Twist-pitch coupled ball-and-socket joint for an aircraft horizontal tail
AssigneeThe United States of America as represented by the Secretary of the Army
InventorsTodd C. Henry, John T. Hrynuk, Kevin P. Haughn, Jeff T. Auletta, Bradley D. Lawrence
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Abstract
Systems and apparatus for controlling presentation of an aircraft tail assembly control surface. Various embodiments contemplate a ball-and-socket joint (optionally additively manufactured) for a sUAS tail that is capable of twist and pitch motion by way of a five-bar linkage. The five-bar linkage is configured to operate an end effector in cartesian coordinates which, when joined to the ball-and-socket, allows for coupled rotation of the SUAS tail in twist and pitch.
Claims18
A control assembly configured to control presentation of an aircraft tail assembly control surface, the control assembly comprising:
- an elongated spine having a proximal end and a distal end, the proximal end of the spine having mounted thereon first and second motors, the distal end defining a first socket operably coupled to a first ball to form a first ball and socket joint, the first ball configured to be connected to the aircraft tail assembly such that motion of the first ball causes a change in presentation of the aircraft tail assembly control surface;
- each of the first and second motors operably coupled to proximate ends of respective first and second elongated tail links via respective first and second elongated motor links, distal ends of the first and second elongated tail links being coupled to an end effector assembly, the end effector assembly being coupled to the first ball such that motion of the end effector assembly causes motion of the first ball;
- wherein each of the first and second motors are configured to rotatably adapt respective first θ1 and second θ2 angles of respective first and second elongated motor links with respect to a neutral position to thereby operate the end effector assembly in cartesian coordinates and impart thereby at least one of pitch and twist motion to a control surface of a connected aircraft tail assembly.
Dependencies are inferred from the claim text.