Method for transonic shock wave interference adaptive suppression of altitude channel

Abstract

The invention discloses a method for transonic shock wave interference adaptive suppression of an altitude channel, belonging to the field of inertia / atmosphere combination navigation. In the invention, an inertial navigation altitude and an atmosphere altitude are solved according to the principles of an inertia navigation system and an atmosphere data system. When transonic section static pressure fluctuation causes atmospheric pressure altitude fluctuation, an adaptive wave filter is utilized to treat a difference value of the atmospheric pressure altitude or the inertial navigation altitude and the atmospheric pressure altitude, and the wave filter outputs corresponding shock wave interference signals; the shock wave interference signals are fed back, and subtract the atmospheric pressure height so as to cancel shock wave interference, or the shock wave interference signals subtract the static pressure after unit conversion so as to cancel the shock wave interference; and an adaptive algorithm is utilized, the adaptive wave filter is regulated according to a altitude difference value of the atmospheric pressure altitude and the inertial navigation altitude, the altitude difference value revises the inertial navigation altitude through an altitude channel damping loop, and a combination altitude for suppressing the shock wave interference is obtained, thereby cancellation and suppression of altitude channel transonic shock wave interference signals are realized. The invention provides stable and reliable attitude information with high accuracy for an aircraft, enhances the navigation control accuracy of the aircraft and improves the operation performance of the aircraft.

Description

technical field [0001] The invention relates to a method for suppressing shock wave interference in a height channel when an aircraft flies at a transonic speed, and belongs to the field of inertial / atmospheric combined navigation. Background technique [0002] Inertial navigation systems and air data systems are widely used navigation systems in modern aircraft. The inertial navigation system is a high-precision autonomous navigation system. It completely relies on the airborne equipment to complete the navigation task independently, and does not have any optical or electrical contact with the outside world. And the ability of global navigation, it can provide navigation parameters such as the position, velocity, attitude, acceleration and angular velocity of the carrier. The air data system is a multi-input and multi-output airborne comprehensive measurement system. It measures the force between the aircraft and the atmosphere and the atmospheric data (such as atmospheric...

AI Technical Summary

Problems solved by technology

However, this method is only applicable to general flight conditions. When the aircraft flies at transonic speed, the static pressure measured by the air data system will fluctuate due to the interference of external shock waves, which will cause fluctuations in the calculated air pressure altitude.

The fluctuating air pressure altitude signal enters the damping circuit of the altitude channel, and finally causes the combined altitude to fluctuate. At this time, not only the atmospheric altitude information is unavailable, but also adversely affects the effect of using the atmospheric altitude information to damp the inertial altitude channel

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