| 摘要 |
FIELD: physics. ^ SUBSTANCE: method involves measurement of aerial parametres and angular parametres of the position of an airplane in space using standard equipment, measurement of trajectory parametres, achieving probe and test modes and post-flight processing of flight test results. The probe mode is achieved at the beginning of each test mode on high angle of attack with heading angle close to the heading angle of the corresponding test mode. For the test mode on high angle of attack, true values of air speed are calculated from the condition of invariance of the value and direction of wind speed when probe and test modes are achieved. Based on trajectory measurements and true calculated values of temperature and static pressure obtained for the probe mode, the actual ambient temperature and static pressure are calculated in the test mode. Using the obtained true values of air speed, temperature and static pressure, the true Mach number, overall pressure and calibrated air speed are calculated. True calculated values of the angle of attack and the gliding angle are determined from the true values of air speed and measurements of angular parametres. The obtained true calculated values of parametres are compared with parametres measured using standard onboard equipment. A set of similar modes is used to construct an expectation function of calibrating curves for standard air pressure receivers and flow angle sensors. Further, the aerial parametres measured by standard onboard equipment are used to accurately determine true values of aerial parametres in flights at high angle of attack taking into account the determined calibrated curves. ^ EFFECT: more accurate determination of aerial parametres in flight tests of aircraft flying at high angle of attack. ^ 5 dwg, 1 tbl |
