Nose landing gear assembly used in aircraft

Abstract

To provide a nose landing device assembly used in a high blade machine for defining a nose device bay.SOLUTION: A nose landing device assembly includes an oleo-shock strut, and a front brace including a first end of a front brace and a second end of the front brace. The first end of the front brace is turnably coupled to a nose device bay around a first turning shaft. The assembly also includes a rear base including a first end of the rear brace and a second end of the rear brace. The first end is turnably coupled to the nose device bay around a second turning shaft, and the second end is turnably coupled to the oleo-shock strut. The actuator includes a first end of the actuator and a second end of the actuator. The second end is coupled to the nose device bay, and the first end is coupled to the front brace. The actuator is configured to move the nose landing device assembly between a retreat position and an extension position.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The field of the disclosure relates generally to nose-mounted landing gear for aircraft, and more particularly to compact nose-mounted landing gear housed within a reduced volume equipment bay. [Background technology]

[0002] Currently known nose landing gear and their stowage mechanism configurations are highly sophisticated based on the type of aircraft and function efficiently under multiple operating conditions, such as taxiing, braking, takeoff / landing, and retracting / extending. Commercial aircraft generally include a passenger area and a luggage area below the passenger area. The luggage area of ​​some known aircraft also includes a landing gear bay that stores the landing gear during flight. However, in aircraft used for cargo-only transportation, the cargo area floor is located as close to the bottom of the aircraft as possible to maximize cargo storage. In such a configuration, the volume available for landing gear storage is reduced, and the volume of the cargo area is limited by the amount of space required to store the landing gear during flight.

[0003] This section is intended to introduce the reader to various aspects of technology that may be related to various aspects of the present disclosure, as 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 discussions are to be read in this light, and not as admissions of prior art. Summary of the Invention

[0004] In one aspect, a nose landing gear assembly for use on a high wing aircraft is provided, the nose landing gear assembly defining a nose gear bay. The nose landing gear assembly includes an oleo strut and a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotally coupled to the nose gear bay 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 pivotally coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotally coupled to the oleo shock 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 forward brace. The actuator is configured to selectively move the nose landing gear assembly between, inclusive of, a retracted position and an extended position.

[0005] In another aspect, an aircraft is provided. The aircraft includes a cargo bay including a cargo bay floor, a nose gear bay disposed below the cargo bay floor, and a nose landing gear assembly selectively disposed within the nose gear bay. The nose landing gear assembly includes an oleo shock strut and a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotally coupled to the nose gear bay 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 pivotally coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotally coupled to the oleo shock 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 forward brace. The actuator is configured to selectively move the nose landing gear assembly between, inclusive of, a retracted position and an extended position.

[0006] In yet another aspect, a method of assembling a nose gear assembly for use on a high-wing aircraft is provided. The high-wing aircraft defines a nose gear bay, where the nose gear assembly includes an oleo shock strut, a forward brace, an aft brace, and an actuator. The method includes pivotally coupling a first end of the forward brace to the nose gear bay about a first pivot axis and pivotally coupling a first end of the aft brace to the nose gear bay about a second pivot axis. The method also includes pivotally coupling a second end of the aft brace to the oleo shock strut, coupling a first end of an actuator to the nose 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, inclusive of, a retracted position and an extended position. [Brief explanation of the drawings]

[0007] [Figure 1]FIG. 1 is a schematic diagram of an exemplary aircraft having an exemplary nose landing gear assembly. [Figure 2] FIG. 2 is a schematic diagram of the nose landing gear assembly shown in FIG. 1 within an equipment bay of an exemplary aircraft. [Figure 3] FIG. 3 is a side view of the nose landing gear assembly shown in FIG. 2 in an extended position. [Figure 4] FIG. 3 is a perspective view of the nose landing gear assembly shown in FIG. 2 in an extended position. [Figure 5] FIG. 3 is a front view of the nose landing gear assembly shown in FIG. 2 in an extended position. [Figure 6] FIG. 3 is a rear view of the nose landing gear assembly shown in FIG. 2 in an extended position. [Figure 7] FIG. 3 is a top view of the nose landing gear assembly shown in FIG. 2 in an extended position. [Figure 8] FIG. 3 is an underside view of the nose landing gear assembly shown in FIG. 2 in the extended position. [Figure 9A] 9A-9F are perspective views of the nose landing gear assembly shown in FIG. 2 moving from an extended position to a retracted position. [Figure 9B] 9A-9F are perspective views of the nose landing gear assembly shown in FIG. 2 moving from an extended position to a retracted position. [Figure 9C] 9A-9F are perspective views of the nose landing gear assembly shown in FIG. 2 moving from an extended position to a retracted position. [Figure 9D] 9A-9F are perspective views of the nose landing gear assembly shown in FIG. 2 moving from an extended position to a retracted position. [Figure 9E] 9A-9F are perspective views of the nose landing gear assembly shown in FIG. 2 moving from an extended position to a retracted position. [Figure 9F] 9A-9F are perspective views of the nose landing gear assembly shown in FIG. 2 moving from an extended position to a retracted position. [Figure 10] FIG. 3 is a side view of the nose landing gear assembly shown in FIG. 2 in a retracted position. [Figure 11] FIG. 3 is a perspective view of the nose landing gear assembly shown in FIG. 2 in a retracted position. [Figure 12] FIG. 3 is a front view of the nose landing gear assembly shown in FIG. 2 in a retracted position. [Figure 13] FIG. 3 is a rear view of the nose landing gear assembly shown in FIG. 2 in a retracted position. [Figure 14] FIG. 3 is a top view of the nose landing gear assembly shown in FIG. 2 in a retracted position. [Figure 15] FIG. 3 is an underside view of the nose landing gear assembly shown in FIG. 2 in a retracted position. [Figure 16] FIG. 1 is a front perspective view of an exemplary nose landing gear assembly in an extended position. [Figure 17] 17 is a right side view of the nose landing gear assembly shown in FIG. 16 in the extended position. The left side view is a mirror image of the right side view. [Figure 18] FIG. 17 is a front view of the nose landing gear assembly shown in FIG. 16 in the extended position. [Figure 19] FIG. 17 is a rear view of the nose landing gear assembly shown in FIG. 16 in the extended position. [Figure 20] FIG. 17 is a top view of the nose landing gear assembly shown in FIG. 16 in the extended position. [Figure 21] FIG. 17 is an underside view of the nose landing gear assembly shown in FIG. 16 in the extended position. [Figure 22] FIG. 17 is a front perspective view of the nose landing gear assembly shown in FIG. 16 in a retracted position. [Figure 23] 17 is a right side view of the nose landing gear assembly shown in FIG. 16 in a retracted position. The left side view is a mirror image of the right side view. [Figure 24] FIG. 17 is a front view of the nose landing gear assembly shown in FIG. 16 in a retracted position. [Figure 25] FIG. 17 is a rear view of the nose landing gear assembly shown in FIG. 16 in a retracted position. [Figure 26] FIG. 17 is a top view of the nose landing gear assembly shown in FIG. 16 in a retracted position. [Figure 27] FIG. 17 is an underside view of the nose landing gear assembly shown in FIG. 16 in a retracted position. DETAILED DESCRIPTION OF THE INVENTION

[0008] Corresponding reference characters indicate corresponding parts throughout the several views. While specific features of various embodiments may be shown in some drawings and not in others, this is for convenience only. Any feature of any drawing may be referenced and / or claimed in combination with any feature of any other drawing.

[0009] Embodiments described herein relate to nose-mounted landing gear for aircraft, and more particularly, to a compact nose-mounted landing gear that can be housed within a reduced-volume gear bay. More specifically, in an exemplary embodiment, a nose-mounted landing gear assembly includes an oleo shock strut and a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotally coupled to a nose gear bay of a high-wing aircraft about a first pivot axis. The nose-mounted 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 pivotally coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotally coupled to the oleo shock 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 forward brace. The actuator is configured to move the nose landing gear assembly between, inclusive of, a retracted position and an extended position.

[0010] The assemblies and methods described herein facilitate packing the nose gear assembly into a more compact configuration to enable storage in a reduced-volume nose gear bay. Generally, the nose gear assemblies described herein are used on cargo aircraft without passenger compartments and with enlarged cargo bays. In such aircraft, the cargo bay floor is located as close to the bottom of the aircraft as possible to maximize cargo storage. Therefore, the volume available for storage of the nose landing gear assembly is reduced. The nose landing gear assemblies described herein enable a retracted configuration that occupies only a small percentage of the space required when in an extended configuration, and therefore can be stored in a relatively small nose gear bay space. As a result, the cargo bay is made larger than known cargo aircraft to enable the transport of a greater amount of cargo.

[0011] FIG. 1 is a schematic illustration of aircraft 100. In the exemplary embodiment, aircraft 100 is a high-wing cargo aircraft including cargo bay 102 and cargo bay floor 104. Additionally, nose gear bay 106 is disposed below cargo bay floor 104 and selectively houses nose gear assembly 108 therein. FIG. 2 is a schematic illustration of nose landing gear assembly 108 disposed within nose gear bay 106. The configuration of aircraft 100 provides limited space below cargo bay floor 104 to house nose gear assembly 108. As described herein, nose gear assembly 108 includes a folding mechanism that allows support trunnions to be positioned relatively close to one another, thus allowing for a relatively compact nose gear bay 106. 2, nose gear bay 106 includes a first side panel 107, a second side panel 109, a forward panel 111 extending between side panels 107 and 109, and an aft panel 113 extending between side panels 107 and 109. Panels 107, 109, 111, and 113 define an interior space in which nose gear assembly 108 is stored during flight.

[0012] Figure 3 is a side view of nose landing gear assembly 108 in the extended position, Figure 4 is a perspective view of nose landing gear assembly 108 in the extended position, Figure 5 is a front view of nose landing gear assembly 108 in the extended position, Figure 6 is a rear view of nose landing gear assembly 108 in the extended position, Figure 7 is a top view of nose landing gear assembly 108 in the extended position, and Figure 8 is a bottom view of nose landing gear assembly 108 in the extended position.

[0013] In the exemplary embodiment, nose device assembly 108 includes a forward brace 110 having a forward brace first end 112 and a forward brace second end 114. Forward brace first end 112 is coupled to nose device bay 106 about a first pivot axis 116. Specifically, forward brace 110 is pivotally coupled to side panels 107 and 109 of nose device bay 106 about first pivot axis 116. Nose device assembly 108 also includes an aft brace 118 having an aft brace first end 120 and an aft brace second end 124. Aft brace first end 120 is coupled to nose device bay 106 about a second pivot axis 122. Specifically, aft brace 118 is pivotally coupled to side panels 107 and 109 of nose gear bay 106 at second pivot axis 122. As best shown in FIG. 5 , first pivot axis 116 is positioned higher within nose gear bay 106 than second pivot axis 122, such that first pivot axis 116 and second pivot axis 122 are vertically offset by a distance D1 between about 1.50 inches and about 3.50 inches. More specifically, first pivot axis 116 and second pivot axis 122 are vertically offset by a distance D1 of about 2.50 inches. Such a relatively small offset distance allows nose gear assembly 108 to be accommodated within a smaller space within nose gear bay 106.

[0014] In the exemplary embodiment, nose 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 second end 130 and an inner cylinder 134 having first end 128. Inner cylinder 134 is telescopically coupled to outer cylinder 132 to increase / decrease the distance between ends 128 and 130. Actuator first end 128 is coupled to forward brace 110, and actuator second end 130 is coupled to nose gear bay 106. As described herein, actuator 126 is configured to selectively move nose landing gear assembly 108 between, inclusive, a retracted position and an extended position.

[0015] 3 and 5, nose device assembly 108 also includes an oleo shock strut 136 pivotally coupled to aft brace second end 124. An impact strut 138 is telescopically coupled to oleo shock strut 136, and a wheel assembly 140 is coupled to a distal end 142 of impact strut 138. Impact strut 138 is configured to retract into oleo shock strut 136 when nose device assembly 108 is in the retracted configuration. Additionally, impact strut 138 is configured to extend from oleo shock strut 136 when nose device assembly 108 is in the extended configuration.

[0016] In the exemplary embodiment, a pair of lower links 144 are coupled between oleo shock strut 136 and forward brace 110. More specifically, lower link 144 includes a lower link first end 146 pivotally coupled to oleo shock strut 136 and a lower link second end 148 pivotally coupled to forward brace second end 114. Lower links 144 allow nose device assembly 108 to fold into a small space to fit within the available space of nose device bay 106.

[0017] As best shown in FIGS. 4 and 5 , forward brace 110 includes a forward brace first leg 150, a forward brace second leg 152, and a forward brace cross beam 154 coupled to and extending between legs 150 and 152. In the exemplary embodiment, legs 150 and 152 are oriented at an angle relative to one another, thereby causing the width of forward brace 110 to taper from forward brace first end 112 to forward brace second end 114. Forward brace cross beam 154 is positioned approximately midway between forward brace first end 112 and forward brace second end 114, and actuator first end 128 is coupled to forward brace cross beam 154. In operation, actuator 126 pulls forward brace 110 to facilitate transitioning nose device assembly 108 from the extended position to the retracted position. Specifically, the actuator 126 pulls on the cross beam 154 of the forward brace, causing the second end 114 of the forward brace to move towards the second end 130 of the actuator.

[0018] Similarly, in the exemplary embodiment, aft brace 118 includes aft brace first leg 156, aft brace second leg 158, and aft brace cross beam 160 coupled to and extending between legs 156, 158. In the exemplary embodiment, legs 156, 158 are oriented at an angle relative to one another, such that aft brace 118 tapers in width from aft brace first end 120 to aft brace second end 124. Aft brace cross beam 160 is positioned approximately midway between aft brace first end 120 and aft brace second end 124. In such a configuration, the actuator outer cylinder 132 extends between the aft brace first leg 156 and the aft brace second leg 158 and is spaced from the first ends 120 of the aft brace first leg 156 and the aft brace second leg 158.

[0019] In the exemplary embodiment, nose device assembly 108 also includes a pair of side links 162 coupled between forward brace 110 and aft brace 118 and extending between forward brace 110 and aft brace 118. Each side link 162 includes a side link first end 164 coupled to forward brace 110 and disposed between forward brace cross beam 154 and forward brace second end 114. Each side link 162 also includes a side link second end 166 coupled to aft brace 118 and disposed between aft brace cross beam 160 and aft brace second end 124.

[0020] As best shown in FIGS. 3 and 5 , forward brace 110 is larger than aft brace 118. More specifically, in the exemplary embodiment, legs 150 and 152 of forward brace 110 are longer than legs 156 and 158 of aft brace 118. Furthermore, first ends 112 of legs 150 and 152 of forward brace 110 are spaced a similar distance apart as first ends 120 of legs 156 and 158 of aft brace 118. However, second ends 124 of legs 156 and 158 of aft brace 118 are positioned closer to each other than second ends 114 of legs 150 and 152 of forward brace 110. Thus, legs 156 and 158 of aft brace 118 are oriented at a steeper angle relative to each other than legs 150 and 152 of forward brace 110. 3, when the nose device assembly 108 is in the extended position, the aft brace 118 is aligned with the oleo shock strut 136 and the impact strut 138, all of which are oriented at an angle relative to a vertical plane perpendicular to the ground surface. Additionally, in the extended position, the side links 162 are oriented substantially parallel to the outer and inner cylinders 132, 134.

[0021] 9A-9F are perspective views of nose landing gear assembly 108 moving from an extended position to a retracted position. In the exemplary embodiment, inner cylinder 134 of actuator 126 retracts into outer cylinder 132, causing first end 112 of forward brace 110 to pivot about first pivot axis 116, moving second end 114 of forward brace 110 rearward and upward toward nose gear bay 106. As second end 114 of forward brace 110 moves rearward, side link 162 similarly pushes second end 124 of aft brace 118 rearward and upward. Additionally, as second end 114 of forward brace 110 moves rearward, lower link 144 pivots relative to forward brace 110. Specifically, the second end 114 of the forward brace 110 pushes rearward on the second end 148 of the lower link 144. Additionally, as the second end 124 of the aft brace 118 moves rearward, the upper end of the oleo shock strut 136 pivots relative to the second end 124, and the lower link 144 begins to lift the oleo shock strut 136, the impact strut 138, and the wheels 140 toward the nose equipment bay 106.

[0022] 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, Figure 12 is a front view of the nose landing gear assembly 108 in the retracted position, Figure 13 is 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.

[0023] 10 , when the nose device assembly 108 is in the retracted position, the first end 120 of the aft 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. Furthermore, the forward brace 110, the aft brace 118, the oleo shock strut 136, the actuator 126, the side link 162, and the lower link 144 at least partially overlap vertically when in the retracted position. Furthermore, in the retracted position, the actuator 126 is substantially horizontal.

[0024] In the exemplary embodiment, nose device assembly 108 defines a first vertical height H1 (shown in FIG. 3 ) in the extended position of between approximately 80.0 inches and approximately 84.0 inches, inclusive. Specifically, in one embodiment, nose device assembly 108 defines first vertical height H1 of approximately 80.0 inches in the extended position. Similarly, nose device assembly 108 defines a second vertical height H2 (shown in FIG. 10 ) in the retracted position of between approximately 28.0 inches and approximately 32.0 inches, inclusive. Specifically, in one embodiment, nose device assembly 108 defines second vertical height H2 of approximately 30.0 inches in the retracted position. Thus, first vertical height H1 is greater than second vertical height H2. Specifically, in one exemplary embodiment, second vertical height H2 is between approximately 34% and approximately 38% of first vertical height H1, inclusive. More specifically, the second vertical height H2 is approximately 36.5% of the first vertical height H1. The relatively smaller, compact height of the nose device assembly 108 in the retracted position compared to the nose device assembly 108 in the extended position allows the nose device assembly 108 to fit within the smaller volume of the nose device bay 106, allowing for a maximum amount of cargo volume within the aircraft 100.

[0025] Similarly, as best shown in FIG. 3 , the first pivot axis 116 is positioned at a third height H3 between about 75.0 inches and about 81.0 inches, inclusive, above ground level when the nose landing gear assembly 108 is in the extended position. More specifically, in one embodiment, the first pivot axis 116 is positioned at a third height H3 about 78.0 inches above ground level. The relatively small ground clearance between the first pivot axis 116 and the ground level allows for a larger cargo bay 102.

[0026] 1 , the equipment bay includes a forward end 103 and an aft end 105. In one embodiment, the forward end 103 includes a height H4 of between about 33.0 inches and about 36.0 inches, inclusive. More specifically, the forward end 103 includes a height H4 of about 34.5 inches. Similarly, the aft end 105 includes a height H5 of between about 36.0 inches and about 40.0 inches, inclusive. More specifically, the aft end 105 includes a height H5 of about 38.0 inches. In such a configuration, the nose equipment bay 106 includes a volume of between about 70,000 cubic inches and about 75,000 cubic inches, inclusive. More specifically, in one embodiment, the nose equipment bay 106 includes a volume of about 72,626 cubic inches. The relatively small volume of the nose equipment bay 106 requires that the nose equipment assembly 108 be large enough to fit within the nose equipment bay 106. As described herein, to allow for a large volume cargo bay 102, the aircraft 100 provides limited space below the cargo bay floor 104 for storing the nose equipment assembly 108.

[0027] Embodiments described herein relate to nose-mounted landing gear for aircraft, and more particularly, to a compact nose-mounted landing gear that can be housed within a reduced-volume gear bay. More specifically, in an exemplary embodiment, a nose-mounted landing gear assembly includes an oleo shock strut and a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotally coupled to a nose gear bay of a high-wing aircraft about a first pivot axis. The nose-mounted 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 pivotally coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotally coupled to the oleo shock 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 forward brace. The actuator is configured to move the nose landing gear assembly between, inclusive of, a retracted position and an extended position.

[0028] The assemblies and methods described herein facilitate packing the nose gear assembly into a more compact configuration to enable storage in a nose gear bay with a reduced volume. Generally, the nose gear assemblies described herein are used on cargo aircraft without passenger compartments and with enlarged cargo bays. In such aircraft, the cargo bay floor is located as close to the bottom of the aircraft as possible to maximize cargo storage. Therefore, the volume available for storage of the nose gear assembly is reduced. The nose landing gear assemblies described herein enable a retracted configuration that occupies only a small percentage of the space required when in an extended configuration, and therefore can be stored in a relatively small nose gear bay space. As a result, the cargo bay is made larger than known cargo aircraft to enable the transport of a greater amount of cargo.

[0029] The systems and methods described herein are not limited to the specific embodiments described herein; rather, the system components and / or method steps may be utilized independently and separately from the other components and / or steps described herein.

[0030] Although specific features of various embodiments of the present disclosure may be shown in some drawings and not in others, this is for convenience only, and in accordance with the principles of the present disclosure, any feature of a drawing may be referenced and / or claimed in combination with any feature of any other drawing.

[0031] As used herein, the use of the singular form "a" or "an" for an element or step does not exclude a plurality of elements or steps, unless the exclusion of a plurality of elements or steps is expressly stated. Furthermore, references to "one embodiment or example embodiment" of the present invention are not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the described features.

[0032] Furthermore, the present disclosure includes embodiments according to the following clauses: Article 1. A nose landing gear assembly 108 for use in a high-wing aircraft 100 defining a nose gear bay 106, comprising: Oleo shock strut 136, a forward brace 110 comprising a forward brace first end 112 and a forward brace second end 114, the forward brace first end 112 pivotally coupled to the nose equipment bay 106 about a first pivot axis 116; an aft brace 118 comprising an aft brace first end 120 and an aft brace second end 124, the aft brace first end 120 pivotally coupled to the nose device bay 106 about a second pivot axis 122 and the aft brace second end 124 pivotally coupled to the oleo shock strut 136; and a nose landing gear assembly 108 comprising an actuator 126 having 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 forward brace 110, the actuator 126 configured to selectively move the nose landing gear assembly 108 between (including) a retracted position and an extended position; Article 2. The nose landing gear assembly 108 described in clause 1, wherein the forward brace comprises a forward brace first leg 150, a forward brace second leg 152, and a forward brace cross beam 154 extending between the forward brace first leg 150 and the forward brace second leg 152, and the first end 128 of the actuator is coupled to the forward brace cross beam 154. Article 3. 3. The nose landing gear assembly (108) of claim 2, wherein the second leg (152) of the forward brace is oriented at an angle relative to the first leg (150) of the forward brace. Article 4. 3. The nose landing gear assembly (108) of claim 2, wherein the forward brace cross beam (154) is positioned approximately midway between the forward brace first end (112) and the forward brace second end (114). Article 5. The nose landing gear assembly 108 of clause 2, wherein the aft brace 118 comprises an aft brace first leg 156, an aft brace second leg 158, and an aft brace cross beam 160 extending between the aft brace first leg 156 and the aft brace second leg 158. Article 6. Clause 5. The nose landing gear assembly (108) of clause 5, further comprising a pair of side links (162) coupled between the forward brace (110) and the aft brace (118). Article 7. The nose landing gear assembly 108 described in clause 6, wherein each side link 162 of the pair of side links has a first end 162 of the side link coupled to the forward brace 110 between the forward brace cross beam 154 and the forward brace second end 114, and each side link 162 of the side link has a second end 166 of the side link coupled to the aft brace 118 between the aft brace cross beam 160 and the aft brace second end 124. Article 8. Clause 5. The nose landing gear assembly (108) of clause 5, wherein the actuator (126) extends between the aft brace first leg (156) and the aft brace second leg (158). Article 9. 2. 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 of approximately 1.50 inches to 3.50 inches. Article 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, the second vertical height being approximately 34% to 38% of the first vertical height. Article 11. a cargo bay 102 comprising a cargo bay floor 104; a nose equipment bay 106 located below the cargo bay 104; and The aircraft 100 includes a nose landing gear assembly 108 selectively positioned within the nose gear bay 106, the nose landing gear assembly 108 comprising: Oleo shock strut 136, a forward brace 110 comprising a forward brace first end 112 and a forward brace second end 114, the forward brace first end pivotally coupled to the nose equipment bay 106 about a first pivot axis 116; an aft brace 118 comprising an aft brace first end 120 and an aft brace second end 124, the aft brace first end 120 pivotally coupled to the nose device bay 106 about a second pivot axis 122 and the aft brace second end 124 pivotally coupled to the oleo shock strut 136; and The aircraft 100 comprises an actuator 126 having 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 forward brace 110, the actuator 126 configured to selectively move the nose landing gear assembly 108 between (inclusive of) a retracted position and an extended position. Article 12. The aircraft 100 described in clause 11, wherein the forward brace 110 includes a forward brace width that tapers from the forward brace first end 112 to the forward brace second end 114, and the aft brace 118 includes an aft brace width that tapers from the aft brace first end 120 to the aft brace second end 124. Article 13. Clause 12. The aircraft 100 of clause 11, wherein the forward brace 110, the aft brace 118, the oleo shock strut 136, and the actuator 126 at least partially overlap in a vertical direction when in the retracted position. Article 14. 12. The aircraft 100 of clause 11, wherein the first pivot axis 116 is positioned 75.0 inches to 81.0 inches above the ground surface when the nose landing gear assembly 108 is in the extended position. Article 15. 12. The aircraft (100) of clause 11, wherein the nose equipment bay (106) has a height of 33.0 inches to 36.0 inches. Article 16. The aircraft 100 described in 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, the second vertical height being approximately 34% to 38% of the first vertical height. Article 17. the forward brace 110 comprises a forward brace first leg 150, a forward brace second leg 152, and a forward brace cross beam 154 extending between the forward brace first leg 150 and the forward brace second leg 152, the first end 128 of the actuator being coupled to the forward brace cross beam 154; 12. The aircraft 100 of claim 11, wherein the aft brace 118 comprises an aft brace first leg 156, an aft brace second leg 158, and an aft brace cross beam 160 extending between the aft brace first leg 156 and the aft brace second leg 158. Article 18. Clause 12. The aircraft (100) of clause 11, further comprising a pair of side links (162) coupled between the forward brace (110) and the aft brace (118). Article 19. A method of assembling a nose device assembly 108 for use in a high-wing aircraft 100 defining a nose device bay 106, the nose device assembly 108 including an oleo shock strut 136, a forward brace 110, an aft brace 118, and an actuator 126, the method comprising: pivotally coupling a first end 112 of the forward brace 110 to the nose equipment bay 106 about a first pivot axis 116; pivotally coupling a first end 120 of the aft brace 118 to the nose equipment bay 106 about a second pivot axis 122; pivotally coupling the second end 124 of the aft brace 118 to the oleo shock strut 136; coupling a first end 128 of the actuator 126 to the nose device bay 106; and The method includes coupling a second end (130) of the actuator (126) to the forward brace (110), the actuator (126) being configured to selectively move the nose device assembly (108) between (including a retracted position and an extended position). Article 20. coupling a pair of side links 162 between the forward brace 110 and the aft brace 118; and 20. The method of claim 19, further comprising coupling a pair of lower links (144) between the second end (114) of the forward brace (110) and the oleo shock strut (136).

[0033] Below is an annotated working example from LULIT-19-0896-US-NP [2] (thanks for the overview):

[0034] 1. A folding assembly 100 movable between a folded configuration 138 and an extended configuration 136, a first rotating link 102 having a first end 104 and a second end 106, the first end 104 being pivotally coupled to a structural member / frame 114; a second rotating link 108 having a first end 110 and a second end 112, the first end 110 of the second rotating link pivotally coupled to the structural member / frame 114; a first connecting link 116 pivotally coupled between the first rotating link 102 and the second rotating link 108; a second connecting link 122 having a first end 124 and a second end 134, the first end 124 of the second connecting link pivotally coupled to the second end 106 of the first rotation link; and A folding assembly (100) comprising a support link (126) having a first end (128) and a second end (130), the first end (128) pivotally coupled to the second end (106) of the first rotation link, the second end (130) of the support link configured to couple to a component (132) to be moved, the support link (126) configured to selectively move the component (132) between a retracted position (20) and an deployed position (12) (including both positions).

[0035] 2. The folding assembly 100 of example 1, wherein the first rotating link 102 is parallel to the first connecting link 116 in the extended configuration 136.

[0036] 3. The folding assembly 100 of example 1, wherein the second rotating link 108 is parallel to the support link 126 in the extended configuration 136.

[0037] 4. The folding assembly 100 described in Example 1, wherein the first connecting link 116 is oriented at an angle relative to at least one of the first rotating link 102 and the second rotating link 108 in the extended configuration 136.

[0038] 5. The folding assembly 100 of example 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.

[0039] 6. The folding assembly 100 described in Example 1, wherein the second end 120 of the first connecting link is coupled to the second rotating link 108 closer to the second end 112 of the second rotating link than the first end 110 of the second rotating link.

[0040] 7. The folding assembly 100 described in Example 1, wherein the first end 118 of the first connecting link is coupled to the first rotating link 102 at a first pivot point 142 that is closer to the second end 106 of the first rotating link than the first end 104 of the first rotating link.

[0041] 8. The folding assembly 100 of Example 7, 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 a second distance is defined between the second end 106 of the first rotating link and the first pivot point 142, and the first distance is substantially similar to the second distance.

[0042] 9. The folding assembly 100 of example 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.

[0043] 10. The folding assembly 100 of Example 9, wherein a 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.

[0044] 11. A folding assembly 100 as described in Example 10, wherein a 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 distance and the fourth distance.

[0045] 12. The folding assembly 100 of Example 11, wherein a sixth distance is defined between the first pivot point 142 and the second end 134 of the second connecting link, and is substantially similar to the third distance, the fourth distance, and the fifth distance.

[0046] 13. The folding assembly 100 of example 1, wherein the first end 110 of the second rotating link 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.

[0047] 14. A method of assembling a folding assembly 100 movable between a folded configuration 138 and an extended configuration 136, comprising: pivotally coupling a first end 104 of the first rotation link 102 to a structural member / frame 114; pivotally coupling a first end 110 of a second rotation link 108 to said structural member / frame 114; pivotally coupling a first connecting link 116 between the first rotating link 102 and the second rotating link 108; pivotally coupling a first end 124 of a second connecting link 122 to a second end 106 of the first rotation link; pivotally coupling a first end 128 of a support link 126 to a second end 112 of the second rotation link; and The method includes pivotally coupling a second end (134) of a second connecting link to the support link (126), the second end (130) of the support link being configured to be coupled to a component (132) to be moved, whereby the support link (126) is configured to selectively move the component (132) between (including) a retracted position (20) and a deployed position (12).

[0048] 15. The method described in Example 14, wherein the first rotating link 102 is parallel to the first connecting link 116 in the extended configuration 136, and the second rotating link 108 is parallel to the support link 126 in the extended configuration 136.

[0049] 16. The method of example 14, 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.

[0050] 17. The method of Example 14, wherein the second end 120 of the first connecting link is coupled to the second rotating link 108 closer to the second end 112 of the second rotating link than the first end 110 of the second rotating link, and the first end 118 of the first connecting link is coupled to the first rotating link 102 at a first pivot point 142, and the first pivot point 142 is closer to the second end 106 of the first rotating link than the first end 104 of the first rotating link.

[0051] 18. The method of example 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 a second distance is defined between the second end 106 of the first rotating link and the first pivot point 142, and the first distance is substantially similar to the second distance.

[0052] 19. The first end 104 of the first rotation link and the first end 110 of the second rotation link define a third distance therebetween; a fourth distance is defined between the first end 104 of the first rotation link and the first pivot point 142; a fifth distance is defined between the first end 110 of the second rotation link and the first pivot point 142; 18. The method of example 17, wherein a sixth distance is defined between the first pivot point 142 and the second end 134 of the second connecting link, and the third distance, the fourth distance, the fifth distance, and the sixth distance are all substantially similar to one another.

[0053] 20. The method of example 14, wherein the first end 110 of the second rotation link and the second end 112 of the second rotation 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.

[0054] This specification uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems, and practicing any methods incorporating the invention. The patentable scope of the invention is defined in the claims, and may include other examples that occur to those skilled in the art. Such other examples are within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they have equivalent structural elements that do not differ insubstantial way from the literal language of the claims.

Claims

1. A nose landing gear assembly 108 for use in a high-wing aircraft 100 defining a nose gear bay 106, comprising: oleo shock strut 136, a forward brace 110 comprising a forward brace first end 112 and a forward brace second end 114, said forward brace first end 112 pivotally coupled to said nose equipment bay 106 about a first pivot axis 116; an aft brace 118 comprising an aft brace first end 120 and an aft brace second end 124, the aft brace first end 120 pivotally coupled to the nose device bay 106 about a second pivot axis 122 and the aft brace second end 124 pivotally coupled to the oleo shock strut 136; an actuator 126 having 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 forward brace 110, the actuator 126 configured to selectively move the nose landing gear assembly 108 between, inclusive, a retracted position and an extended position; and A nose landing gear assembly (108) comprising a pair of side links (162) coupled between the forward brace (110) and the aft brace (118).

2. 2. The nose landing gear assembly 108 of claim 1, wherein the forward brace comprises a forward brace first leg 150, a forward brace second leg 152, and a forward brace cross beam 154 extending between the forward brace first leg 150 and the forward brace second leg 152, and wherein the actuator first end 128 is coupled to the forward brace cross beam 154.

3. 3. A nose landing gear assembly (108) as described in claim 2, wherein the forward brace second leg (152) is oriented at an angle relative to the forward brace first leg (150).

4. 3. The nose landing gear assembly of claim 2, wherein the forward brace cross beam is disposed midway between the forward brace first end and the forward brace second end.

5. 5. The nose landing gear assembly 108 of claim 2, wherein the aft brace 118 comprises an aft brace first leg 156, an aft brace second leg 158, and an aft brace cross beam 160 extending between the aft brace first leg 156 and the aft brace second leg 158.

6. 6. The nose landing gear assembly 108 of claim 2, wherein each side link 162 of the pair of side links comprises a first end 162 of the side link coupled to the forward brace 110 between the forward brace cross beam 154 and the forward brace second end 114, and each side link 162 of the side link comprises a second end 166 of the side link coupled to the aft brace 118 between the aft brace cross beam 160 and the aft brace second end 124.

7. The nose landing gear assembly (108) of claim 5, wherein said actuator (126) extends between said aft brace first leg (156) and said aft brace second leg (158).

8. 8. The nose landing gear assembly of claim 1, wherein the first pivot axis and the second pivot axis are vertically offset by a distance of between 1.50 inches and 3.50 inches.

9. 9. 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, the second vertical height being between 34% and 38% of the first vertical height.

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