Aircraft system for reduced observer visibility

Patent metadata

Field	Value
Publication number	US-9902489-B2
Application number	US-201414184542-A
Country	US
Kind code	B2
Filing date	Feb 19, 2014
Priority date	Aug 19, 2011
Publication date	Feb 27, 2018
Grant date	Feb 27, 2018

Abstract

An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.

First claim

What is claimed is:

1. An aircraft apparatus, comprising:
a fuselage boom having proximal and distal ends;
a wing coupled to the proximal end of said fuselage boom;
a first transparent stabilizer coupled to a distal end of said fuselage boom;
a servo housed in said distal end of said fuselage boom, said servo having a servo arm; and
a servo horn slidably coupled to said first transparent stabilizer to slidably receive and detachably couple said servo arm to said first transparent stabilizer.

2. The apparatus of claim 1 , wherein said first transparent stabilizer is a horizontal stabilizer.

3. The apparatus of claim 2 , wherein said horizontal stabilizer is a canard.

4. The apparatus of claim 1 , wherein said first transparent stabilizer is a vertical fin.

5. The apparatus of claim 1 , wherein said first transparent stabilizer is a ruddervator.

6. The apparatus of claim 1 , further comprising:
a servo housed in said distal end of said fuselage boom to drive said first transparent stabilizer; and
a plurality of calibration lines marked on an exterior surface of said distal end of said fuselage boom and adjacent to said first transparent stabilizer to provide calibration marks for said first transparent stabilizer.

7. The apparatus of claim 6 , further comprising:
a memory housed in the proximal end of said fuselage boom to store calibration information.

8. The apparatus of claim 1 , wherein said wing comprises:
a center section; and
a port outboard wing section and a starboard outboard wing section, each of said port and starboard outboard wing sections detachably connectable to said center section and each having curved leading and trailing edges of varying radii.

9. The apparatus of claim 1 , wherein said first transparent stabilizer comprises a flat-plate airfoil.

10. The apparatus of claim 1 , wherein said first transparent stabilizer consists of clear polycarbonate plastic.

11. An aircraft apparatus, comprising:
a wing;
a tubular boom extending from said wing; and
a first clear polycarbonate plastic stabilizer coupled to said tubular boom;
a fuselage boom having proximal and distal ends, wherein a servo is housed in said distal end of said fuselage boom said servo having a servo arm; and
a servo horn slidably coupled to said first clear polycarbonate plastic stabilizer to slidably receive and detachably couple said servo arm to said first clear polycarbonate plastic stabilizer.

12. The apparatus of claim 11 , wherein said first clear polycarbonate plastic stabilizer is an elevator.

13. The apparatus of claim 12 , further comprising a clear vertical stabilizer positioned proximate to said elevator.

14. The apparatus of claim 13 , further comprising:
a rigid pin extending from said tubular boom; and
an attachment clip coupled to said clear vertical stabilizer, said attachment clip having a channel to receive said rigid pin;
wherein said clear vertical stabilizer is rotatable about said rigid pin.

15. The apparatus of claim 13 , wherein said clear vertical stabilizer is a flat-plate airfoil.

16. The apparatus of claim 11 , wherein said first clear polycarbonate plastic stabilizer is a vertical stabilizer.

17. The apparatus of claim 16 , further comprising:
a metal pin extending from said tubular boom; and
an attachment clip coupled to said first clear polycarbonate plastic vertical stabilizer, said attachment clip having a channel to receive said metal pin;
wherein said first clear polycarbonate plastic vertical stabilizer is rotatable about said metal pin.

18. The apparatus of claim 17 , further comprising a clear polycarbonate plastic elevator.

19. The apparatus of claim 18 , wherein said clear polycarbonate plastic elevator comprises a flat-plate airfoil.

20. The apparatus of claim 17 , wherein said tubular boom has a distal end having calibration marks disposed underneath a rotational travel path of said first clear polycarbonate plastic vertical stabilizer to assist calibration of trim for said first clear polycarbonate plastic vertical stabilizer.

21. The apparatus of claim 11 , wherein a center section of said wing comprises a fuselage compartment.

22. The apparatus of claim 11 , wherein said wing comprises a center section, an outboard port portion and outboard starboard portion, said outboard port portion and outboard starboard portion each having leading and trailing edges defining non-linear lines.

23. An aircraft apparatus, comprising:
a wing;
a fuselage boom extending from said wing and having proximal and distal ends;
a servo housed in said distal end of said fuselage boom, said servo having a servo arm;
a stabilizer means coupled to said fuselage boom for providing transparent aircraft tail stabilization; and
a servo horn slidably coupled to said stabilizer means to slidably receive and detachably couple said servo arm to said stabilizer means.

24. The apparatus of claim 23 , wherein stabilizer means consist of an elevator of clear rigid plastic.

25. The apparatus of claim 24 , further comprising a clear polycarbonate plastic vertical stabilizer positioned proximate to said elevator.

26. The apparatus of claim 25 , further comprising:
a rigid pin extending from said fuselage boom; and
an attachment clip coupled to said clear polycarbonate plastic vertical stabilizer, said attachment clip having receiving means to receive said rigid pin;
wherein said clear polycarbonate plastic vertical stabilizer is rotatable about said rigid pin.

27. The apparatus of claim 24 , further comprising a non-reflective coating on said stabilizer means.

Assignees

• Aerovironment Inc

Inventors

• Fisher Christopher Eugene
• Chambers Steven Bradley
• Belik Pavil
• Gunder Austin Craig
• Zwaan John Peter

Classifications

• B64U20/10

  for stealth, e.g. reduction of cross-section detectable by radars · CPC title

• B64C9/00

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title

• B64C39/024

  of the remote controlled vehicle type, i.e. RPV · CPC title

• B64C39/12

  Canard-type aircraft · CPC title

• B64C3/10 Primary

  Shape of wings · CPC title