Guidance-light display apparatus and method for in-flight link-up of two aircraft

• US 4,158,885 A
• Filed: 11/09/1977
• Issued: 06/19/1979
• Est. Priority Date: 11/09/1977
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Neuberger, Wayne K.
• Primary Examiner(s): Gruber, Felix D.
• Application Number:
  US05/849,940
• Time in Patent Office: 587 Days
• Field of Search: 244/135 A, 340/25, 340/27 NA, 340/27 AT, 340/27 SS, 343/12, 343/112 S, 343/112 CA, 35/12 N, 356/5, 356/152, 364/460, 364/461, 364/565
• US Class Current: 701/300
• CPC Class Codes: B64D 39/00 Refuelling during flight filling or emptying fuel tanks B64D37/14
• CPC Class Codes: G01S 17/88 Lidar systems specially adapted for specific applications

Abstract

A display panel of selectively operated pilot guiding lights is mounted on the belly of a fuel tanker aircraft for guiding a piloted receiver aircraft into proper orientation for an in-flight refueling link-up in which a fuel dispensing boom that projects rearwardly and downwardly from the belly of the tanker aircraft is coupled to a complimentary, refueling receptacle mounted above the cockpit of the receiver aircraft. The guidance-lights are selectively and automatically operated by computer processed position signals developed by an optical position sensor system that continuously monitors the position of the receiver aircraft relative to the boom. A first set of guidance-lights are disposed lengthwise of the aircraft to form a fore-aft position indicating array, and a second set of lights are disposed in a cross-shaped array for providing a coordinated visual display of elevational and azimuthal position. In addition to these position indicating lights, the fore-aft array includes a series of longitudinally spaced lights which are sequentially strobed toward the nose or tail of the tanker aircraft to respectively indicate that the receiver aircraft is either closing on or falling behind the target refueling position and the frequency of such strobing is varied to indicate to the receiver pilot the rate at which he is closing on or falling behind such target position.

Claims

1. A guidance-light display apparatus for mounting on a lead aircraft so as to be visible by a pilot of a trailing aircraft for guiding such pilot in flying the trailing aircraft into a predetermined in-flight link-up position with respect to the lead aircraft, comprising:

sensor means for producing an electrical signal representing the instantaneous position of the trailing aircraft relative to the lead aircraft and associated means responsive to said sensor means for producing an electrical signal representing the relative velocity between the lead and trailing aircraft along a fore-aft axis that is parallel to the longitudinal axis of the lead aircraft;

an array of spaced apart guidance lights arranged on the body of the lead aircraft along a line extending parallel to said longitudinal axis;

light operating means responsive to said associated means for sequentially strobing said lights lengthwise of said array at a strobing frequency that varies as a function of said signal representing said relative velocity.

2. The guidance-light display apparatus of claim 1, furth comprising:

means responsive to said associated means for producing an electrical signal representing the direction of said relative velocity between said aircraft; and

means for changing the direction along said array at which said lights are sequentially strobed in response to said signal representing the direction of said relative velocity.

11. The guidance-light display apparatus of claim 1 further comprising slow velocity detection means responsive to said signal representing the relative velocity between the aircraft for detecting a predetermined, minimum, relative velocity;

and

light operating means responsive to said slow velocity detection means for causing said array of guidance-lights to assume a steady illumination mode so as to indicate that the trailing aircraft has attained a fore-aft velocity approximately matching that of the lead aircraft.

3. A guidance-light display apparatus suitable for being mounted on a lead aircraft for guiding the pilot of a trailing aircraft into said predetermined target position for in-flight link-up of the lead and trailing aircraft, comprising:

position sensor means mounted on the lead aircraft for producing electrical signals representing the instantaneous position of the trailing aircraft with respect to the lead aircraft;

an array of electrically controllable guidance lights disposed on the body of the lead aircraft in a position visible by the pilot of the trailing aircraft as the latter approaches the former for link-up;

electrical computer means for receiving said electrical signals representing said instantaneous position and for comparing said electrical signals with stored data representing a predetermined plurality of imaginary three-dimensional cue zones in the free space surrounding said predetermined target position, said computer means producing encoded electrical signals representing the position of the trailing aircraft with respect to said plurality of said cue zones; and

electrical decoding means responsive to said encoded electrical signals reproduced by said computer means for operating said guidance lights in response to the movement of said trailing aircraft through said plurality of cue zones.

4. The guidance-light display apparatus of claim 3, wherein said stored data in said computer means represents imaginary cue zones that are oriented along each of a set of three orthogonal axes, including a fore-aft axis, an elevation axis, and an azimuth axis, and wherein said array of lights comprises a fore-aft array of lights arranged in a line extending lengthwise of the fuselage of the lead aircraft, and an elevation-azimuth array of lights including two lines of lights, one of which extends lengthwise of the fuselage of said lead aircraft in spaced parallel relation to said fore-aft array of lights and represents relative position along said elevation axis, and the other line of lights of said elevation-azimuth array extends crosswise of the fuselage of said lead aircraft and intersects with the first mentioned line of lights of said elevation-azimuth array and represents relative position along said azimuth axis;

and

wherein said computer means includes means for receiving electrical signals from said position sensing means and for selectively controlling the illumination of said lights in said fore-aft array and in said elevation-azimuth array as a function of the instantaneous position of the trailing aircraft relative to the imaginary cue zones represented by said stored data.

5. The guidance-light display apparatus of claim 4 further comprising a plurality of rate indicating strobe lights arranged in a line proximate and parallel to said fore-aft array of lights;

said computer means having means for deriving an electrical signal representing the relative velocity between said lead and trailing aircraft along said fore-aft axis from said electrical signals representing said instantaneous position; and

circuit means for sequentially strobing said plurality of strobe lights lengthwise of said fore-aft array at a strobing frequency that varies as a function of said signal representing said relative velocity along said fore-aft axis.

6. The guidance-light display apparatus of claim 5, said computer means further comprising means for deriving an electrical signal representing the direction of said relative velocity between said aircraft along said fore-aft axis from said electrical signals representing said instantaneous position;

and

said circuit means further including means responsive to said signal representing the direction of said relative velocity for changing the direction of sequential strobing of said strobe lights as a function of said signal representing the direction of said relative velocity.

7. The guidance-light display apparatus of claim 4, wherein said elevation-azimuth array comprises a center position indicator that has a generally square-shaped display face in which such display face is segmented into four individually illuminatable, triangular shaped quadrants in which a first pair of opposing quadrants are aligned with the first mentioned line of lights in said elevation-azimuth array, and the remaining pair of opposing quadrants are aligned with the other line of lights of said elevation-azimuth array;

and further comprising circuit means responsive to said computer means for causing said first pair of quadrants of said center position indicator of said elevation-azimuth array to be illuminated with a predetermined color code when the trailing aircraft has attained on target elevation positioning for said predetermined target position, and for causing said second pair of quadrants of said indicator to be illuminated with a predetermined color code when the trailing aircraft has attained on target azimuthal positioning for said predetermined target position.

8. The guidance-light display of claim 7, wherein said elevation-azimuth array of lights is further defined by each of said lights of said two lines of lights being arrow-shaped, in which all of the arrow-shaped lights are arranged with the apexes pointing to the center of said elevation-azimuth array.

9. The guidance-light display apparatus of claim 4, wherein said fore-aft array of lights comprises a center position light, arranged along said line of lights in said fore-aft array so as to provide a reference that represents said predetermined target position along said fore-aft axis, and further comprising circuit means responsive to said computer means for selectively controlling the illumination of said lights of said fore-aft array so as to visually indicate the fore-aft position of the trailing aircraft with respect to the target position represented by said center position indicator.

10. The guidance-light display apparatus of claim 5, further comprising slow rate detection means responsive to said signal representing said relative velocity for detecting a predetermined minimum relative velocity, in either direction;

and

said circuit means further including means responsive to said slow rate detection means for causing said strobe lights to assume a steady illumination mode when said predetermined minimum velocity has been detected so as to visually indicate that the trailing aircraft has attained a relative fore-aft velocity approximately matching that of the lead aircraft.