MODE OF MEASURING OF LOADS ACTING ON THE WING OF A FLYING VEHICLE IN FLIGHT AND AN ARRANGEMENT FOR ITS EXECUTION Russian patent published in 2008 - IPC G01M5/00 G01N9/04 

FIELD: the invention refers to measuring technique and may be used for definition of the moment when a puncture appears in the wing of a flying vehicle at impacting on it with the means of destruction.

SUBSTANCE: the mode is in measuring of twisting moments and cutting-off forces with the aid of strain gauges, placed in transversal cuts along the span of the wing, and in measuring of bending moments with the aid of the strain gauges located in the upper and the low surfaces of the wing in the zones of the first and the rear spars of the wing, in measuring of strained-deformed state of the wing, twisting moments and cutting-off forces in the cuts of the wing with the aid of the strain gauges located on the walls of the first and the rear spars on neutral axles of the spars under the angle of 45^o to the planes of the transversal cuts of the wing. At that the strain gauges are switched to recording apparatus. The reference values of the frequency and the amplitude of vibrations of the wing at all possible conditions are preliminary defined and are introduced into the problem book the signals. At definition of current conditions of operations of the wing- altitude and speed of the flight, consumption of fuel in fuel tanks, availability of aviation means of destruction are separated, the reference values of the amplitude and the frequency, vibrations at given conditions of exploitation of the wing are separated, comparison of current values of the amplitude and the frequency of vibrations with the reference one at given conditions of exploitation is made, they signal to the pilot about appearance of cracks or punctures at impacting with the means of destruction at discrepancies between the current values of the amplitude and the frequency to reference one.

EFFECT: increases volume of data transmitted to the crew of the flying vehicle due to separation and evaluation of the degree of danger received by the flying vehicle.

3 cl, 4 dwg