RU10677U1 - AIRPLANE WITH FLAT TAILS - Google Patents

Abstract

A plane with a tail unit comprising a fuselage, wings, tail unit with two bearing surfaces, a landing gear, a power plant and kinematic control levers, characterized in that on the two rear edges of the horizontal tail unit there are double rudders mounted at an acute angle to the axis of the fuselage with the possibility of sectorial movements up and down, and at the place where the rudders were sealed in the fuselage, kinematic control levers, consisting of steering levers, to which four rods are articulated, are connected to their axles going in pairs crosswise to the rocker arms, which have the possibility of sectorial movements relative to the hinge bracket, which is connected to the pedal by the upper end, and its hinge is fixed in the rack, which, in turn, is connected to a rocker bearing a hinged steering wheel connected by rods to the rocker arms.

Description

M.cl. B64G 7/00; 9/00 Author: Dyabin N.V.

self-propelled flat tail

The present invention relates to the field of aircraft industry in participation, to the design of the tail unit of the aircraft and its steering.

A plane is known, the tail of which has a swept shape, and the rudders have rotations located at g @ 9 fb} bi angle with respect to the axis of the foselage (I).

The disadvantage of this aircraft design is the low flight performance in handling.

A plane (2) is taken as a prototype of the invention, the tail unit of which consists of two planes, the angle between which is. Aerodynamic rudders are made along the trailing edges of the planes with the possibility of free deflection up and down relative to the longitudinal axes of the planes. Through brackets and a hinge, the trailers are connected to a system of kinematic levers and foot controls.

The disadvantage of this aircraft is the complexity of its control scheme, in addition, the area of the "" -nimous plumage, in particular the rudders themselves, meet the incoming air stream at a large angle of inclination, which reduces its ability, and in general, all this reduces the flight characteristics of the machine.

To increase the flight characteristics of the aircraft by simplifying its control scheme and increasing unreliable abilities, the proposed aircraft contains a fuselage, wings, j ocTOBoe plumage with two bearing surfaces, a landing gear, a power plant and kinematic control levers. New is that there are two trailing edges of the horizontal tail the feathers are made of double rudders mounted at an acute angle to the fuselage © with the possibility of sectorial movements up and down, and at the place where the rudders were sealed in the fuselage, kinematics were brought to their axes natural control levers, consisting of steering levers, to which a tire has been connected to the four rods running in pairs crosswise to the yokes and the ability to

Plumage

sectoral evacuations of an ethno-symbolic bracket, the top end of which is connected to the pedal, and its hinge zaf1 $ ksirdvan in the rack with the end in turn is connected in turn to the articulated carrier rocker, connected by rods to the bracket arm.

On F1G. I of the accompanying drawings shows a proposed aircraft, side view; y, in FIG. Z "front view in FIG. 3 section in FIG. 2, on city 4 Yu1nematichvsk 1st scheme of levers of steering control, on f {g. 5 a diagram of the position of the rudders when cabling the aircraft; FIG. 6 a diagram of the position of the rudders during a dive of an airplane; FIG. a diagram of the position of the rudders when changing the flight direction to the left, in FIG. 8 “a diagram of the position of the rudders when changing the flight direction to the right, in FIG. 9 is a diagram of the position of the rudders during the roll of the aircraft from left to right, in FIG. 10 a diagram of the position of the rudders and flinting of the aircraft right to the left; on city II a diagram of the position of the rudders while increasing the effectiveness of the rudders and flight stability.

The proposed aircraft contains the fuselage I, connected to the wing 2, turbojet engines 3, the left and landing gear 4, the central landing gear 5, on the tail of the fuselage mounted in the form of two brackets horizontal tail unit 6, on the rear edges of which are made by two pairs of steering wheels 7 (cm Fig. 4), installed at an acute angle to the axis (| of the user with the possibility of sectorial movements up and down. The steering levers 8 are connected to the balls of the four rudders on the side of the fuselage, as four links 9 are pivotally connected in pairs crosswise to the cor Thought 10 and having the possibility of sectorial movements relative to the articulated arm II, one end of which is connected to the pedal 12, and its shariir zaf {ksir01an in rack 13, to which, in turn, is rocked by a rocker 14, which carries the articulated steering wheel 15 connected at the top spherical hinges with rods with brackets 17 rocker arms 10.

And the flight of rush is always ajar. This orientation of the rudders in space ensures the stability of the flight of the aircraft along the course and altitude.

The device operates as follows.

When the pilot deflects the rocking chair 14 to himself through the thrust 16, the brackets 17 of the rocker arm 10 half-sectional sector movements with the upper ends of the rockers back and the lower ends forward, corjiacHo

what is the thrust 9, cross-over® to the left-hand side of the boat 8, moving the steering wheel pair 7 onwards, and the plane will be wheeled If the pilot deflects the rocker, the rudders 7 lower themselves and the airplane gets a dive moment. When the hinge rudder 15 is turned through the TAG 16, versatile sectorial movements are made for the brackets 17 and the rocker arms 10. For example, when the IS rudder is turned to the right, the right rocker 10 moves with the upper part and upper link 16 to the pilot, and the lower end of the rocker 10 and lower link 16 from the pilot . Since the thrusts go to the steering levers 8 crosswise under the considered action of the right rocker arm 10, the right pair of rudders 7 deviates upward. At the same time, by moving the left link 16 of the bracket 17 upward, the upper left link will move from the pilot, and the lower left link 16 to the pilot. P @ q their influence rudders 7 will fall down and airplane1 will receive a heeling moment from left to right. When the pilot turns the articulated steering wheel 15 to the left. Similarly, in order, the steering wheels 7 deviate right down, and left up and the plane will receive a heeling moment from right to left.

When the pilot presses the left pedal 12, the bracket II and the left rocker 10 will move before. The left pair of rods 9 through the levers of the rudders 7 will deflect the upper rush up, and the lower left rudder down. When they interact with the oncoming air flow, the aircraft will receive a torque by changing the direction of movement from right to left. Pressing the pilot right pedal 12 deflects the right handlebars 7 and the aircraft receives torque from left to right.

Ex {1 pressed by the pilot simultaneously with the left and right pedals, an overview of the pair of rudders is opened. This action is used u) and the need to increase the efficiency of the rudders and increase the stability of flight in extreme conditions of flight of the machine, for example, during take-off, landing, turning, stalling.

Teams to change the flight altitude, heading or roll can simultaneously be performed by cy ttA pilot’s arms and legs. It can be performed in small increments, ensuring a smooth flight of the aircraft along the most complex trajectories.

Compared with existing aircraft designs, the proposed aircraft has the following advantages:

lateral vibrations under the action of incident turbulent air flows;

 the action of air sweats, the lifting force of the planes acts vertically, and not at an angle to it, as a “plumage”;

-the two-surface horizontal tail unit provides a variety of options for putting its work in the mode of development of lifting force from the bottom up.

This is the number of factors listed above, and the weight return of the tail feathering, which ultimately increases the load-bearing capacity of the aircraft.

In the aircraft we offer, U1C is achieved) flight sustainability due to the following:

 in the lettering of “1 four wheels are used instead of two, they are aamiMaxjT symmetrical position relative to the flight path;

- the system of kinematic levers for controlling the rudders is simpler and more advanced and transmits only those commands that are needed: hands control the aircraft in height through the rocker, hands through the shirshfday rudders for misleading the right and left rudders to get the heeling of the airplane, and pedads to open one of the pairs rudders to obtain the moment of change in the course of the aircraft;

 the rudders provide a new seventh kind of command when the pilot pedals opens all four rudders and a team is formed to slow down the flight of the aircraft or to increase the aerodynamic moments p5 / lei with a subsequent change in their position depending on the control teams;

- all teams are summed up and easily individually changed in small increments, which is necessary for smooth adjustment of the flight of the aircraft.

Claims (1)

A plane with a tail unit comprising a fuselage, wings, tail unit with two bearing surfaces, a landing gear, a power plant and kinematic control levers, characterized in that on the two rear edges of the horizontal tail unit there are double rudders mounted at an acute angle to the axis of the fuselage with the possibility of sectorial movements up and down, and at the place where the rudders were sealed in the fuselage, kinematic control levers, consisting of steering levers, to which four rods are articulated, are connected to their axles going in pairs crosswise to the rocker arms, which have the possibility of sectorial movements relative to the hinge bracket, which is connected to the pedal with its upper end, and its hinge is fixed in the rack, which, in turn, is connected to a rocker bearing a hinged steering wheel connected by rods to the rocker arms.