Wing lift/drag optimizing system

• US 4,899,284 A
• Filed: 09/27/1984
• Issued: 02/06/1990
• Est. Priority Date: 09/27/1984
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Nelson, David W., Thomasson, Robert E., Lewis, George E.
• Primary Examiner(s): Walsh, Donald P.
• Application Number:
  US06/656,131
• Time in Patent Office: 1,958 Days
• Field of Search: 244/219, 416/23, 416/240, 364/435
• US Class Current: 701/3
• CPC Class Codes: B64C 3/48 by relatively-movable parts of wing structures
• CPC Class Codes: G05D 1/0607 specially adapted for aircraft
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A wing camber command system (28) is provided for calculating the optimum camber of a wing (52) during aircraft operation. The wing (52) has at least one movable leading edge surface (42, 44) and at least one movable trailing edge surface (46, 48, 50) for varying wing camber, while maintaining smooth upper surface contours. Flight conditions and aircraft parameters including aircraft speed (30), normal acceleration (32), weight (34), and the dynamic pressure of air (36) are sensed during the aircraft maneuver. An onboard computer (40) monitors the sensed conditions and parameters and calculates a coefficient of lift therefrom. The computer contains stored data indicating the desired positions for the leading and trailing edge surfaces necessary to achieve a wing camber that optimizes the wing lift/drag (L/D) ratio during aircraft operation. The computer uses this stored data to command optimum wing camber.

Claims

1. For an aircraft that includes a wing having at least one leading edge surface and at least one trailing edge surface, wherein said surfaces are movable to vary said wings, camber, said aircraft being subject to variations in flight conditions that include changes in aircraft speed, altitude and normal acceleration, all of which are substantially caused by aircraft in-flight maneuvers, an apparatus for continuously optimizing the L/D ratio of said wing during said maneuvers, comprising:

means for continuously sensing actual values of aircraft, speed, aircraft normal acceleration, aircraft weight, and air dynamic pressure while said aircraft is in-flight,

an on-board computer, operatively connected to said sensing means for continuously receiving said sensed speed, acceleration, weight and dynamic pressure therefrom, said computer being operative to continuously calculate a coefficient of lift from said sensed acceleration, weight and dynamic pressure,

with said computer including a data memory bank having stored test data that indicates the desired optimum position for each of said surfaces for optimizing said wing'"'"'s L/D ratio given certain values of coefficient of lift, aircraft speed, and dynamic pressure, wherein

said computer is operatively connected to said leading and trailing edge surfaces to move said surfaces, and wherein

said computer is further operative to continuously obtain from said data memory bank the optimum position of said surfaces by compairing said test data with said calculated coefficient of lift, said actual aircraft speed and said actual dynamic pressure, and to accordingly adjust said surfaces to said optimum position in a continuous manner during said maneuvers.

2. The apparatus of claim 1, wherein said computer includes a separate data memory bank for each of said leading and trailing edge surfaces, to continuously calculate the optimum position for each of said surfaces independently from the other during said maneuvers.

3. The apparatus in accordance with claim 2, wherein said wing includes an upper surface having a smooth and continuous surface contour.