Adjustable interior mockup

Patent metadata

Field	Value
Publication number	US-10894616-B2
Application number	US-201414510020-A
Country	US
Kind code	B2
Filing date	Oct 8, 2014
Priority date	Oct 8, 2014
Publication date	Jan 19, 2021
Grant date	Jan 19, 2021

Abstract

A system and method for simulating a structure is disclosed. An adjustable interior mockup for simulating a structure has a base with a first elongated side and a second elongated side, the first elongated side being nonadjacent the second elongated side; and an adjustable frame secured to the base. The adjustable frame includes a plurality of girder members secured along the first and second elongated sides to form an arc; a plurality of brackets; a plurality of arms having a latch attached to one end; and a sheet of fabric. The girders are securely fastened along the first elongated side of the base at predetermined intervals; the brackets are secured to the girders; the arms are received by the brackets and adjustably anchored to the girders via a fastener; and the latches engage the sheet of fabric, thus pulling the fabric into a shape that resembles the structure.

First claim

The invention claimed is:

1. An adjustable interior mockup for simulating a three-dimensional replica representing internal surface dimensions for a proposed aircraft structure, comprising:
a frame internally supporting a flexible sheet of material, the frame comprising a plurality of girder members, each of the plurality of girder members curved to form an arc shape;
a plurality of arms adjustably secured by a respective one of a plurality of mechanical couplers to the plurality of girder members, such that each one of the plurality of arms may independently be retracted outwardly or extended inwardly with respect to the arc shape;
wherein each of the plurality of arms comprises:
an inner end having either:
a) a latch adapted for grasping the flexible sheet of material; or
b) a shaped end adapted for pressing the flexible sheet of material; and

the flexible sheet of material being configurable into an envelope portion by positioning each of the plurality of arms outwardly or inwardly, the inner end of each one of the plurality of arms either pulling the flexible sheet of material outwardly via the latch or pressing the flexible sheet of material inwardly via the shaped end, thereby forming the envelope portion comprising the shape of the internal surface dimensions for a proposed aircraft structure.

2. The system of claim 1 wherein each of the plurality of arms further comprises a clamping member enabling each of the plurality of arms to be clampable into different outwardly extended or inwardly retracted positions, thereby making the flexible sheet of material movable and then securable for conforming to the internal surface dimensions.

3. The system of claim 1 further comprising a plurality of rods, wherein the flexible sheet of material is constructed of fabric and the plurality of rods are included into the fabric, each of the plurality of rods being receivable onto at least one of the plurality of latches, such that each of the rods forms a feature in the internal envelope dimensional configuration of one of the proposed plurality of aircraft designs.

4. The system of claim 1 wherein the latch comprises a clasp having opposing rollers.

5. The system of claim 1 wherein the latch comprises a hook.

6. A system for representing an aircraft interior, the system comprising:
a frame on a base;
a plurality of arms translatable radially inwardly and outwardly relative to the frame;
a flexible elastic sheet adapted for forming an internal envelope dimensional configuration to represent one of a plurality of proposed aircraft designs;
a plurality of latches each respectively coupled to a first end of one of the plurality of arms, each of the latches being adapted to removably grasp the flexible elastic sheet; and
a plurality of mechanical couplers adapted to respectively support each of the plurality of arms on the frame, wherein each of the mechanical couplers enables independent translation of a respective one of the arms, such that the plurality of arms are positioned to push or pull the flexible elastic fabric for forming the internal envelope dimensional configuration of one of the proposed plurality of aircraft designs.

7. The system of claim 6 further comprising a plurality of rods sewn into a fabric used to construct the flexible elastic sheet, each of the plurality of rods being selectively receivable onto at least one of the plurality of latches, such that each of the rods constrains the position of a portion of the flexible elastic sheet.

8. The system of claim 6 wherein the frame comprises a plurality of spaced-apart girder members extending upward from the base, and a plurality of struts spanning laterally between the girder members.

9. The system of claim 6 further comprising a plurality of clamping members each coupled to a respective one of the plurality of arms, wherein each clamping member is configured to enable its respective arm to be a) translatable inwardly and outwardly and b) securable, thereby enabling the flexible elastic sheet to match the internal envelope dimensional configuration of one of the proposed plurality of aircraft designs.

10. The system of claim 6 wherein the inside end of at least one of the arms in the plurality has a shaped end, the shaped end being pressed into an outside surface of the flexible elastic panel to form depressions that extend inwardly into the flexible elastic panel to simulate an inwardly protruding feature of one of the plurality of proposed aircraft designs.

11. The system of claim 6 wherein the arms have position indicators enabling a user to determine a relative position into which the arm has been translated.

Assignees

• Textron Innovations Inc

Inventors

• Davis David Wayne
• Thisius Todd
• Trask Chris
• Pinkerton Chris

Classifications

• G09B25/02

  of industrial processes; of machinery · CPC title

• B64F5/00

  Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for · CPC title

• B64F5/10 Primary

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title