Mukhamedov's wing

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Wing 1 comprises wing center section made up of shaped bearing disk 2 with front and rear edges along generatrix of bearing disk. Panels 3 are jointed with wing center section bearing disk 2 on its sides so that the shape of front and rear edges of said disk 2 are unchanged along said generatrix in plan. Wing panels 3 feature trapezoidal and sweep and/or rectangular aerodynamic shape. Wing 1 has aerodynamic extensions 4 made along wing lengthwise axis at wing front on both sides that feature triangular and ogival aerodynamic shape in plan.

EFFECT: higher maneuverability.

5 cl, 7 dwg

 

The invention relates to aircraft and can be used when designing a wing for maneuverable fighter aircraft, training aircraft, aircraft have to meet certain requirements on manoeuvring characteristics.

The current level of technology know annular wing aircraft designer Richards, arranged on the plane in a horizontal plane, and having a controllable aerodynamic surfaces (see Dasavali, "Aircraft special schemes." M: "engineering", 1989, str, RES).

To achieve the desired technical result in the analog of the claimed device prevents the fact that it had wings essentially no bearing center section wing ring in the horizontal plane is a ring with a hole in the middle.

The current level of technology is also known wing of American aircraft company McDonnell Douglas created the AFTI program (Advanced Fighter Technology Integration), consisting of a center section and consoles, connected with the center section of its sides. The console is made integrally rotatable with the possibility of unidirectional and differential deflection. Turning the console have slats, say no to high angles of attack. The fuselage of the aircraft is displaced along the longitudinal axis relative to the center section of the wing and smoothly connected with him (is. The results of science and technology. Aircraft engineering, volume 2, Strukov P. "Modern aircraft USA and countries of Western Europe, part II, VINITI, 1976, s-171, RIS, 235).

To achieve the desired technical result in the analog of the claimed device prevents the fact that it itself bearing center section of the wing such, indeed, is not, and is part of a load-bearing fuselage.

The closest technical solution chosen for the prototype is wing discipline developed in the USSR in the 1960-ies containing the wing center section, made in the form of a profiled support disc in the front and rear edges for forming a support disc - wing performed "round" (see N.a.suhanov, "Man overcomes gravity", the magazine "Wings of Motherland", 1960, No. 6, p.16, 17).

The distinguishing characteristics of the circular wing, in contrast to the triangular and square are unseparated, its smooth flow to large angles of attack α=45°, the maximum lift coefficient Cymax=1.8V, the maximum angles of attack of the round wing is stable parachutisme, without trends stall into a spin, which is typical for all other wings.

To achieve the desired technical result in the prototype prevents that the round wing low value of the aerodynamic qualities of the (Kmah=7) and low values of lift coefficient at take-off and landing modes 12°-15°, what makes the development of an aircraft from a purely round wings and high wing loads typical of modern aircraft.

Task to be solved by the claimed invention is directed, is the creation of a wing for maneuvering aircraft with high aerodynamic performance in all flight modes.

Technical results achievable with the use of this invention, include the increasing aerodynamic properties of the wing and increase the value of the lift coefficient at take-off and landing modes, leading to increased lifting force on transitional regimes and improving the maneuverability of the aircraft, which claimed the wing can be applied.

The problem is solved and the technical result is achieved by the fact that the wing includes a wing center section, made in the form of a profiled support disc in the front and rear edges for forming a rotor disk, console, connected to a host drive of the center section at its sides preserve the shape of the front and rear edges of the support disc by forming a support disc in plan, and having a trapezoidal plan, and/or arrow-shaped, and/or rectangular and/or arbitrary aerodynamic shape and aerodynamic flows along the longitudinal axis of the wing, located in the front it is part and on both sides from the longitudinal axis of the wing, and having a triangular plan and/or ogival and/or arbitrary aerodynamic shape.

Wing profiled on the host drive of the center section can be performed aerodynamic control surface in the form of nasal segments of the support disc of the center section with the front edge along the circumference of the rotor disk, and nasal segments are pivoted each on its axis coinciding in its continuation in the plan with the front edge of the adjacent console.

In the wing, each of the consoles can be made rotatable, equipped with say no to toe and installed on the host drive of the center section of the wing hinge so that the axis of rotation deny each sock turning the console and the axis of rotation adjacent a nasal segment of the support disc of the center section parallel with each other in the plan, and the point of application of the increment of the total positive or negative lifting force Y when the deviation of the rotary consoles as close as possible to the point of the aerodynamic center with the possibility of a control without changing the longitudinal moment.

Wing shaped bearing disk of the center section of the wing may be provided with a feed segments, placed on either side of its longitudinal axis, is made rotatable relative to the transverse axis of profileroland the th support disc of the wing center section, located behind the axis of rotation of the outer wings along the longitudinal axis of the wing, with the possibility of differential deflection of the swivel segments and fulfil functions such as ailerons and flaps.

The wing elements may be arranged in such a way that the aerodynamic focus of the wing can be located by 0.4 chord shaped rotor disk of the center section with the 5%-10% of static instability, and the center of gravity of the wing is located at the geometric center of the profiled support disc of the center section.

The invention is illustrated by drawings, where

figure 1 shows the claimed wing in the plan in combination with swept consoles and arched waves in the sample layout on an aircraft;

figure 2 - wing in the plan in conjunction with trapezoidal consoles and arched waves in the sample layout on an aircraft;

figure 3, 4, 5 - wing in the plan in conjunction with its various elements (triangular, arched flows; rectangular, jib etc. console) and in the example layout for an aircraft;

figure 6 - wing in one of its possible configurations on an aircraft with controllable aerodynamic surfaces according to claim 2-5 claims;

7 is a chart formation lifting force declared the wing.

Wing 1 contains centrop the Academy of Sciences, made in the form of profiled rotor disk 2 in plan with front and rear edges for forming a rotor disk.

Console 3 is connected with the bearing disk 2 of the center section at its sides preserve the shape of the front and rear edges of the bearing disk 2 component in the plan.

Console 3 can have a trapezoidal plan, and/or arrow-shaped, and/or rectangular and/or arbitrary aerodynamic shape.

Wing 1 has an aerodynamic flows 4 along the longitudinal axis of the wing 1, located at the front and on both sides of the longitudinal axis of the wing 1, and having a triangular plan, and/or ogival, and/or arbitrary aerodynamic shape.

Elements of the wing 1 may be arranged in such a way that the aerodynamic focus of the wing 1 is 0.4 chord shaped rotor disk 2 of the center section with the 5%-10% of static instability, and the center of gravity of the wing 1 is located at the geometric center of the profiled support disc 2 of the center section.

Wing 1 on the shaped support disk 2 of the center section can be performed aerodynamic control surface in the form of nasal segments 5 of the bearing disk 2 of the center section with the front edge along the circumference of the rotor disk 2.

Nasal segments 5 are pivoted each on its axis coinciding in its continued and in plan with a front edge adjacent the console 3.

Wing 1 each of the 3 consoles can be made rotatable, equipped deny toe 6 and installed on the host disk 2 of the center section of the wing 1 hinged so that the axis of rotation deny sock 6 each rotary console 3 and the axis of rotation adjacent a nasal segment 5 of the bearing disk 2 of the center section parallel with each other in the plan, and the point of application of the increment of the total positive or negative lifting force Y rejecting turning 3 consoles as close as possible to the point of the aerodynamic center with the possibility of a control without changing the longitudinal moment.

Wing 1 profiled bearing disk 2 of the center section of the wing 1 may be provided with a feed segments 7, placed on either side of its longitudinal axis, is made rotatable relative to the transverse axis of the profiled support disc 2 of the center section, located behind the axis of rotation 3 consoles wing 1 along the longitudinal axis of the wing 1, with the possibility of differential deflection of the swivel segments 7 and fulfil functions such as ailerons and flaps.

The wing performs its functions as follows.

Being arranged in a certain way on an aircraft wing is an organic component and an aerodynamic element, creating a lifting effect.

the example of the functioning of the wing Mukhamedova can be illustrated by using elements, shown in Fig.6 of the drawings of the present application.

Before takeoff the aircraft on which you installed and which are arranged declared wing 1, the rotary console 3 wing 1 reject at a positive angle of attack and aft segments of the 7 host drive 2 of the wing 1 in mode reject flaps on take-off angle. This nasal segments 5 of the bearing disk 2 of the wing 1 reject down at a negative angle of an axis coinciding in its continuation in the plan with the front edge of the adjacent rotary console 3.

In flight while maneuvering in the vertical and horizontal planes when the deviation is turning 3 consoles at a given angle with the simultaneous deviation of the nasal segments and socks 5 6 3 consoles, the axis of rotation which are parallel to each other in the plan, increments the lifting force is proportional to the angles of deflection of the mentioned control of the aerodynamic surfaces. Increment the lifting force occurs near the center of gravity of the aircraft, which allows you to make spatial maneuvers without changing the angle of attack, i.e., to exercise direct control of the lifting force.

It is important to note that in a particular wing configuration Mukhamedova on an aircraft, the point of application of the increment of the total positive or negative lifting force plane Y when you reject the AI turning 3 consoles can be as close as possible to the point of the aerodynamic center with the possibility of a control without changing its longitudinal moment.

In large and critical angles of attack on command reject nasal segments and socks 5 6 3 consoles that allows you to tighten the disruption of the flow at even greater angles of attack.

When the differential deflection of the swivel 3 consoles with the simultaneous deviation of the nasal segments 5 of the disk 2 of the center section and socks 6 3 consoles, the axis of rotation which are parallel to each other in the plan, manage the roll in a wide range of angles of attack.

When the glide-slope descent reject nasal segments and socks 5 6 3 consoles with the simultaneous deviation of fodder segments 7 in the mode of flaps, which reduces the distance reduction.

In the claimed invention as 3 consoles can be used console having a trapezoidal plan, and/or arrow-shaped, and/or rectangular and/or arbitrary aerodynamic shape.

Trapezoidal, arrow-shaped, rectangular or arbitrary aerodynamic shape consoles can be used in the same combination (arrow - arrow-shaped, rectangular - rectangular and the like), and in the alternative combination forms consoles (swept - rectangular, trapezoidal - swept, arbitrary rectangular, etc. aerodynamic shape).

However, in alternative combination forms consoles in terms of this model on the face of the wing and the aircraft in General, on which such wing arranged, becomes unbalanced.

Examples of asymmetrical wings and aerodynamic configurations of aircraft with them in aviation history is known and they have their advantages.

With the modern development of on-Board electronics of the aircraft aerodynamic control asymmetrical wings and the aircraft on which such wings in a certain way linked, is not a difficult technical task.

The benefits of such aircraft with the declared wing associated with increased maneuverability in flight, especially important, for example, in the air confrontation, are preserved.

Also in the claimed invention as of aerodynamic flows 4, placed along the longitudinal axis of the wing 1, and located at the front and on both sides of the longitudinal axis of the wing 1, can be applied to flows having a triangular plan, and/or ogival, and/or arbitrary aerodynamic form.

Triangular, arched or arbitrary aerodynamic shape flows 4 can also be used as in the same combination (triangular - triangular, arched - ogival etc), and in the alternative combination of form flows 4 (triangular - arched, arched arbitrary Aero is enmicasa form of influx, etc.).

As noted above, examples of asymmetrical wings and aerodynamic configurations of aircraft, as well as special aerodynamic schemes and layouts of aircraft in aviation history is known and they also have their advantages (see Dasavali, "Aircraft special schemes." M: "engineering", 1985, p.27, RIS; p.38, (figure 1.15), 1.16; p.47, RIS; p.108, RIS; p.110-112, RIS, 2.9, 2.10).

Wing Mukhamedova can be performed by traditional constructive way (metal, wood, carbon and the like) and are produced under conditions of serial and/or experimental production.

1. The wing containing the wing center section, made in the form of a profiled support disc in the front and rear edges for forming a rotor disk, console, connected to a host drive of the center section at its sides preserve the shape of the front and rear edges of the support disc by forming a support disc in plan, and having a trapezoidal plan and swept and/or rectangular aerodynamic shape and aerodynamic flows along the longitudinal axis of the wing, located at the front and on both sides of the longitudinal axis of the wing, and having triangular and arched aerodynamic shape.

2. Wing according to claim 1, characterized in that the profiled host drive of the center section of the wing is made to Desk the matter of aerodynamic surfaces in the form of nasal segments of the support disc of the center section with the front edge along the circumference of the rotor disk, and nasal segments are pivoted each on its axis coinciding in its continuation in the plan with the front edge of the adjacent console.

3. Wing according to claim 1 or 2, characterized in that each of the consoles are pivoted equipped deny toe and installed on the host drive of the center section of the wing hinge so that the axis of rotation deny each sock turning the console and the axis of rotation adjacent a nasal segment of the support disc of the center section parallel with each other in the plan, and the point of application of the increment of the total positive or negative lifting force Y when the deviation of the rotary consoles as close as possible to the point of the aerodynamic center with the possibility of a control without changing the longitudinal moment.

4. Wing according to claim 1 or 3, characterized in that the profiled bearing disk of the center section of the wing is equipped with aft segments, placed on either side of its longitudinal axis, is made rotatable relative to the transverse axis of the profiled support disc of the wing center section, located behind the axis of rotation of the outer wings along the longitudinal axis of the wing, with the possibility of differential deflection of the swivel segments and fulfil functions such as ailerons and flaps.

5. Wing according to claim 1, characterized in that the wing elements is arranged so what this model the focus of the wing is 0.4 chord shaped rotor disk of the center section with regard to 5-10% of static instability, and the center of gravity of the wing is located at the geometric center of the profiled support disc of the center section.



 

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