Abstract:

The aircraft attitude angle calculation formulae represented by one order and two order derivatives of the air-path vector function are derived by using the aircraft dynamic equation, the aircraft kinematics equation and so on. The calculation formula of air-path bank angle of an aircraft is discussed. First of all, the calculation formula of the tangent of an air-path bank angle is derived, then a method of determining the sign of the air-path bank angle is established by using the relationship between the left wing or right wing sinking and direction of the principal normal vector of the air-path vector function. On the basis of them, the calculation formula of air-path bank angle of an aircraft is given. By using the derived formula,the air-path bank angle calculation formula of varying accelerated circular motion of an aircraft in the oblique plane is provided. Compared with the attitude angle calculation results of the six-degree-of-freedom aircraft kinematics model, the effectiveness of these attitude angle calculation formulae is verified.