A. I. Oleynik

With the development of aircraft engineering, enlargement of quantity and complexity of tasks being performed by an airborne vehicle (AV) the requirements for information support of the flight have significantly increased. One of the general problems of altitude-velocity parameters computation (AVP) consists in determination of altitude, vertical velocity and outside air temperature. Existing methods of AVP determination have certain disadvantages. The immediate determination of the flight altitude by direct measurements of static pressure and vertical velocity by differentiation of these parameters in most cases in absolutely unacceptable. That is conditioned by large-scale inaccuracy, both dynamic and fluctuating, of barometric altimeter. Analogous pattern is also observed in the performance of this task only by means of vertical accelerometer indications. One of possible solutions of the problem of AVP determination to a high precision is impossible whise using the data of this sensor only. All the requirements might be satisfied only by means of application of the data from several sensors of different physical nature. Complex information system always possesses the qualities exceeding the quality of each constituent information sensor. The algorithm for calculation of vertical speed, flight altitude and outside air temperature on the basis of integrated processing of static-pressure and temperature sensors output signals and data of vertical accelerometer mounted on gyroplatform is proposed within the frame of this work for solution of the task of onboard systems information support. The algorithm of optimal evaluation founds on mathematical models of primary measurement units inaccuracy and constraint equation, determining the interoperation between controlled parameters. Besides that, the task of identification of data paths time constants is being solved simultaneously. The task of calculation of parameter estimation is formulated in th form of optimal evaluation task: on the basis of values of temperature, pressure and acceleration measured in discrete moments it is necessary to determine estimates of state vector on the assumption that the initial status of the system is determined by accidental normal vector with appropriate antecedent characteristics. Numerical modeling preformed for the study of evaluation algorithm accuracy properties has shown that proposed method of calculation of AV flight parameters provides the required accuracy.