초록 ▼

A complete, computer based, vehicle management system (VMS) for X-Wing aircraft using digital “fly-by-wire”technology controlling many subsystems and providing functions beyond the classical aircraft flight control system. The vehicle management system receives input signals from a multiplicity of s

A complete, computer based, vehicle management system (VMS) for X-Wing aircraft using digital “fly-by-wire”technology controlling many subsystems and providing functions beyond the classical aircraft flight control system. The vehicle management system receives input signals from a multiplicity of sensors and provides commands to a large number of actuators controlling many subsystems. The VMS includes－segregating flight critical and mission critical factors and providing a greater level of back-up or redundancy for the former; centralizing the computation of functions utilized by several subsystems (e.g. air data, rotor speed, etc.); integrating the control of the flight control functions, the compressor control, the rotor conversion control, vibration alleviation by higher harmonic control, engine power anticipation and self-test, all in the same flight control computer (FCC) hardware units. The VMS uses equivalent redundancy techniques to attain quadruple equivalency levels; includes alternate modes of operation and recovery means to back-up any functions which fail; and uses back-up control software for software redundancy.

대표청구항 ▼

A method of providing a vehicle management computer system (VMS) for an X-Wing type aircraft controlling many mechanical subsystems and functions including flight control functions, compressor and pneumatic distribution control, rotor conversion control, rotor vibration alleviation and self-test, co

A method of providing a vehicle management computer system (VMS) for an X-Wing type aircraft controlling many mechanical subsystems and functions including flight control functions, compressor and pneumatic distribution control, rotor conversion control, rotor vibration alleviation and self-test, comprising the following steps: (a) segregating flight critical and mission critical factors; (b) centralizing the computation of functions utilized by several mechanical subsystems, including air data and rotor speed; (c) integrating the flight control functions, the compressor and pneumatic distribution control, the rotor conversion control, rotor vibration alleviation and self-test to be under the control of a single integrated flight control computer system contained within the same hardware unit; and (d) providing redundancy for the integrated computer system with multiple number of like flight control computer systems contained in separate hardware units, at least some of which likewise include the integration step of step “c,”and providing multiple redundancy for backing up flight critical factors and mission critical factors, with the redundancy of the former being greater than the latter; wherein in step “c,”in the controlling of the self-test, there is included the following step(s): allowing conversion of the rotor from one state to the opposite state only after a self-test is initiated, which test is initiated when a switch is activated under a pilot\s manual control, and in the self-test, assessing whether the sensors and actuators required for conversion to the opposite state are operational to effect a conversion to the opposite state.