초록 ▼

The present invention comprises a system and method for detecting icing conditions in a multi-mode aircraft by indirectly detecting ice accretion through the measurement of aircraft performance related characteristics. Indirect characteristics are used, sometimes in additional to traditional icing s

The present invention comprises a system and method for detecting icing conditions in a multi-mode aircraft by indirectly detecting ice accretion through the measurement of aircraft performance related characteristics. Indirect characteristics are used, sometimes in additional to traditional icing sensor input, because it is difficult to safely and effectively position icing sensors in aircraft that may fly in the hover mode or the fixed wing mode as well as modes in between. Typical indirect characteristics might include thrust and rotor response for a given torque. This information is compared to a model of the expected aircraft performance to determine if icing is likely to take place. For example, decreased thrust or lift for a given torque may indicate the onset of icing. Inputs from the traditional icing sensors may also be employed as additional useful, predictive data. A recursive filter having a variable gain feedback control produces an output predictive of icing conditions and provides warning information to a cockpit display as well as control signals the anti-icing equipment.

대표청구항 ▼

[ What is claimed is:] [1.]1. A method for detecting icing on a rotor driven aircraft capable of at least two modes of flight, one of said modes comprising a hover mode and another of said modes comprising a fixed wing mode, said aircraft including icing sensors for directly detecting the presence o

[ What is claimed is:] [1.]1. A method for detecting icing on a rotor driven aircraft capable of at least two modes of flight, one of said modes comprising a hover mode and another of said modes comprising a fixed wing mode, said aircraft including icing sensors for directly detecting the presence of ice on said aircraft and aircraft performance sensors, said method comprising the steps of:a. detecting an output from said aircraft performance sensors;b. comparing said aircraft performance sensor output to a model of said aircraft performance;c. creating an error signal as a result of said comparison and using said error signal to detect icing conditions;d. detecting an output of said icing sensors;e. comparing said icing sensor output to a model of expected outputs; andf. modifying the error signal created in step c in response to said comparison in step e.