Wing lock and disconnect mechanisms for a rc aircraft

Patent metadata

Field	Value
Publication number	US-2018057136-A1
Application number	US-201715692524-A
Country	US
Kind code	A1
Filing date	Aug 31, 2017
Priority date	Sep 1, 2016
Publication date	Mar 1, 2018
Grant date	—

Abstract

Remote control aircraft may benefit from airframes with components that are easy to connect and disconnect. For example, during repair, storage, or transport, it is beneficial to disconnect a wing from a fuselage of a remote controlled aircraft. Systems and methods for connecting and disconnecting airframe components are described herein. For example, a snap-fit mechanism is used in some instances to provide a solid connection during operation or flight, and also to quickly and easily disconnect components at various times, such as during repair, storage, or transport. The snap-fit mechanism allows for a quick disconnect without the use of tools and without causing any loose parts.

First claim

We claim:

1 . A radio-controlled (RC) aircraft comprising:
a structural member; a wing configured to disconnect from a fuselage, the wing comprising:
a lock mechanism coupled to the wing and adapted to fit within a lock recess of the fuselage;
a wing structural member recess configured to receive the structural member; and
wherein the fuselage comprises:
a fuselage structural member recess that corresponds to the wing structural member recess;
a lock recess adapted to receive the lock mechanism; and
an aperture adapted to provide access to the lock mechanism;
wherein the wing is disconnected from the fuselage by unlocking the lock mechanism; and wherein the structural member is adapted to fit within the wing structural member recess and the fuselage structural member recess.

2 . The RC aircraft of claim 1 , further comprising a stabilizing mechanism adapted to prevent rotation of the wing when the wing is connected to the fuselage.

3 . The RC aircraft of claim 2 , wherein the stabilizing mechanism comprises:
a stabilizing protrusion on the wing adapted to fit within a stabilizing recess on the fuselage.

4 . The RC aircraft of claim 1 , wherein the lock mechanism is a biased lock mechanism such that the wing is disconnected from the fuselage by applying a force against the bias of the biased lock mechanism.

5 . The RC aircraft of claim 4 , wherein the biased lock mechanism is a U-shaped tab with an outward bias and a tab cut-out portion;
wherein the lock recess further comprises a locking structure that corresponds to the tab cut-out portion; and wherein the wing is connected to the fuselage at least in part when the lock recess receives the U-shaped tab and the lock recess compresses the U-shaped tab against the outward bias until the tab cut-out portion passes the locking structure of the lock recess such that the outward bias of the U-shaped tab presses the tab cut-out portion against the locking structure and connects the wing to the fuselage.

6 . The RC aircraft of claim 1 , wherein the wing and the fuselage each further comprise matching support rod recesses; and
wherein the RC aircraft further comprises a support rod adapted to fit within the matching support rod recesses of the wing and fuselage.

7 . The RC aircraft of claim 1 , wherein the wing and the fuselage each comprise a plurality of matching support rod recesses;
wherein the RC aircraft further comprises a plurality of support rods adapted to fit within the matching support rod recesses; and wherein at least two of the matching support rod recesses are positioned on either side of the lock mechanism.

8 . The RC aircraft of claim 1 , further comprising a wing electronics aperture and a fuselage electronics aperture.

9 . A radio-controlled (RC) aircraft with a removable wing comprising:
a snap-fit locking mechanism coupled to the removable wing and a fuselage; a structural member coupled to the removable wing and the fuselage; an aperture adapted to provide access to the snap-fit lock mechanism, and a stabilizing mechanism comprising:
a stabilizing protrusion on either the wing or the fuselage; and
a corresponding stabilizing recess on the other of the wing or the fuselage adapted to receive the stabilizing protrusion when the wing is connected to the fuselage;
wherein the wing is disconnected from the fuselage by applying a force to the snap-fit locking mechanism.

10 . The RC aircraft of claim 9 , wherein the removable wing and the fuselage further comprise a wing electronics aperture and a corresponding fuselage electronics aperture.

11 . The RC aircraft of claim 9 , wherein the removable wing and the fuselage each further comprise matching support rod recesses; and
wherein the RC aircraft further comprises a support rod adapted to fit within the matching support rod recesses of the removable wing and fuselage.

12 . The RC aircraft of claim 9 , wherein the removable wing and the fuselage each comprise a plurality of matching support rod recesses;
wherein the RC aircraft further comprises a plurality of support rods adapted to fit within the matching support rod recesses; and wherein at least two of the matching support rod recesses are positioned on either side of the snap-fit lock mechanism.

13 . The RC aircraft of claim 9 , further comprising a balancing point.

14 . A radio-controlled (RC) aircraft comprising:
a structural member; a fuselage comprising:
a lock mechanism adapted to fit within a lock mechanism recess of a wing;
a fuselage structural member recess;
a wing configured to disconnect from a fuselage, the wing comprising:
the lock mechanism recess;
a wing structural member recess configured to receive the structural member and that corresponds to the fuselage structural member recess; and
an aperture adapted to provide access to the lock mechanism;
wherein the wing is disconnected from the fuselage by unlocking the lock mechanism; and wherein the structural member is adapted to fit within the wing structural member recess and the fuselage structural member recess.

15 . The RC aircraft of claim 14 , further comprising a stabilizing mechanism adapted to prevent rotation of the wing when the wing is connected to the fuselage.

16 . The RC aircraft of claim 15 , wherein the stabilizing mechanism comprises:
a stabilizing protrusion on the fuselage adapted to fit within a stabilizing recess on the wing.

17 . The RC aircraft of claim 14 , wherein the lock mechanism is a biased lock mechanism such that the wing is disconnected from the fuselage by applying a force against the bias of the biased lock mechanism.

18 . The RC aircraft of claim 17 , wherein the biased lock mechanism is a U-shaped tab with an outward bias and a tab cut-out portion;
wherein the lock recess further comprises a locking structure that corresponds to the tab cut-out portion; and wherein the wing is connected to the fuselage at least in part when the lock recess receives the U-shaped tab and the lock recess compresses the U-shaped tab against the outward bias until the tab cut-out portion passes the locking structure of the lock recess such that the outward bias of the U-shaped tab presses the tab cut-out portion against the locking structure and connects the wing to the fuselage.

19 . The RC aircraft of claim 14 , wherein the wing and the fuselage each further comprise matching support rod recesses; and
wherein the RC aircraft further comprises a support rod adapted to fit within the matching support rod recesses of the wing and fuselage.

20 . The RC aircraft of claim 14 , further comprising a wing electronics aperture and a fuselage electronics aperture.

Assignees

• Horizon Hobby Llc

Inventors

• Haley James
• Mcconville Mike
• Shell Aaron
• Huhn Chris
• Buescher Dustin

Classifications

• B64U2201/20

  Remote controls · CPC title

• B64C2211/00

  Modular constructions of airplanes or helicopters · CPC title

• B64C2039/105

  of blended wing body type · CPC title

• A63H27/001

  Making or assembling thereof, e.g. by folding · CPC title

• B64C2201/104

  Operations & Transport · mapped topic