Segmentized flap system

• US 4,892,274 A
• Filed: 08/26/1986
• Issued: 01/09/1990
• Est. Priority Date: 08/29/1985
• Status: Expired due to Term

• Current Assignee: Messerschmitt-Boelkow-Blohm GmbH (Mercedes-Benz Group AG)
• Original Assignee: MBB GmbH
• Inventors: Renken, Juergen, Pohl, Ulrich
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US06/900,508
• Time in Patent Office: 1,232 Days
• Field of Search: 244/213, 244/214, 244/215, 244/216, 244/217, 244/218, 244/219, 244/75 R
• US Class Current: 244/213
• CPC Class Codes: B64C 13/26 without power amplification or where power amplification is irrelevant
• CPC Class Codes: B64C 9/16 at the rear of the wing

Abstract

A flap system along the trailing edge of a transonic aircraft wing which system includes segments arranged in span direction, a driving system for protraction and retraction of the segments includes a plurality of spindle drives connected to the segments such that each segment is connected to at least two spindle drives; are controlled the spindle drives in such a manner that at least some of the drives are independently controlled from each other so that the segments can pivot on vertical axes, in addition to a regular pivoting about respective horizontal axes.

Claims

1. A flap system for transonic aircraft wings which system includes flap segments arranged in span direction, a driving system for protraction and retraction of the flap segments, comprising:

a plurality of spindle drives connected to said flap segments such that each flap segment is connected to at least two spindle drives; and

control means for controlling said spindle drives in such a manner that at least some of the drives are independently controlled from each other, such that those of the spindle drives that are connected to the same flap segment, are controlled independently from each other to obtain pivoting of that same flap segment on a vertical axis.

2. The system as in claim 1, wherein each spindle drive is separately and individually controlled.

3. The system as in claim 1, including for at least two of the spindle drives, acting upon the same flap segment, a common controlled drive input, there being a differential gear interposed between the latter two spindle drives, there being means for separately controlling the differential gear.

4. The system as in claim 1, the flap segments being arranged along the trailing edge.

5. A flap system for transonic aircraft wings which includes segments arranged in the span direction, and including means for protraction and retraction of the segments as well as pivoting on horizontal axes, the improvement of a plurality of independent means coupled to and acting on respective opposite ends of the segments for thereby pivoting the segments additionally about different vertical axes, independently from any protraction and retraction of any of the segments as a whole.