# The method of determining the position of the point of application of external forces helicopter

(57) Abstract:

The invention relates to an aircraft, and relates to a method of determining the position of the point of application of external forces helicopter. The purpose of the invention is the positioning of the point of application of the thrust bearing system. On the hovering mode of measuring the increment of the pitch angle of the helicopter after ustanovki in the fuselage cargo shifted in the longitudinal direction relative to the center of mass of the helicopter. Using the increment value of the pitch angle, the value of the cargo and its longitudinal displacement, determine the position of the point of application of the thrust bearing system of the helicopter relative to its center of mass. 1 Il.

The invention relates to an aircraft, and relates to a method of determining the position of the point of application of external forces helicopter.

There is a method of determining the position of the point of application of external forces helicopter, namely the method of determining the position of the center of mass of the product, which consists in determining, from the force of its weight of reactions in two points of a product and calculating the position of the point of application of force of gravity (center of mass).(Anan'ev, I. V. and P. Timofeev, Vibrations of elastic systems and their damping. M. engineering, 1965, S. 300).

Under these spoo weight force. The position of the point of application of the thrust bearing system of the helicopter is not defined.

The aim of the invention is the positioning of the point of application of the thrust bearing system of the helicopter.

The aim is achieved in that the method includes loading design static power, the determination of the reaction of the force and the position of the point of application of external forces, helicopter display mode, hovering, determine the initial pitch angle of the helicopter, static loading is carried out by installing the load Q in the fuselage, which is offset in the longitudinal direction relative to the center of mass of the helicopter at a distance L, measured in the hovering mode of the increment of the pitch angle of the helicopter and the distance H from the point of application of the thrust bearing system to the center of mass of the helicopter is calculated by the formula H= where G is the weight of the helicopter.

The drawing shows the helicopter in hovering mode, side view.

In the fuselage of the helicopter 1 with center of mass 2 (point a) is the load 3 (weight (Q) at a distance L from point A. the Center of mass 4 (point O) of the helicopter 1 with the load 3 is displaced relative to the point And in the direction of the load 3 at a distance X.

Point 5, point b) application of the thrust force T carrier system vertamae helicopter after installation of the cargo 3

On the hovering mode of the thrust T of the carrier system of the helicopter passes through the center of mass. Attached to the helicopter force Q in the form of cargo 3, installed in the fuselage, we obtain the increment of the pitch angle of the helicopter and the offset of the center of mass Z Of the triangle AOW have Because X, we obtain the expression for determining the position of the point of application of the thrust bearing system H

P R I m m e R. On the Ka-32 helicopter weight 8730 kg on the hovering mode of measuring the initial pitch angle 1,1 acting In the fuselage set a weight 1770 kg at a distance of 1.6 m from the center of mass of the helicopter. Take the helicopter for hovering mode and measure the pitch angle of 6.5about. After installation in the fuselage of the helicopter cargo received the increment of the angle of pitch of 5.4about. The distance from the point of application of the thrust bearing system to the center of mass of the helicopter, calculated according to the description of the formula is 2,865 m

Thus, the obtained value of the distance from the point of application of the thrust bearing system to the center of mass of the helicopter. It clarifies the real effect of external loads, which improves the reliability of the strength calculations and, consequently, the safety of operation.

The METHOD of DETERMINING the POSITION of the point of APPLICATION of EXTERNAL FORCES Weedline position of the point of application of external forces, characterized in that, to determine the position of the point of application of the thrust bearing system, helicopter display mode of application, determine the initial pitch angle of the helicopter, static loading is carried out by installing the load Q in the fuselage, which is offset in the longitudinal direction relative to the center of mass of the helicopter at a distance L, measured in the hovering mode of the increment of the angle of pitch of the helicopter, and the distance H from the point of application of the thrust bearing system to the center of mass of the helicopter is determined by the formula

< / BR>
where G is the weight of the helicopter.

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