US 11,912,396 B2
Axial load capable torque tube assembly and manufacturing methods thereof
Victor Barger, Lake in the Hills, IL (US); Joseph M. Bielefeldt, Rockford, IL (US); Jude C. Lai, Rockford, IL (US); and Eric W. Karlen, Rockford, IL (US)
Assigned to HAMILTON SUNDSTRAND CORPORATION, Charlotte, NC (US)
Filed by Hamilton Sundstrand Corporation, Charlotte, NC (US)
Filed on Oct. 21, 2020, as Appl. No. 17/075,933.
Claims priority of provisional application 62/935,903, filed on Nov. 15, 2019.
Prior Publication US 2021/0147067 A1, May 20, 2021
Int. Cl. B64C 13/28 (2006.01); B21D 39/04 (2006.01); F16D 1/10 (2006.01)
CPC B64C 13/28 (2013.01) [B21D 39/04 (2013.01); F16C 2326/43 (2013.01); F16D 1/10 (2013.01); F16D 2001/103 (2013.01); F16D 2500/5116 (2013.01); F16L 2201/10 (2013.01)] 12 Claims
OG exemplary drawing
 
1. An assembly for transmitting torque to an aircraft actuator comprising:
a torque tube having a longitudinal axis;
an end fitting comprising:
a connector portion; and
an engagement portion inserted into the torque tube,
wherein the engagement portion includes:
a first end adjacent the connector portion;
a second end opposite the first end; and
a coupling region between the first and second end that includes an outer coupling surface having an outer diameter and having a continuous groove formed thereon;
wherein the continuous groove includes two axial grooves that extend along outer coupling surface along the longitudinal axis and a first parallel groove that extends circumferentially about the longitudinal axis along the outer coupling surface and that joins the two axial grooves;
wherein the continuous groove further includes a third axial groove and a second parallel groove, the second parallel groove connecting one of the two axial grooves to the third axial groove;
wherein the first parallel groove is at the first end and the second parallel groove is at the second end.