Flying vehicle power support system
FIELD: power plants for auxiliary-purpose flying vehicles.
SUBSTANCE: proposed system includes panel of lifting surface of flying vehicle with device for localization of overflow of airflow; this device includes flow-through nacelle, power loop and air-jet engine with exit nozzle. Axis of nacelle lies in way of motion of lifting surface of flying vehicle; inlet part is made in form of side inlet window located on lower part of lifting surface panel. Power loop includes at least one wind wheel with at least one electric power generator which are arranged inside flow-through nacelle in parallel with inlet window. Engine is mounted in outlet part of flow-through nacelle.
EFFECT: extended field of application; enhanced safety of flight.
System power supply the craft relates to power aircraft, namely to design a power generating device that converts the energy of incoming air flow into electrical energy and generates reactive thrust of the aircraft.
From the aerodynamic known that when the flow around the bearing surface of the air flow, due to the formation of a pressure gradient between the lower and upper surfaces of the bearing surface, and especially the wing of small aspect ratio, is the air mass flow from areas of high pressure to a zone of lower pressure (see the book "Aircraft and flight safety" Ed. by Dyachenko A.A. - M.: vvia. Professor N.E. Zhukovsky. 1987, s-577, 28,3.). The process flow leads to an increase in resistance of the aircraft as a whole and to reduce the lifting force, and also promotes the formation of a cocurrent track, which together reduces the level of flight safety.
To address this phenomenon in the construction of load-bearing surfaces of aircraft use aerodynamic chokes as mounted on the cantilever part of the bearing surface turned down the wings through which the process flow is reduced (see the journal series "news foreign science and those who nicks. Technical information, TSAGI, 1987, No. 2, pp.2, 5.).
However, this design has the disadvantage that it increases the interference between the cantilever portion and the wing, and, consequently, increases the power load on the cantilever portion of the bearing surface, requiring strengthening of its construction.
Also known device structure localization phenomena flowing air masses and the destruction of the cocurrent track through their suppression of the turbulence promoters. Such a device is placed on the consoles bearing surfaces nacelles with the flow of air (see the book "Aircraft and flight safety" Ed. by Dyachenko A.A. - M.: vvia. Professor N.E. Zhukovsky, 1987, C-578, RES.).
However, such flow-through nacelles weakly quenched eddy gotowanie trace stream for the aircraft, which reduces the level of flight safety. In addition, the presence of the flow channel gondola does not eliminate the effects of flow on the console bearing surface, and does not completely eliminate the interference at the junction of the cantilever part with running gondola.
The technical result of the proposed invention is to improve the efficiency of the energy supply of the aircraft and safety of flight.
The invention consists in that in the system n is reticello security of the aircraft, consisting of console, the bearing surface of the aircraft with the localization device of the flowing air stream, the localization device includes flowing the gondola, the energy circuit and the air-jet engine with an output nozzle, the gondola is the axis in the direction of the bearing surface of the aircraft, the input part of the gondola is made in the form of a side entrance window located at the bottom of the console bearing surface, while the power circuit consists of at least one wind turbine with at least one generator of electric energy that are flowing inside the gondola, parallel to the entrance window, and in the output part of the flow-through nacelles placed above mentioned engine.
The proposed solution is illustrated graphically, in which figure 1 shows a General view of the system in the back, figure 2 - view of the system a-a of figure 1, figure 3 - view of the system for b-B of figure 1 and 2.
The system of energy supply of the aircraft consists of console 1 the bearing surface of the aircraft, and the castle 2 (for example, type "dovetail") it is attached all along the section of the reception flow nacelle 3 with the head fairing 4, between the bottom chord 5 of the bearing surface 6 of the console 1 and the edge 7 flow-through nacelle 3 has a lateral tangential the output window 8 flow-through nacelle 3. Inside flow-through nacelle 3, opposite side of the tangential entrance window 8 with axial reduction Δ relative to the bottom chord of the last 5, installed pylons 9, in which the axes 10 are one or more wind turbine 11 with peripheral vanes 12, the plane 12A which is perpendicular to the incident flow. Propeller 11 interact with one or more generators 13 and clutch 14.
For power circuit consisting of windwheels 11 and the generator 13, a circuit of the air-jet engine 15 (for example, ramjet engine) with an output nozzle 16. Air-jet engine 15 can represent any known engine of this class.
The selection produced by the generator 13 electric energy is produced through the cable line 17, and the fuel supply to the air-jet engine 15 is performed by the fuel supply system 18.
The overall management of the system of energy supply of the aircraft is made through the cable line 17 remote control 19.
Control the gradient of the static pressure between the lower and upper parts of the bearing surface 6 is made by the sensors 20, which, through communication lines 21, is transmitted to the control unit 19 of the aircraft.
The system of energy supply is maternova apparatus operates as follows.
When the movement (flight) aircraft moving air masses from the lower part of the chord 5 occurs in the longitudinal direction of the bearing surface 6 and enters the lateral tangential inlet window 8 flow-through nacelle 3.
The sensors 20 are passed through the communication line 21, the information about the gradient of the static pressure between the lower and upper parts of the bearing surface 6 on the remote control 19 of the aircraft. Upon reaching the desired pressure gradient, on command from the control unit 19, the clutch 14 during the interaction of the wind turbine 11 through the axis 10, with one or more generators 13.
Tangential pressure input air flow in circular cross section receiving the flowing gondola 3 contributes to the formation of a wall surface of the centrifugal movement of the air stream.
Air flow together and raced under pressure on the peripheral blades 12, rotates the propeller 11, interact with one or more generators 13. The generator 13 generates electric energy through cable lines 17, according to commands from a control panel 19, is passed to the consumers of the aircraft.
After passing through the energy contour (propeller 11 and the generator 13), a pressure air mass enters the path of the air-jet engine 15. On command from the control panel 19 is provided poda is and fuel into the engine 15 by the fuel supply system 18 with subsequent incineration and output of products of combustion through the outlet nozzle 16. Thus, the motor 15 provides for the creation of reactive power by applying the effect of the flowing air masses from the root portion of the bearing surface 6 to its console 1.
As you approach the end of the movement (flight) aircraft, on command from the remote control 19 (on cable lines 17) is the overlap of the fuel (via fuel supply system 18) to the path of the air-jet engine 15. The engine 15 is stopped. Clutch 14 is disconnected propeller 11 from the generator 13. The production of electrical energy is terminated.
Thus, the proposed solution allows you to convert the effect of the flowing air mass on the bearing plane of the aircraft into electrical energy and jet thrust, and therefore, improve the efficiency of energy supply of the aircraft and the level of flight safety.
Presented to the protection of the patent system of energy supply of the aircraft can be implemented at the enterprises producing similar products.
The system of energy supply of the aircraft, consisting of a console, the bearing surface of the aircraft with the localization device of the flowing air stream, characterized in that the device localizar and includes running the gondola, the energy circuit and the air-jet engine with an output nozzle, the gondola is the axis in the direction of the bearing surface of the aircraft, the input part of the gondola is made in the form of a side entrance window located at the bottom of the console bearing surface, while the power circuit consists of at least one wind turbine with at least one generator of electric energy that are flowing inside the gondola in parallel to the input window and the output part of the flow-through nacelles posted mentioned the engine.
FIELD: aircraft manufacture; arrangement of power plants in aircraft.
SUBSTANCE: proposed flying vehicle has outer wing-panels, power plant with set of pulse-jet detonating engines; each engine includes detonating pipe closed at one end and provided with nozzle at other end, oxidizer and fuel supply units and detonation initiating unit. Detonating pipes are curved in plan according to shape of leading edges of outer wing-panels; detonating pipes are mounted inside wing and are inclined downward; they are brought out of outer wing-panels.
EFFECT: reduced aerodynamic drag; reduced consumption of propellant.
4 cl, 6 dwg
FIELD: attachment units of aircraft power plants.
SUBSTANCE: part 1 of engine mount has ends for holding connecting rods 8 and 9 articulated with turbo-jet engine 3 forming pair of eyes 5 separated by slot 19 made in part 1 to avoid propagation of fatigue cracks 20. Attachment units 11 having cap nuts 13 are located in widened sections 15 of eyes 5 above connecting rods 8 and 9, thus ensuring static strength of eyes 5 when one of them is defective. Provision is also made for reduction of moment created by projection between attachment units 11 and connecting rods 8 and 9.
EFFECT: enhanced safety of engine mount part with no change in dimensions and mass.
2 cl, 1 dwg
FIELD: aeronautical engineering; various flying vehicles.
SUBSTANCE: proposed tip has end plate and is provided with additional swept aerodynamic surface of low aspect ratio with sharp leading edge mounted on the outside of end plate. Trailing edge of additional aerodynamic surface is combined with trailing edge of end plate. Nose is located on leading edge of end plate below level of trailing edge; sweep ranges from 60° to 85°.
EFFECT: enhanced aerodynamic efficiency at high subsonic speeds.