Compact rotorcraft seat assembly with nonlinear seat pan guide channel

Abstract

The present disclosure relates to compact rotorcraft seat assemblies with nonlinear seat pan guide channels. A rotorcraft seat assembly includes a seat pan supporting a seat pan, the seat pan having left and right side panel portions. Each side panel portion has a linear seat pan guide channel disposed into an inner surface thereof (including an upper portion for adjusting the seat pan relative to the seat pan for different pilot heights and a lower portion for energy attenuation (EA) movement in response to a crash event) and a seat pan guide slot disposed into an outer surface thereof (including a linear upper portion corresponding to an adjustment range of the seat pan and a curved lower portion allowing the seat pan to translate forward and away from the seat pan during EA movement). The curved outer seat pan guide slot allows a desired EA movement distance within a minimum vertical space between the seat pan and a cockpit floor.

Description

Technical Field

[0001] Embodiments of the inventive concept disclosed herein generally relate to seat assemblies, and particularly to seat assemblies for cockpit seats for rotorcraft operators. Background Technology

[0002] Seats for helicopters and / or rotorcraft (e.g., for pilots, operators, and / or passengers) require stroking distance (which must be along a straight axis) to absorb energy and decelerate substantially vertically (e.g., along the Z-axis, parallel to the operator's spine) in response to dynamic events. Firstly, the seat must be able to accommodate a wide range of pilot heights. For example, a seat can be adjusted to accommodate very tall pilots, but at the cost of vertical stroking distance between the seat pocket and the cockpit floor. This problem can be addressed with a sub-floor or recesses or depressions set into the cockpit floor into which the seat pocket can be moved below floor level. However, size, weight, and power factors (SWaP-c) may not always provide space for a sub-floor, leaving a limited amount of vertical space between the seat pocket and the floor in which the required stroking distance can be achieved. Summary of the Invention

[0003] A compact rotorcraft seat assembly with a nonlinear bucket guide channel is disclosed. In an embodiment, the seat assembly includes a seat bucket and a seat base, the seat base being mountable to the cockpit or cockpit floor of a helicopter or other similar rotorcraft. The seat base includes a base portion mountable to the floor and spaced-apart left and right side panel portions that rise at an obtuse angle (e.g., beyond vertical) above the base portion. Each of the left and right side panel portions includes a linear bucket guide channel and a bucket guide slot, the bucket guide channel being disposed in an inner surface and the bucket guide slot being disposed in an outer surface, the bucket guide slot having a straight, linear upper portion transitioning to a curved lower portion. The seat base supports the seat bucket, and the seat bucket, in turn, supports the pilot or operator of the rotorcraft. The seat bucket is slidably connected to the inner bucket guide channel and outer bucket guide slot of each side panel portion such that the seat bucket can be raised or lowered relative to the seat base by translating through the respective upper portions of the bucket guide channel and bucket guide slot (e.g., to accommodate a shorter or taller pilot). In the event of a collision or other similar dynamic event, the impact energy (e.g., downward force) of the seat pocket is attenuated by translation through the lower part of the straight inner seat pocket guide channel. At the same time, the seat pocket pivots forward and away from the seat base and cockpit floor by transitioning to the curved lower part of the seat pocket guide channel (e.g., to avoid collision with the seat base or cockpit floor).

[0004] In some embodiments, the inner bucket guide passage and the outer bucket guide slot extend relative to the seat base and cabin floor between the same top and bottom heights (e.g., corresponding to the endpoints of the passage or slot).

[0005] In some embodiments, the upper support assembly fixed to the seat pocket translates through the inner seat pocket guide channel, and the lower support assembly fixed to the seat pocket translates through the outer seat pocket guide groove.

[0006] In some embodiments, the upper support assembly includes an upper support member pivotally connected to the support assembly, the upper support member being able to attenuate impact energy by moving downward through the lower portion of the bucket guide channel opposite the curved portion of the bucket guide slot.

[0007] In some embodiments, the lower support assembly includes a lower support bracket that translates through an outer seat guide slot via an inner bearing that shares a common axis with the outer bearing. In some embodiments, the lower support assembly also includes a stabilizer bracket that is attached to the upper support assembly and includes a slot through which the outer bearing translates.

[0008] In some embodiments, the seat base is mounted to the cabin or cockpit floor via tracks fixed to the floor, the tracks extending parallel (e.g., left and right) and the seat base is capable of translating along the tracks.

[0009] In some embodiments, both the left and right tracks extend beneath the seat pocket.

[0010] In some embodiments, either the left or right track (but not both) extends beneath the seat pocket.

[0011] In some embodiments, the seat pocket is tilted relative to the seat base.

[0012] In some embodiments, the rear surfaces of the left and right panel portions can be positioned flush with the bulkhead of the rotorcraft.

[0013] This summary is provided solely as an introduction to the subject matter fully described in the detailed description and accompanying drawings. It should not be considered as describing essential features or used to define the scope of the claims. Furthermore, it should be understood that both the foregoing summary and the following detailed description are exemplary and illustrative only, and do not necessarily limit the claimed subject matter. Attached Figure Description

[0014] The specific embodiments are described with reference to the accompanying drawings. The use of the same reference numerals in different instances in the specification and drawings may indicate similar or identical items. Various embodiments or examples (“Examples”) of this disclosure are disclosed in the following detailed description and drawings. The drawings are not necessarily to scale. Generally, unless otherwise provided in the claims, the disclosed processes can be performed in any order. In the drawings: Figure 1 This is a rear axonometric view showing a rotorcraft seat assembly according to an exemplary embodiment of the present disclosure; Figure 2A yes Figure 1 A detailed view of the side panel portion of the seat base of the seat assembly, including internal and external guide channels; Figure 2B and 2C They are Figure 1 External and internal views of the side panel portion of the seat base; Figure 2D and 2E They are Figure 2B and 2C An exploded view of the exterior and interior; Figures 3A to 3C yes Figure 1 Left profile view of the seat bucket adjustment operation of the seat assembly; Figures 3D to 3F yes Figures 3A to 3C The left profile view of the energy decay (EA) movement operation of the seat assembly; Figures 4A to 4C yes Figures 3A to 3C The corresponding rear axle view of the seat bucket adjustment operation; Figures 4D to 4F yes Figures 3D to 3F The corresponding rear axonometric plot of the EA movement operation; and Figure 5A , 5B 5C, 5D, 5E and 5F are respectively Figure 1 Top / top view, bottom / lower view, right profile view, left profile view, front view, and rear view of the rotorcraft seat assembly.

[0015] This summary is provided solely as an introduction to the subject matter fully described in the detailed description and accompanying drawings. It should not be considered as describing essential features or used to define the scope of the claims. Furthermore, it should be understood that both the foregoing summary and the following detailed description are exemplary and illustrative only, and do not necessarily limit the claimed subject matter. Detailed Implementation

[0016] Before explaining one or more embodiments of this disclosure in detail, it should be understood that the embodiments are not limited in their application to the details of the construction and arrangement of components or steps or methods set forth in the following description or shown in the accompanying drawings. In the following detailed description of the embodiments, many specific details may be set forth to provide a more thorough understanding of this disclosure. However, it will be apparent to those skilled in the art who will benefit from this disclosure that the embodiments disclosed herein can be practiced without some of these specific details. In other instances, well-known features may not be described in detail to avoid unnecessarily complicating this disclosure.

[0017] As used herein, the letters following the reference numerals are intended to indicate embodiments of features or elements that may be similar to, but not necessarily identical to, the aforementioned elements or features having the same reference numerals (e.g., 1, 1a, 1b). Such shorthand notation is used for convenience only and should not be construed as limiting this disclosure in any way unless expressly stated otherwise.

[0018] Furthermore, unless explicitly stated to the contrary, "or" refers to inclusive or rather than exclusive or. For example, condition A or B is satisfied by any one of the following: A is true (or exists) and B is false (or does not exist), A is false (or does not exist) and B is true (or exists), and both A and B are true (or exist).

[0019] Furthermore, the terms "a" or "an" may be used to describe elements and components of the embodiments disclosed herein. This is merely for convenience, and "a" and "an" are intended to include "one" or "at least one," and the singular includes the plural, unless it is obvious that they have other meanings.

[0020] 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 an embodiment is included in at least one embodiment disclosed herein. The phrase “in some embodiments” appearing in various places in the specification does not necessarily refer to all the same embodiments, and embodiments may include one or more, or any combination or sub-combination of two or more features expressly described or inherently present herein, together with any other features that may not be expressly described or inherently present in this disclosure.

[0021] In summary, embodiments of the inventive concept disclosed herein relate to a helicopter seat assembly capable of providing full energy decay (EA) movement within a minimal vertical space between the bottom of the seat bucket and the cockpit floor during a collision or other similar dynamic event. In addition to a linear guide channel for EA movement, a curved external guide channel supports and guides the lower portion of the seat bucket forward and away from the base seat structure during downward movement, preventing lateral swaying of the seat bucket. Furthermore, the use of the curved external channel allows for a shorter base seat structure, allowing for further tilting of the seat bucket relative to the base seat structure, even when directly mounted in front of the bulkhead.

[0022] refer to Figure 1 The image shows a seat assembly 100 for a helicopter or rotorcraft. The seat assembly 100 may include a seat bucket 102 and a base seat structure 104.

[0023] In embodiments, the seat bucket 102 can be configured to accommodate the pilot, operator, or passenger of the rotorcraft. For example, the seat bucket 102 can be adjustable relative to the base seat structure 104, for instance, to accommodate a wide range of heights and body types of pilots or other occupants in a position where the pilot's eye level and / or positioning relative to the rotorcraft controllers may be optimal.

[0024] In embodiments, the base seat structure 104 may be mounted to the cockpit or cabin floor 106 of a rotorcraft. For example, the base seat structure 104 may be mounted to a track 108 disposed in the cockpit floor 106, as described in more detail below. In embodiments, the base seat structure 104 may include a base portion 104a and side panel portions 104b. For example, the base portion 104a may extend substantially horizontally along the cockpit floor 106 (and may be mounted directly to the track 108, for example), while the left and right side panel portions 104b extend above the base portion at substantially obtuse angles. In some embodiments, the left and right side panel portions 104b extend above the base portion at an angle not greater than 120 degrees with respect to the cockpit floor 106 (e.g., not greater than 30 degrees with respect to the vertical direction); in other embodiments, this angle may vary depending on the precise construction of the cockpit or cabin.

[0025] In one embodiment, the seat bucket 102 may be mounted to the side panel portion 104b and may be adjustable relative to the base seat structure 104. For example, the seat bucket 102 may be adjustable relative to the base seat structure 104 within a range 110 of incrementally locked adjustment positions, such as adjusting upwards to accommodate shorter pilots and downwards to accommodate taller pilots. In some embodiments, the seat bucket 102 will accommodate any pilot between the 5th percentile (e.g., height / weight) of a female operator and the 95th percentile of a male operator.

[0026] In some embodiments, track 108 extends parallel (108a) to the cockpit floor 106 below the seat pocket 102. Therefore, the base portion 104a of the base seat structure 104 may similarly include left and right portions extending forward from the left and right panel portions 104b, respectively, with each left and right portion of the base portion mounted to a corresponding track and also extending below the seat pocket 102. In some embodiments, track 108 and seat pocket 102 may be offset such that either the left or right track extends entirely below the seat pocket (but not both).

[0027] In some embodiments, the left and right sides of the base portion 104a may include a locking mechanism (not shown) by which the base seat structure 104 can be locked in one of several incremental positions relative to the track 108, for example by a pin-slot system or any other suitable means of securing the base seat structure to a position relative to the track and the cockpit floor 106.

[0028] In some embodiments, the left and right side panel portions 104b of the base seat structure 104 are configured to allow the seat pocket 102 to move downward and pivot forward in response to a collision event, thereby allowing the seat pocket to attenuate downward forces through limited vertical space without affecting or damaging the base portion 104a of the base seat structure, the track 108, or the cockpit floor 106. Similarly, in embodiments, the height of the base seat structure 104 (e.g., terminating at the transverse member 104c connecting the left and right side panel portions 104b) may be low enough to allow the seat pocket 102 to pivot forward without interference. For example, when the seat pocket 102 pivots forward, its seat back portion 102a may tilt backward toward the left and right side panel portions 104b. Furthermore, in embodiments, the height of the base seat structure 104 may allow the seat pocket 102 to tilt relative to the base seat structure.

[0029] Now for reference Figures 2A to 2C The image shows the seat assembly 100.

[0030] In the embodiments, particular reference is made to Figure 2AEach of the left and right panel portions 104b may include a linear upper bucket guide channel 200 machined or otherwise disposed in its inner surface (e.g., disposed in the right side of the left side panel portion and disposed in the left side of the right side panel portion) and a curved lower bucket guide groove 202 disposed in its outer surface (e.g., directly opposite each corresponding upper bucket guide channel).

[0031] In one embodiment, the seat bucket 102 can be connected to the base seat structure 104 via an upper support assembly and a lower support assembly, thereby allowing adjustment of the seat bucket relative to the base seat structure (e.g., as described above, to accommodate pilots of different heights) and movement in response to energy decay (EA) in the event of a collision. For example, the upper support 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 support assembly. Similarly, in one embodiment, the lower support assembly may include a lower bucket support bracket 208 fixed to the seat bucket 102.

[0032] In an embodiment, each of the upper and lower support assemblies, each fixed to the seat basket 102, can be further connected to each other via a lower basket support having an inner stabilizer support 210 and an outer stabilizer support 212. For example, each inner stabilizer support 210 can be fixed to the upper basket support bracket receiver 206 (e.g., fixed to either side thereon) and to the outer stabilizer support 212. In an embodiment, particularly reference is made to... Figure 2C and 2E The upper support assembly is translatable along a linear upper bucket guide channel 200 via an upper bucket support 214 configured to pivot within the inner stabilizer support 210 and translate within the linear upper bucket guide channel (e.g., via support, sliding, or rolling members). For example, 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 movement in response to a collision event, as discussed in more detail below. In some embodiments, the linear upper bucket guide channel 200 may also include a vertical locking adjustment device 216 (e.g., a damper) allowing the seat bucket 102 to lock relative to the base seat structure in specific incremental positions.

[0033] In the embodiments, particular reference is made to Figure 2A , 2BIn addition to 2D, the outer stabilizer bracket 212 can be pivotally attached to the lower bucket support bracket 208, which can then translate along the curved lower bucket guide groove 202 via shaft 208a and inner bearing 208b. The lower bucket support bracket 208 may also include an outer bearing 208c. For example, as the lower bucket support bracket 208 translates through the lower curved portion of the curved lower bucket guide groove 202 (shown in more detail below), the outer bearing 208c can slidably translate within a groove 212a provided in the outer stabilizer bracket 212, thereby allowing the seat bucket 102 to pivot forward and away from the base seat structure 104.

[0034] Now for reference Figures 3A-3F Figures 4A-4F show seat assembly 100. For Figures 3A to 3F Each left-side outline view shown, Figures 4A to 4F The corresponding rear axonometric drawing is provided.

[0035] refer to Figure 3A and 4A The seat assembly 100 is shown in a fully upward and fully rearward configuration. For example, a base seat structure 104 configured for translation along track 108 can be positioned at the rearmost point relative to the track. In an embodiment, track 108 can be disposed within cockpit floor 106 such that the track terminates substantially adjacent to a rear bulkhead 300. For example, when in... Figure 3A and 4A In the fully rearward position shown, the rear surfaces 302 of the left and right side panel portions 104b can be substantially flush with the aft bulkhead 300. For example, the base seat structure 104 can be locked in one of several incremental positions relative to the track 108 and relative to the aft bulkhead 300 (e.g., via a pin-slot system or any other suitable means of securing the base seat structure to the position relative to the track).

[0036] In the embodiment, the included curved lower seat guide groove 202 allows the side panel portion 104b, and thus the base seat structure 104 as a whole, to have an optimal minimum height relative to the cockpit floor 106. Therefore, even when installed substantially flush with the rear bulkhead 300 (e.g., Figure 3A As shown), if the aft bulkhead 300 (or the position of the base seat structure relative to the aft bulkhead) and the height of the seat bucket relative to the base seat structure provide sufficient space, the seat assembly 100 can still provide the tilt of the seat bucket 102 relative to the base seat structure 104 (e.g., by moving the seat assembly forward relative to the track 108, and / or via the pivoting of the outer stabilizer bracket 212 relative to the base seat structure and the lower seat bucket support bracket 208).

[0037] In an embodiment, the linear upper seat bucket guide channel (200, Figure 2C / 2E) and the curved lower seat bucket guide 202 may extend relative to the base portion 104a and the cockpit floor 106 between the same maximum height 304 and minimum height 306 (e.g., on either side of each side panel portion 104b). The curved lower seat bucket guide 202 may include a generally linear upper portion 202a through which the lower seat bucket support bracket 208 can translate (see also) the upper portion 202a. Figure 3B and 4B ), for example, for adjusting the seat bucket 102 relative to the base seat structure 104 to accommodate a taller or shorter pilot (e.g., via range 110, Figure 1 ).

[0038] Now for reference Figure 3C and 4C The seat assembly 100 is shown located at the lower end of the seat pocket 102 relative to the base seat structure 104 within its normal range of travel, for example, corresponding to the curved lower seat pocket guide groove (202, Figure 3A / B) The lower end of the basic linear upper part 202a at point 308. For example, when in Figure 3C and 4C When in the position shown, the seat assembly 100 can be configured to accommodate the highest percentile of the pilot or operator.

[0039] Now for reference Figures 3D to 3F Figures 4D through 4F show the seat assembly 100 in a collision.

[0040] In one embodiment, at point 308, the curved lower bucket guide groove 202 transitions from a generally linear upper portion 202a to a curved lower portion 202b. For example, as the lower bucket support bracket 208 begins to translate downward through the curved lower portion 202b, the upper bucket support member (214, Figure 2C / 2E) can begin moving through the upper seat guide passage (200, Figure 2C / 2E), for example, to attenuate the downward force associated with a collision event. In an embodiment, the lower seat support bracket 208 (e.g., its inner bearing (208b, Figure 2C As the lower portion 202b of the curved lower seat bucket guide groove 202 continues through the curved lower portion 202b, the outer bearing 208c can be offset forward relative to the groove 212a set in the outer stabilizer bracket 212, thereby allowing the lower seat bucket support bracket (e.g., and the seat bucket 102 fixed thereto) to move forward and away from the base portion 104a of the base seat structure 104. In embodiments, the precise dimensions of the curved lower portion 202b (e.g., the degree of curvature, the length of the curvature) may vary depending on the construction and dimensions of the cockpit / cabin.

[0041] in conclusion It should be understood that embodiments of the methods disclosed herein may include one or more steps described herein. Furthermore, such steps may be performed in any desired order, and two or more of the steps may be performed simultaneously with each other. 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 performed as two or more sub-steps. In addition, other steps or sub-steps may be performed besides or as alternatives to one or more of the steps disclosed herein.

[0042] Although the inventive concept has been described with reference to embodiments shown in the accompanying drawings, equivalents and substitutions may be used herein without departing from the scope of the claims. The components shown and described herein are merely examples of systems / apparatus and components that can be used to implement embodiments of the inventive concept and may be replaced with other apparatuses and components without departing from the scope of the claims. Furthermore, any dimensions, degrees, and / or numerical ranges provided herein should be understood as non-limiting examples unless otherwise specified in the claims.

Claims

1. A rotorcraft seat assembly, comprising: A seat base and a seat structure, the seat structure being configured to support the seat base in a seated position, the seat structure comprising: The base portion, which can be mounted to the cockpit floor of the rotorcraft; and Left and right side panel portions, the left and right side panel portions rising from the base portion and inclined relative to the base portion, each side panel portion including: A bucket guide channel, wherein the bucket guide channel is disposed in the inner surface of the side panel portion; and A bucket guide groove is provided in the outer surface of the side panel portion, opposite to the bucket guide channel, the bucket guide groove is fixed relative to the bucket guide channel and includes 1) a linear upper portion and 2) an arc-shaped lower portion; The seat pocket is slidably connected to each of the left and right side panel portions via the seat pocket guide channel and the seat pocket guide groove, and the seat pocket is configured as follows: The operator supporting the rotorcraft; and Responding to dynamic events: The impact energy of the seat bucket is attenuated by slidably translating along the bucket guide channel; and The seat bucket is moved in the downward and forward directions by slidingly translating along the lower part of the bow shape of the bucket guide groove.

2. The rotorcraft seat assembly as claimed in claim 1, wherein, The bucket guide channel and the bucket guide groove extend between a first height above the base portion and a second height above the base portion.

3. The rotorcraft seat assembly as claimed in claim 1, wherein, The seat pocket is slidably connected to the left and right side panel portions via the following: An upper support assembly, which is fixed to the seat pocket and configured to slidably translate along the seat pocket guide channel; and A lower support assembly is fixed to the seat pocket and is configured to slidably translate along the seat pocket guide groove.

4. The rotorcraft seat assembly as claimed in claim 3, wherein: The upper support assembly is configured to slidably translate along the seat bucket guide channel via an upper support member pivotally connected to the upper support assembly. The upper support member is configured to attenuate the energy of the seat bucket by moving downward through the lower part of the seat bucket guide channel, the lower part of the seat bucket guide channel corresponding to the lower part of the bow shape of the seat bucket guide groove.

5. The rotorcraft seat assembly as claimed in claim 3, wherein: The lower support assembly includes 1) a lower bucket support bracket configured to be slidably translated along the bucket guide groove via at least one inner bearing, and 2) at least one outer bearing sharing a common shaft with the inner bearing. as well as A stabilizer bracket, fixed to the upper bracket assembly and including at least one stabilizer slot configured to receive the outer bearing, the outer bearing being configured to slidably translate along the stabilizer slot when the inner bearing translates along the lower part of the bow-shaped guide slot of the seat bucket.

6. The rotorcraft seat assembly as claimed in claim 1, wherein: The base portion can be mounted to the cockpit floor via two or more rails, which are fixed to the cockpit floor and extend parallel to it. in The base seat structure is configured to slide along two or more tracks.

7. The rotorcraft seat assembly as claimed in claim 6, wherein, The two or more tracks extend along the cockpit floor beneath the seat pocket.

8. The rotorcraft seat assembly as claimed in claim 6, wherein, The two or more tracks extend along the cockpit floor, and one of the two or more tracks extends beneath the seat pocket.

9. The rotorcraft seat assembly as claimed in claim 1, wherein: The seat pocket is configured to be tilted relative to the base seat structure.

10. The rotorcraft seat assembly of claim 1, wherein: In response to the dynamic event, the seat pocket is configured to pivot in the forward direction without affecting the cockpit floor.

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