Retractable landing gear with self-braced folding strut

• US 5,100,083 A
• Filed: 02/13/1990
• Issued: 03/31/1992
• Est. Priority Date: 02/13/1990
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Veenstra, Gerrit N., Large, David T.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): Bidwell, Anne E.
• Application Number:
  US07/479,516
• Time in Patent Office: 777 Days
• Field of Search: 244/102 R, 244/102 SS, 244/102 SL
• US Class Current: 244/102.0SS
• CPC Class Codes: B64C 25/14 fore-and-aft
• CPC Class Codes: B64C 25/34 wheeled type, e.g. multi-wheeled bogies

Abstract

A folding strut having upper and lower portions (14, 16/62, 64) are connected together by a pivotal joint (18, 66, 68) for folding movement relative to one another upon extension and retraction of the strut. The upper portion (14, 62) of the strut is pivotally mounted to the aircraft frame (52, 80). A locking brace (42, 44/84, 86) extends between the upper and lower strut portions (14, 16/62, 64) to brace the strut against folding. The upper and lower portions of the strut are axially aligned (C, F) when the strut is in a fully-deployed position and the locking brace (42, 44/84, 86) maintains the strut portions (14, 16/62, 64) in this axially-aligned position. The locking brace (42, 44/84, 86) is releasable to allow relative folding movement of the upper and lower portions (14, 16/62, 64) for retraction of the strut to a stowed position. An actuation/locking mechanism (106) is provided to maintain folding members (42, 44/84, 86) of the locking brace in an axially-aligned, locked position and to displace members (42, 44/84, 86 ) of the locking brace from the axially-aligned position for retraction of the gear (10, 12).

Claims

1. A retractable landing gear for an aircraft, comprising:

a folding strut having first and second portions connected by a pivotal joint for folding movement relative to one another upon extension and retraction of said strut, said first portion being pivotally mounted to said aircraft for pivotal movement relative to said aircraft upon extension and retraction of said strut;

a brace flange extending from one of said first and second portions and having a joint location positioned radially outwardly a fixed distance from said pivotal joint;

a locking brace extending between said joint location on said brace flange and the other one of said first and second portions; and

a ground-contacting wheel assembly pivotally mounted to said second portion of said strut,

said first and second strut portions being axially aligned when said strut is in a fully-deployed position, said locking brace maintaining said first and second portions in said axially-aligned position, and said locking brace being releasable to allow relative folding movement of said first and second portions for retraction of said strut to a stowed position.

2. The landing of claim 1, further comprising a drag brace extending between said aircraft and said second portion of said strut, said drag brace having a fixed length at all times.

3. The landing gear of claim 2, wherein said folding movement of said first and second portions upon retraction of said strut is toward said drag brace.

4. The landing gear of claim 2, wherein said folding movement of said first and second portions upon retraction of said strut is away from said drag brace.

5. The landing gear of claim 2, wherein said pivotal mount of said first portion to said aircraft includes transversely spaced-apart mounts positioned to carry both vertical and side loads.

6. The landing gear of claim 1, wherein said second portion includes an axially-displaceable shock-absorbing means.

7. The landing gear of claim 1, wherein said wheel assembly includes at least a pair of tandem-mounted wheels openly mounted on an elongated beam, said beam being pivotally attached to said second portion of said strut.

8. A retractable landing gear for an aircraft, comprising:

a folding strut having first and second portions connected by a pivotal joint for folding movement relative to one another upon extension and retraction of said strut, said first portion being pivotally mounted to said aircraft;

a locking brace extending between said first and second portions; and

a ground-contacting wheel assembly pivotally mounted to said second portion of said strut,

said first and second strut portions being axially aligned when said strut is in a fully-deployed position, said locking brace maintaining said first and second portions in said axially-aligned position, and said locking brace being releasable to allow relative folding movement of said first and second portions for retraction of said strut to a stowed position;

wherein upon retraction of said strut from said fully-deployed position to a stowed position, said first portion pivots forwardly relative to said aircraft and said first and second portions fold relative to one another such that, when retracted, said seocnd portion is at least partially positioned above said pivotal mounting between said first portion and said aircraft.

9. The landing of claim 8, further comprising a drag brace extending between said aircraft and said second portion of said strut, said drag brace having a fixed length at all times.

10. The landing gear of claim 9, wherein said folding movement of said first and second portions upon retraction of said strut is toward said drag brace.

11. A retractable landing gear for an aircraft, comprising:

a folding strut having first and second portions connected by a pivotal joint for folding movement relative to one another upon extension and retraction of said strut, said first portion being pivotally mounted to said aircraft;

a locking brace extending between said first and second portions; and

a ground-contacting wheel assembly pivotally mounted to said second portion of said strut,

said first and second strut portions being axially aligned when said strut is in a fully-deployed position, said locking brace maintaining said first and second portions in said axially-aligned position, and said locking brace being releasable to allow relative folding movement of said first and second portions for retraction of said strut to a stowed position;

wherein upon retraction of said first from said fully-deployed position to a stowed position, said first portion pivots forwardly relative to said aircraft and said first and second portions fold relative to one another such that, when retracted, said second portion is at least partially positioned below said pivotal mounting between said first portion and said aircraft.

12. The landing of claim 11, further comprising a drag brace extending between said aircraft and said second portion of said strut, said drag brace having a fixed length at all times.

13. The landing gear of claim 12, wherein said folding movement of said first and second portions upon retraction of said strut is away from said drag brace.

14. A retractable landing gear for an aircraft, comprising:

a folding strut having first and second portions connected by a pivotal joint for folding movement relative to one another upon extension and retraction of said strut, said first portion being pivotally mounted to said aircraft;

a locking brace extending between said first and second portions; and

a ground-contacting wheel assembly pivotally mounted to said second portion of said strut,

said first and second strut portions being axially aligned when said strut is in a fully-deployed position, said locking brace maintaining said first and second portions in said axially-aligned position, and said locking brace being releasable to allow relative folding movement of said first and second portions for retraction of said strut to a stowed position;

wherein said locking brace includes first and second elongated members pivotally attached together for relative folding movement, said first member being pivotally attached to said first strut portion and said second member being pivotally attached to said second strut portion, said first and second brace members being in an axially-aligned position when said gear is in said fully-deployed position, and said first and second brace members folding relative to one another to permit said retraction of said strut.

15. The landing gear of claim 14, wherein said locking brace further includes a means for releasably latching said brace members into said axially-aligned position.

16. The landing gear of claim 15, wherein said locking brace further includes an actuating means for dislocating said brace members from said axially-aligned position.

17. The landing gear of claim 15, whereikn said latching means includes a latch hook positioned to releasably hold one of said brace members against a stop means in said axially-aligned position.

18. Th landing gear of claim 17, wherein said locking brace further includes an actuator means for dislocating said brace members from said axially-aligned position.

19. In combination, retractable main landing gear for an aircraft having a body and a wing, comprising:

a wing-mounted, body-stowed gear; and

a body-mounted, body-stowed gear;

comprising;

a folding strut having first and second portions connected by a pivotal joint for folding movement relative to one another upon extension and retraction of said strut, said first portion being pivotally mounted to said aircraft body for pivotal movement relative to said a aircraft body upon extension and retraction of said strut;

a brace flange extending from one of said first and second portions and having a joint location positioned radially outwardly a fixed distance from said pivotal joint;

a locking brace extending between said joint location on said brace flange and the other one of said first and second portions; and

a ground-contacting wheel assembly pivotally mounted to said second portion of said strut,

said first and second strut portions being axially aligned when said strut is in a fully-deployed position, said locking brace maintaining said first and second portions in said axially-alinged position, and said locking brace being releasable to allow relative folding movement of said first and seocnd portions for retraction of said strut to a stowed position within said body.

20. The landing gear of claim 19, wherein said wing-mounted, body-stowed gear is stowed outboard of said body-mounted, body-stowed gear.

21. The landing gear of claim 19, wherein said wing-mounted, body-stowed gear is stowed forward of said body-mounted, body-stowed gear.