Method and system for aligning propulsion system and vehicle having such propulsion alignment
An aircraft ( 10 ) is described as including a reference axis extending along at least a portion of the aircraft, and a propulsion system having a thrust vector feature ( 43 ) defining generally a direction of thrust of the turbofan engine ( 18 ), the thrust vector feature ( 43 ) extending relative to a thrust vector axis, where the turbofan engine ( 18 ) is disposed on the aircraft with the thrust vector feature ( 43 ) oriented with respect to the reference axis of the aircraft.
1. A method of establishing and varying alignment of a propulsion system on an aircraft, the propulsion system comprising a turbofan engine, the method comprising:
determining a reference axis of the aircraft by identifying an axis extending generally longitudinally through a fuselage of the aircraft;
determining a thrust vector feature of the propulsion system by delimiting an exit plane ata rearward end of the turbofan engine, and defining the thrust vector feature as an axis perpendicular to the exit plane; and
aligning the propulsion system horizontally and/or vertically with respect to the aircraft based on a relationship between the thrust vector feature and the reference axis of the aircraft.
2. The method of claim 1 , wherein said determining the reference axis of the aircraft comprises identifying a wing symmetry axis which extends relative to a wing of the aircraft.
3. The method of claim 1 , wherein delimiting said exit plane further comprises assigning at least three points at a rearward terminal end of a nacelle extending over the turbofan engine, and extending a plane between said points.
4. The method of claim 3 , wherein delimiting said exit plane further comprises identifying a first plurality of points on a rearward terminal surface of a first cowl of the nacelle and identifying a second plurality of points on a rearward terminal surface of a second cowl of the nacelle and identifying a least square plane delimited by the first and second plurality of points.
5. The method of claim 1 , wherein said aligning the propulsion system horizontally and/or vertically with respect to the aircraft comprises projecting an axis perpendicular to the thrust vector feature onto the reference axis and orienting the projected axis with respect to the reference axis.
6. The method of claim 5 , wherein the axis perpendicular to the thrust vector feature is disposed in a least square plane formed by a plurality of points located at a rearward terminal edge of a nacelle disposed over the turbofan engine.
7. The method of claim 1 , further comprising confirming alignment of the propulsion system including:
measuring a plurality of points at a rearward terminal end of the propulsion system,
establishing a least square plane defined by said points,
projecting the exit plane to the reference axis, and
comparing an orientation of the exit plane projection with the reference axis.
8. The method of claim 1 , further comprising:
calculating a possible variation of the thrust vector relative to the reference axis of the aircraft due to a variation of various aircraft components; and
adapting a design of the aircraft to account for such variations.
9. A method of establishing and varying alignment of a propulsion system on an aircraft, comprising:
determining a reference axis of the aircraft;
determining a thrust vector feature of the propulsion system; and
aligning the propulsion system horizontally and/or vertically with respect to the aircraft by arranging the thrust vector feature relative to the reference axis of the aircraft;
wherein:
said determining the thrust vector feature comprises delimiting an exit plane at a rearward end of the propulsion system and defining the thrust vector feature as an axis perpendicular to the exit plane;
the propulsion system is a turbofan engine;
delimiting said exit plane further comprises assigning at least three points at a rearward terminal end of a nacelle extending over the turbofan engine, and extending a plane between said points; and
delimiting said exit plane further comprises identifying a first plurality of points on a rearward terminal surface of a first cowl of the nacelle and identifying a second plurality of points on a rearward terminal surface of a second cowl of the nacelle and identifying a least square plane delimited by the first and second plurality of points.