Systems and methods for icing flight tests

Patent metadata

Field	Value
Publication number	US-10337952-B2
Application number	US-201715640960-A
Country	US
Kind code	B2
Filing date	Jul 3, 2017
Priority date	Sep 16, 2014
Publication date	Jul 2, 2019
Grant date	Jul 2, 2019

Abstract

Systems and methods for the manufacture and use of artificial ice shapes for aircraft certification, including methods of manufacturing artificial ice shapes, artificial ice component systems for attachment to aircraft, methods of flight testing aircraft having artificial ice sections attached thereto, and artificial ice testing systems.

First claim

What is claimed is:

1. A method of evaluating an aircraft's performance under icing conditions, comprising:
creating a set of artificial ice sections, the ice sections being configured for sequential adjacent attachment to a surface of an aircraft to form an artificial ice component that simulates ice accretion, each ice section being marked to indicate a specific mounting location relative to other ice sections in the set;
attaching the set of artificial ice sections to the surface of the aircraft via a double-sided adhesive system;
flight testing the aircraft to evaluate the aircraft's performance; and
removing the ice sections from the aircraft by disrupting the adhesive system.

2. The method of claim 1 , wherein the adhesive system includes a double-sided foam tape configured for attaching the artificial ice sections to the surface of the aircraft, and line members configured for disrupting the adhesive system attaching the artificial ice sections and the aircraft after flight testing.

3. The method of claim 1 , further comprising:
including plural line members between artificial ice sections and the surface of the aircraft, the removing step including disrupting the adhesive system by translating the line members through the adhesive system.

4. The method of claim 1 , wherein the creating step includes digitally designing surface roughness features for the artificial ice sections consistent with a surface roughness of ice accretion.

5. The method of claim 1 , further comprising:
applying a protective layer to the surface of the aircraft prior to the attaching step.

6. The method of claim 1 , wherein the surface of the aircraft includes a leading edge of a wing.

7. The method of claim 1 , wherein the surface of the aircraft includes a leading edge of a vertical stabilizer or a horizontal stabilizer.

8. The method of claim 1 , wherein the adhesive system includes double-sided foam tape and a string, the removing step including, for each section, pulling the string through the double-sided foam tape to detach the section from the surface of the aircraft.

9. A method of preparing an aircraft for evaluating its performance under icing conditions, comprising:
designing an artificial ice component having an inner surface contoured to complement a selected aircraft surface, and an outer surface contoured to simulate ice accretion;
manufacturing the artificial ice component; and
installing the component on the selected aircraft surface.

10. The method of claim 9 , wherein the designing step includes the step of specifying surface roughness features for the artificial ice component consistent with a surface roughness of ice accretion.

11. The method of claim 9 , wherein the artificial ice component includes a set of sections configured for sequential adjacent attachment to the selected aircraft surface.

12. The method of claim 11 , wherein the artificial ice component is configured for installation on a leading edge of a wing of an aircraft.

13. The method of claim 11 , wherein the artificial ice component is configured for installation on a leading edge of a horizontal or vertical stabilizer of an aircraft.

14. The method of claim 11 , wherein the manufacturing step includes producing the sections of the artificial ice component by additive layer manufacturing.

15. The method of claim 11 , wherein the manufacturing step includes producing one or more sections with a honeycomb internal structure.

16. The method of claim 11 , wherein the designing step includes configuring each section of the artificial ice component for attachment to a particular location on the selected aircraft surface.

17. The method of claim 11 , wherein the manufacturing step includes the step of marking each section with an indication of where the section is to be located relative to the other sections when attached to the aircraft surface.

18. A method of modifying a vehicle using an artificial environmental accretion, comprising:
designing an artificial environmental accretion component having an inner surface contoured to complement a selected vehicle surface, and an outer surface contoured to simulate a selected environmental accretion;
manufacturing the artificial environmental accretion component; and
installing the component on the selected vehicle surface.

19. The method of claim 18 , wherein the artificial environmental accretion component is contoured to simulate an accretion of mud, snow, or ice.

20. The method of claim 18 , wherein the selected vehicle is a wheeled motor vehicle.

Assignees

• Boeing Co

Inventors

• Bosetti Chris
• Krueger Fred Norman
• Gunter Ian Miles
• Walters Dean

Classifications

• G01M17/00

  Testing of vehicles (testing fluid tightness G01M3/00; testing elastic properties of bodies or chassis, e.g. torsion-testing, G01M5/00; testing alignment of vehicle headlight devices G01M11/06; testing of engines G01M15/00) · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• G01M9/08 Primary

  Aerodynamic models · CPC title