RU2123456C1 - Flying saucer - Google Patents

Abstract

FIELD: aeronautical engineering. SUBSTANCE: flying saucer includes casing, engine, compressor connected with engine and pipe inside which engine and compressor are located. One end of pipe is made in form of diffuser and other end is made in form of jet nozzle. Rotary-type steam engine works on superheated water. Positive-displacement compressor is also of rotary type. Compressor is connected with engine by means of hollow shaft. Above-mentioned casing of flying saucer includes load-bearing skeleton coated with sheet metal and rigid ceiling base which are made from steel pipe of round, oval or rectangular shape. Flying saucer has first combustion chamber and first delivery tube used for connecting the first combustion chamber with compressor. Flying saucer is also provided with at least four additional jet nozzles. Each nozzle is end of tube secured in swivel spherical base and used for engagement with second delivery tube which is also connected with combustion chamber for performing vertical flight. EFFECT: high safety and enhanced reliability of flight. 5 cl, 6 dwg

Description

 The invention relates to aircraft helicopter manufacturing.

 Flying saucer in simplicity of design and operation will become easier than a child’s toy.

 Due to imperfection, insecurity, inefficiency, modern aircraft often crash, killing the lives of innocent people.

 All the troubles of modern aircraft are that in order to create an effective reaction force of the thrown gas stream - m • V (the product of its mass m and speed V), effective inventions are not used so that aircraft can take off and land vertically and fly at the required speed (including supersonic) horizontally is extremely reliable.

The mass m of air entering modern turbojet engines used in modern aircraft containing up to two tens of thousands of parts [2, p. 38] is compressed by an ineffective vane compressor and sent to the combustion chamber, where fuel is burned. The combustion products, forced cooling, drastically reducing efficiency, passing through the turbine, having a temperature of 950 - 1000K (700 - 727 ^o C), are ejected from the jet nozzle at a speed of 410 m / s [1, p. 14], creating jet thrust with an effective Efficiency = 0.25 [5, p. 41].

 In the combustion chamber, the combustion temperature of kerosene is 2600–2700K [5, p. 174], so as not to deform the turbine blades, the temperature is forcibly reduced to 1200–1300K [5, p. 75], drastically reducing efficiency.

The real possibility of building a flying saucer with high capabilities is manifested using the inventions of the author "Steam rotary engine Sultanova A.Z." - RF patent N 1807219 (a working sample is available) and related inventions - "Rotary engine Sultanova A.Z." - RF patent N 2016246, "Reversible distributor of the working fluid Sultanova A.Z.," - a. from. N 1820010, “Rotary engine reversing mechanism” - patent N 2015350. The effective coefficient of the proposed rotary engine is η _e = 0.7 or more, and it is easy to obtain 5 million kW of power in one unit, the specific fuel consumption is about 140 gW / h . A rotary engine will operate as a volumetric rotary pump-compressor with the required capacity and pressure with volumetric filling efficiency η _n = 1, and a piston - 0.9 [3, p. 18].

 Due to the lack of efficient, simple in design, reliable fuel pumps, plunger, gear, and centrifugal pumps are used [5, p. 241].

 Known aircraft [source. 1] IL-76, containing the fuselage, a wing with four turbojet engines, each containing up to two tens of thousands of parts [2, p. 38] with an effective efficiency = 0.25 [5, p. 41].

The disadvantages are:
- protruding wings with a length of 50.5 m, an area of 300 m ² , with a fuselage length of 46.6 m, a stabilizer area of 63 m ² , an aircraft height of 14.76 m, three-axle heavy landing gears, the lion's share of fuel is consumed during its flight for constant transportation, with a take-off mass of 170 tons, the fuel is 84.6 tons, and the payload is only 47 tons, the fuselage volume is about 800 m ³ , the empty mass is about 38 tons;
- it can’t take off vertically, so for a run you need a reinforced concrete strip with a length of 1600 m, built with huge costs and maintenance staff, etc.

 Known helicopter [6, p. 76] MI-76 (prototype), comprising a housing, an engine, a rotor.

The disadvantages are:
- rotor with a large diameter, dubious reliability and resource that does not meet flight safety, moreover, it cannot be rotated through an angle of 90 ^o . The screw shakes and discards the air without creating real pressure, and the rejected air, touching the housing, reduces efficiency;
- limited carrying capacity - 40 tons, flight range up to 2000 km at a speed of about 370 km, so it is used to transport some goods and war.

 The author has an invention "Airplane Sultanova A.Z." - A.S. N 1832098, but it cannot become a flying saucer.

If only the industry begins to introduce the author’s wind turbines: "Rotary wind turbine" - RF patent N 2006665, a.s. N 1372094, a.s. N 1373861, a.s. With coefficients N 1548503 wind η _in = 3 or more, and wind using wind turbines with modern coefficient η _n = 0.45, or (3: 0.45 = 6.6), 6.6-fold higher efficiency energy obtained by decomposing water into its constituent parts — oxygen and hydrogen and burning them in rotary engines (mentioned above), at the end of the 20th and beginning of the 21st centuries, all flying saucers will serve the people of the planet Earth and pristine ecology will come.

 Only 850 author's rotary wind turbines with the cost of constructing one nuclear power plant located around Moscow will generate 44 trillion kW of electricity during the year, provide electricity to Moscow - all TPPs, TPPs, which in 1995 generated 43.5 trillion kW of electricity.

 To achieve this objective, it is important that the flying saucer contains a housing carrying a screw, characterized in that a pipe is installed inside the housing containing a diffuser ending in a jet nozzle, inside which a steam rotary engine is placed, interacting through a shaft with a volumetric rotary pump-compressor, the rigid body of the flying saucer is made of a steel support pipe - round, oval or rectangular in shape, and the rigid steel ceiling frame, made in the form of a support pipe, with single steel support pipes forming a steel rigid frame, coated with sheet metal; the vertical flight combustion chamber is connected by the discharge pipe of the pump-compressor branch pipe, and at least four pipes depart from the combustion chamber, terminating with spherical bearings, interacting spherical rotary bearings, to which tubes ending in jet nozzles are fixed; the second branch of the discharge pipe of the pump-compressor, ending in a horizontal flight combustion chamber, ends with a horizontal flight jet nozzle; horizontal arms of vertical flight are pivotally connected to brackets fixed to the tubes of the jet nozzles, the other ends of which are pivotally connected to the lower end of the control lever fixed to the ball interacting with a spherical support fixed by the brackets to the supporting frame.

 In FIG. 1 shows a flying saucer with a vertical section and a top view of the frame.

 In FIG. 2 - mount jet nozzle vertical flight.

 In FIG. 3 - control jet nozzles vertical flight.

 In FIG. 4, 5, 6 - a vertical section of one section of a rotary engine and a compressor pump in three positions according to patent N 1807219.

 A flying saucer (l.p., Figs. 1-6), comprising a housing 1, a support frame 2 made of a closed pipe in the form of a round (Fig. 1c, concentrically located 2, 3 or more - a dotted circle), oval or rectangular shape, ceiling frame 3, made in the form of a support frame 2 connected to it by means of tubular four supports 4, serving as a strong frame receiver (container for compressed air), coated with sheet steel. Inside the frame, a crew cabin, a passenger compartment (second floor), an engine compartment, a cargo compartment, standing on a support strut (wheels and other types not shown) are formed.

 Two "Sultanov A.Z. Rotary engines" 5 with cone radomes are installed in the engine compartment - RF patent N 2016219 with effective efficiency = 0.7 or more (effective efficiency of the WFD - air taxiway - 0.25 [5, p. 41] containing 5 breakdown parts in 2-chamber engines, compressors, it is easy to get 5 million kW of power in one unit.The hollow shaft 6 is connected to a rotary pump-compressor 7 - this is “Sultanov A.Z. Steam Rotary Engine” N 1807219, operating in the most efficient volumetric air pump-compressor mode with an efficiency of nap lnenii = 1 (piston - 0.9) [3 p. 13], (gear - 0.7) [3 p. 16], the filling efficiency of the axial vane air compressor used on modern aircraft only relative internal efficiency = 0, 6 [4, p. 183]. The gap between the engine 5 and the compressor 7 is closed by a cover 8. The engine 5 and the compressor 7 are placed inside the pipe 9 made by the diffuser 10 and the jet nozzle 11.

 The suction pipe 12 (Fig. 4) goes into the pipe 9, and the discharge pipe 13 ends (Fig. 1a) with a horizontal flight combustion chamber 14 made with Laval jet nozzles 15, fuel nozzles 16. The branches of the discharge pipe 13 - pipe 17 ends with a combustion chamber 18 vertical flight with fuel injectors 19.

 The inner walls of the combustion chambers 14, 18 are faced with a chamber that can withstand the highest temperature - more than 2700K, and the temperature of the combustion chamber of the VRT does not exceed 950-1000K [5, p. 183], which sharply reduces the efficiency and efficiency.

 Pipes 20 (at least 4) diverge from the combustion chamber 18, ending with spherical bodies 21 (Figs. 1c, 2), interacting rotary ball bearings 22, made with holes to which pipes 23 are fastened, ending with jet nozzles 24, to which the brackets are attached 25 with holes interacting with horizontal rods 26, the other ends of which are pivotally connected to the lower end of the lever 27 (Fig. 3), mounted on a ball 28, interacting with a spherical support 29, mounted by brackets (known) to the pipes 20.

 To facilitate the concept of a rotary engine (the mentioned patents), cross sections (Figs. 4, 5, 6) of one section of a chamber containing a tubular body 30, to which a suction pipe 12 is inserted, which is included in the pipe 9, a discharge pipe 13, the continuation of which (Fig. . 1a) ends with the combustion chamber 14 of horizontal flight. The rotor 31 is made with the radial surface "AB" in the sector "AOW" - the angle α with a radius R = R '+ e (Fig. 6), made with seals 32, and at the end of the rotor 31 are installed ring seals 33 (Fig. 4) interacting with the planes of the covers of the housing 30. Between the inner surface of the housing 30 and the surface of the rotor 31 a sickle-shaped working chamber 34 is formed, separated by a shutter 35. If a circle is drawn with a radius r from the center o (dashed lines of FIGS. 5, 6), then the combustion chamber 34 turns into a ring (for calculation) with a thickness h.

The cross-sectional area of the suction pipe 12 is equal to the cross-sectional area of the annular working chamber with a thickness h, length L of the rotor 31. Therefore, the filling factor of the working chamber 34 is η _n = 1, therefore, the pipes 12, 13 are made without valves.

To start the engine 5 (Fig. 5, 6, 7), a tubular water coil boiler (not shown), placed inside the hollow shaft 6, is heated by nozzle torches placed inside the hollow shaft 6. When the water in the boiler coil is heated to 300 ^o C its pressure rises to 180 at (kgf / cm ² ) and more. The exhaust gases are heated by the hollow shaft 6, rotor 31, housing 30. Using the "Reversible distributor of the working fluid Sultanov A.Z." - A.S. N 1820010 heated water during the working stroke (Fig. 6) is injected into the working chamber 34, which is faster than the combustion of the working fluid in the internal combustion engine and the burning of gunpowder powder, turning into superheated steam, taking the engine heat, i.e. cooling it, rotates the rotor 31. The exhaust steam, cooling in a radiator (known), turning into condensate, is fed to the engine by a rotary pump. The engine runs without steam and superheater boilers.

 When the rotor 31 (Fig. 1-6), made with seals 32, 33 rotates through the suction pipe 12, air from the pipe 9 fills the working chamber 34, separated by a shutter 35. Compressed air through the discharge pipe 13 fills the combustion chamber 18 through the pipe 17 lined with ceramics that can withstand any high temperature (the bottleneck in the WFD).

When burning kerosene coming from nozzles 19, with a temperature of 2700 K, at least 2 at (2 kgf / cm ² ), through pipes 20 and tubes 23 mounted on ball bearings 22 interacting with spherical bodies 21 are thrown out through jet nozzles 24 with a speed 756 m / s, creating the necessary traction, and the hull 1 begins a vertical flight.

 For horizontal flight, the lever 27 (Fig. 3), mounted on a ball 28, interacting with a spherical support 29, mounted by an arm (known) on the pipe 20, rotates to the right (Fig. 3B). In this case, horizontal thrusts 26, the ends of which are pivotally connected to the lower end of the lever 27 and the brackets 25, turn the jet nozzles 24 to the left and horizontal flight begins at a speed V (Fig. 1a).

To increase the horizontal speed V, the valve (known) of the compressor discharge pipe 13 opens and the compressed air fills the combustion chamber 14. As soon as the fuel coming from the nozzles 16 is ignited, at a high temperature of 2700 K and a pressure of at least 2 kgf / cm ² , Laval nozzles 15 and 11, creating the necessary thrust, are emitted into the atmosphere (arrows). From the afterburner of the turbojet engine (Fig. 1.6) at a pressure of 0.7 - 0.8 kgf / cm ² [5, p. 189], temperature 2200 - 2300K [5, p. 184, Fig. 8.8] products are released into the atmosphere.

The air entering through the diffuser 10, mounted on a support frame 2, which is fixed using tubular supports 4, the ceiling tube frame 3, moving along the pipe 9, cooling the engine 5, cover 8, compressor 7, combustion chamber 14, Laval nozzle 15, sharply heating up to at least 900 ^o C and more (at 900 ^o C the air speed reaches 600 m / s) [5, p. 42], through nozzles 11, creating the necessary thrust, it is released into the atmosphere, moving the flying saucer at any speed including supersonic.

Features of a volumetric rotary pump-compressor with the following parameters:
R is the inner radius of the housing 30 (Fig. 4, 5, 6) - R = 0.5 m, r is the radius of the rotor is r = 0.2 m, the length of the rotor is L = 1 m, the rotational speed of the rotor is n = 3000 r / min (shaft speed of the turbojet engine - n = 5000 - 18000 r / min) [5, p. 202], diameter - 1.2 - 1.5 m, length 5 - 6 m, low traction - 1.5 tf , average thrust 1.5 - 7 tf, high thrust 7 - 12 tf [5, p. 73].

The cross-sectional area S of one annular chamber 34 S = π • (R ² - r ² ) = 3.14 (0.5 ² - 0.2 ² ) = 0.66 m ² , the volume of the annular chamber Q = SL = 0.66 x 1 = 0.66 m ³ .

Air productivity by one chamber in one second - Q = Q • n = 0.66 • 3000/60 = 33 m ³ / s, mass (weight) - Q = Q • n = 33 • 1.3 = 43 kg / s.

A thrust G _t arising in nozzles 11, 24, at a pressure in the combustion chambers 14, 18 P = 2 kgf / cm ² and expiration velocities V = 600 m / s - G = G • V = 43 • 600 = 25800 kgf or G = 25.8 tf or 25.8: 7 + 12/2 = 2.7 times the large thrust of the turbojet engine.

 The thrust of a four-chamber pump-compressor will be - G = G • 4 = 25.8 • 4 = 103.2 tf, or 103.2: 7 + 12/2 = 10 times the greater thrust [5, p. 73]. The calculation was carried out with the mass of air produced by the pump-compressor 7.

When kerosene is burned in the working chambers 14, 18, the temperature of the combustion products rises above 2700K, and the pressure reaches 10 atm, the speed of the combustion products in the jet nozzle is at least V = 756 m / s [5 p. 54]. At this speed (we take the air mass as much as the pump-compressor 7 produces), the thrust will be: G _t = G • V = 43 • 756 = 32508 kgf or G = 32.5 tf, with four chambers of the pump-compressor, the thrust will be: G ₄ = G _t • 4 = 32.5 • 4 = 130.0 tf.

For absolute safety, 2 engines with a total thrust of G ₂ = G ₄ • 2 = 130 • 2 = 260 tf and a flight speed of about 600 km / h will be installed on the flying saucer.

 The specific fuel consumption by the best turbojet engines is q = 0.7 - 0.8 kg / h per 1 kg of thrust [2, p. 68] or 0.08 - 0.1 kg / (N.h.) [5, p. .78], and the specific consumption of the rotary engine (mentioned) is about 140 g / kW • h, therefore, the total fuel consumption will be (750: 140 = 5) 5 times less.

 Take the take-off weight l. t. 200 t with a diameter of one support frame 2 (maybe 2, 3, etc.) D = 20 m (Fig. 1c), the diameter of the steel pipe is 0.3 m, the wall thickness is 1 cm, and the mass of the frame support with one pipe it will be - 2.1 tons, we will take the total mass of the body 1 20 tons, two engines - 8 tons, the total mass of l. without fuel, we take 35 tons.

при средней высоте 4,5 м - объем составит - 300 • 4,5 = 1350 м³ (объем фюзеляжа самолета ИЛ-76 - 800 м³).Area l t. -

with an average height of 4.5 m - the volume will be - 300 • 4.5 = 1350 m ³ (the fuselage of the IL-76 airplane is 800 m ³ ).

At the end of the 20th century, a high-speed railway is being designed between Moscow and St. Petersburg, along which trains will move at a speed of 350 km / h. Everyone can imagine the cost of construction, but no one can imagine safety!
The construction of flying saucers, designed to serve the entire Russian Federation, will require even less money than the mentioned construction site, but after putting in l. pristine ecology will come.

 The fuel will be used oxygen and hydrogen, obtained by the decomposition of water, with the help of electricity received by the "Rotary wind motors" of the author - patent N 2006665 of the Russian Federation 1372094, a.s. N 1548503.

 Moscow will be provided with electricity by 850 revolving wind turbines generating 44 billion kW of electricity during the year; in 1995, all TPPs and TPPs in Moscow generated 43.5 billion kW.

 The cost of building 850 wind turbines is the cost of building one nuclear power plant.

 Flying saucers will occupy not only the surface of the Earth, but also space expanses.

 Construction and operation simpler than a children's toy.

 An experimental working model with the presence of the author will be built within 3 months.

Sources of information
1. I.S. Vasin et al. Aerodynamics of the IL-76T aircraft. - M .: Transport, 1983.

 2. K. A. Gilzin. Engines of unprecedented speeds. - M.: Mechanical Engineering, 1965.

 3. V.I. Tur and others. Pumps and pumping stations. - Stroyizdat, 1977.

 4. S.V. Balyan. Technical thermodynamics and heat engines. - L .: Engineering, 1975.

 5. N.A. Maksimov. Aircraft and helicopter engines. - M.: Military Publishing House, 1977.

 6. Polytechnical dictionary. - M.: Soviet Encyclopedia, 1980.

Claims (5)

 1. A flying saucer comprising a housing, an engine, a compressor connected to an engine, a pipe inside which the engine and compressor are located, one end of the pipe is made in the form of a diffuser, and the other end is in the form of a jet nozzle, characterized in that the engine is made of a steam rotor type and is designed to operate on superheated water, the compressor is made of a volumetric-rotor type and is connected to the specified engine via a hollow shaft.  2. A flying saucer according to claim 1, characterized in that said body has a sheet metal-coated supporting frame and a rigid ceiling base made of a steel pipe of round, oval or rectangular shape.  3. The flying saucer according to claim 2, characterized in that it has a first combustion chamber and a first discharge pipe designed to connect the first combustion chamber to the specified compressor, and at least four additional jet nozzles, each of which is the end of the tube fixed in ball rotary base and designed to interact with the second discharge pipe, also connected to the combustion chamber for vertical flight.  4. The flying saucer according to claim 3, characterized in that it is equipped with a control lever, brackets, spherical rotary bearings designed to install the specified additional jet nozzles, and horizontal rods, and the control lever is mounted in a spherical support and has a lower end that is articulated connected to rods to control additional jet nozzles.  5. The flying saucer according to claim 2, characterized in that it has a second combustion chamber and a second discharge pipe designed to connect the second combustion chamber to the specified compressor, the main jet nozzle being located at the outlet of the second combustion chamber and is intended for horizontal flight .

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