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The optimal algorithm for calculating the altitude and vertical flight speed of an aircraft, which is based on complex processing of information from static pressure sensors, outdoor air temperature, and vertical acceleration is described. Information processing is performed using nonlinear estimation methods. Adaptive properties of the estimation algorithm are achieved by including into the state vector the parameters that characterize the properties of sensors and static pressure transmission paths.

The article presents a mathematical model of a pyro actuator found in the mechanism for unfolding aerodynamic surfaces of aircraft, which includes a collector system. The mathematical model proposed takes into account linked gas dynamic processes in the internal pyro actuator chambers and the dynamics of its mechanical traveller. We supply results of numerically investigating the main parameters of working body flow, obtained by using the ANSYS software package.

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teristics of the elements of an isolated object are performed on unstructured computational meshes. The hinge moments occurring on the deflected element of one of the opening rudders are calculated for Mach numbers 0.8 and 1.2, and the angles of attack in the range of-4 to 24 degrees. The obtained aerodynamic characteristics are compared with the experimental data of TsAGI. A conclusion about the correctness of the proposed method for studying aerodynamic characteristics of missiles in transonic and supersonic flight regimes is made.