RU2647294C2 - "sampo 2" aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: aircraft comprises a body, a wing, a horizontal and vertical tail fin, a power plant with two engines, a transmission, streamlined horizontal beams, a landing gear, an airscrew propeller of horizontal thrust, counterrotating left and right circular wings, each of which is designed with the possibility of rotation braking and has swinging blades located radially along the perimeter. Each blade is designed to reach the maximum low point of its oscillation at the moment when the projection of the blade axis intersects with a line passing through the axis of this wing and parallel to the axis of the body, during the wing rotation. The free end of the blade is directed towards the nose of the aircraft and it is possible to rotate the wings in such a way that the same pair of blades of the left and right wing reaches the maximum low point of oscillation at the same point of time.

EFFECT: improved performance.

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Description

The invention relates to aviation, and more particularly to aircraft intended for the carriage of passengers, baggage and cargo.

Famous aircraft "SAMPO" (RF Application 2014120293, 12/10/2015).

The objective of the claimed technical solution is to improve the operational qualities of the aircraft, including simplifying the process of controlling this aircraft.

This problem is solved in that the main mode of operation of the blades is converted as follows. In this mode, the blade reaches its lowest point of oscillation at the moment when the projection of the blade axis (during rotation of the wing) intersects with a line passing through the axis of the wing and parallel to the axis of the fuselage, and the free end of the blade is directed (along this line) to the nose the aircraft, in addition, it is possible to rotate the wings in such a way that the same pair of blades of the left and right wing reaches the maximum lower point of oscillation at the same time.

The claimed technical solution from the prototype differs in that the main mode of oscillation of the blades is changed. In the claimed embodiment, the blade reaches its lowest point of oscillation at the moment when the projection of the axis of the blade during rotation of the wing intersects with a line passing through the axis of the wing and parallel to the axis of the fuselage. In this case, the free end of the blade is directed to the nose of the aircraft. In addition, it is possible to rotate the wings in such a way that the same pair of blades of the left and right wing reaches the maximum lower point of oscillation at the same time.

The claimed aircraft functions similarly to the prototype (Application of the Russian Federation 2014120293 A, 12/10/2015). That is, it has two flight options at the take-off and landing stage and two flight options at the cruise mode, as well as a separate operating mode of the aircraft in maneuvering areas.

In the first version, at the take-off and landing stage, the maximum power of the power plant is applied to the rotating wings, ensuring the aircraft is torn off from the ground and climb is sufficient for safe horizontal flight.

In the second variant, corresponding to the airplane version of take-off, the maximum power of the power plant is applied to the horizontal thrust propeller. As a certain take-off speed is reached, the necessary power is transmitted to the rotating wings, thereby providing a shortened take-off.

After completing the take-off section and gaining the necessary height, the aircraft continues to use the mode of operation of the blades corresponding to the end point of climb (the first version of the cruise flight). It should also be noted that this version of the flight allows you to fly at a lower speed than is acceptable for conventional aircraft.

In another version of cruising flight, the aircraft uses the second additional mode of operation of the blades and is included in the work only after reaching a certain horizontal flight speed. This mode provides zero amplitude of oscillation of the blades, setting them motionless in the plane of the wing. In this case, the connection between the power plant and the rotating wings is disconnected. The latter, due to the impact of the incoming air flow, change the direction of their rotation and pass into the so-called autogyro version of the flight, which allows (in addition to the usual flight) to perform a more secure emergency landing of the aircraft.

And the changes introduced increase its operational qualities, including simplifying the process of controlling this aircraft by ensuring the collinearity of the horizontal thrust screw vector and the force vector of the air flow from the rotating wings. In addition, the disturbing effects on these wings during the flight are reduced (due to the phase difference between the oscillations of the left and right wing blades).

The technical result is manifested in improving the operational qualities of the aircraft due to the introduction of distinctive features.

Brief Description of the Drawings

To clarify the invention presented the following graphic materials:

FIG. 1. Options for synchronous and non-synchronous rotation of the wings;

FIG. 2. Scheme of the main part of the transmission of the aircraft;

FIG. 3. Clutch with synchronization.

In FIG. 1 shows a variant of the synchronous rotation of the wings (option "a") and a variant of the non-synchronous rotation of the wings (option "b"). To simplify the drawing, one wing is shown on each wing. The synchronous rotation of the wings refers to the simultaneous passage of points B _i (Fig. 1b) by the blades of the left and right wings. The proposed solution corresponds to option “a”. For the prototype, it is possible to implement both options, with the predominant predominance of option "b". When implementing option "b", the angle AOW _{2 is} less than the angle of COW ₁ , and therefore, the blade "A" has a greater inclination to the wing plane than the blade "C". And this leads to various effects of the blades on the air environment under the wings.

The structure of the circuit shown in FIG. 2, the following items are included:

1 - box long-term separation of the shafts,

2 - clutch 1,

3, 4 - gears of constant gearing,

5 - clutch 2 (with synchronization),

6 - clutch 3 (with synchronization),

7 - left braking device,

8 - brake disc

9 - the right braking device.

The scheme of the main part of the transmission of the aircraft demonstrates the principle of synchronization of the wings of the aircraft. “Clutch 1” (circuit element 2) disables the transmission of torque from the power plant to the wings, after which a set of measures can be taken to brake the wings or the transmission can be disconnected for a long time using the box (1) (similar to zero transmission of a variable gearbox of a car). To perform the braking of the right wing, “clutch 2” (5) is turned on immediately after activating the “clutch 1” (2) and thereby provides the possibility of braking the rotation of the right wing by the device (9), after the electromagnets are switched on (1c of Fig. 3). Similarly, the rotation of the left wing is braked. After completion of the braking process, the step of returning to the so-called synchronous mode is carried out. First, “clutch 1” (2) is turned off, and then “clutch 2” (5). Next, the "clutch 1" (2) is turned on, the electromagnets are turned off (1c of Fig. 3), and after the "clutch 2" (5) is slowly turned on, the electromagnet pin enters the corresponding hole of the friction disk. The synchronization process ends by turning off “clutch 2” (5) and “clutch 1” (2).

In FIG. 3 shows a clutch variant that provides synchronization of wing rotation and contains the following elements:

1s - electromagnet,

2s - master drive,

3s - pin

4c - friction disk (with friction pads),

5c - clamping disk,

6c - release bearing

7c is an elastic plate.

The lower electromagnet is conventionally shown in the on state (the upper one is in the off state). In normal mode, both electromagnets work in concert.

Claims (1)

An aircraft comprising a fuselage, a wing, a horizontal and a vertical tail unit, a power plant, preferably of two engines, a transmission, streamlined horizontal beams, a landing gear, a horizontal thrust propeller, rotating left and right round wings, each of which is made with the possibility of braking rotation and has swinging blades radially spaced around the perimeter, characterized in that each said blade is configured to achieve maximum about the lower point of its oscillation at the moment when the projection of the axis of the blade during rotation of the wing intersects with a line passing through the axis of the wing and parallel to the axis of the fuselage, while the free end of the blade is directed to the nose of the aircraft and it is possible to rotate the wings so that the same pair of blades of the left and right wing reaches the maximum lower point of oscillation at the same time.

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