This contest is closed.
Patexia is looking for descriptions of an airframe, subfloor structure, and bowl hull structure for a rotary wing aircraft or helicopters, hybrid rotorcraft, UAV drone rotorcrafts with multiple fastening means for connecting different parts together.
Submitted documents describing this system must be:
- filed or published before 30/12/2013
- not on the known references list
The entire submission must describe a subfloor structure for a rotary wing aircraft with the following components:
- An air-frame (2)
- A subfloor structure (3) that records the distance vector for each link within the network
- A bowl hull structure (18) connected to both air-frame (2) and subfloor structure (3)
- Web portions (20) connected to the subfloor structure (3)
- inner ribs (10) , the lateral outer borders being attached to the webs (20) by mechanical fastening means (27)
Figure 1: Air-frame system with multiple components of interest
This contest is part two of a two part study for a prior art search for European Patent 2889212 with a focus on claims 2, 3, 4, 5, 7, 10, 11, 12, 13, and 14. The first part of this study can be found here.
|1||Is the reference either a US patent filed, a foreign patent published, or a non-patent document published before December 30, 2013?||T/F|
|2||Does the reference show a subfloor structure for a rotary wing aircraft or helicopters, hybrid rotorcraft, UAV drone rotorcrafts?||5|
|3||Does the reference further show the upward web portions integrally extending from the bottom central portion by forming the two longerons and being integrated to the integral subfloor bowl hull together with the two lateral transitional locations?||10|
|4||Does the reference show the subfloor structure comprises: an integral subfloor bowl hull having at least a pair of upper external extensions each laterally extending from the upward web portions at least locally in a plane parallel to the floor surface?||10|
|5||Does the reference further show each of the upward web portions having a transitional location rigidly attached to the corresponding upper external extension by mechanical fastening means?||15|
|6||Does the reference further show each transitional location being located proximal a top end portion of the corresponding upward web portion?||15|
|7||Does the reference further show the upward web portion extends at least locally parallel to the anteroposterior XZ plane and the transitional location is extending atop the upward web portion, below the floor surface?||15|
|8||Does the reference further show one inner rib of a crossbeam is attached to an inner portion of the corresponding upward web portion and to an upper portion of the bottom central portion of the integral subfloor bowl hull, by mechanical fastening means?||15|
|9||Does the reference further show the transition regions and the transitional locations each form a cross-sectional contour, the cross-sectional contour describing an all along, smooth and tangential continuity in a transverse plane perpendicular to a longitudinal direction of the subfloor structure?||15|
This is a Prior Art Search contest aimed at determining if a patent idea was known and publicly available before a patent was filed.
+5 bonus points will be awarded for non-patent literature and for foreign language references.
This contest will close on Sunday, March 27th, 2016 at 11:59 PM PST.
Please review the Contest Rules. For more information on how to submit to this Contest type, please read the Intro to Prior Art Search page.
- All work must be original and prepared by a single author
- Maximum of one entry per person allowed
- Maximum length of 1,500 words
- Entries must be in English
- Ideas should be clearly expressed at a college-educated, non-expert level
- All submissions are subject to Patexia's contest legal terms
- Failure to follow these rules may lead to disqualification from the contest
- European Search for EP 13400042 Completed by the European Patent Office on June 2 2014 3 Pages
- COPPINGER. Flight International April 26 2005 Col. 167 No. 4982 Pg. 26 XP-001227208 Composites Soften Impact downloaded from : https://flightglobal.com/news/articles/composites-soften-impact-197140/
- , A new composite energy absorbing system for aircraft and helicopter Composite Structures 2006 Vol. 75 pgs. 14-23
- Crash simulation of composite and aluminum helicopter fuselages using a finite-element program ,
- Multi Terrain impact testing and simulation of a composite energy absorbing fuselage section ,
- , Development of a scale model composite fuselage concept for improved crashworthiness Journal of aircraft Vol. 38 No. 1 January-February 2001
- Structural crashworthiness and failure
- , Theory and application of finite element analysis to structural crash simulation Computers & Structures Vol. 13 pp. 277-285 1981