Nose landing gear assembly for an aircraft

Abstract

A nose landing gear assembly for an aircraft. A nose landing gear assembly includes a hydraulic strut, a front strut including a front strut first end and a front strut second end. The front strut first end is pivotably coupled to a nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes a rear strut including a rear strut first end and a rear strut second end. The rear strut first end is pivotably coupled to the nose gear bay about a second pivot axis and the rear strut second end is pivotably coupled to the hydraulic strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end is coupled to the front strut. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

Description

TECHNICAL FIELD

[0001] The field of the present disclosure relates generally to nose-mounted landing gear for aircraft, and more particularly to compact nose-mounted landing gear housed in a reduced volume gear well. BACKGROUND

[0002] Currently known nose landing gear and its retraction mechanisms are highly modified based on the type of aircraft and operate effectively under a variety of operating conditions, such as taxi, braking, takeoff / landing, and retraction / deployment. Commercial passenger aircraft typically include a passenger zone and a baggage zone below the passenger zone. The baggage zone on some known aircraft also includes a landing gear well that houses the landing gear during flight. However, in aircraft used only for cargo transport, the cargo zone floor is positioned as close as possible to the bottom of the aircraft to enable the maximum amount of cargo to be stored. In such a configuration, the available volume for storing the landing gear is reduced, and the volume of the cargo zone is limited by the amount of space required to house the landing gear during flight.

[0003] This section is intended to introduce the reader to various aspects of art that can be related to various aspects of the present disclosure and 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 disclosure. Accordingly, it should be understood that these statements are to be read in this light, and not as admissions of prior art. SUMMARY

[0004] In one aspect, a nose landing gear assembly for a high-wing aircraft defining a nose gear well is provided. The nose landing gear assembly includes a hydraulic strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear well about a first pivot axis. The nose landing gear assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear well about a second pivot axis, and the aft brace second end is pivotably coupled to the hydraulic strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear well and the actuator first end is coupled to the forward brace. The actuator is configured to selectively move the nose landing gear assembly between a retracted position and a deployed position.

[0005] In another aspect, an aircraft is provided. The aircraft includes a cargo bay including a cargo bay floor, a nose landing gear bay positioned below the cargo bay floor, and a nose landing gear assembly selectively positioned within the nose landing gear bay. The nose landing gear assembly includes a hydraulic strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose landing gear bay about a first pivot axis. The nose landing gear assembly also includes a rear brace including a rear brace first end and a rear brace second end. The rear brace first end is pivotably coupled to the nose landing gear bay about a second pivot axis, and the rear brace second end is pivotably coupled to the hydraulic strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose landing gear bay and the actuator first end is coupled to the forward brace. The actuator is configured to selectively move the nose landing gear assembly between a retracted position and an extended position.

[0006] In yet another aspect, a method of assembling a nose landing gear assembly for a high wing aircraft is provided. The high wing aircraft defines a nose landing gear bay, wherein the nose landing gear assembly includes a hydraulic strut, a forward brace, a rear brace, and an actuator. The method includes pivotably coupling a first end of the forward brace to the nose landing gear bay about a second pivot axis. The method also includes pivotably coupling a second end of the rear brace to the hydraulic strut, coupling a first end of the actuator to the nose landing gear bay, and coupling a second end of the actuator to the forward brace. The actuator is configured to selectively move the nose landing gear assembly between a retracted position and an extended position. BRIEF DESCRIPTION OF DRAWINGS

[0007] Figure 1 is a schematic illustration of an exemplary aircraft with an exemplary nose landing gear assembly.

[0008] Figure 2 is Figure 1 is a schematic illustration of the nose landing gear assembly illustrated in

[0009] Figure 3 is Figure 2 is a side view of the nose landing gear assembly illustrated in

[0010] Figure 4 is Figure 2 is a perspective view of the nose landing gear assembly illustrated in

[0011] Figure 5 is Figure 2 is a front view of the nose landing gear assembly illustrated in

[0012] Figure 6 isFigure 2 rear view of the nose landing gear assembly illustrated in FIG. 1 in the extended position.

[0013] Figure 7 is Figure 2 top view of the nose landing gear assembly illustrated in FIG. 1 in the extended position.

[0014] Figure 8 is Figure 2 bottom view of the nose landing gear assembly illustrated in FIG. 1 in the extended position.

[0015] Figures 9A-9F is Figure 2 perspective view of the nose landing gear assembly illustrated in FIG. 1 moving from the extended position to the retracted position.

[0016] Figure 10 is Figure 2 side view of the nose landing gear assembly illustrated in FIG. 1 in the retracted position.

[0017] Figure 11 is Figure 2 perspective view of the nose landing gear assembly illustrated in FIG. 1 in the retracted position.

[0018] Figure 12 is Figure 2 front view of the nose landing gear assembly illustrated in FIG. 1 in the retracted position.

[0019] Figure 13 is Figure 2 rear view of the nose landing gear assembly illustrated in FIG. 1 in the retracted position.

[0020] Figure 14 is Figure 2 top view of the nose landing gear assembly illustrated in FIG. 1 in the retracted position.

[0021] Figure 15 is Figure 2 bottom view of the nose landing gear assembly illustrated in FIG. 1 in the retracted position.

[0022] Figure 16 is a front perspective view of an exemplary nose landing gear assembly in the extended position.

[0023] Figure 17 is Figure 16 right side view of the nose landing gear assembly illustrated in FIG. 1 in the extended position, and the left side view is a mirror image of the right side view.

[0024] Figure 18 is Figure 16 front view of the nose landing gear assembly illustrated in FIG. 1 in the extended position.

[0025] Figure 19 is Figure 16 a rear view of the nose landing gear assembly shown in FIG. 1 in the extended position.

[0026] Figure 20 is Figure 16 a top view of the nose landing gear assembly shown in FIG. 1 in the extended position.

[0027] Figure 21 is Figure 16 a bottom view of the nose landing gear assembly shown in FIG. 1 in the extended position.

[0028] Figure 22 is Figure 16 a front perspective view of the nose landing gear assembly shown in FIG. 1 in the retracted position.

[0029] Figure 23 is Figure 16 a right side view of the nose landing gear assembly shown in FIG. 1 in the retracted position, and the left side view is a mirror image of the right side view.

[0030] Figure 24 is Figure 16 a front view of the nose landing gear assembly shown in FIG. 1 in the retracted position.

[0031] Figure 25 is Figure 16 a rear view of the nose landing gear assembly shown in FIG. 1 in the retracted position.

[0032] Figure 26 is Figure 16 a top view of the nose landing gear assembly shown in FIG. 1 in the retracted position.

[0033] Figure 27 is Figure 16 a bottom view of the nose landing gear assembly shown in FIG. 1 in the retracted position.

[0034] Throughout the drawings, corresponding reference characters indicate corresponding parts throughout the several views. While specific features of various examples can be shown in some drawings and not in others, this is for convenience only as such features can be combined with any or all of the other features set forth herein and / or claimed. DETAILED DESCRIPTION

[0035] The embodiments described herein relate to nose-mounted landing gear for an aircraft, and more particularly to compact nose-mounted landing gear housed in a reduced volume gear well. More particularly, in exemplary embodiments, a nose-mounted landing gear assembly includes a hydraulic strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to a nose gear well of a high wing aircraft about a first pivot axis. The nose-mounted landing gear assembly also includes an aft brace having an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear well about a second pivot axis, and the aft brace second end is pivotably coupled to the hydraulic strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear well and the actuator first end is coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

[0036] The assemblies and methods described herein facilitate folding the nose landing gear assembly into a more compact configuration in order to allow storage in a reduced volume nose gear well. Generally, the nose landing gear assemblies described herein are used for cargo aircraft use that do not have a passenger cabin and an enlarged cargo bay. In such aircraft, the cargo bay floor is positioned as close to the bottom of the aircraft as possible to enable the maximum amount of cargo to be stored. As such, the available volume for storing the nose landing gear assembly is reduced. The nose landing gear assemblies described herein allow the retracted configuration to occupy only a small percentage of the space required when it is in the extended configuration, thus enabling storage in a relatively small nose gear well volume. As a result, the cargo bay is made larger than the cargo bays of known cargo aircraft to enable a larger volume of cargo to be transported.

[0037] Figure 1 is a schematic view of an aircraft 100. In exemplary embodiments, the aircraft 100 is a high wing cargo aircraft that includes a cargo bay 102 and a cargo bay floor 104. In addition, a nose gear well 106 is positioned below the cargo bay floor and selectively houses a nose landing gear assembly 108 therein. Figure 2 is a schematic view of a nose landing gear assembly 108 positioned in the nose gear well 106. The configuration of the aircraft 100 gives limited volume below the cargo bay floor 104 to stow the nose landing gear assembly 108. As described herein, the nose landing gear assembly 108 includes a folding mechanism that allows the support trunnions to be placed in very close proximity to each other, allowing for a more compact nose gear well 106. In particular, as described herein, the folding mechanism includes a forward brace 202 and an aft brace 204 that are pivotably coupled to the nose gear well 106. The forward brace 202 is pivotably coupled to the aft brace 204 about a pivot axis 206. The folding mechanism also includes a hydraulic strut 208 that is pivotably coupled to the aft brace 204 about a pivot axis 210. The folding mechanism also includes an actuator 212 that is coupled to the nose gear well 106 and the forward brace 202. The actuator 212 is configured to move the nose landing gear assembly 108 between a retracted position and an extended position. Figure 2As shown, the nose landing gear bay 106 includes a first side panel 107, a second side panel 109, a front panel 111 extending between the side panels 107 and 109, and a rear panel 113 extending between the side panels 107 and 109. The panels 107, 109, 111, and 113 define an interior volume in which the nose landing gear assembly 108 is stored during flight.

[0038] Figure 3 is a side view of the nose landing gear assembly 108 in the extended position, Figure 4 is a perspective view of the nose landing gear assembly 108 in the extended position, and Figure 5 is a front view of the nose landing gear assembly 108 in the extended position. Figure 6 is a rear view of the nose landing gear assembly 108 in the extended position, Figure 7 is a top view of the nose landing gear assembly 108 in the extended position. Figure 8 is a bottom view of the nose landing gear assembly 108 in the extended position.

[0039] In the example embodiment, the nose landing gear assembly 108 includes a front strut 110 having a front strut first end 112 and a front strut second end 114. The front strut first end 112 is coupled to the nose landing gear bay 106 about a first pivot axis 116. Specifically, the front strut 110 is pivotably coupled to the side panels 107 and 109 of the nose landing gear bay 106 at the first pivot axis 116. The nose landing gear assembly 108 also includes a rear strut 118 having a rear strut first end 120 and a rear strut second end 124. The rear strut first end 120 is coupled to the nose landing gear bay 106 about a second pivot axis 122. Specifically, the rear strut 118 is pivotably coupled to the side panels 107 and 109 of the nose landing gear bay 106 at the second pivot axis 122. As Figure 5 As best shown, the first pivot axis 116 is positioned higher within the nose landing gear bay 106 than the second pivot axis 122, such that the first and second pivot axes 116 and 122 are vertically offset by a distance Di between about 1.50 inches and about 3.50 inches. More specifically, the first and second pivot axes 116 and 122 are vertically offset by a distance Di of about 2.50 inches. This relatively small offset distance enables the nose landing gear assembly 108 to be folded into a relatively small volume of the nose landing gear bay 106.

[0040] In the exemplary embodiment, the nose landing gear assembly 108 also includes an actuator 126 having an actuator first end 128 and an actuator second end 130. More specifically, the actuator includes an outer cylinder 132 having the second end 130 and an inner cylinder 134 having the first end 128. The inner cylinder 134 is telescopically coupled to the outer cylinder 132 to increase / decrease the distance between the ends 128 and 130. The actuator first end 128 is coupled to the forward brace 110 and the actuator second end 130 is coupled to the nose landing gear bay 106. As described herein, the actuator 126 is configured to selectively move the nose landing gear assembly 108 between a retracted position (contained) and an extended position (contained).

[0041] As Figure 3 and Figure 5 As best shown, the nose landing gear assembly 108 also includes a hydraulic strut 136 pivotably coupled to the rear brace second end 124. A shock strut 138 is telescopically coupled to the hydraulic strut 136 and a wheel assembly 140 is coupled to a distal end 142 of the shock strut 138. The shock strut 138 is configured to retract into the hydraulic strut 136 when the nose landing gear assembly 108 is in the retracted configuration. Additionally, the shock strut 138 is configured to extend from the hydraulic strut 136 when the nose landing gear assembly 108 is in the extended configuration.

[0042] In the exemplary embodiment, a pair of lower links 144 are coupled between the hydraulic strut 136 and the forward brace 110. More specifically, the lower links 144 include a lower link first end 146 pivotably coupled to the hydraulic strut 136 and a lower link second end 148 pivotably coupled to the forward brace second end 144. The lower links 144 enable the nose landing gear assembly 108 to collapse into a smaller volume to fit within the available volume of the nose landing gear bay 106.

[0043] As Figure 4 and Figure 5As best shown, the front brace 110 includes a front brace first leg 150, a front brace second leg 152, and a front brace crossbeam 154 coupled to and extending between the legs 150 and 152. In the example embodiment, the legs 150 and 152 are obliquely oriented relative to one another such that the width of the front brace 110 tapers from the front brace first end 112 to the front brace second end 114. The front brace crossbeam 154 is positioned approximately midway between the front brace first end 112 and the front brace second end 114, and the actuator first end 128 is coupled to the front brace crossbeam 154. In operation, the actuator 126 pulls the front brace 110 to facilitate the nose landing gear assembly 108 transitioning from the extended position to the retracted position. Specifically, the actuator 126 pulls the front brace crossbeam 154 to cause the front brace second end 114 to move toward the actuator second end 130.

[0044] Similarly, in the example embodiment, the rear brace 118 includes a rear brace first leg 156, a rear brace second leg 158, and a rear brace crossbeam 160 coupled to and extending between the legs 156 and 158. In the example embodiment, the legs 156 and 158 are obliquely oriented relative to one another such that the width of the rear brace 118 tapers from the rear brace first end 120 to the rear brace second end 124. The rear brace crossbeam 160 is positioned approximately midway between the brace first end 120 and the rear brace second end. In this configuration, the actuator outer cylinder 132 extends between and is spaced apart from the first ends 120 of the rear brace first leg 156 and the rear brace second leg 158.

[0045] In the example embodiment, the nose landing gear assembly 108 also includes a pair of side links 162 coupled to and between the front brace 110 and the rear brace 118. Each side link 162 includes a side link first end 164 coupled to the front brace 110 and positioned between the front brace crossbeam 154 and the front brace second end 114. Each side link 162 also includes a side link second end 166 coupled to the rear brace 118 and positioned between the rear brace crossbeam 160 and the rear brace second end 124.

[0046] As Figure 3 and Figure 5As best shown, the front brace 110 is larger than the rear brace 118. More specifically, in the exemplary embodiment, the legs 150 and 152 of the front brace 110 are longer than the legs 156 and 158 of the rear brace 118. Additionally, the first ends 112 of the legs 150 and 152 of the front brace 110 are spaced apart a distance similar to the first ends 120 of the legs 156 and 158 of the rear brace 118. However, the second ends 124 of the legs 156 and 158 of the rear brace 118 are positioned closer to each other than the second ends 114 of the legs 150 and 152 of the front brace 110. However, the legs 150 and 152 of the rear brace 118 are more obliquely oriented relative to each other than the legs 150 and 152 of the front brace 110. As such, the legs 156 and 158 of the rear brace 118 are more obliquely oriented relative to each other than the legs 150 and 152 of the front brace 110. As shown, Figure 3 As shown, when the nose landing gear assembly 108 is in the extended position, the rear brace 118 is aligned with the hydraulic strut 136 and the shock strut 138, all of which are obliquely oriented relative to a vertical plane that is perpendicular to the ground surface. Additionally, in the extended position, the side link 162 is oriented substantially parallel to the outer cylinder 132 and the inner cylinder 134.

[0047] Figures 9A-9F is a perspective view of the nose landing gear assembly 108 moving from the extended position to the retracted position. In the exemplary embodiment, the inner cylinder 134 of the actuator 126 is retracted into the outer cylinder 132, which causes the first end 112 of the front brace 110 to pivot about the first pivot axis 116 and move the second end 114 of the front brace 110 rearward and upward toward the nose landing gear bay 106. As the second end 114 of the front brace 110 moves rearward, the side link 162 also pushes the second end 124 of the rear brace 118 rearward and upward. Additionally, as the second end 114 of the front brace 110 moves rearward, the lower link 144 pivots relative to the front brace 110. Specifically, the second end 114 of the front brace 110 pushes the second end 148 of the lower link 144 rearward. Additionally, as the second end 124 of the rear brace 118 moves rearward, the top end of the hydraulic strut 136 pivots relative to the second end 124, and the lower link 144 begins to raise the hydraulic strut 136, the shock strut 138, and the wheel 140 toward the nose landing gear bay 106.

[0048] Figure 10 is a side view of the nose landing gear assembly 108 in the retracted position, Figure 11 is a perspective view of the nose landing gear assembly 108 in the retracted position, and Figure 12 is a front view of the nose landing gear assembly 108 in the retracted position. Figure 13is a rear view of the nose landing gear assembly 108 in the retracted position, Figure 14 is a top view of the nose landing gear assembly 108 in the retracted position, and Figure 15 is a bottom view of the nose landing gear assembly 108 in the retracted position.

[0049] As Figure 10 best shown, when the nose landing gear assembly 108 is in the retracted position, the first end 120 of the rear brace 118, the first end 164 of the side link 162, and the first end 146 of the lower link 144 are all substantially vertically aligned. Further, when in the retracted position, the front brace 110, the rear brace 118, the hydraulic strut 136, the actuator 126, the side link 162, and the lower link 144 at least partially overlap in the vertical direction. Additionally, in the retracted position, the actuator 126 is substantially horizontal.

[0050] In an exemplary embodiment, the nose landing gear assembly 108 defines a first vertical height H1 (as shown in Figure 3 ) of between about 80.0 inches (inclusive) and about 84.0 inches (inclusive) in the extended position. Specifically, in one embodiment, the nose landing gear assembly 108 defines a first vertical height H1 of about 80.0 inches in the extended position. Similarly, the nose landing gear assembly 108 defines a second vertical height H2 (as shown in Figure 10 ) of between about 28.0 inches (inclusive) and about 32.0 inches (inclusive) in the retracted position. Specifically, in one embodiment, the nose landing gear assembly 108 defines a first second vertical height H2 of about 30.0 inches in the extended position. As such, the first vertical height H1 is greater than the second vertical height H2. Specifically, in one exemplary embodiment, the second vertical height H2 is between about 34% (inclusive) to about 38% (inclusive) of the first vertical height H1. More specifically, the second vertical height H2 is about 36.5% of the first vertical height H1. The relatively smaller compressed height of the nose landing gear assembly 108 in the retracted position as compared to the nose landing gear assembly 108 in the extended position allows the nose landing assembly 108 to fit within a smaller volume of the nose landing gear bay 106 to allow for the maximum amount of cargo volume in the aircraft 100

[0051] Similarly, as Figure 3As best shown, when the nose landing gear assembly 108 is in the extended position, the first pivot axis 116 is positioned at a third height H3, which is between approximately 75.0 inches (inclusive) and approximately 81.0 inches (inclusive) above the ground. More specifically, in one embodiment, the first pivot axis 116 is positioned at a third height H3 of approximately 78.0 inches above the ground. The relatively small ground clearance between the first pivot axis 116 and the ground allows for a larger cargo compartment 102.

[0052] In addition, such as Figure 1 As shown, the landing gear bay includes a front end 103 and a rear end 105. In one embodiment, the front end 103 includes a height H4 between approximately 33.0 inches (inclusive) and approximately 36.0 inches (inclusive). More specifically, the front end 103 includes a height H4 of approximately 34.5 inches. Similarly, the rear end 105 includes a height H5 between approximately 36.0 inches (inclusive) and approximately 40.0 inches (inclusive). More specifically, the rear end 105 includes a height H5 of approximately 38.0 inches. In such a configuration, the nose landing gear bay 106 includes a volume between 70,000 cubic inches (inclusive) and approximately 75,000 cubic inches (inclusive). More specifically, in one embodiment, the nose landing gear bay 106 includes a volume of approximately 72,626 cubic inches. The relatively small volume of the nose landing gear bay 106 requires the nose landing gear assembly 108 to be fully folded for mounting within the nose landing gear bay 106. As described herein, the aircraft 100 provides a limited volume below the cargo hold floor 104 to store the nose landing gear assembly 108, thereby allowing for a large cargo hold 102.

[0053] The embodiments described herein relate to nose-mounted landing gear for an aircraft, and more specifically to a compact nose-mounted landing gear housed in a reduced-volume cabin. More specifically, in an exemplary embodiment, the nose-mounted landing gear assembly includes a hydraulic strut, a front support including a first end and a second end of a front support. The first end of the front support is pivotally coupled about a first pivot axis to a nose landing gear bay of a high-wing aircraft. The nose-mounted landing gear assembly also includes a rear support having a first end and a second end of a rear support. The first end of the rear support is pivotally coupled about a second pivot axis to the nose landing gear bay, and the second end of the rear support is pivotally coupled to the hydraulic strut. An actuator includes a first end and a second end of an actuator. The second end of the actuator is coupled to the nose landing gear bay, and the first end of the actuator is coupled to the front support. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

[0054] The assemblies and methods described herein facilitate folding the nose landing gear assembly into a more compact configuration to allow storage in a reduced volume nose landing gear bay. Generally, the nose landing gear assemblies described herein are used for cargo aircraft that do not have a passenger cabin and an enlarged cargo bay. In such aircraft, the cargo bay floor is positioned as close to the bottom of the aircraft as possible to enable the maximum amount of cargo to be stored. As such, the available volume for storing the nose landing gear assembly is reduced. The nose landing gear assemblies described herein allow the retracted configuration to occupy only a small percentage of the space required when in the extended configuration, and thus can be stored in a relatively small nose landing gear bay volume. As a result, the cargo bay is made larger than the cargo bays of known cargo aircraft to enable a larger volume of cargo to be transported.

[0055] The systems and methods described herein are not limited to the particular embodiments described herein, but, rather, components of systems and / or steps of methods can be utilized independently and separately from other components and / or steps described herein.

[0056] While certain specific features of the various examples are illustrated, described and / or claimed in the drawings, it will be appreciated that the features are not limited to the specific examples illustrated and / or described and can be employed independently and separately from other features described and / or claimed herein. For example, an example feature can be implemented or claimed in one example independently of any other examples or features, or used in any other example.

[0057] As used herein, recitation of "a" or "an" can be understood to mean one or more than one and recitation of "an embodiment" or "one embodiment" is not intended to be interpreted as excluding additional embodiments that incorporate features of the embodiment or example. Any embodiment or example that is described herein can be combined with any other embodiment or example, or used in any other example.

[0058] Further, the present disclosure includes embodiments according to the following clauses:

[0059] Clause 1. A nose landing gear assembly 108 for a high wing aircraft 100 defining a nose landing gear bay 106, the nose landing gear assembly 108 comprising:

[0060] a hydraulic strut 136;

[0061] a forward brace 110 comprising a forward brace first end 112 and a forward brace second end 114, the forward brace first end 112 being pivotably coupled to the nose landing gear bay 106 about a first pivot axis 116;

[0062] a rear brace 118 comprising a rear brace first end 120 and a rear brace second end 124, the rear brace first end 120 being pivotably coupled to the nose landing gear bay 106 about a second pivot axis 122 and the rear brace second end 124 being pivotably coupled to the hydraulic strut 136; and

[0063] an actuator 126 including an actuator first end 128 and an actuator second end 130, the actuator second end 130 coupled to the nose landing gear bay 106 and the actuator first end 128 coupled to the front brace 110, wherein the actuator 126 is configured to selectively move the nose landing gear assembly 108 between a retracted position (inclusive of) and an extended position (inclusive of).

[0064] Clause 2. The nose landing gear assembly 108 of Clause 1, wherein the front brace includes a front brace first leg 150, a front brace second leg 152, and a front brace crossbeam 154 extending therebetween, wherein the actuator first end 128 is coupled to the front brace crossbeam 154.

[0065] Clause 3. The nose landing gear assembly 108 of Clause 2, wherein the front brace second leg 152 is obliquely oriented relative to the front brace first leg 150.

[0066] Clause 4. The nose landing gear assembly 108 of Clause 2, wherein the front brace crossbeam 154 is positioned at about mid-way between the front brace first end 112 and the front brace second end 114.

[0067] Clause 5. The nose landing gear assembly 108 of Clause 2, wherein the rear brace 118 includes a rear brace first leg 156, a rear brace second leg 158, and a rear brace crossbeam 160 extending therebetween.

[0068] Clause 6. The nose landing gear assembly 108 of Clause 5, further comprising a pair of side links 162 coupled between the front brace 110 and the rear brace 118.

[0069] Clause 7. The nose landing gear assembly 108 of Clause 6, wherein each side link 162 of the pair of side links includes a side link first end 162 coupled to the front brace 114 between the front brace crossbeam 154 and the front brace second end 114, and wherein each side link 162 of the pair of side links includes a side link second end 166 coupled to the rear brace 118 between the rear brace crossbeam 160 and the rear brace second end 124.

[0070] Clause 8. The nose landing gear assembly 108 of Clause 5, wherein the actuator 126 extends between the rear brace first leg 156 and the rear brace second leg 158.

[0071] Clause 9. The nose landing gear assembly 108 of clause 1, wherein the first pivot axis 116 and the second pivot axis 122 are vertically offset by a distance of approximately 1.50 inches and 3.50 inches.

[0072] Clause 10. The nose landing gear assembly 108 of clause 1, wherein the nose landing gear assembly 108 defines a first vertical height in the extended position and a second vertical height in the retracted position, wherein the second vertical height is approximately 34% to 38% of the first vertical height.

[0073] Clause 11. An aircraft 100, comprising:

[0074] a cargo bay 102 comprising a cargo bay floor 104;

[0075] a nose landing gear compartment 106 positioned below the cargo bay floor 104; and

[0076] a nose landing gear assembly 108 selectively positioned within the nose landing gear compartment 106, the nose landing gear assembly 108 comprising:

[0077] a hydraulic strut 136;

[0078] a front leg 110 comprising a front leg first end 112 and a front leg second end 114, the front leg first end 112 pivotably coupled to the nose landing gear compartment 106 about a first pivot axis 116.

[0079] a rear leg 118 comprising a rear leg first end 120 and a rear leg second end 124, the rear leg first end 120 pivotably coupled to the nose landing gear compartment 106 about a second pivot axis 122 and the rear leg second end 124 pivotably coupled to the hydraulic strut 136; and

[0080] an actuator 126 comprising an actuator first end 128 and an actuator second end 130, the actuator second end 130 coupled to the nose landing gear compartment 106 and the actuator first end 128 coupled to the front leg 110, wherein the actuator 126 is configured to selectively move the nose landing gear assembly 106 between a retracted position and an extended position.

[0081] Clause 12. The aircraft 100 of clause 11, wherein the front leg 110 comprises a front leg width that gradually increases from the front leg first end 112 to the front leg second end 114, and wherein the rear leg 118 comprises a rear leg width that gradually increases from the rear leg first end 120 to the rear leg second end 124.

[0082] Clause 13. The aircraft 100 of clause 11, wherein the front brace 110, the rear brace 118, the hydraulic strut 136, and the actuator 126 at least partially overlap in a vertical direction when in the retracted position.

[0083] Clause 14. The aircraft 100 of clause 11, wherein the first pivot axis 116 is positioned 75.0 inches to 81.0 inches above a ground surface when the nose landing gear assembly 108 is in the extended position.

[0084] Clause 15. The aircraft 100 of clause 11, wherein the nose landing gear bay 106 comprises a height of 33.0 inches to 36.0 inches.

[0085] Clause 16. The aircraft 100 of clause 11, wherein the nose landing gear assembly 108 defines a first vertical height in the extended position and a second vertical height in the retracted position, wherein the second vertical height is approximately 34% to 38% of the first vertical height.

[0086] Clause 17. The aircraft 100 of clause 11, wherein:

[0087] the front brace 110 comprises a front brace first leg 150, a front brace second leg 152, and a front brace crossbeam 154 extending therebetween, wherein the first end 128 of the actuator is coupled to the front brace crossbeam 154; and

[0088] wherein the rear brace 118 comprises a rear brace first leg 156, a rear brace second leg 158, and a rear brace crossbeam 160 extending therebetween.

[0089] Clause 18. The aircraft 100 of clause 11, further comprising a pair of side links 162 coupled between the front brace 110 and the rear brace 118.

[0090] Clause 19. A method of assembling a nose landing gear assembly 108 for a high-wing aircraft 100 defining a nose landing gear bay 106, wherein the nose landing gear assembly 108 comprises a hydraulic strut 136, a front brace 110, a rear brace 118, and an actuator 126, the method comprising:

[0091] pivotably coupling a first end 112 of the front brace 110 to the nose landing gear bay 106 about a first pivot axis 116;

[0092] pivotably coupling a first end 120 of the rear brace 118 to the nose landing gear bay 106 about a second pivot axis 122;

[0093] pivotably coupling a second end 124 of the rear brace 118 to the hydraulic strut 136;

[0094] a first end 128 of the actuator 126 is coupled to the nose landing gear bay 106; and

[0095] a second end 130 of the actuator 126 is coupled to the front support 110, wherein the actuator 126 is configured to selectively move the nose landing gear assembly 108 between a retracted position (inclusive) and a deployed position (inclusive).

[0096] Clause 20. The method of clause 19, further comprising:

[0097] a pair of side links 162 are coupled between the front support 110 and the rear support 118; and

[0098] a pair of lower links 144 are coupled between the second end 114 of the front support 110 and the hydraulic strut 136.

[0099] LULIT - Annotated claims from 19-0896-US-NP [2] (Thanks for the description):

[0100] 1. A folding assembly 100 movable between a compressed configuration 138 and a deployed configuration 136, the folding assembly 100 comprising:

[0101] a first rotary link 102 comprising a first end 104 and a second end 106, wherein the first end 104 is pivotably coupled to a structural element / frame 114;

[0102] a second rotary link 108 comprising a first end 110 and a second end 112, wherein the second rotary link first end 110 is pivotably coupled to the structural element / frame 114;

[0103] a first connecting link 116 pivotably coupled between the first rotary link 102 and the second rotary link 108;

[0104] a second connecting link 122 comprising a first end 124 and a second end 134, wherein the second connecting link first end 124 is pivotably coupled to the first rotary link second end 106; and

[0105] a support link 126 comprising a first end 128 and a second end 130, wherein the first end 126 is pivotably coupled to the first rotary link second end 106, and the support link second end 130 is configured to be coupled to a component 132 to be moved, wherein the support link 126 is configured to selectively move the component 132 between a compressed position 20 (inclusive) and a deployed position 12 (inclusive).

[0106] 2. The folding assembly 100 according to claim 1, wherein the first rotating link 102 is parallel to the first connecting link 116 in the extended configuration 136.

[0107] 3. The folding assembly 100 according to claim 1, wherein the second rotating link 108 is parallel to the support link 126 in the extension configuration 136.

[0108] 4. The folding assembly 100 according to claim 1, wherein the first connecting link 116 is oriented obliquely relative to at least one of the first rotating link 102 and the second rotating link 108 in the extended configuration 136.

[0109] 5. The folding assembly 100 according to claim 1, wherein the second end 134 of the second connecting link is coupled to the support link 126 at approximately the midpoint 140 of the support link 126.

[0110] 6. The folding assembly 100 according to claim 1, wherein the second end 120 of the first connecting link is closer to the coupling of the second rotating link 108 to the second end 112 of the second rotating link than the first end 110 of the second rotating link.

[0111] 7. The folding assembly 100 according to claim 1, wherein the first end 118 of the first connecting link is coupled to the first rotating link 102 at the first pivot point 142, and is closer to the second end 106 of the first rotating link than the first end 104 of the first rotating link.

[0112] 8. The folding assembly 100 of claim 7, wherein a first distance is defined between the first end 124 and the second end 134 of the second connecting link, and wherein a second distance is defined between the second end 106 of the first rotating link and the first pivot point 142, wherein the first distance is substantially similar to the second distance.

[0113] 9. The folding assembly 100 of claim 7, wherein the first end 104 of the first rotating link and the first end 110 of the second rotating link define a third distance therebetween.

[0114] 10. The folding assembly 100 of claim 9, wherein the fourth distance defined between the first end 104 of the first rotating link and the first pivot point 142 is substantially similar to the third distance.

[0115] 11. The folding assembly 100 of claim 10, wherein the fifth distance defined between the first end 110 of the second rotating link and the first pivot point 142 is substantially similar to the third and fourth distances.

[0116] 12. The folding assembly 100 of claim 11, wherein the sixth distance defined between the first pivot point 142 and the second end 134 of the second connecting link is substantially similar to the third distance, the fourth distance, and the fifth distance.

[0117] 13. The folding assembly 100 of claim 1, wherein the first end 110 and the second end 112 of the second rotating link define a distance substantially similar to the distance defined between the first end 128 of the support link and the midpoint 140 of the support link.

[0118] 14. A method of assembling a foldable assembly 100 movable between a compression configuration 138 and an extension configuration 136, the method comprising:

[0119] The first end 104 of the first rotating link 102 is pivotally coupled to the structural element / frame 114;

[0120] The first end 110 of the second rotating link 108 is pivotally coupled to the structural member / frame 114;

[0121] The first connecting rod 116 is pivotally coupled between the first rotary connector 102 and the second rotary connector 108;

[0122] The first end 124 of the second connecting rod 122 is pivotally coupled to the second end 106 of the first rotating connecting rod;

[0123] The first end 128 of the support link 126 is pivotally coupled to the second end 112 of the second rotating link; and

[0124] The second end 134 of the second connecting link is pivotally coupled to the support link 126, wherein the second end 130 of the support link is configured to be coupled to the movable component 132, such that the support link 126 is configured to selectively move the component 132 between a retracted position 20 (inclusive) and an extended position 12 (inclusive).

[0125] 15. The method of claim 14, wherein the first rotating link 102 is parallel to the first connecting link 116 in the extension configuration 136, and wherein the second rotating link 108 is parallel to the supporting link 126 in the extension configuration 136.

[0126] 16. The method of claim 14, wherein the second end 134 of the second connecting rod is coupled to the support rod 126 at approximately the midpoint 140 of the support rod 126.

[0127] 17. The method of claim 14, wherein the second end 120 of the first connecting link is closer to the coupling of the second rotating link 108 to the second end 112 of the second rotating link than the first end 110 of the second rotating link, and wherein the first end 118 of the first connecting link is coupled to the first rotating link 102 at a first pivot point 142, the first pivot point 142 being closer to the second end 106 of the first rotating link than the first end 104 of the first rotating link.

[0128] 18. The method of claim 17, wherein a first distance is defined between the first end 124 of the second connecting link and the second end 134 of the second connecting link, and wherein a second distance is defined between the second end 106 of the first rotating link and the first pivot point 142, wherein the first distance is substantially similar to the second distance.

[0129] 19. The method of claim 17, wherein the first end 104 of the first rotating link and the first end 110 of the second rotating link define a third distance therebetween;

[0130] A fourth distance is defined between the first end 104 of the first rotating link and the first pivot point 142;

[0131] A fifth distance is defined between the first end 110 of the second rotating link and the first pivot point 142; and

[0132] A sixth distance is defined between the first pivot point 142 and the second end 134 of the second connecting rod, and the third, fourth, fifth and sixth distances are substantially similar to each other.

[0133] 20. The method of claim 14, wherein the first end 110 and the second end 112 of the second rotating link define a distance substantially similar to the distance defined between the first end 128 of the support link and the midpoint 140 of the support link 126.

[0134] This written description discloses the invention using examples including the best mode and also enables any person skilled in the art to practice the invention, including making and using any device or system and performing any combined methods. The patentable scope of the invention is defined by the claims and may include other examples that would occur to a person skilled in the art. Such other examples are intended to be included within the scope of the claims if they have structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A nose landing gear assembly (108) for a high-wing aircraft (100), the high-wing aircraft defining a nose gear bay (106), the nose landing gear assembly (108) comprising: a hydraulic strut (136); a front strut (110) comprising a front strut first end (112) and a front strut second end (114), the front strut first end (112) pivotably coupled to the nose gear bay (106) about a first pivot axis (116), wherein the front strut comprises a front strut first leg (150), a front strut second leg (152), and a front strut crossbeam (154) extending therebetween; a rear strut (118) comprising a rear strut first end (120) and a rear strut second end (124), the rear strut first end (120) pivotably coupled to the nose gear bay (106) about a second pivot axis (122), and the rear strut second end (124) pivotably coupled to the hydraulic strut (136), wherein the rear strut (118) comprises a rear strut first leg (156), a rear strut second leg (158), and a rear strut crossbeam (160) extending therebetween; a pair of side links (162) coupled between the front strut (110) and the rear strut (118); wherein each side link (162) of the pair of side links comprises a side link first end (162) coupled to the front strut (110) between the front strut crossbeam (154) and the front strut second end (114), and wherein each side link (162) of the pair of side links comprises a side link second end (166) coupled to the rear strut (118) between the rear strut crossbeam (160) and the rear strut second end (124); and an actuator (126) comprising an actuator first end (128) and an actuator second end (130), the actuator second end (130) coupled to the nose gear bay (106) and the actuator first end (128) coupled to the front strut (110), wherein the actuator (126) is configured to selectively move the nose landing gear assembly (108) between a retracted position and an extended position, the retracted position and the extended position comprising.

2. The nose landing gear assembly (108) of claim 1, wherein the actuator first end (128) is coupled to the front strut crossbeam (154).

3. The nose landing gear assembly (108) of claim 2, wherein the front strut second leg (152) is obliquely oriented relative to the front strut first leg (150).

4. The nose landing gear assembly (108) of claim 2, wherein the front strut crossbeam (154) is positioned at about a mid-way location between the front strut first end (112) and the front strut second end (114).

5. The nose landing gear assembly (108) of any of claims 2-4, wherein the actuator (126) extends between the rear cradle first leg (156) and the rear cradle second leg (158).

6. The nose landing gear assembly (108) of claim 1, wherein the first pivot axis (116) and the second pivot axis (122) are vertically offset by a distance between 1.50 inches and 3.50 inches.

7. The nose landing gear assembly (108) of claim 1, wherein the nose landing gear assembly (108) defines a first vertical height in the extended position and a second vertical height in the retracted position, wherein the second vertical height is 34-38% of the first vertical height.

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