Training flight yak-54

 

(57) Abstract:

The invention relates to aviation, in particular to the training of flight and aircraft. The aircraft includes a fuselage, a propeller located in the forward fuselage, a propulsion unit for driving the screw, trapezoidal symmetric wing profile, consisting of polycrylic with ailerons, horizontal and vertical tail, and the plane of the chord of the profile of each polycryl, construction horizontal fuselage and the axis of the propeller are located in one plane. On the bottom of each Aileron polycryl in the middle part is made aerodynamic joints. The wing is made by lengthening 5-5,3, the ratio of the area of the ailerons to the wing area is 23-25%, the ratio of the distance from the center of gravity of the aircraft up to 25% mean aerodynamic chord of the vertical tail is not more than 2/3 of the total length of the aircraft. The control system is designed with flaps down to the 15oif possible differential deflection relative to the released position. The aircraft is equipped with a hatch in the bottom of the fuselage, in which you installed the glass. The invention is aimed at improving aerobatic and agile is, the sludge.

The invention relates to the field of aviation, in particular to the training of flight and aircraft.

Famous aerobatic plane containing the fuselage, propeller, located in the nose of the fuselage, a propulsion unit for driving the screw, trapezoidal wing, which is made so that the plane of the chord of the wing, building horizontal fuselage and the axis of the propeller are located in one plane, ailerons, located on the wing, horizontal and vertical tail, the control unit Aileron /USSR Author's certificate 764275, 64 1/26, 1982/.

The plane has limited capabilities when performing aerobatics.

Also known training, double, aerobatic YAK-52, containing the fuselage, propeller, located in the nose of the fuselage, a propulsion unit for driving the screw, trapezoidal wing asymmetrical profile, consisting of polycrylic with ailerons, horizontal and vertical tail, and the plane of the chord of the profile of each polycryl, construction horizontal fuselage and the axis of the propeller are located in one plane /Jane's. All the word's Aircraft. 1994-95, R. 281/.

Known samag the ratio of maximum positive and negative overload +Uy/-Uyor = 0.6, which negatively affects the running back figures.

The minimum allowable airspeed defined by the design of the aircraft, it is not possible to obtain a high landing characteristics.

Low weight impact design affects performance.

The wing is made with asymmetrical profile and complex shape of the outer surface, and therefore has a high complexity of manufacturing.

The objective of the invention is the creation of training, double, aircraft, high flight and maneuvering characteristics for all flight modes when performing a complex set of aerobatics.

Another object of the invention is the increase of weight of the aircraft structure by reducing the length of the rear fuselage while maintaining the static moment of the vertical fin and the increase maneuvering and handling properties of the aircraft.

The invention is directed also to the increase in disposable overload when performing reverse aerobatics due to the symmetrical wing profile.

To solve ukazanny the forward part of the fuselage, power unit for driving the screw, trapezoidal wing, consisting of polycrylic with ailerons, horizontal and vertical tail. Thus the plane of the chord of the profile of each polycryl, construction horizontal fuselage and the axis of the propeller are located in one plane.

On the bottom of each Aileron polycryl in the middle part is made aerodynamic joints.

The wing is made with symmetrical profile elongation 5-5,3.

To increase the effectiveness of the ailerons value ratio of the area of the ailerons to the wing area is 23-25%.

The ratio of the distance from the center of gravity of the aircraft up to 25% mean aerodynamic chord of the vertical tail is not more than 2/3 of the total length of the plane.

The aircraft can be fitted with a hatch in the bottom of the fuselage, in which you installed the glass.

In a preferred embodiment, the aircraft power plant has a four-stroke air-cooled engine, the fuselage type polymenakos and srednerosloe wing relative to the fuselage.

The aircraft has a three-bladed controllable-pitch propeller and a trapezoidal tail surfaces.

Reduction rasmala tail reduces the mass of the aircraft, hence, to increase maneuverability and aerobatic properties at a constant value of the static moment.

INin= (SinLintoC.t)/(Skrlkr) = const,

where Sin- the area of the vertical fin,

Skr- wing area,

LindaboutC.tdistance from the center of gravity of the aircraft up to 25% mean aerodynamic chord of the vertical tail,

lkr- wing span.

When equal to the squares of Sinand Skrby reducing elongation relative to the prototype to 5-5,3 it is possible to reduce the wing span lkrand length LintoC.tand consequently to reduce the weight of the fuselage as a whole by 20%.

The invention is illustrated by drawings.

Fig. 1 - General view of the YAK-54.

Fig. 2 is a plane side view.

Fig. 3 is a plane front view.

Fig. 4 is a plane view from above.

Fig. 5 is a graph of the effect of lengthening the relative disposable speed roll.

Fig. 6 is a graph of the effect of relative area of the ailerons on the relative disposable speed roll.

Training flight YAK-54 (foda screw 2, trapezoidal wing 3 symmetric profile, consisting of polycrylic 4 and 5 with the ailerons 6 and 7, the horizontal trapezoidal tail 8 and the vertical tail 9.

The aircraft has retractable with hollow springs tricycle landing gear, made with a tail wheel.

The plane of the chord of the profile of each polycryl 4 and 5, building 10 horizontal fuselage 1 and the axis of the propeller 2 is located in the same plane.

On the bottom of each Aileron polycryl 4 and 5 in the middle part is made aerodynamic joints 11 and 12.

In the Central part of the fuselage is a double cabin 13 crew.

Wing 3 is made with extension

kr= lkr/insakh= 5,15,

where lkr- wingspan,

insakh- mean aerodynamic chord.

Wing 3 is made with a symmetric profile relative to the chord. The ratio of the area of the ailerons 6 and 7 to the square of the wing 3 is determined from the dependence of Se= Se/Skr100% = 23-25%.

The fuselage is made in such a way that the ratio of the distance LC. o.from the center of gravity of the aircraft up to 25% mean aerodynamic chord of the vertical tail 9 is not more than 2/3 of oblena glass. The hatch is designed for visual orientation and observation of the lower hemisphere when flying in a confined space 1x1x1 km.

Aircraft power plant has a four-stroke air-cooled engine.

The aircraft has a three-bladed screw 2 controllable pitch, the fuselage 1 type polymenakos and srednerosloe relative to the fuselage 1 wing 2.

In the system 15 of the control plane, there is an additional control channel ailerons 6 and 7 to "hang", i.e. the root part down to 15 degrees with a possibility of their differential deflection relative to the released position.

In flight when the deflection of the ailerons 6 and 7 in opposite directions at an angle of 25 degrees changes the profile of the wing 2 so that the difference in the lifting force of polycrylic creates krenawi moment about the longitudinal axis.

The deflection of the ailerons in opposite directions causes the increment of the lifting forces on the right and left polacrilex directed in opposite directions. The result is the aerodynamic moment causing rotation of the plane in the side of the raised Aileron.

The experiments showed that the maximum IC is E. according to the program of world Champions.

Angular deflection of the ailerons on the maximum angle provides the YAK-52 rotating with a speed of up to 3.5 rad/sec.

The effectiveness of the transverse control of the proposed YAK-54 at 70% higher, which is confirmed by experimental studies of models in wind tunnels (Fig. 5 and 6). The position of the point a corresponds to the characteristics of the YAK-52, and the position of the point B corresponds to the characteristics of the YAK-54.

The degree of influence on the relative disposable speed roll lengthening is 30%.

The optimal size of lengtheningkr= 5 - 5,3 (Fig. 5).

The greatest degree of influence on the speed of the roll relative to the area of the ailerons 6 and 7 is 40%, and the optimal degree of influence 23-25% (Fig. 6).

When the reverse figures improved flight properties of the aircraft, with symmetrical wing profile, due to the convergence of disposable and maximum negative g-forces. This allows for increased training of pilots to participate in the world Championships.

In flight when the deflection of the ailerons 6 and 7 tail down angle up to 15 degrees you can perform aerobatic complex by differential from avicenia" ailerons 6 and 7 at an angle up to 15 degrees allows you to have the minimum flight speed by 10% compared with the prototype, i.e. significantly improve the landing characteristics.

The plane passed factory bench tests and flight tests.

It is planned to re-static tests to confirm the assigned resource and control tests to obtain the certificate of airworthiness.

1. The plane containing the fuselage, propeller, located in the nose of the fuselage, a propulsion unit for driving the screw, trapezoidal wing, consisting of polycrylic with ailerons, control system ailerons, horizontal and vertical tail, and the plane of the chord of the profile of each polycryl, construction horizontal fuselage and the axis of the propeller are located in one plane, characterized in that on the bottom of each Aileron polycryl in the middle part is made aerodynamic joints, wing performed with a symmetric profile and has an elongation 5-5,3, the ratio of the area of the ailerons to the wing area is 23-25%, the ratio of the distance from the center of gravity of the aircraft up to 25% mean aerodynamic chord of the vertical tail is not more than 2/3 of the total length of the plane.

2. The plane p. 1, characterized in that the KJV is ferentiating deviations relative to the released position.

3. The plane p. 1, characterized in that it is provided with a hatch in the bottom of the fuselage, in which you installed the glass.

4. The plane p. 1, characterized in that the power unit has a four-stroke air-cooled engine.

5. The plane p. 1, characterized in that it has a three-bladed controllable-pitch propeller.

6. The plane p. 1, characterized in that it has the fuselage of the type polymenakos and srednerosloe wing relative to the fuselage.

7. The plane p. 1, characterized in that the horizontal stabilizer is made trapezoidal.

 

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