the ascent F z are relevant for moving of the disc flying object in atmospheric area (of Earth or some other heavenly body). Flying through cosmic area, this profile offers other advantages and the most important is that the hits of micrometeorites pose minimum danger in harming the covering and the advantage of the profile for excellent maneuver abilities for avoiding crashes with greater meteorites as well as remarkable surveying.
  • the form of the flying object can be accomplished conjoining two discs, or, to be more specific, conjoining two semi-discs linked longitudinally with elliptic cylinder in moving direction 16.
  • This form of the flying object is suitable for minor flying velocities and heavier loads.
  • the combination of three discs is also possible, i.e. of the parts, the thirds of the discs linked with elliptic semi-cylinders, and in the center with flat surfaces on the top and lower side 17.
  • This form of the flying object is appropriate for even smaller flying velocities and even heavier loads.
  • the profile of the disc flying object involves large inner volume and large ascent surface with relatively small outer surface. In that way the great useful space and ascent with relatively small flying resistance is provided.
  • Walls of the disc flying object, the armour 1 and the body 2 consists of thin and solid profiles made from light metal alloys, the inner as well as the outer covering.
  • the inner covering is made of light metal sheets or of technical polymers.
  • the outer covering is made of light metal sheets (for smaller flying velocities), and for great flying velocities from titanium or polycarbonates.
  • the outer covering can be lined with material slightly reflecting electromagnetic waves (invisible for radars, and the profile itself has slight reflection), or with soft material for absorption energy of meteorite hits during flying through cosmos, for example with expanding polyurethane adapted for low temperatures and covered with carbonate fibers.
  • thermo-insulating material Between the inner and outer covering thermo-insulating material can be installed (for smaller flying velocities) or the air could flow for cooling (for greater flying velocities during flying through atmosphere), as well as for heating (for flying into space).
  • the windows are set at the profile 1 armour flanges and in one or two rows in the same direction on the body 2, and as usual, above the disc floor. Some windows could be set at the lower side of the profile for surveying from the luggage area.
  • the shape, size, number of rows and number of windows in line, as well as other specifics will be determined by the object constructor.
  • Position, number and size of the doors on the disc flying object are also to be determined by the object constructor depending on the application. Generally, above the floor are the doors for entrance of the passengers or for specifically light loading.
  • A R 2 * ⁇ [ m ] - is the disc surface stressed with ascent force v [ m / s ] - is the object's velocity. It is noticeable that it is necessary to increase the swivelling angle ⁇ and thus the ascent coefficient c z during flying through fluid of smaller density, i.e.
  • the ascent coefficient c z should experimentally be measured for each profile of the disc flying space, depending on the ratio of semi-axis of the ellipse - a to bi and b 2 .
  • the maximum value of the swivelling angle should also be determined when it comes to the revolving around y-axis. That leads to the change of the direction and course in vertical plane, i.e. it comes to the moving in vertical bend of small radius that is required for the objects of special application and not for usual passenger or cargo planes .
  • center of gravity of weight G of the object does not move, and with it apparently moves backwards for a small unit, which is positive for the disc stability.
  • center of pressure i.e. the point of application of the force F, which is the vector addition of the movement resistance force F x and the ascent force F 2 ; moves backwards from the course of moving, i.e. it moves towards the origin of coordinates of the x 0 z system.
  • the value of such moving must experimentally be deduced for each profile of the disc.
  • the swiveling angle ⁇ of the armour 1 in relation to the course of flying should not exceed 10° for small ratio of the semi-axis a : b, and it should not exceed 5° for great ratio a : b.
  • Swivelling the armour 1 of the disc flying object around x-axis in the flying course for a smaller angle ⁇ in relation to the y-axis the buoyancy centre of the point of application of the force F moves to the side of lifting and it changes the angle effect whose component in direction of y-axis reacts to the disc in a way that it turns in great curve to the opposite direction.
  • the turning coefficient c should also be experimentally deduced as the function of swivelling angle ⁇ to y-axis and the flying velocity of the disc. Meaning, the flying altitude is changing by changing the swivelling angle ⁇ to x-axis and the course of flying (turning in great curve at the same altitude) is changed by changing of the swivelling angle ⁇ in relation to y-axis. Combining the changes of the angles, basic manoeuvre abilities of the disc flying object (up-left, left-right) are achieved. Naturally, these forces do not exist in cosmic space, so that the manoeuvring must be performed using the appropriate group of rocket engines in order to reach the wanted point of destination.
  • the swivelling of the armour 1 in relation to the body 2 of the disc is achieved using hydraulic cylinders 17, flexibly connecting the armature and the body of the disc.
  • the number and the powers of the cylinders are determined by the size of the object and by the forces of movement resistance and ascent, and there are at least four pairs of the cylinders.
  • the centers of coordinate systems of the airframe (x , y , z ') and the body of the disc coincide in every position.
  • the armour and the body are connected with slide connections 7 in the shape of slide valve for example, through balls or elastic joints.
  • the supports 6 include telescopically bound hydraulic cylinders drawn out under pressure, and drawn in with under pressure of hydraulic liquid.
  • the length and number of singular cylinders in the telescope depends on the altitude at which the horizontal axis of the disc should be, or on the altitude between the lowest point of the disc and supporting surface.
  • the diameter of the cylinders depends on the working pressure of hydraulic system and on the weight of the object.
  • the biggest cylinder is the hatch closing the opening of the outer covering when the cylinder is drawn inside the object: it is shaped as the covering of that part.
  • Supports 6, trestles can have jointly bound foots or wheels. If wheels are used, one or one pair of supports should be able to revolve about its axis so that the moving direction could be changed when the object moves on flat and solid surface.
  • a platform for taking-off and landing, which can be static or mobile (automotive or drawn), then jointly bound foots can be applied.
  • the mentioned can also be used during landing on some other heavenly body or on a cosmic station.
  • the pressure in certain cylinders can be redistributed using appropriate sensors and regulators, so that the cylinders have different drawing heights keeping the disc in horizontal position.
  • the disc's stabilization In the course of flying different forces continually react on the disc, which would, if there were no stabilization process, practically tumble the disc throughout the space. Such flight would be impossible.
  • the profile is an ellipse and from the direction of z-axis it is a circle. That is why the object stabilization during flying must be performed using a special interior stabilizer.
  • Stabilizer 14 is placed beneath the floor and it is bound with tight connections 15 to it. The height of these connections depends on the engine diameter (turbojet or rocket) bound to the floor at the lower side.
  • the stabilizer is a ring whose cross section is a square or rectangle, as shown on cut in picture 8.
  • the diameter of the ring-stabilizer is generally 0,6 - 0,8 of the disc radius.
  • the cross section size depends on the size of the object and the extent of forces that act on it as well as on the type of drive and the abutment of the rotating rings.
  • the stabilizer 14 actually consists of the stator tightly bound with the connections 15 to the floor from the lower side, and two rotating rings.
  • the stator has the form I of the profile including the vertical 20, the upper arm 21 and the lower arm 22. Between the arms there are rotating rings, the outer 23 and the inner 24.
  • the rotations of the outer 23 and the inner ring 24 are of opposite-direction and the rotations can be accomplished in several ways - mechanically, using fluid and with inverse magnetic field.
  • the mechanical drive including cogwheels and friction wheels can only be used in the smallest and the trenage objects.
  • the fluid is supplied through the appropriate nozzles 25 bound to the vertical part of the stator 20 and it activates the rotating rings having blades that present the working circuits of a turbine.
  • the angle velocity of ring rotation depends on the pressure and the supplied fluid in a time unit.
  • air for the rotation of the rings is possible only for objects flying in air space of Earth.
  • inverse magnetic field for all sorts of objects and flying conditions.
  • the polyphase alternating current is run through the threads.
  • the inverse magnetic field the currents create makes the rings that are then short - circuited rotors of electric motor, rotate.
  • the rotating rings are leaning on the stator arms, and thus on the floor and on the whole object with supports 26 that can be mechanical (balls or cones) through fluid cushions created with appropriate nozzles on stator arms, or through very powerful magnetic fields obtained by appropriate electromagnets.
  • supports 26 can be mechanical (balls or cones) through fluid cushions created with appropriate nozzles on stator arms, or through very powerful magnetic fields obtained by appropriate electromagnets.
  • air cuss ions is possible only for flying in air space.
  • the mechanical support can only be used with small objects but its existence is necessary for all other ways of supports when the rings are static.
  • the rotating rings, outer 23 and inner 24 have a common rotation axis and revolve one towards the other in opposite directions. With the rings rotation the gyroscopic effect is accomplished so that the stabilizer is, in this case, a mega gyroscope.
  • the gyroscope With rings-rotation having a specific moment of inertia, using the corresponding velocity angle, the gyroscope realizes a self kinetic moment that balances the moments of some external forces and with the rotation of the outer ring in opposite direction, the moments of other external forces are balanced. Thus the precession and notation are reduced to zero or the insignificant value.
  • the gyroscope must fulfill the following condition for one rotating ring:
  • I 0 [ kgm 2 ] is the ring inertia moment ⁇ [ 1 / s ] is the angle velocity of the ring rotation
  • I c [ kgm 2 ] is the inertia moment of the center of gravity of the object
  • e [ m ] is the distance between the center of gravity of the ring and the center of gravity of the object
  • G [ N ] is the weight of the object
  • the ring rotation velocity also needs to be decreased during detour of the object to the left or right side in horizontal plane, so that the object " leans " and compensates the effect of centrifugal force in the curve. It is not necessary while side engines for lateral moving of the object are working. Also, the decrease of angle velocity of ring -rotation is necessary in the course of changing of flying angle in vertical plane, for example, for oblique flight on taking-off or landing to get to the horizontal flight.
  • the disc flying object is drived with four engine groups for different flying conditions: for vertical flying and hovering 13, for flying forwards 16, for braking and flying backwards 3 and for lateral flying 9 and 29. Each engine group includes the appropriate turbojet or rocket engines or their combination. The type of engines used depends upon application of the disc flying object.
  • turbojet engines For flying in air space with velocities of 2 - 2,5 M (Mach) turbojet engines are used. For greater velocities up to 5 M and greater flying altitudes, rocket engines are added to these engines. For flying on closed trajectories around Earth (satellite), the combination of turbojet (for vertical and lateral flying) and rocket engines for flying forwards and braking are used. For flying on open trajectories in space, turbojet (or plasma reactive) engines are exclusively used.
  • the turbojet engines can be classical, turbofan or with additional combustion.
  • the rocket engines when classical, generally use liquid fuel, or they can be plasma reactive engines. The plasma reactive engines do not exist nowadays but they will exist in recent future.
  • the number and the power of these engines depends on the size and application of the object, but concerning the number, there should be at least six engines.
  • buoyancy force of half of the engines should be such to keep the object in a hovering position.
  • These engines are used for vertical ascend, landing and hovering of the object in space. They are also used for rapid increase in flying altitude when required and in case the increase of the armour swiveling angle cannot provide it.
  • all of the engines from the group have the buoyancy direction opposite from the gravity force direction. In opentrajectori.es of the flight, this group of engines must have both effects, so that the course of flying could be changed to " vertical ".
  • the engine group 16 for the drive of the disc flying object is set at the flanges of the disc opposite the moving direction and has that kind of buoyancy.
  • the number and the power of the group depend on the size, application and the speed of the object. Generally, there are three, one central and two engines at side. In this manner, it is possible to use, if necessary, only one, only two or all three engines. Also, there can be more than three engines. For flying through air space and for 2 - 2,5 M (Mach) velocities, turbojet engines used; and for velocities up to 5 M and greater flying altitudes, rocket engines 28 are added. Also, for turning of the object in greater bend in horizontal plane, a performance of one engine at a side, besides the central one, can be used.
  • the engine group 3 for abrupt braking and flying forwards is set at the flanges of the front part of the disc.
  • this group includes two engines symmetrically set in relation to the flying axis (x- axis), but the number can be bigger, for example, there could be three engines as the case is with the group for moving forwards of the objects of specific application.
  • This group of engines is used for abrupt braking, stopping and moving backwards. In order to stop the object flying in a gravity field, the engines for vertical flying need to be activated so that it would not come to the rapid dive. Also, the engines of this and previous group when used separately and if set symmetrically provide turning of the object around vertical, z-axis. The type of engines in this group is the same as in the previous.
  • the engine group 9 and 29 for lateral moving of the object are set at the flanges of disc vertical to the moving direction, to x-axis, i.e. in the y-axis direction, the 9 on the left side and the 29 on the right side.
  • x-axis i.e. in the y-axis direction
  • the 9 on the left side and the 29 on the right side there are two engines on each side of the disc.
  • the power, i.e. the buoyancy of the engines is the smallest from the same of other engine groups.
  • These engines are used for abrupt moving of the object from one side to the other away from x-axis, i.e. in the direction of y-axis, when disc is in moving or hovering position.
  • the lower is in the shape of the ring of diverse cross sections 5 and it is bound below the stabilizer 15.
  • the ring shape is suggested because of decrease of inertia forces effects and because of the compactness of the central space for the auxiliary equipment and cargo, as well as for easier manipulation with it.
  • Beneath the floor 11, at the front part of the disc in the course of flying is the cabin 4 for flying staff (cockpit at airplanes).
  • the remaining space above the floor is for passengers and their hand-baggage.
  • special flying objects instead of the passenger's area, in this area, for example, scientific equipment, etc. can be installed.
  • the central part of the area by vertical at flying objects with plasma reactive engines drives will be occupied with the devices of the plasma reactive generator that will also be the subject of a specific patent.
  • the space 12 inside the gyroscope rings 15 and the lower fuel tank 5 and below them is intended for storing of the auxiliary equipment 8 and for useful load.
  • Hydraulic set of machines and proper installation is necessary for drawing in and out of the undercarriage 6, for swiveling of the disc armour for a specific angle in relation to the flying course using hydraulic cylinders 17, for opening and closing of the air hatches at the entrances of the turbojet engines, for opening and closing of the doors on the object and other commands.
  • the compressor and the proper installation is necessary for keeping the pressure in the aircraft during flying at great altitudes in air space, for cooling of the engine, for cooling of the outer covering with circulation between it and the inner covering at great flying velocities; it can also be applied for opening and closing of the doors in the state of inaction and for other commands.
  • electric energy is required for starting the engine and with it of the disc flying object.
  • accumulator battery is sufficient for starting the engine, and then the engines provide the adequate quantity of electric energy for performance of other consumers, for example, the gyroscope, the hydraulic set of machines, the compressor, the lighting, the controls, etc.
  • accumulators are used for starting the set of machines for electric energy production, and when the engines take over the production, the accumulator remains as the reserve.
  • the sources of electric energy can be different, for example: solar cells, combustible cells, nuclear batteries or reactors, and also in the recent future, plasma generators.
  • Number and type of measuring instruments, regulatory and controls equipment depends primarily on the application of the aircraft and the equipment installed in it. Some of it are common, such as; altitude meter, speed indicator, indicator of the object position regarding all three axis, the stabilizer parameters, the parameters of the running motor for moving, the parameters of the auxiliary devices, the pressure at hydraulic and pneumatic installation, the pressure in the object, etc.
  • Each of the objects must have devices for audio and visual contact with the base and other participants in the transportation, cameras, etc. Naturally, the flight of the object such as this is inconceivable without proper computers.
  • the control of the disc flying object as the new type of aircrafts in atmosphere and space is not complicated because it includes the most of the components which operating is well known.
  • the stabilizer 15 For taking-off, it is necessary to activate the stabilizer 15 before activating the engine group 13 for vertical flight.
  • the armour is swiveled towards the body 2 in the greatest angle ⁇ foreseen for the aircraft and the engine group 16 for flying forwards is activated.
  • the aircraft increases the altitude and the velocity at oblique flight. With the increase of flying velocity the angle ⁇ between the armour 1 and the body 2 decreases as well as the buoyancy of the engine group 13 for vertical flying. Reaching the altitude and the speed foreseen for that aircraft, it transits to horizontal flight, without engine group 13 for vertical flying.
  • the altitude change during flying is obtained by changing the angle ⁇ between the armour 1 and the body 2, or by occasional slight activating of proper engines from the group 13 for vertical flight. In the course of the flight it is possible to change course by swiveling the armour 1 around the transverse axis from the flying course, i.e.
  • the disc flying object uses so far rocket engines instead of the turbojet, and it is constructively adjusted for the conditions. It rises vertically only few hundred meters and then it constantly mounts to the orbit altitude for 45° to 75°. When it finals the predicted mission lasting from several days to several years, the disc flying object returns to Earth using the reversed procedure. After the overhauling, the aircraft is ready for flying into space again.
  • the great volume of the aircraft enables taking into cosmos a great number of people, scientific equipment and food, drink and oxygen provisions, as well as the fuel for departure and return.
  • the similar procedure is for the open flight, i.e. interplanetary, till 2 nd cosmic speed is achieved and until the object emerges from the earth orbit. After that the aircraft moves at inertia, occasionally specific rocket engines are activated for the correction of the trajectory.
  • the mission on some planet is completed, the object, using the same procedure as in taking-off from the Earth, flies off from the planet and continues the return. Multiple usages are possible concerning these aircrafts, i.e. after the overhaul it can be used for new missions.
  • the disc flying object in air and cosmic transition has broad application possibilities.
  • the disc flying object is constructed for each concrete application. Concerning the size, it can be small, medium and great; it can be civil, military, passenger aircraft or for cargo; for flying through atmosphere, space or the combination of the two and other applications. It is primarily intended for drives with the plasma reactive engines, but until their production begins, the existing engines can be used for air and space aircrafts. Also, for projecting and constructing these objects, a special knowledge is not required, but the one used for projecting air and space aircrafts, i.e. the knowledge in mechanical engineering, electrotechnic, aerial and cosmonautics.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)

Abstract

L'objet volant à forme de disque constitue une nouvelle forme d'aéronef destiné à voler dans l'atmosphère ou l'espace. Le blindage (1) et le corps (2) présentent une forme de disque, c'est-à-dire, la forme d'une ellipse observée depuis des directions des axes x et y et la forme d'un cercle observé depuis la direction de l'axe z. Le corps (2) est divisé par le plancher (11) en partie supérieure (10) et partie inférieure (12). La partie supérieure est conçue pour recevoir la zone de commande (4), pour recevoir des passagers ou des dispositifs scientifiques. Dans la partie inférieure se trouve un stabilisateur spécial (14), un groupe de moteurs (13) permettant le vol vertical et le vol stationnaire, un groupe moteur (16) permettant de voler vers l'avant, un groupe moteur (3) permettant de voler vers l'arrière, un groupe moteur (9 et 29) permettant le déplacement latéral de l'objet, ainsi qu'un train d'atterrissage (6), un réservoir à combustible (5), un équipement auxiliaire (8) et une charge utile. Le stabilisateur (14) et les groupes moteurs (turboréacteur, fusée ou réactif plasma) assurent à l'objet volant en forme de disque une stabilité dans l'espace et des capacités de manoeuvre remarquables, étant donné qu'il peut voler dans toutes les directions à vitesse élevée, transportant une lourde charge sur des distances importantes.
PCT/YU2003/000025 2003-08-19 2003-08-19 Objet volant en forme de disque Ceased WO2005016746A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/YU2003/000025 WO2005016746A1 (fr) 2003-08-19 2003-08-19 Objet volant en forme de disque
AU2003267324A AU2003267324A1 (en) 2003-08-19 2003-08-19 Disc flying object

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/YU2003/000025 WO2005016746A1 (fr) 2003-08-19 2003-08-19 Objet volant en forme de disque

Publications (1)

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WO2005016746A1 true WO2005016746A1 (fr) 2005-02-24

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2327607C2 (ru) * 2006-07-31 2008-06-27 Олег Васильевич Черемушкин Конструкция кабины размещения пассажиров, экипажа, оборудования
EP2495172A1 (fr) * 2011-03-03 2012-09-05 Vincenzo Todaro Principe de propulsion à froid pour engin spatial
US11084564B1 (en) 2020-02-03 2021-08-10 Space Perspective Inc. Aerospace vehicle system and method of operation
CN114072334A (zh) * 2019-07-09 2022-02-18 杰姆·卡拉科 一种承载装置
CN114779816A (zh) * 2022-05-17 2022-07-22 成都工业学院 一种面向震后废墟环境起降的搜救无人机及其具有的系统

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FR2081263A1 (fr) * 1970-03-25 1971-12-03 Pennacchio Pierre
US5259571A (en) * 1991-03-06 1993-11-09 Blazquez Jose M R Aircraft with gyroscopic stabilization system
US5351911A (en) * 1993-01-06 1994-10-04 Neumayr George A Vertical takeoff and landing (VTOL) flying disc
DE19630026A1 (de) * 1996-07-25 1998-01-29 Georg Redel Flugobjekt
US5730390A (en) * 1992-05-14 1998-03-24 Klaus Kunkel Reusable spacecraft
DE19818945A1 (de) * 1998-04-28 1999-11-04 Rothkugel Klaus Peter Flugscheibe "Omega-Diskus 98"

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2081263A1 (fr) * 1970-03-25 1971-12-03 Pennacchio Pierre
US5259571A (en) * 1991-03-06 1993-11-09 Blazquez Jose M R Aircraft with gyroscopic stabilization system
US5730390A (en) * 1992-05-14 1998-03-24 Klaus Kunkel Reusable spacecraft
US5351911A (en) * 1993-01-06 1994-10-04 Neumayr George A Vertical takeoff and landing (VTOL) flying disc
DE19630026A1 (de) * 1996-07-25 1998-01-29 Georg Redel Flugobjekt
DE19818945A1 (de) * 1998-04-28 1999-11-04 Rothkugel Klaus Peter Flugscheibe "Omega-Diskus 98"

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2327607C2 (ru) * 2006-07-31 2008-06-27 Олег Васильевич Черемушкин Конструкция кабины размещения пассажиров, экипажа, оборудования
EP2495172A1 (fr) * 2011-03-03 2012-09-05 Vincenzo Todaro Principe de propulsion à froid pour engin spatial
CN114072334A (zh) * 2019-07-09 2022-02-18 杰姆·卡拉科 一种承载装置
US11084564B1 (en) 2020-02-03 2021-08-10 Space Perspective Inc. Aerospace vehicle system and method of operation
WO2021158417A1 (fr) * 2020-02-03 2021-08-12 Space Perspective Inc. Système de véhicule aérospatial et procédé de fonctionnement
US11878784B2 (en) 2020-02-03 2024-01-23 Space Perspective Inc. Aerospace vehicle system and method of operation
CN114779816A (zh) * 2022-05-17 2022-07-22 成都工业学院 一种面向震后废墟环境起降的搜救无人机及其具有的系统

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