Title:
FLAP DEPLOYMENT MECHANISM WITH SWING ARMS
Document Type and Number:
WIPO Patent Application WO/2003/013956
Kind Code:
A1
Abstract:
The spar (4) of the wing has a support bracket (27) on which the flap arm (6) is attached at its proximal end (10). The flap arm is connected to the flap by a flap extension (39) fixed to the flap (5) and parallel to longitudinal axis. There are a number of flap arms on the spar. Each of these flap arms has similar lengths and directional orientation of the sector swept by them. All of them move through a sector of ninety degrees, are always parallel to each other at any time and when the flaps move they have a parallelogramming effect. The angulating mechanism (59) on the fixed end of flap arm moves the flaps to make an angle with plane of wing (24) and sequencing mechanism (61) on the moveable end gives a pre-programmed movement to the flaps.
Inventors:
NARVEKAR NILESH SHRIRAM (IN)
Application Number:
PCT/IN2002/000072
Publication Date:
February 20, 2003
Filing Date:
March 21, 2002
Export Citation:
Assignee:
NARVEKAR NILESH SHRIRAM (IN)
International Classes:
B64C9/14; B64D15/04; (IPC1-7): B64C9/14
Foreign References:
GB157567A | 1921-01-24 | |||
US1394344A | 1921-10-18 | |||
US20020005462A1 | 2002-01-17 | |||
US5836550A | 1998-11-17 | |||
DE2354420A1 | 1975-05-07 | |||
DE1756515A1 | 1970-10-29 | |||
EP0539112A1 | 1993-04-28 |
Other References:
None
Download PDF:
Claims:
AMENDED CLAIMS [received by the International
Bureau on 7 May 2003 (07.05. 03); original claims 1-30
cancelled; new claims 31-45 added (4 pages)] 3
1. | An wing flap deployment system, comprising: (a) a wing having a spar, (b) a bracket attached rigidly to said spar of said wing, (c) a arm having a proximal end and distal end and is shaped such that least possible portion of said arm comes in between to obstruct the airflow when said arm moves thereby said arm will offer least resistance as possible to the airflow, (d) a first hinge is formed by connecting the proximal end of said arm to said bracket such that the axis of rotation of said hinge is inclined at predetermined angle to the vertical axis and makes similar angle of forty five degrees with longitudinal and lateral axis thereby said arm rotates around the axis of said hinge to make angle with said wing, (e) a member having annular shape and predetermined diameter with two holes diametrically opposite to said member and internal screw threads being formed on said member, (f) a second hinge is formed by connecting the distal end of said arm into the holes of said member such that axis of rotation of said hinge is inclined at predetermined angle to the vertical axis thereby said member moves around the axis of said hinge to make angle with said arm, (g) a flap on said wing, (h) a short lengthed extension having external screw threads on one end and other end being rigidly attached to said flap such that said extension is parallel to longitudinal axis thereby said extension provides least resistance as possible to the airflow when said flap operates, (i) said extension is connected to said member by engaging the screw threads of said extension with mating screw threads on said member, whereby said arm will move to deploy said flap and depending on the angles of inclination of the axes of said hinges to the vertical axis said flap will get programmed sequencing movement so as to make angle with the wing. |
2. | 32 The wing flap deployment system of Claim 31 further including a aft flap fitted on the aft of said flap. |
3. | 33 The wing flap deployment system of Claim 31 further including a actuating member for actuating said aft flap situated on said arm in proximity to said second hinge. |
4. | 34 The wing flap deployment system of Claim 31 further including a mechanical linkage for connecting said actuating member to said aft flap where said linkage passes externally in close proximity along the side of said flap. |
5. | 35 The wing flap deployment system of Claim 31 wherein said arm is shaped in form of capital letter 1 with the smaller end and longer end of letter 1 is connected to said first hinge and said second hinge respectively thereby least possible portion of said arm comes in between to obstruct the airflow when flap operates. |
6. | 36 The wing flap deployment system of Claim 31 further including a flap position transmitter placed on said first hinge and said transmitter is made up of a stationary part and a movable part. |
7. | 37 The wing flap deployment system of Claim 36 wherein said stationary part is connected to said bracket and said movable part is connected to said arm. |
8. | 38 The wing flap deployment system of Claim 31 further including a line joining said first hinge and said second hinge and with said flap in fully retracted position said line will make angle of thirty degrees with lateral axis and with said flap in fully deployed position said line will make angle of sixty degrees with lateral axis. |
9. | 9 An antiicing system used for aircraft leading edge flaps, comprising: (a) a plurality of leading edge slats on individual wing, (b) a supply duct situated on the wing and open end of said duct being bulb shaped, (c) a connecting duct is a short lengthed duct having a proximal end and a distal end and said ends are open and bulb shaped, (d) a first joint is formed by inserting into each other the bulb shaped open end of said supply duct and mating bulb shaped said proximal end of said connecting duct, (e) a fastener is installed on said first joint to hold the two bulb shaped said ends together and said fastener is inclined to the vertical axis at predetermined angle and makes similar angle of fourty five degrees with longitudinal and lateral axis thereby said joint will move in axis parallel to said fastener, (f) a heating duct is placed inside said leading edge slats and open end of said duct is bulb shaped, (g) a second joint is formed by inserting into each other the bulb shaped open end of said heating duct and mating bulb shaped said distal end of said connecting duct thereby said joint is fully movable and rotates around all axes, whereby said antiicing system used on leading edge provides a passage for the antiice air supplied by said supply duct to pass through said connecting duct via said first joint and pass from said connecting duct to said heating duct via said second joint, and whereby said antiicing system of the leading edge provides unrestricted passage for the antiice air to flow from the wing to said leading edge slats. |
10. | 40 The antiicing system in Claim 39 further including a coupling joint used to connect each individual said antiice heating ducts inside said leading edge slats end to end to allow unrestricted passage for antiice air to pass through all said heating ducts inside said leading edge slats on individual wing. |
11. | 41 The antiicing system in Claim 39 wherein said antiicing system is installed on each wing on approximately the inboard side of said leading edge slats. |
12. | 42 The antiicing system in Claim 39 further including a plurality of arms connected to said leading edge slats to operate said slats. |
13. | 43 The antiicing system in Claim 42 wherein said connecting duct moves in similar manner as said arms of said leading edge slats and said connecting duct being always parallel to said arms. |
14. | 44 The antiicing system in Claim 39 wherein said fastener is installed parallel to the axis of rotation of the first hinge of the leading edge flap arm. |
15. | 45 An planform of flap and of wing, comprising: (a) a planform of wing, (b) a planform of flap, (c) said flap has a sufficient span and has an extreme end each on two opposite sides of said flap along said span, (d) a movement of said flap takes place along the direction of said span and said extreme end towards which said flap moves during said movement will have predetermined angle to said span of said flap and said opposite extreme end will be perpendicular to said span of said flap, (e) a similar shaped cutout made on said wing such as to accommodate said flap so that said flap is fully faired with said wing when said flap is retracted and said wing will not obstruct any part of said flap during the deployment of said flap, whereby the planform of said flap and said wing are such that they do not obstruct the operation of said flap during deployment and also allow said flap to get fully faired with the surface of said wing when retracted. STATEMENT UNDER ARTICLE 19 (1) The claims have been amended to define the invention more particularly and distinctly so as to overcome the rejections in the search report and define the invention over the prior art. The amended claims have been drafted in such a way that it introduces each feature of the invention and defines it properly. Proper wordings related to aeronautical engineering have been used in the claims to explain certain features of the invention and these wordings can be unambiguously understood by anyone skilled in the art. |
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