Aircraft

 

(57) Abstract:

Usage: devices to modify the characteristics of the aircraft and the stabilizing surfaces that are installed on the wings.The inventive vertical aerodynamic surfaces are rigidly interconnected and are located on the ends of the chord of the wing with the possibility of longitudinal movement. When failure of the main on-Board electrical system of the aircraft shafts generators, which are cross-shaped aerodynamic surfaces automatically disinhibited, vertical surfaces move back to horizontal surfaces and together they begin to work as an air turbine, including the operation of emergency generators electrical system of the aircraft. Effect: reduction of induced drag of the wing and increase the level of safety. 9 Il.

The invention relates to aircraft, and more specifically to methods and devices for modifying the aerodynamic characteristics of the aircraft and stabilizing surfaces, mounted on the wings.

Known aircraft with diffusers war the wing on its end chord [1]

This solution serves to reduce the magnitude of the inductive resistance of the bearing surface.

The disadvantage of this aircraft is its narrow function, increasing safety, for example, failure of on-Board electrical system.

The closest technical solution is known for the development of the consortium Airbus industry design for wide-bodied aircraft, a-330 and a-340 limit the aerodynamic surfaces of the rear end of the chord of the wing, reducing its inductive resistance in flight. Failure of on-Board electrical system these cross aerodynamic surfaces disinhibited and working as an air turbine, result in rotation of the rotors of the generators of the emergency electrical system of the aircraft, and the generators are located in the wing tips [2]

However, this solution is characterized by the lack of reduction in induced drag of the wing due to the removal end of the aerodynamic surfaces of the main place of education a powerful end vortices formed near the toe end of the chord of the wing. This is evidenced by conventional, proven practices, the installation location of the limit kr is the solution induced drag of a wing of an aircraft.

The objective is achieved by the fact that in the proposed aircraft containing the wing and located on the ends of the chord of the wing power generators, on the shafts which are installed crosswise aerodynamic surface, motionless in normal flight and automatically rastormazhivanie failure of on-Board electrical system, forming in this case, the air turbine, vertical aerodinamicheskoi surface are movable in the longitudinal direction, rigidly connected to each other, equipped with a closed hydraulic system and Bolotnikova switch that interacts with the brake device, and a guide for longitudinal movement of the vertical aerodynamic surfaces is a groove in the shaft of the generator, which communicates connecting a jumper between the two vertical aerodynamic surfaces.

In Fig.1 shows the device in normal flight, the vertical aerodynamic surfaces are in the front position, top view; Fig.2 is the same, with the failure of on-Board electrical system, vertical aerodynamic surfaces are in the rear position and work as an air turbine, a top view; Fig. 3 is the same, rear view in the first section of the shaft of the generator and the lodgments in section; in Fig.5 the front part of the fairing on the tail of the wing chord with the proposed device (upper trim panel fairing conditionally withdrawn and aerodynamic surfaces not shown), a top view; Fig.6 section a-a in Fig.5; Fig.7 section b-B in Fig.5; Fig.8 brake device with stopper and Bolotnikova the switch in the normal flight; Fig.9 is the same, in the position of the failure of on-Board electrical system, i.e. in the position of the air turbine.

Aircraft wing contains 1, at the end chord of which is fixed the inner 2 and outer 3 horizontal aerodynamic surfaces and interconnected by jumpers 4 upper 5 and lower 6 vertical aerodynamic surfaces, made with a possibility of longitudinal movement of the latter along the end of the chord of the wing. Horizontal aerodynamic surfaces 2 and 3 are installed in the cavity of the tip chord of the wing at its rear edge. In stationary front part of the fairing 7 is an electric generator 8, the brake disc 9 which is rigidly fixed on a hollow shaft 10 of the electric generator 8. In the nose of the fairing 7 pinned cylinder 11, the piston rod of which is pivotally attached to the crosspiece 4 between the vertical aerod is cumulator 12, located in the cavity of the wing 1 and the slide switch 13. Inside the front part of the hollow shaft 10 is the piston rod of the hydraulic cylinder 11, and in the rear part of the shaft 10 is made a groove 14 for moving the jumper 4. The tail section of the shaft 10 is rigidly attached to the rear part of the fairing 7, separated from the front, and horizontal aerodynamic surfaces 2 and 3. In the front part of the fairing 7 rigidly fixed two lodgement 15, in which is located the shaft 10 of the electric generator 8. The braking device comprises two solenoid 16, attached to the fairing 7. Located in the solenoids 16 cores 17 is attached through a spring 18 to the design of the fairing 7. By the end of the core 17 by a clamp attached to the lever to move the valve spool of the switch 13. On facing the brake disc 9 to the end of the core 17 made the space 19 with the brake Shoe 20, and the inside of the groove in the core 17 is spring-loaded latch 21 that communicates with a transverse slot 22 in the brake disk 9. To the inner surface of the brake pads 20 is attached a friction strip 23, which interacts with the brake disc 9. The length of the groove 14 in the shaft 10 corresponds exactly to the sum of the length of the lintel 4 and length required PE the existing way.

During normal operation in-flight on-Board electrical system of the aircraft all four aerodynamic surface using clamps 21 included in slotted brake disc 9, retarded. Aerodynamic surfaces 2 and 3 are located somewhat to the rear of the wing 1 horizontally and work as normal, but additional bearing surface, and the vertical aerodynamic surfaces 5 and 6 with a closed hydraulic system, the hydraulic cylinder 11 and the spool switch 13, directing the slurry on retraction of the rod are located in the front position. Thus the top 5 and bottom 6 of the aerodynamic surface of the work, known as leaf wings, greatly reducing induced drag of the wing 1, effectively preventing the formation of a powerful vortices on the wing 1 (one of the variants of "wings of Witcombe"). Lower effect and horizontal aerodynamic surfaces 2 and 3, which is associated with some remove them from the zone of origin of the powerful vortices at the wing tips. Failure of on-Board electrical system, such as failure of engines, de-energized solenoids cores 16 and 17 by means of springs 18 away from the brake disc 9 and removed from the slots 22, the latches 21. The shaft 10 is given in the front of the cylinder 11. The slurry from the rear side of the cylinder 11 extends through a nozzle of small bore, campfire efforts cylinder 11 and the drag of the aerodynamic surfaces 5 and 6, making their movement back smooth and bumpless. The cradle 15, interacting with the crosspiece 4, does not result in the movement to turn back the aerodynamic surfaces 5 and 6 to complete the transition jumper 4 in the tail part of the fairing 7. After moving all cross aerodynamic surfaces 2, 3, 5 and 6 under the influence of powerful trailing vortices generated at the wing tips, start to rotate, turning in the air turbine, operate the generator 8 is connected electrically with the emergency electrical system of the aircraft.

In the case of recovery in the air of the main on-Board electrical system of the aircraft are powered solenoids 16, the lever slide switch 13 perepuskat slurry in the rear part of the cylinder 11. At this time, the shaft 10 of the electric generator 8 is retarded and is fixed in the initial position, and the vertical aerodynamic surfaces 5 and 6 come forward smoothly to its original position for normal flight.

When polnogo energy-intensive equipment or devices, set in this flight on Board the aircraft, possibly temporary remote power energy generators 8.

Use this emergency generators 8 eliminates the use of additional sources of supply for such additional, temporarily installed on-Board equipment.

In addition, the use of generators 8 airborne allows you to set the propulsion engines are less powerful generators that reduces their drive fuel.

The application of the proposed device allows to reduce the induced drag of the wing in flight, to increase the range, gain fuel savings and other positive effects.

AIRCRAFT containing the wing and located on the ends of the chord of the wing power generators, on the shafts which are installed crosswise aerodynamic surface, motionless in normal flight and automatically rastormazhivanie failure of on-Board electrical system forming this air turbine, characterized in that, in order to reduce induced drag of a wing flying apparatus is sealed between them equipped with a closed hydraulic system and Bolotnikova switch channels, interacting with the brake device, and a guide for longitudinal movement of the vertical aerodynamic surfaces is a groove in the shaft of the generator, which communicates middle connecting a jumper between the two vertical aerodynamic surfaces.

 

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