Patent Publication Number: US-2023144561-A1

Title: Compact rotorcraft seating assembly with non-linear bucket guide channels

Description:
TECHNICAL FIELD 
     Embodiments of the inventive concepts disclosed herein are directed generally to seating assemblies and particularly for cockpit seating for rotorcraft operators. 
     BACKGROUND 
     Seating for helicopters and/or rotorcraft (e.g., for pilots, operators, and/or passengers) require a stroking distance (which must be along a straight axis) for substantially vertical (e.g., Z-axis, parallel to the operator&#39;s spine) energy absorption and deceleration in response to a dynamic event. In a first aspect, seating must be able to accommodate a broad range of pilot heights. For example, the seat can be adjusted to accommodate very tall pilots, but at the expense of vertical stroking distance between the seat bucket and the cockpit floor. This problem may be addressed by a sub-floor, or an indentation or depression set into the cockpit floor into which the seat bucket may stroke below floor level. However, size, weight and power considerations (SWaP-c) may not always provide space for a sub-floor, leaving a limited amount of vertical space between the seat bucket and the floor in which to achieve the required stroking distance. 
     SUMMARY 
     A compact rotorcraft seating assembly with non-linear bucket guide channels is disclosed. In embodiments, the seating assembly includes a seat bucket and a seat base mountable to a cockpit or flight deck floor of a helicopter or other like rotorcraft. The seat base includes a base portion mountable to the floor and spaced-apart left and right side panel portions rising above the base portion at an obtuse angle (e.g., past vertical). Each of the left and right side panel portions includes a linear bucket guide channel set into the inside face and a bucket guide slot set into the outside face, the bucket guide slot having a straight linear upper portion transitioning into a curved lower portion. The seat base supports the seat bucket, and the seat bucket in turn supports a pilot or operator of the rotorcraft. The seat bucket is slidably connected to the inner bucket guide channels and outer bucket guide slots of each side panel portion, such that the seat bucket can be raised or lowered relative to the seat base (e.g., to accommodate shorter or taller pilots) by translating through the respective upper portions of the bucket guide channel and bucket guide slot. In the event of a crash or other like dynamic event, the crash energy (e.g., downward force) of the seat bucket is attenuated by translating through the lower portion of the straight inner bucket guide channel. At the same time, the seat bucket is pivoted forward and away from the seat base and flight deck floor (e.g., to avoid impact with the seat base or the flight deck floor) by transitioning through the curved lower portion of the bucket guide slot. 
     In some embodiments, the inner bucket guide channels and the outer bucket guide slots extend between the same top height and bottom height (e.g., corresponding to the endpoints of the channel or slot) relative to the seat base and cabin floor. 
     In some embodiments, an upper bracket assembly fixed to the seat bucket translates through the inner bucket guide channels, and a lower bracket assembly fixed to the seat bucket translates through the outer bucket guide slots. 
     In some embodiments, the upper bracket assembly includes an upper bracket support pivotably connected to the bracket assembly, the upper bracket support capable of attenuating the crash energy by stroking downward through the lower portion of the bucket guide channel opposite the curved portion of the bucket guide slot. 
     In some embodiments, the lower bracket assembly includes a lower support bracket that translates through the outer bucket guide slot via an inside bearing sharing a common axle with an outside bearing. In some embodiments, the lower bracket assembly also includes a stabilizer bracket fixed to the upper bracket assembly and including a slot through which the outside bearing translates. 
     In some embodiments, the seat base mounts to the cabin or cockpit floor via tracks fixed to the floor, the tracks extending in parallel (e.g., left-side and right-side) and the seat base capable of translating along the tracks. 
     In some embodiments, both the left-side and right-side tracks extend beneath the seat bucket. 
     In some embodiments, either of the left-side or the right-side tracks (but not both) extends beneath the seat bucket. 
     In some embodiments, the seat bucket reclines relative to the seat base. 
     In some embodiments, the rear faces of the left-side and right-side panel portions are positionable flush with a bulkhead wall of the rotorcraft. 
     This Summary is provided solely as an introduction to subject matter that is fully described in the Detailed Description and Drawings. The Summary should not be considered to describe essential features nor be used to determine the scope of the Claims. Moreover, it is to be understood that both the foregoing Summary and the following Detailed Description are example and explanatory only and are not necessarily restrictive of the subject matter claimed. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The detailed description is described with reference to the accompanying figures. The use of the same reference numbers in different instances in the description and the figures may indicate similar or identical items. Various embodiments or examples (“examples”) of the present disclosure are disclosed in the following detailed description and the accompanying drawings. The drawings are not necessarily to scale. In general, operations of disclosed processes may be performed in an arbitrary order, unless otherwise provided in the claims. In the drawings: 
         FIG.  1    is a rear isometric view illustrating a rotorcraft seating assembly according to example embodiments of this disclosure; 
         FIG.  2 A  is a detailed view of a side panel portion of a seat base of the seating assembly of  FIG.  1    incorporating inner and outer guide channels; 
         FIGS.  2 B and  2 C  are respectively exterior and interior views of the side panel portion of the seat base of  FIG.  1   ; 
         FIGS.  2 D and  2 E  are respectively exploded views of the exterior and interior views of  FIGS.  2 B and  2 C ; 
         FIGS.  3 A through  3 C  are left-side profile views of seat bucket adjustment operations of the seating assembly of  FIG.  1   ; 
         FIGS.  3 D through  3 F  are left-side profile views of energy attenuation (EA) stroking operations of the seating assembly of  FIGS.  3 A through  3 C ; 
         FIGS.  4 A through  4 C  are counterpart rear isometric views of the seat bucket adjustment operations of  FIGS.  3 A through  3 C ; 
         FIGS.  4 D through  4 F  are counterpart rear isometric views of the EA stroking operations of  FIGS.  3 D through  3 F ; 
       and  FIGS.  5 A,  5 B,  5 C,  5 D,  5 E, and  5 F  are respectively top/overhead, bottom/underside, right-side profile, left-side profile, forward, and rear views of the rotorcraft seating assembly of  FIG.  1   . 
     
    
    
     This Summary is provided solely as an introduction to subject matter that is fully described in the Detailed Description and Drawings. The Summary should not be considered to describe essential features nor be used to determine the scope of the Claims. Moreover, it is to be understood that both the foregoing Summary and the following Detailed Description are example and explanatory only and are not necessarily restrictive of the subject matter claimed. 
     DETAILED DESCRIPTION 
     Before explaining one or more embodiments of the disclosure in detail, it is to be understood that the embodiments are not limited in their application to the details of construction and the arrangement of the components or steps or methodologies set forth in the following description or illustrated in the drawings. In the following detailed description of embodiments, numerous specific details may be set forth in order to provide a more thorough understanding of the disclosure. However, it will be apparent to one of ordinary skill in the art having the benefit of the instant disclosure that the embodiments disclosed herein may be practiced without some of these specific details. In other instances, well-known features may not be described in detail to avoid unnecessarily complicating the instant disclosure. 
     As used herein a letter following a reference numeral is intended to reference an embodiment of the feature or element that may be similar, but not necessarily identical, to a previously described element or feature bearing the same reference numeral (e.g.,  1 ,  1   a,    1   b ). Such shorthand notations are used for purposes of convenience only and should not be construed to limit the disclosure in any way unless expressly stated to the contrary. 
     Further, unless expressly stated to the contrary, “or” refers to an inclusive or and not to an exclusive or. For example, a condition A or B is satisfied by any one of the following: A is true (or present) and B is false (or not present), A is false (or not present) and B is true (or present), and both A and B are true (or present). 
     In addition, use of “a” or “an” may be employed to describe elements and components of embodiments disclosed herein. This is done merely for convenience and “a” and “an” are intended to include “one” or “at least one,” and the singular also includes the plural unless it is obvious that it is meant otherwise. 
     Finally, as used herein any reference to “one embodiment” or “some embodiments” means that a particular element, feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment disclosed herein. The appearances of the phrase “in some embodiments” in various places in the specification are not necessarily all referring to the same embodiment, and embodiments may include one or more of the features expressly described or inherently present herein, or any combination or sub-combination of two or more such features, along with any other features which may not necessarily be expressly described or inherently present in the instant disclosure. 
     Broadly speaking, embodiments of the inventive concepts disclosed herein are directed to a helicopter seating assembly capable of providing full energy attenuation (EA) stroking during a crash or other like dynamic event within a minimal vertical space between the bottom of the seat bucket and the flight deck floor. In addition to the linear guide channel for EA stroking, a curved outer guide channel supports and guides the lower portion of the seat bucket forward and away from the base seat structure while stroking downward, preventing lateral sway of the seat bucket. Further, the use of a curved outer channel allows for a shorter base seat structure allows the seat bucket to recline further relative to the base seat structure, even when mounted directly ahead of a bulkhead wall. 
     Referring to  FIG.  1   , a seating assembly  100  for a helicopter or rotorcraft is shown. The seating assembly  100  may include a seat bucket  102  and a base seat structure  104 . 
     In embodiments, the seat bucket  102  may be configured to accommodate a pilot, operator, or passenger of the rotorcraft. For example, the seat bucket  102  may be adjustable relative to the base seat structure  104 , e.g., in order to accommodate pilots or other occupants of a wide range of height and build in a position where the pilot&#39;s eye level and/or positioning relative to rotorcraft controls may be optimal. 
     In embodiments, the base seat structure  104  may be mounted to a cockpit or cabin floor  106  of the rotorcraft. For example, the base seat structure  104  may be mounted to tracks  108  set into the flight deck floor  106 , as described in greater detail below. In embodiments, the base seat structure  104  may include a base portion  104   a  and side panel portions  104   b.  For example, the base portion  104   a  may extend substantially horizontally along the flight deck floor  106  (and, e.g., may be directly mounted to the tracks  108 ), while left-side and right-side side panel portions  104   b  extend above the base portion at substantially obtuse angles. In some embodiments, the left-side and right-side panel portions  104   b  extend above the base portion at an angle not more than 120 degrees from the flight deck floor  106  (e.g., no more than 30 degrees from vertical); in other embodiments, this angle may vary according to the precise configuration of the cockpit or cabin. 
     In embodiments, the seat bucket  102  may be mounted to the side panel portions  104   b  and may be adjusted relative to the base seat structure  104 . For example, the seat bucket  102  may be adjusted through a range  110  of incremental lockout adjustment positions relative to the base seat structure  104 , e.g., adjusted upward to accommodate shorter pilots and adjusted downward to accommodate taller pilots. In some embodiments, the seat bucket  102  will accommodate any pilot between the 5 th  percentile (e.g., height/weight) for female operators and the 95 th  percentile for male operators. 
     In some embodiments, the tracks  108  extend along the flight deck floor  106  in parallel ( 108   a ) underneath the seat bucket  102 . Accordingly, the base portion  104   a  of the base seat structure  104  may similarly comprise left-side and right-side portions extending forward from the left and right side panel portions  104   b  respectively, the left-side and right-side portions of the base portion each mounted to a corresponding track and likewise extending beneath the seat bucket  102 . In some embodiments, the tracks  108  and the seat bucket  102  may be offset such that either of the left-side or right-side tracks extends fully beneath the seat bucket (but not both). 
     In some embodiments, the left-side and right-side portions of the base portion  104   a  may include a locking mechanism (not shown) via which the base seat structure  104  may be locked in one of several incremental positions relative to the tracks  108 , e.g., via a pin-and-slot system or any other appropriate means of securing the base seat structure into a position relative to the tracks and to the flight deck floor  106 . 
     In some embodiments, the left and right side panel portions  104   b  of the base seat structure  104  are configured to allow the seat bucket  102  to stroke downward in response to a crash event but also to pivot forward, allowing the seat bucket to attenuate downward force through a limited vertical space without impacting or damaging either the base portion  104   a  of the base seat structure, the tracks  108 , or the flight deck floor  106 . Similarly, in embodiments the height of the base seat structure  104  (e.g., terminating in crossmember  104   c  connecting the left and right side panel portions  104   b ) may be sufficiently low as to allow the seat bucket  102  to pivot forward without interference. For example, as the seat bucket  102  pivots forward, a seatback portion  102   a  thereof may tilt rearward toward the left and right side panel portions  104   b.  Further, in embodiments the height of the base seat structure  104  may allow the seat bucket  102  to recline relative to the base seat structure. 
     Referring now to  FIGS.  2 A through  2 C , the seating assembly  100  is shown. 
     In embodiments, referring in particular to  FIG.  2 A , each of the left-side and right-side side panel portions  104   b  may include a linear upper bucket guide channel  200  machined or otherwise set into its interior face (e.g., set into the right side of the left-side side panel portion and into the left side of the right-side side panel portion) and a curved lower bucket guide slot  202  set into its exterior face (e.g., directly opposite each respective upper bucket guide channel). 
     In embodiments, the seat bucket  102  may be connected to the base seat structure  104  by an upper bracket assembly and a lower bracket assembly allowing adjustment of the seat bucket relative to the base seat structure (e.g., as indicated above, to accommodate pilots of varied heights) as well as energy attenuation (EA) stroking in response to a crash event. For example, the upper bracket assembly may include an upper bucket support bracket  204  fixed to the rear of the seat bucket  102 , and an upper bucket support bracket receiver  206  fixed to the upper bucket support bracket and connecting the upper bucket support bracket to the lower bracket assembly. Similarly, in embodiments the lower bracket assembly may include a lower bucket support bracket  208  fixed to the seat bucket  102 . 
     In embodiments, the upper and lower bracket assemblies, each fixed to the seat bucket  102 , may be further connected to each other by a lower bucket support having an inner stabilizer bracket  210  and an outer stabilizer bracket  212 . For example, each inner stabilizer bracket  210  may be fixed to (e.g., to either side of) the upper bucket support bracket receiver  206  and to the outer stabilizer bracket  212 . In embodiments, referring in particular to  FIGS.  2 C and  2 E , the upper bracket assembly may translate along the linear upper bucket guide channel  200  via an upper bucket support  214  configured to pivot within the inner stabilizer bracket  210  and translate within the linear upper bucket guide channel (e.g., via bearing, sliding, or rolling members). For example, the translation of the upper bucket support  214  within the linear upper bucket guide channel  200  may allow adjustment of the seat bucket  102  relative to the base seat structure  104  and may also provide EA stroking in response to a crash event, as discussed in greater detail below. In some embodiments, the linear upper bucket guide channel  200  may further include a vertical lockout adjustment device  216  (e.g., dampener) allowing the seat bucket  102  to be locked relative to the base seat structure at a particular incremental position. 
     In embodiments, referring in particular to  FIGS.  2 A,  2 B, and  2 D , the outer stabilizer bracket  212  may be pivotably attached to the lower bucket support bracket  208 , which in turn may translate along the curved lower bucket guide slot  202  via axle  208   a  and inner bearing  208   b.  The lower bucket support bracket  208  may further include an outer bearing  208   c.  For example, the outer bearing  208   c  may slidably translate within a roller slot  212   a  set into the outer stabilizer bracket  212  as the lower bucket support bracket  208  translates through the lower curved portion of the curved lower bucket guide slot  202  (as shown in greater detail below), allowing the seat bucket  102  to pivot forward and away from the base seat structure  104 . 
     Referring now to  FIGS.  3 A- 3 F and  4 A- 4 F , the seating assembly  100  is shown. For each left-side profile view shown by  FIGS.  3 A through  3 F ,  FIGS.  4 A through  4 F  provide a respective counterpart rear isometric view. 
     Referring to  FIGS.  3 A and  4 A , the seating assembly  100  is shown in a fully-up and fully-aft configuration. For example, the base seat structure  104 , configured for translation along the tracks  108 , may be set in a rearmost position relative to the tracks. In embodiments, the tracks  108  may be set into the flight deck floor  106  such that the tracks terminate substantially adjacent to a rear bulkhead wall  300 . For example, when in the fully-aft position shown by  FIGS.  3 A and  4 A , the rear faces  302  of the left-side and right-side side panel portions  104   b  may be substantially flush with the rear bulkhead wall  300 . For example, the base seat structure  104  may be locked in one of several incremental positions relative to the tracks  108  and relative to the rear bulkhead wall  300  (e.g., via a pin-and-slot system or any other appropriate means of securing the base seat structure into a position relative to the tracks. 
     In embodiments, the incorporation of the curved lower bucket guide slot  202  may enable the side panel portions  104   b,  and therefore the base seat structure  104  as a whole, to have an optimally minimal height relative to the flight deck floor  106 . Accordingly, even when mounted substantially flush to a rear bulkhead wall  300  (as shown by  FIG.  3 A ), the seating assembly  100  may still provide for reclining of the seat bucket  102  relative to the base seat structure  104  (e.g., by tracking the seating assembly forward relative to the tracks  108 , and/or via pivoting of the outer stabilizer bracket  212  relative to the base seat structure and lower bucket support bracket  208 ) if the rear bulkhead wall  300  (or the position of the base seat structure relative to the rear bulkhead wall) and the height of the seat bucket relative to the base seat structure provides sufficient space). 
     In embodiments, the linear upper bucket guide channel ( 200 ,  FIGS.  2 C / 2 E) and the curved lower bucket guide slot  202  may extend (e.g., on either side of each side panel portion  104   b ) between the same maximum height  304  and minimum height  306  relative to the base portion  104   a  and to the flight deck floor  106 . The curved lower bucket guide slot  202  may include a substantially linear upper portion  202   a  through which the lower bucket support bracket  208  may translate (referring also to  FIGS.  3 B and  4 B ), e.g., for adjustment of the seat bucket  102  relative to the base seat structure  104  to accommodate taller or shorter pilots (e.g., through the range  110 ,  FIG.  1   ). 
     Referring now to  FIGS.  3 C and  4 C , the seating assembly  100  is shown at the lower end of the normal range of travel of the seat bucket  102  relative to the base seat structure  104 , e.g., the point  308  corresponding to the lower end of the substantially linear upper portion  202   a  of the curved lower bucket guide slot ( 202 ,  FIG.  3 A /B). For example, when in the position shown by  FIGS.  3 C and  4 C , the seating assembly  100  may be configured for accommodating the tallest percentiles of pilots or operators. 
     Referring now to  FIGS.  3 D through  3 F and  4 D through  4 F , the seating assembly  100  is shown in a crash event. 
     In embodiments, at the point  308  the curved lower bucket guide slot  202  may transition from the substantially linear upper portion  202   a  to a curved lower portion  202   b.  For example, as the lower bucket support bracket  208  begins to translate downward through the curved lower portion  202   b,  the upper bucket support ( 214 ,  FIGS.  2 C / 2 E) may begin stroking through the upper bucket guide channel ( 200 ,  FIGS.  2 C / 2 E), e.g., to attenuate downward force associated with the crash event. In embodiments, as the lower bucket support bracket  208  (e.g., the inner bearing ( 208   b,    FIGS.  2 C / 2 E) thereof) continues through the curved lower portion  202   b  of the curved lower bucket guide slot  202 , the outer bearing  208   c  may shift forward relative to the roller slot  212   a  set into the outer stabilizer bracket  212 , allowing the lower bucket support bracket (e.g., and the seat bucket  102  fixed thereto) forward and away from the base portion  104   a  of the base seat structure  104 . In embodiments, the precise dimensions of the curved lower portions  202   b  (e.g., degree of curvature, length of curvature) may vary according to cockpit/cabin configuration and dimensions. 
     CONCLUSION 
     It is to be understood that embodiments of the methods disclosed herein may include one or more of the steps described herein. Further, such steps may be carried out in any desired order and two or more of the steps may be carried out simultaneously with one another. Two or more of the steps disclosed herein may be combined in a single step, and in some embodiments, one or more of the steps may be carried out as two or more sub-steps. Further, other steps or sub-steps may be carried in addition to, or as substitutes to one or more of the steps disclosed herein. 
     Although inventive concepts have been described with reference to the embodiments illustrated in the attached drawing figures, equivalents may be employed and substitutions made herein without departing from the scope of the claims. Components illustrated and described herein are merely examples of a system/device and components that may be used to implement embodiments of the inventive concepts and may be replaced with other devices and components without departing from the scope of the claims. Furthermore, any dimensions, degrees, and/or numerical ranges provided herein are to be understood as non-limiting examples unless otherwise specified in the claims.