Twist-Pitch Coupled Ball-and-Socket Joint for an Aircraft Horizontal Tail
US20260131916A1
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.
Description (excerpt)
GOVERNMENT INTEREST The invention described herein may be manufactured and used by or for the Government of the United States for all governmental purposes without the payment of any royalty. FIELD OF THE DISCLOSURE The present disclosure relates generally to aircraft pitch and yaw control and, more particularly, to a control mechanism for an aircraft tail assembly for use in aircraft such as small Unmanned Aerial Systems (SUAS). BACKGROUND This section is intended to introduce the reader to various aspects of art, which may be related to various aspects of the present invention that are described and/or claimed below. This discussion is believed to be helpful in providing the reader with background information to facilitate a better understanding of the various aspects of the present invention. Accordingly, it should be understood that these statements are to be read in this light, and not as admissions of prior art. Traditional aircraft control yaw and pitch via uncoupled control surfaces on a tail assembly; namely, via a rudder (vertical tail) and elevator (horizontal tail). While this system has worked well for many years, improvements are desired, especially improvements resulting in improved maneuverability and agility in spaces where adverse aerodynamics and obstacles exist such as at very low altitudes. SUMMARY OF THE INVENTION Various deficiencies in the prior art are addressed below by a control assembly configured to control presentation of an aircraft tail assembly control surface. Various embodiments contemplate a ball-and-socket joint (optionally additively manufactured) for an aircraft such as a small Unmanned Aerial System (SUAS) 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. A control assembly configured to control presentation of an aircraft tail assembly control surface according to an embodiment comprises: 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 θ 1 and second θ 2 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. Additional objects, advantages, and novel features of the invention will be set forth in part in the description which follows, and in part will become apparent to those skilled in the art upon examination of the following or may be learned by practice of the invention. The objects and advantages of the invention may be realized and attained by means of the instrumentalities and combinations particularly pointed out in the appended claims. BRIEF DESCRIPTION OF THE DRAWINGS The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present invention and, together with a general description of the invention given above, and the detailed description of the embodiments given below, serve to explain the principles of the present invention. FIGS. 1 - 2 illustrate a control assembly according to various embodiments and configured to control presentation of an aircraft tail assembly control surface; FIG. 3 illustrates a side view of a portion of the control assembly of FIGS. 1 - 2 ; <figref idrefs="DRAWINGS"
Filing details
- Inventors
- Todd C. Henry
- Assignee
- U.S. Government, As Represented By The Secretary Of The Army
- Filed
- Nov 7, 2024
- Granted
- Application pending
Bibliographic data and excerpted text sourced from Google Patents (public record) as part of IP TechMatch's current-filings monitor. This filing is not part of the 2019 historical archive. For the authoritative full text, drawings, and legal status, see the source links above or consult USPTO records directly.