RU2288141C1 - Flying vehicle - Google Patents

Abstract

FIELD: aircraft manufacture; designing aircraft and gliders.

SUBSTANCE: proposed flying vehicle has fuselage 1, panels 4 and 5 with controls 9 and 10 and vertical tail 3 in tail section of fuselage. Center of mass is located in plane of symmetry of fuselage between two vertical straight lines on which centers of pressure of two panels (set apart along length of fuselage) are projected. Flying vehicle is provided with steeped wing; it is monoplane in modification slightly sensitive to shift of center of mass and with no relative effect of lifting and stabilizing planes. Auto-rotation in horizontal plane is excluded due to profiling of lower surface of fuselage in such way that total aerodynamic moment of rotation around center of mass in horizontal plane is equal to zero. Auto-rotation is also excluded at use of panels of opposite sweep with twist.

EFFECT: enhanced longitudinal stability; reduction of interference.

3 cl, 3 dwg

Description

The invention may find application in aircraft construction, for example, in the design of gliders and aircraft.

The aim of the invention is the elimination of loss of interference between the wings and increase the longitudinal stability of the aircraft by the stepwise arrangement of the wings (consoles).

The famous single-seat glider tandem BA-1 designed by A.A. Borin, O.K. Antonov, built in 1935 (See A.P. Krasilshchikov "Gliders of the USSR", Moscow, Mechanical Engineering, 1991).

Signs of a glider tandem BA-1:

a) tandem wing biplane;

b) the center of mass is located in the plane of symmetry of the fuselage, between two vertical lines on it, onto which the pressure centers of the four consoles, spaced along the length of the fuselage, are projected (coincides with the feature of the invention, except for the number of consoles);

c) vertical plumage at the ends of the hind wing.

The BA-1 tandem glider is a biplane in a variant that is slightly sensitive to the displacement of the center of mass.

The following circumstances prevent the exclusion of interference losses between the wings of the glider tandem BA-1. Installing the rear wing of the BA-1 glider above its front wing weakens the effect of the wings on each other, but does not exclude it. The interaction of the wings increases the overall resistance compared to the sum of the resistances of similar isolated wings.

Loss of interference between the wings of the BA-1 glider remains due to the tandem scheme.

Famous aircraft invented in Russia by Bumakov V.D. (21) 97 118 157/28; (22) 10.30.97; (51) 6 B 64 C 39/08; (72) Bumakov V.D .; (71) Bumakov V.D .; (74) Grunin A.E .; (98) 12.11.65; Moscow, PO Box 15, LLC Justis (54) Airplane. Official Bulletin of the Russian Agency for Patents and Trademarks. Inventions (applications and patents) 1999 FIPS Moscow 20 (1 part).

Signs of the aircraft Bumakova V.D .:

a) tandem wing biplane;

b) the center of mass is located in the plane of symmetry of the fuselage, between two vertical lines on it, onto which the pressure centers of four consoles, spaced along the length of the fuselage, are projected (coincides with the feature of the invention, except for the number of consoles);

c) vertical plumage at the ends of the hind wing.

Aircraft Bumakova V.D. - This is a biplane in a variant that is slightly sensitive to the displacement of the center of mass. But the interference losses between the wings of this aircraft remain due to the tandem scheme.

Known aircraft with connected wings, invented in the UK. The prototype of the invention. (51) MKI 4 V 64 C 39/08; (11) Application N 2208112; (52) NKI B 7 W; Publication 890301 N 9; (53) UDC 629735; (54) Aircraft with connected wings. Inventions of the countries of the world. Abstract information. All-Union Research Institute of Patent Information. Issue 48 MKI B 64 N 12, Moscow, 1989. Ballooning; aviation; astronautics.

Signs of an aircraft with connected wings:

a) a biplane with connected wings;

b) the center of mass is located in the plane of symmetry of the fuselage, between two vertical lines on it, onto which the pressure centers of the four wings are projected (coincides with the feature of the invention, except for the number of wings);

c) vertical plumage in the rear of the fuselage (coincides with a feature of the invention).

An aircraft with connected wings is a biplane in a variant that is slightly sensitive to the displacement of the center of mass. But the interference losses between the wings of this aircraft remain due to the two-winged scheme.

It is known that biplanes in terms of both lift and speed are inferior to monoplanes with the same wing area. This is due to the mutual influence of the wings of the biplane and the additional resistance created by the uprights and stretch marks.

Therefore, the monoplane is declared in a modification that is slightly sensitive to the displacement of the center of mass and without the mutual influence of the bearing and stabilizing planes. This is an aircraft with vertical plumage in the rear of the fuselage and a step wing. Its center of mass is located in the plane of symmetry of the fuselage, between two vertical lines on it, onto which the pressure centers of two consoles, spaced along the length of the fuselage, are projected.

Low sensitivity to the displacement of the center of mass increases the longitudinal stability of the aircraft.

Also excluded are interference losses between consoles located on opposite sides of the fuselage.

The following contradictions were resolved.

1. As a result of the removal of the consoles from each other (within the length of the fuselage), the moments of rotation around the center of mass increase. This leads to poor controllability and an increase in the mass of the durable fuselage bearing a torsional load.

2. The stepped arrangement of straight trapezoidal consoles in the presence of a transverse V angle and a vertical descent speed causes the aircraft to rotate around the center of mass in the horizontal plane.

3. The removal of the front console to the nasal tip limits the field of view of the pilot.

Regarding the solution of the first contradiction. An estimate of the distances from the center of mass to each center of pressure of the cantilevers for the two layout options (an aircraft with a step wing and a classic monoplane glider) shows their small difference. This difference is within 10% with a wingspan of 15 meters and a distance of 3 meters between projections on the plane of symmetry of the fuselage of the pressure centers of the step wing.

This means that the moments of rotation around the center of mass of an aircraft with a step wing for this case will differ little in magnitude from the moments of rotation around the center of mass of a classic monoplane.

Therefore, the size and shape of the aerodynamic controls for an aircraft with a stepped wing can be calculated by methods known for the classic monoplane.

Regarding the solution of the second contradiction. The elimination of self-rotation in the horizontal plane of an aircraft with a step wing can be achieved in two ways. In one embodiment, the front console can be a direct sweep with a negative twist, and the rear console can be a reverse sweep with a positive twist. In another embodiment (cantilevers without sweeps), the lower surface of the fuselage is profiled from the projection of the center of mass to the tail end so that the aerodynamic moment of counter-rotation occurs in flight.

The total aerodynamic moment of rotation around the center of mass in the horizontal plane in both cases should be equal to zero.

Regarding the solution of the third contradiction. Removing the left console to the front end of the aircraft limits the pilot's field of vision. The field of view of the pilot in this case can be expanded using technical means. In the cockpit set the screen of the field of view of the camera, remote and installed in front of / under the front console.

Technical result

A stepped-wing aircraft is a new layout scheme for a glider (airplane) with increased longitudinal stability and without interference.

Figure 1 Aircraft with right wing, front view.

Figure 2 The same, a top view.

Figure 3 The same, left view.

The front view of the aircraft with left-wing wing is a mirror image of figure 1.

A top view of an aircraft with a left-wing wing is a mirror image of FIG. 2.

The right side view of an aircraft with a left-wing wing is a mirror image of FIG. 3.

The fuselage 1 with the cockpit 2 and the vertical tail 3. Front, low in the nose of the fuselage, console 4.

Rear, high in the middle of the fuselage, console 5.

The cockpit 2 is closed by a streamlined transparent removable cap 6. The rudder 7 is installed on the vertical tail unit 3. The lower surface of the fuselage has a profiled surface 8 from the projection of the center of mass of the aircraft to the tail end. Consoles 4 and 5 have controls 9 and 10. During flight, the load is evenly distributed on the front console 4 and the rear console 5.

The oncoming air flow, flowing around the console 4, 5 and the vertical tail 3, creates forces that stabilize the longitudinal and track stability of the aircraft.

Flight control is carried out by means of controls 7, 9, 10.

In flight, an aircraft with a step wing will develop greater lift and higher speed than an aircraft with a tandem wing arrangement and equal specific load.

An aircraft with a step wing can be used for training by the export method and for glider (airplane) sports. Throughout the existence of aircraft, designers improve them using advanced materials and technologies for their time. So, the USSR record-breaking glider LAK-15 was made using composite materials (see A.P. Krasilshchikov. Gliders of the USSR. Moscow. Mechanical Engineering, 1991).

In the design of an aircraft with a stepped wing, special attention will be required to the pilot's cabin and part of the fuselage between the consoles, which constantly carries a torsional load.

Claims (3)

1. Aircraft containing the fuselage, consoles with controls, vertical tail in the rear of the fuselage, characterized in that the center of mass is located in the plane of symmetry of the fuselage between the two vertical lines on it, onto which the pressure centers of the two consoles extended along the length of the fuselage are projected. 2. The aircraft according to claim 1, characterized in that the lower surface of the fuselage from the projection of the center of mass to the tail end can be profiled. 3. The aircraft according to claim 1, characterized in that the front console can be a direct sweep with a negative twist, and the rear console can be a reverse sweep with a positive twist.

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