SYSTEM FOR DETERMINING PERFORMANCE MEASUREMENT airborne air data and aircraft performance AIRCRAFT DURING FLIGHT TEST

摘要

The invention relates to the technical physics, measurement techniques and technology of aeronautics and in particular to measuring instruments of the aircraft flight parameters (LA) and may be used in aircraft flight test to determine the performance characteristics. The utility model is focused on testing the aircraft, equipped with modern flight control and navigation systems. The technical result to achieve is directed utility model is to determine the real values ​​of the air data, calibration curves for the receivers and sensors coefficients of aerodynamic forces and moments, the critical values ​​of speed and aerodynamic aircraft angles at unsteady flight regimes, such large angles of attack, by results of flight tests of the aircraft. determining airborne characteristics measuring system overhead parameters and performance characteristics of the aircraft during flight tests consists of sequentially connected units: unit recording data of angular parameters of the position of the aircraft (LA) in space, aircraft mass constituting acceleration trajectory flight parameters, air data from onboard systems in probing, by a horizontal platform (SE) without slip, and test flight regimes; correction unit total and static pressures in the probing mode, the second input of which is connected to the unit characteristics and Where P _{c edited,} P _{n ism} - the measured values of static and total pressures, M, α - the measured values of the Mach number and angle of attack, δ - configuration of the aircraft; a block determining the true values ​​of airspeed and atmospheric parameters - pressure, temperature, wind speed vector on the probe adjustment mode according to the values ​​of temperature, total and static pressure and the trajectory probing parameters in mode; comparator ΔH≤ΔH _backside where? H - flying height variation in the test mode, ΔH _ass - setpoint changes the height, whose output is connected to the normally open switch connecting the output unit determining the true values of airspeed and atmospheric parameters from input actual values ​​of the air data calculation unit - aerial V speed, Mach number, static pressure, angle of attack α and sliding β in a test mode, under the terms of the atmospheric conditions obtained in the probing mode, the current trajectory measurements, angular parameters aircraft position in space, calibration curves calculation unit for on-board air pressure characteristics receivers and , Aerodynamic angle sensors Grips technical aircraft characteristics associated with aerodynamic and aircraft dynamics _{- c x, y, z,} m x, y, z, critical values V _s velocity, angle of attack α _s based on true values overhead parameters trajectory measurements for a number of these modes, depending on the free-stream, the aircraft configuration, dynamic parameters. Entrance block connected to the output of calculation block true values ​​of the air data. Furthermore, in determining the characteristics of airborne aircraft measurement parameters and performance characteristics of the aircraft during flight tests administered coupled to a block for determining the true values ​​of airspeed atmospheric parameters and the second comparing unit ΔH ΔH _backside whose output is connected to the second normally open relay. Connects the output relay unit determining the true values ​​of airspeed and atmospheric parameters with wind input values calculating block is the velocity vector components U _x (H) and U _z (H) to perform altitude test mode. block output connected to an input unit for calculating the true values ​​of the parameters of the air in the test mode. It will take into account the change in the wind characteristics of the atmosphere at different altitudes. Moreover, in determining the characteristics of airborne measuring air data and flight characteristics of the aircraft during flight tests in the case of performing the test mode without slip additionally introduced connected to the output of the block correction circuit of series-connected blocks: determining parameters of the atmosphere at the height of the probing mode, except for the wind velocity; calculating the true values ​​of the parameters of air - air speed V, the Mach number, static pressure, angle of attack α of test mode conditions atmospheric conditions obtained in the probing mode, the current trajectory measurements, the angular position parameters of the aircraft in space; calculate calibration curves for on-board air pressure receivers, sensors, angle of attack, flight performance characteristics of the aircraft within the longitudinal bore, associated with the aerodynamics of the aircraft dynamics, and - with _{y, m z, V s,} α s of a number of such modes. This allows to determine: the values ​​of atmospheric parameters - temperature, pressure, wind speed vector air parameters in the test mode, the calibration according to the air receiver pressure and the aerodynamic angle sensors, the flight performance of the aircraft; reduce the effect of random variability factors atmospheric parameters considered to determine the error performance in the test mode of flight; improve the reliability and accuracy of the results of flight tests.