Method and apparatus for obtaining accurately the angle of attack of an aircraft

• US 3,930,610 A
• Filed: 06/03/1974
• Issued: 01/06/1976
• Est. Priority Date: 06/03/1974
• Status: Expired due to Term

• Current Assignee: Jean-Guy Hache
• Original Assignee: Jean-Guy Hache
• Inventors: Hache, Jean-Guy
• Primary Examiner(s): Morrison, Malcolm A.
• Assistant Examiner(s): Smith, Jerry
• Application Number:
  US05/475,863
• Time in Patent Office: 582 Days
• Field of Search: 235/150.2, 235/150.22, 235/150.26, 235/186, 244/77 D, 340/27 AT, 73/178 R
• US Class Current: 701/6
• CPC Class Codes: G01P 13/025 indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
• CPC Class Codes: G06G 7/78 for direction-finding, locating, distance or velocity measuring, or navigation systems

Abstract

This invention relates to a method and apparatus for obtaining the angle of attack of an aircraft developed as a result of an appropriate processing of the vertical speed, the airspeed, and the pitch attitude of the aircraft. The latter involves resolving the inverse sine of the vertical speed signal over the airspeed signal, and subsequently differentially combining the end product of the inverse sine computation and the chord line angle signal. The air speed signal is corrected by a corrective network which receives a feedback signal proportional to the angle of attack as well as a signal proportional to drift angle.

Claims

1. A system for generating a signal representative of the angle of attack of an aircraft using vertical speed, air speed and pitch attitude data, said system comprising means for generating a pitch attitude signal proportional to aircraft pitch attitude, a processor for receiving said pitch attitude signal and for developing therefrom an output signal the magnitude and sense of which vary as a function of the aircraft chord line angle, means for generating a relative wind angle signal, comparison means for receiving and differentially combining said relative wind angle signal and the output signal from said processor so as to produce a signal whose magnitude and sense are respectively definitive of the extent and direction of the aircraft angle of attack, said means for generating a relative wind angle signal including an airspeed sensor for producing an airspeed signal, a corrective network connected to the output of said airspeed sensor for correcting said airspeed signal so as to provide a true airspeed signal, drift angle sensor means for generating a drift angle signal, means for connecting said drift angle signal to said corrective network and feedback means for connecting the output of said comparison means to said corrective network.

2. A system for generating a signal representative of the angle of attack on an aircraft using vertical speed, airspeed and pitch attitude data, said system comprising means for generating a pitch attitude signal proportional to aircraft pitch attitude, a processor for receiving said pitch attitude signal and for developing therefrom an output signal the magnitude and sense of which vary as a function of the aircraft chord line angle, means for generating a relative wind angle signal, comparison means for receiving and differentially combining said relative wind angle signal and the output signal from said processor so as to produce a signal whose magnitude and sense are respectively definitive of the extent and direction of the aircraft angle of attack, said means for generating a relative wind angle signal including an airspeed sensor for producing an airspeed signal, means for generating a vertical speed signal, a vertical speed signal modulator, an airspeed signal modulator, a carrier source for coupling a reference signal to said vertical speed signal modulator and said airspeed signal modulator, a resolver for producing a signal related to an angle whose sign is the ratio of said vertical speed signal over said airspeed signal, said resolver including first and second inputs for receiving the outputs of said vertical speed signal modulator and said airspeed signal modulator, a feedback loop, including a motor, connected to said resolver for adjusting the angular position of the resolver rotor so as to nullify the effect of the input signals to said resolver, and means including a rotary variable differential transformer and a phase-sensitive demodulator, controlled by said carrier source and responsive to the output of said resolver, for producing an electrical signal proportional to the relative wind angle.

3. A method of producing a signal proportional to the angle of attack of an aircraft in flight, comprising generating a vertical speed signal, an airspeed signal, and a pitch attitude signal, resolving the inverse sine of the ratio of the vertical speed signal over the airspeed signal so as to generate a relative wind angle signal, generating a chord angle signal by adding an offset angle signal related to the geometry of the aircraft to said pitch signal and differentially combining said relative wind angle signal and said chord line angle signal so as to produce a signal which is proportional to the angle of attack of said aircraft, said method further including generating a drift angle signal and applying said drift angle signal to a corrective network, and feeding back said signal proportional to the angle of the attack to said corrective network so as to obtain a corrected true airspeed signal.