Landing gear for ultralight aircraft

• US 4,372,506 A
• Filed: 06/05/1980
• Issued: 02/08/1983
• Est. Priority Date: 06/05/1980
• Status: Expired due to Term

• Current Assignee: David Cronk, Lyle M. Byrum
• Original Assignee: David Cronk, Lyle M. Byrum
• Inventors: Cronk, David, Byrum, Lyle M.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US06/156,768
• Time in Patent Office: 978 Days
• Field of Search: 244/100 R, 244/13, 244/DIG. 1, 244/16, 244/120, 244/117 R
• US Class Current: 244/100.00R
• CPC Class Codes: B64C 25/04 Arrangement or disposition on aircraft
• CPC Class Codes: B64C 31/028 Hang-glider-type aircraft; Microlight-type aircraft

Abstract

A landing gear for ultralight aircraft includes a main landing gear assembly disposed in a position relative to the longitudinal axis of the aircraft to permit either tail wheel type landing or tricycle landing operations with the assembly including an arched axle wherein the arch provides a spring for the landing gear as well as provides clearance to enable foot launching of the aircraft. A nose wheel strut assembly is linked to and extends forward of the main wheel landing gear assembly and includes a resilient tension link member.

Claims

1. A landing gear assembly for light winged aircraft, said gear comprising:

an elongated main axle having a wheel on each end and arch intermediate the ends;

a pair of elongated main struts, each connected at an upper end to the airframe of an aircraft and at the lower end to said axle adjacent an end thereof, said struts forming with said axle a generally triangular configuration;

a hand control cross bar disposed above and forward of said axle;

a pair of upper downwardly depending struts, each connected at an upper end to the airframe and at the lower end to an outer end of said cross bar, and

a pair of forward link members, each connected at a lower end to the main axle at one end thereof and extending upwardly and forwardly and connected to an end of said cross bar.

2. The landing gear assembly of claim 1 wherein said arch of said axle extends upward behind the axis of the wheels thereon and lines in a plane between the horizontal and the vertical tubular member.

3. A landing gear assembly for light winged aircraft, said gear comprising:

an elongated main axle having a wheel on each end and arch intermediate the ends;

a pair of elongated main struts, each connected at an upper end to the airframe of an aircraft and at the lower end to said axle adjacent an end thereof, said struts forming with said axle a generally triangular configuration,

a nose wheel assembly, said nose wheel assembly comprising a pair of upper downwardly depending struts, each connected at an upper end to the airframe and at the lower end to an outer end of a cross bar, and

a pair of forward triangular struts connected to the main axle at each end thereof and extending forwardly to an end of a nose wheel axle.

4. The landing gear assembly of claim 3 wherein said forward struts each comprise an upper compression member and a lower tension member, said lower tension member comprises a curved tubular member.

5. The landing gear of claim 4 wherein said tension member has an inner end connected by a pivoting link to the main axle.

6. The landing gear of claim 5 wherein said main gear is disposed just aft of the center of gravity and the aircraft includes a tail skid.

7. The landing gear of claim 4 wherein said main landing gear struts extend substantially vertically in side elevation, and include closely spaced connection of the upper ends to the airframe and distal spaced connections of the lower ends so that said struts and said axle defines a triangle in front elevation view, and

a plurality of tension cables connected to said strut assembly and to the airframe for securing said landing gear in place.

8. The landing gear of claim 7 wherein said forward triangular struts include first and second link members connected at a lower end to opposite ends of said main axle and at an upper end to said cross bar, and one end of each of said compression members is connected to the upper end of one of said link members.

9. The landing gear of claim 8 wherein said link members are each disposed forward of said main axle at an angle of between 30 and 60 degrees to said cross bar.

10. The landing gear of claim 8 wherein said compression members extend downward at an angle to the horizontal to the front axle, and a foot bar extends between and is connected at each end to one of said compression members.