Patent Description:
Displays can be mounted within the aircraft. As aircraft displays utilize increased space for functions such as touch-sensitive screens or larger readout sizes, strategic use of fastener size and placement can be beneficial to optimize displayed information.

<CIT> discloses an arrangement comprising a quarter turn fastener with leaf spring.

<CIT> discloses systems and methods relating to aircraft instrumentation.

The invention is directed to an avionics display assembly according to claim <NUM>.

In one aspect, an avionics display assembly includes a frame assembly including a mounting flange, a touch screen display operably coupled to the frame assembly, at least one fastener assembly including a spring locking quarter turn fastener having a head on a non-display side of the assembly and a thread extending to a display side of the assembly, wherein the spring locking quarter turn fastener comprises a rail engagement fastener in the form of a quarter turn line fastener configured to mount to a cockpit rail by way of a fastener spring; a spring assembly including at least two leaf springs in a stacked configuration moveably coupled about at least a portion of the thread, and mounting hardware configured to secure the spring assembly to the thread.

The described embodiments of the present disclosure are directed to a fastener assembly. For purposes of illustration, the present disclosure will be described with respect to an aircraft cockpit electronics fastener assembly.

While "a set of" various elements will be described, it will be understood that "a set" can include any number of the respective elements, including only one element. As used herein, the terms "axial" or "axially" refer to a dimension along a longitudinal axis of an electric machine or along a longitudinal axis of a component disposed within the engine. As used herein, the terms "radial" or "radially" refer to a dimension extending between a center longitudinal axis of the engine, an outer rotational circumference, or a circular or annular component disposed within the engine. The use of the terms "proximal" or "proximally," either by themselves or in conjunction with the terms "radial" or "radially," refers to moving in a direction toward the center longitudinal axis, or a component being relatively closer to the center longitudinal axis as compared to another component.

All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, aft, etc.) are only used for identification purposes to aid the reader's understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of the disclosure. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and can include intermediate members between a collection of elements and relative movement between elements unless otherwise indicated. As such, connection references do not necessarily infer that two elements are directly connected and in fixed relation to one another. The exemplary drawings are for purposes of illustration only and the dimensions, positions, order and relative sizes reflected in the drawings attached hereto can vary.

<FIG> illustrates a non-limiting example of a portion of an aircraft cockpit <NUM>. While a commercial aircraft has been illustrated, it is contemplated that aspects of the disclosure can be used in any type of legacy aircraft, for example, without limitation, fixed-wing, rotating-wing, rocket, personal aircraft, and military aircraft. A first user (e.g., a pilot) can be present in a seat <NUM> at the left side of the cockpit <NUM> and another user (e.g., a co-pilot) can be present at the right side of the cockpit <NUM> in a seat <NUM>. A flight deck <NUM> can include various instruments <NUM>, various displays <NUM>, and a set of avionics display assemblies <NUM>. In one non-limiting aspect of the disclosure, a display assembly <NUM> can include a multifunction flight display with a display screen <NUM> that can be located in front of the pilot or co-pilot and can provide the flight crew with information to aid in flying the aircraft.

The display screen <NUM> can include either primary flight displays or multi-function displays and can display a wide range of aircraft, flight, navigation, and other information used in the operation and control of the aircraft. Non-limiting aspects of the display screen <NUM> can include displaying color graphics or text to a user, pilot, or co-pilot. The set of display assemblies <NUM> can be laid out in any manner, and need not be coplanar or the same size.

A touch screen display or touch screen surface can be included in the display screens <NUM> and can be used by one or more flight crewmembers, including the pilot and co-pilot, to interact with the systems of the aircraft.

<FIG> illustrates that the touch screen surface of the display screen <NUM> can be located within a frame assembly <NUM>. A lower housing <NUM> and upper housing <NUM> can be included in the frame assembly <NUM>. A mounting flange <NUM> can be provided or integrally formed within the lower housing <NUM>. A fastener assembly <NUM> can be provided to secure the frame assembly <NUM> to a portion of the aircraft cockpit <NUM>. While a single fastener assembly <NUM> is illustrated in detail, it will be appreciated that a set of fastener assemblies <NUM> can be included in the avionics display assembly <NUM>. As such a set of phantom schematic fastener assemblies <NUM> have been illustrated at various locations about the frame assembly <NUM>. More specifically, fastener assemblies <NUM> have been included at the corners and several of the midpoints of edges of the frame assembly <NUM>. It will be understood that any suitable number of fastener assemblies can be included at any suitable locations.

A cavity <NUM> can be defined within the lower housing <NUM>, and the fastener assembly <NUM> can be housed within the cavity <NUM> as shown in <FIG>. A spring locking quarter turn fastener <NUM> having a head <NUM> and a thread <NUM> can be included in the fastener assembly <NUM>, where the head <NUM> can be positioned on a non-display side 20A of the display assembly <NUM>, and the thread <NUM> can extend to a display side 20B of the display assembly <NUM> as shown. A standard <NUM>-40UNC thread is contemplated for the thread <NUM>, and it will be understood that any suitable thread may be used.

The spring locking quarter turn fastener <NUM> can form a rail engagement fastener configured to mount to a cockpit rail by way of a fastener spring <NUM>, a portion of which is illustrated in <FIG>. The quarter turn fastener <NUM> is illustrated herein as a quarter turn line fastener that can move downward to engage the fastener spring <NUM>, where a quarter-turn rotation of the head <NUM> can lock the fastener spring <NUM> into place and secure the frame assembly <NUM> in the cockpit <NUM>. It will be understood that other types or styles of fasteners are contemplated for use in the fastener assembly <NUM>.

A spring assembly <NUM>, movably coupled about at least a portion of the thread <NUM>, can also be included in the fastener assembly <NUM>. The spring assembly <NUM> can include a set of stacked leaf springs, illustrated as a first leaf spring <NUM> and second leaf spring <NUM>. By way of non-limiting example, the first leaf spring <NUM>' and second leaf spring <NUM> can be made of <NUM> stainless steel. The leaf springs <NUM> and <NUM> can be sized to exert the same or differing amounts of spring force under a given amount of compression as desired. It can be appreciated that the spring forces exerted by each leaf spring <NUM>, <NUM> are combined when the leaf springs <NUM>, <NUM> are in the stacked arrangement.

A bushing <NUM> can be included in the fastener assembly <NUM>. The bushing <NUM> can be located about at least a portion of the thread <NUM> and can be configured to space the spring assembly <NUM> from the mounting flange <NUM>. The bushing can be formed from stainless steel in a non-limiting example, and can also be integrally formed with the flange <NUM> or provided as a separately-attachable piece as shown.

Mounting hardware <NUM> can be included within the fastener assembly <NUM> and used to secure the spring assembly <NUM> to the thread <NUM>. In the illustrated example, the mounting hardware <NUM> is illustrated, in a non-limiting example, as a stainless steel threaded nut <NUM> and washer <NUM>. It will be understood that any suitable mounting hardware <NUM> can be utilized.

The fastener assembly <NUM> can be seen in greater detail in the exploded view of <FIG>. The quarter turn fastener <NUM> can be positioned below the mounting flange <NUM> such that the thread <NUM> can extend through the mounting flange <NUM> when assembled. The bushing <NUM> can be positioned above the mounting flange <NUM>. The first leaf spring <NUM> and second leaf spring <NUM> can be positioned above the bushing <NUM> in a stacked configuration as shown. The mounting hardware <NUM> can be positioned at the distal end of the thread <NUM> to hold the spring assembly <NUM> onto the thread <NUM>.

When assembled as shown in <FIG>, the bushing <NUM>, first leaf spring <NUM>, and second leaf spring <NUM> can be slidably received on the thread <NUM>, and the mounting hardware <NUM> (such as the threaded nut) can be tightened about the thread <NUM> to secure the components to form the assembled fastener assembly <NUM>. The spring assembly <NUM> is illustrated in a first position, where the leaf springs <NUM>, <NUM> are at rest and the quarter-turn fastener <NUM> is positioned abutting the mounting flange <NUM>.

The spring assembly <NUM> can compress in a vertical direction when assembled and tightened by the mounting hardware <NUM>, and <FIG> illustrates the spring assembly <NUM> in a second, flexed or compressed position. When the spring assembly <NUM> has been compressed, the quarter turn fastener <NUM> is displaced in a vertical direction shown by an arrow <NUM> during compression of the spring assembly <NUM> and become spaced apart from the mounting flange <NUM>. In a non-limiting example the spring assembly <NUM> can be configured to allow the quarter turn fastener <NUM> to be displaced vertically by <NUM> compared with a non-flexed position of the spring assembly <NUM>. It can be appreciated that the vertical displacement of the quarter turn fastener <NUM> can provide for engagement with the fastener spring <NUM> (<FIG>) to mount the frame assembly <NUM> to the cockpit <NUM> (<FIG>). The spring assembly <NUM> can also provide a retention force sufficient to ensure the proper retention force required by aircraft manufactures to secure cockpit electronics, and in one non-limiting example the spring assembly <NUM> can be configured to provide a retention force of at least <NUM> N when assembled and secured with the mounting hardware <NUM>.

The quarter turn fastener <NUM> can have a fastener width <NUM> and the mounting hardware <NUM> can have a hardware width <NUM> as shown. It should be understood that the fastener width <NUM> and hardware width <NUM> can describe the diameter or the largest dimension of the quarter turn fastener <NUM> and mounting hardware <NUM>, respectively. It is contemplated that the fastener width <NUM> can be <NUM> or smaller, and a <NUM> (quarter-inch) nut is contemplated for use with the mounting hardware <NUM>.

Turning to <FIG>, the fastener assembly <NUM> is illustrated while mounted to a portion of the frame assembly <NUM>. It is contemplated that an overall width <NUM> of the fastener assembly <NUM> can be the same size as the fastener width <NUM>, such as <NUM> or smaller in a non-limiting example. The hardware width <NUM>, such as that of the quarter-inch (<NUM>) nut, can be smaller than the overall width <NUM> of the fastener assembly <NUM>. In one non-limiting example the overall width <NUM> can be the same size as a width of the leaf springs <NUM>, <NUM> as well as a width of the bushing <NUM>. In another non-limiting example a width of the bushing <NUM> can be the same size or smaller than the overall width <NUM> such that the bushing <NUM> can fit fully within the leaf springs <NUM>, <NUM>.

Quarter turn fasteners traditionally contain internal coil springs, where the force exerted by the coil springs is used to secure an electronics display to a mounting piece. Traditionally-used quarter turn fasteners include coil springs within their interior. A coil spring of sufficient strength, to securely mount the electronics display, generally has a standard diameter of <NUM> inches (<NUM>).

It can be appreciated that aspects of the avionics display assembly described in the present disclosure can provide for a variety of benefits. One benefit is at least a <NUM>% reduction in width of the fastener assembly <NUM>, which can increase the available space for touch screen displays. It can be further appreciated that in limited-space applications such as airplane cockpits, increasing the size or usable area of display or touch screens can improve the quality or delivery of information as well as optimize touch-screen applications such as keyboards. An additional benefit can be found in the use of the stacked leaf springs which can provide for an increase in available spring force, compared with springs found in traditional quarter turn fasteners, without increasing the overall width of the fastener assembly. While other traditional mounting systems such as cams or levers can be used to mount display screens, the complexity involved in arranging such systems within aircraft cockpits can increase cost or failure rates. It can be appreciated that the fastener assembly <NUM> as described herein can be used in current existing aircraft cockpit electronics and also utilize pre-existing aircraft rails or wires to mount the display assembly <NUM> to the cockpit <NUM>.

To the extent not already described, the different features and structures of the various embodiments can be used in combination, or in substitution with each other as desired. That one feature is not illustrated in all of the embodiments is not meant to be construed that it cannot be so illustrated, but is done for brevity of description. Thus, the various features of the different embodiments can be mixed and matched as desired to form new embodiments, whether or not the new embodiments are expressly described. All combinations or permutations of features described herein are disclosed.

Claim 1:
An avionics display assembly (<NUM>), comprising:
a frame assembly (<NUM>) including a mounting flange (<NUM>);
a touch screen display (<NUM>) operably coupled to the frame assembly (<NUM>); and
at least one fastener assembly (<NUM>) comprising:
a spring locking quarter turn fastener (<NUM>) having a head (<NUM>) on a non-display side (20A) of the assembly (<NUM>) and a thread (<NUM>) extending to a display side (20B) of the assembly (<NUM>), wherein the spring locking quarter turn fastener (<NUM>) comprises a rail engagement fastener (<NUM>) in the form of a quarter turn line fastener (<NUM>) configured to mount to a cockpit rail by way of a fastener spring (<NUM>);
a spring assembly (<NUM>) including at least two leaf springs (<NUM>, <NUM>) in a stacked configuration moveably coupled about at least a portion of the thread (<NUM>); and
mounting hardware (<NUM>) configured to secure the spring assembly (<NUM>) to the thread (<NUM>).