SE8205007L - flight control - Google Patents

flight control

Info

Publication number
SE8205007L
SE8205007L SE8205007A SE8205007A SE8205007L SE 8205007 L SE8205007 L SE 8205007L SE 8205007 A SE8205007 A SE 8205007A SE 8205007 A SE8205007 A SE 8205007A SE 8205007 L SE8205007 L SE 8205007L
Authority
SE
Sweden
Prior art keywords
fuselage
flight
control
aircraft
lateral forces
Prior art date
Application number
SE8205007A
Other languages
Swedish (sv)
Other versions
SE8205007D0 (en
Inventor
W Herbst
Original Assignee
Messerschmitt Boelkow Blohm
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Messerschmitt Boelkow Blohm filed Critical Messerschmitt Boelkow Blohm
Priority to SE8205007A priority Critical patent/SE8205007L/en
Publication of SE8205007D0 publication Critical patent/SE8205007D0/en
Publication of SE8205007L publication Critical patent/SE8205007L/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers

Landscapes

  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

The method is for off-setting the longitudinal axis of the fuselage of an aircraft to align it with a target without changing the flight path. It comprises superimposing a moment in the opposite direction to a force generated by rudder deflection. The lateral forces resulting from the rudder force are balanced and flight path remains unaltered. It also involves effecting a rotation independent of lift of the fuselage about a transverse axis, or effecting a rotation free from lateral forces of the fuselage about the yaw axis, or both and superimposing them on the flight stage. - Control is effected by the inter-connection of a weapon fire control and the aircraft flight control.
SE8205007A 1982-09-02 1982-09-02 flight control SE8205007L (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SE8205007A SE8205007L (en) 1982-09-02 1982-09-02 flight control

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE8205007A SE8205007L (en) 1982-09-02 1982-09-02 flight control

Publications (2)

Publication Number Publication Date
SE8205007D0 SE8205007D0 (en) 1982-09-02
SE8205007L true SE8205007L (en) 1984-03-03

Family

ID=20347700

Family Applications (1)

Application Number Title Priority Date Filing Date
SE8205007A SE8205007L (en) 1982-09-02 1982-09-02 flight control

Country Status (1)

Country Link
SE (1) SE8205007L (en)

Also Published As

Publication number Publication date
SE8205007D0 (en) 1982-09-02

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Legal Events

Date Code Title Description
NAV Patent application has lapsed

Ref document number: 8205007-1

Effective date: 19870605