Pitch control system for aircraft

US5112009A · kind A · utility

Assignee

• Societe Anonyme dite Aerospatiale Societe Nationale Industrielle · FR

Inventor

• Jacques Farineau · Toulouse, FR

Key dates

• Filing date: Apr 24, 1991
• Grant date: May 12, 1992
• Expiry date: Apr 24, 2011

Classification

• Technology area (CPC G): Physics
• CPC primary: G05D1/0816
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

A pitch control system for an aircraft flying at a Mach number greater than 0.7 and including a horizontal plane that is adjustable in deflection and air brakes having a nose-down effect. According to the invention, the system comprises: PA1 first means providing the aerodynamic incidence (.alpha.) of said aircraft at each instant; PA1 second means for generating a nose-down first command (.DELTA.iHC) for said adjustable horizontal plane when said aerodynamic incidence is greater than said first threshold (.alpha.0), the amplitude of said first command being such that if said adjustable horizontal plane were to take up the corresponding position instantaneously, it would compensate the increase in the nose-up effect on said aircraft due to the way in which said aerodynamic pitching couple varies above said first threshold; PA1 third means for generating a signal (.DELTA.iHe) representative of the deflection response rate of said adjustable horizontal plane in response to said first command; PA1 fourth means for forming the difference d(.DELTA.iH) between said first command (.DELTA.iHc) and said signal (.DELTA.iHe) representative of the response of said adjustable horizontal plane; …