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IPC classes for russian patent Method of control over aircraft jet thrust vector (RU 2504683):
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Jet engine / 2454559
Jet engine consists of housing, nozzle and electric current generator (for, example, solar batteries). Firing device uses feed device to allow interaction of fuel composed of alloy Be(BH4)2 or Al(BH4)3 (metal hydrides) made as wire or band with electric arc that generates plasma from ionised ions in combustion chamber.
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FIELD: engines and pumps.
SUBSTANCE: proposed method comprises control over jet engine thrust vector, fuel flow running out from combustion chamber along Laval nozzle, lengthwise duplex control electromagnets mounted at nozzle outer expanded section, current MHD-generator installed at the nozzle throat, current stabiliser and rectifier and aircraft control system that controls said electromagnets. Control over jet engine thrust vector is ensured by deflection of plasma flow running out from combustion chambers with respect to nozzle mirror axis by electromagnetic field induced by control electromagnets. Plasma consists of positive-charge ions and negative-charge electrons. Note here that mass of ions is several orders of magnitude higher than that of electrons. This defines the thrust vector by the direction of positive ion flow.
EFFECT: simplified aircraft design, decreased weight and overall dimensions of jet engine.
2 cl, 1 dwg
The technical field
The method of controlling the thrust vector of the rocket motor refers to aerospace engineering.
The level of technology
A device synchrotron for control and acceleration of protons in increasing magnetic field. Soviet encyclopedia, 1968, str.
The characteristic which is common to the known and the claimed method, is the impact of electromagnetic fields on elementary particles, including protons.
For reasons that prevent obtaining the specified result is that the protons are in a toroidal vacuum chamber, creating conditions for the acceleration of these protons to very high speeds, but not to discard the flow of protons from the axis of motion.
The known method of forming on the surface of the ferromagnetic fluid formations in the form of "hedgehog's needles". When increasing the magnetic field strength near the surface of the fluid, the magnetic fluid is attracted and goes up to the magnet and forms a surface similar to the spines of a hedgehog. The journal "Technology youth", No. 921, June, 2010, p.42, a report from the exhibition of innovation, Ivan Sedov.
The characteristic common to known and claimed solution is moving the mass of the ionized particles to the poles of a magnet.
The reason that prevent obtaining the desired result, is what is visualization of the effect of magnetic field on the shape change of the surface of zero was conducted on a quiet stationary surface of the liquid, located in the tank.
There is a method of alignment of the whirling stream of air entering the air intake of a gas turbine engine (GTE) with a propeller due to ionization of the air flow and exposure to magnetic fields.
The characteristic which is common to the known and the inventive method is the control action of the electromagnets on the ionized gas stream.
Barriers to obtaining the desired result in this way is that for control (equalize) the swirling stream of air prior to intake:
a) the air flow necessary artificially to ionize due to the impact of PA electric discharge generated is introduced into the flow electrodes, whereas in the proposed method, the ionization of the gas stream flowing from the combustion chamber, is achieved by high temperature combustion (thermal ionization);
b) the movement of ions gas flow occurs across the axis of flow from the periphery to the center of the stream, and does not affect the direction of the thrust vector of the CCD.
The article "Management of ionized gas stream to subsonic input device GTE (gas turbine engine) air screw, O.V. Drach, UDC 629.735.03.621.43.031.3 (045)
http://www.nbuv.gov.ua/portal/natural/Vejpt/2007_6_4/EEJET_6_4_2007_13-16.pdf
The closest of those who practical essence and the achieved result to the claimed invention is a method for the control beam (flow) of electrons in the tube.
The characteristic common to known and claimed process is the impact on the flow of charged particles (electrons)emitted from the electron gun, magnetic field deflecting system consisting of vertical and horizontal deflecting coils, affecting the flow of electrons by a magnetic field, and causing the flow of electrons to deviate in two dimensions (up-down and right-left).
For reasons that prevent obtaining a specific result is that waive the flow of electrons into force of negligible mass flow has no kinetic effects on the elements of the device.
Disclosure of inventions
The essence of the proposed method
Flowing from the combustion gases flow at a temperature of 3500°C in the combustion chamber up to 1500°C at the outlet nozzle is ionized, (located in the plasma state) due to the impact of the specified temperature (the so-called thermal ionization), i.e. consisting of positively charged ions and negatively charged electrons. When exposed to the plasma flow electromagnets control the flow of positively charged ions will be deflected towards the negative pole of the magnet, and electrons to the positive. The mass of the ions in the flux by several orders of magnitude higher than the mass of electrons. As a consequence, UPRAVLENIE thrust vector is determined by the direction of flow of positive ions relative to the nozzle axis under the influence of the electromagnets control.
The thrust vector control KMG is achieved by the deviation with respect to the axis of symmetry of the nozzle flowing from the combustion chamber of the plasma flow due to the electromagnetic field generated by the electromagnets control.
Thus, the thrust vector control of the motor is not achieved by tilting the axis of the movable part of the nozzle relative to the direction of flow of the flowing gas, and the deviation massive positively charged part of the stream flowing gas with respect to an axis of a jet engine under the influence of magnetic fields of governors of the magnets located in the planes of symmetry of I-III and II-IV.
The technical result of the proposed method
The tasks of the proposed method thrust vector control jet engine aircraft are:
1. To simplify the design of nozzles jet engine due to the replacement of governors (mobile) stationary nozzles.
2. Reducing the weight of a jet engine.
The solution to these problems is achieved by excluding from the design of a jet engine:
- electro-hydraulic or Electromechanical steering actuators, providing a deviation of a movable nozzle, and elements of their fixture.
- suspension of the movable part of the nozzle, sealing and insulation of the suspension;
a battery b is Tara or other airborne sources for steering control nozzles LA.
The technical result of these tasks is respectively:
1. Improving the reliability of a jet engine of the aircraft by eliminating mechanical components of the design of a jet engine.
2. Increase flight range with the same amount of fuel by reducing the weight of the jet engine.
The novelty of technical solutions is that changing the direction of the thrust vector EP is due to the impact of electromagnets control PA flowing from the nozzle the flow of products of combustion of fuel, representing an ionized gas (plasma) due to the temperature of fuel combustion (thermal ionization). Flue gas temperature is in the range from 3500°C in the combustion chamber and up to 1500°C at the outlet nozzle. The mass flow of positive ions by several orders of magnitude higher than the mass of electrons.
The technical result of the proposed method lies in the fact that the electromagnets control deviates the flow relative to the axis of symmetry of the nozzle. defines the direction of the thrust vector.
List of figures
Brief description of drawing
Structural scheme of the device shown in the drawing. On the stationary nozzle (1) has two pairs of electromagnets control (2) in the form of, for example, prodolzhpyut the generatrix of the supercritical part on the outer surface of the socket (3), in the planes of symmetry of I-III and II-IV.
With the purpose of obtaining electric current needed to supply to the electromagnets thrust vector control nozzle, downstream of the plasma flow in cross section, for example in a critical section, set the MHD generator (4). The electric current produced by the MHD generator, passes through the rectifier (5) and the stabilizer (6).
On the pair of electromagnets control (2)installed in the plane of symmetry of I-III or II-IV, is supplied electric current of opposite signs on the command signals of the control system aircraft.
1. The method of controlling the thrust vector of a jet engine of an aircraft, characterized in that for changing the direction of the thrust vector is deflected relative to the axis of symmetry of the stream flowing from the nozzle gases consisting of plasma (ions and electrons) through exposure to a pair of electromagnets control, in the form of, for example, strips installed along the generatrix of the supercritical part on the outer surface of the socket in the planes of symmetry, the pair of electromagnets control electrical current of opposite signs on the command signal of the control system aircraft.
2. The method of controlling the thrust vector according to claim 1, characterized in that for obtaining elektricheska the current required for submission to the electromagnets thrust vector control, a nozzle mounted MHD induction generator type.
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