阅读说明：本技术 用于飞机的机头着陆起落架组件 (Nose landing gear assembly for aircraft ) 是由 M·S·卡拉皮迪恩 H·李 于 2021-05-06 设计创作，主要内容包括：用于飞机的机头着陆起落架组件。一种机头着陆起落架组件包括油压撑杆、包括前支架第一端和前支架第二端的前支架。该前支架第一端绕第一枢转轴线可枢转地耦接至高翼飞机的机头起落架舱。该组件还包括后支架,该后支架包括后支架第一端和后支架第二端。该后支架第一端绕第二枢转轴线可枢转地耦接至机头起落架舱,并且后支架第二端可枢转地耦接至油压撑杆。致动器包括致动器第一端和致动器第二端。致动器第二端耦接至机头起落架舱并且致动器第一端耦接至前支架。致动器被配置为使机头着陆起落架组件在缩回位置和伸展位置之间移动。(A nose landing gear assembly for an aircraft. A nose landing gear assembly includes an oil strut, a forward bracket including a forward bracket first end and a forward bracket second end. The forward carrier first end is pivotably coupled to a nose landing gear bay of the high wing aircraft about a first pivot axis. The assembly also includes a rear bracket including a rear bracket first end and a rear bracket second end. The rear carrier first end is pivotably coupled to the nose landing gear bay about a second pivot axis, and the rear carrier second end is pivotably coupled to the oleo strut. The 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 bracket. An actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.)

1. A nose landing gear assembly 108 for a high wing aircraft 100 defining a nose landing gear bay 106, said nose landing gear assembly 108 comprising:

the oil strut 136;

a forward bracket 110 including a forward bracket first end 112 and a forward bracket second end 114, the forward bracket first end 112 being pivotably coupled to the nose landing gear bay 106 about a first pivot axis 116.

A rear bracket 118 including a rear bracket first end 120 and a rear bracket second end 124, the rear bracket first end 120 being pivotably coupled to the nose landing gear bay 106 about a second pivot axis 122, and the rear bracket second end 124 being pivotably coupled to the oleo strut 136; and

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 fore-stock 110, wherein the actuator 126 is configured to selectively move the nose landing gear assembly 108 between the retracted position and the extended position including a retracted position and an extended position.

2. The nose landing gear assembly 108 of claim 1, wherein the forward carrier includes a forward carrier first leg 150, a forward carrier second leg 152, and a forward carrier cross member 154 extending therebetween, wherein the actuator first end 128 is coupled to the forward carrier cross member 154.

3. The nose landing gear assembly 108 according to claim 2, wherein the forward support second leg 152 is oriented obliquely relative to the forward support first leg 150.

4. The nose landing gear assembly 108 according to claim 2, wherein the forward carrier cross-member 154 is positioned approximately midway between the forward carrier first end 112 and the forward carrier second end 114.

5. The nose landing gear assembly 108 according to any of claims 2-4, wherein the rear bracket 118 includes a rear bracket first leg 156, a rear bracket second leg 158, and a rear bracket cross member 160 extending therebetween.

6. The nose landing gear assembly 108 according to claim 5, further including a pair of side links 162 coupled between the forward support 110 and the aft support 118.

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

8. The nose landing gear assembly 108 as claimed in claim 5 wherein said actuator 126 extends between said rear bracket first leg 156 and said rear bracket second leg 158.

9. The nose landing gear assembly 108 according to claim 1, wherein the first pivot axis 116 and the second pivot axis 122 are vertically offset by a distance of about 1.50 inches and about 3.50 inches.

10. 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 approximately 34% to 38% of the first vertical height.

Technical Field

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 landing gear bay.

Background

Currently known nose landing gear and its stow mechanism configuration are highly improved based on the type of aircraft and operate efficiently under a variety of operating conditions, such as taxiing, braking, takeoff/landing and retraction/extension. Commercial passenger aircraft typically include a passenger region and a luggage region below the passenger region. The luggage area on some known aircraft also includes landing gear wells that house landing gear during flight. However, in aircraft used only for cargo transportation, the cargo area 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 landing gear is reduced, and the volume of the cargo area is limited by the amount of space required to accommodate the landing gear during flight.

This section is intended to introduce the reader to various aspects of art that may be related to various aspects of the present disclosure, which 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.

Disclosure of Invention

In one aspect, a nose landing gear assembly for a high wing aircraft for defining a nose landing gear bay is provided. The nose landing gear assembly includes an oleo strut, a forward bracket including a forward bracket first end and a forward bracket second end. The nose bracket 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 bracket including a rear bracket first end and a rear bracket second end. The rear bracket first end is pivotably coupled to the nose landing gear bay about a second pivot axis, and the rear bracket second end is pivotably coupled to the oleo strut. The 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 bracket. An actuator is configured to selectively move the nose landing gear assembly between a retracted position (inclusive) and an extended position (inclusive).

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 an oleo strut, a forward bracket including a forward bracket first end and a forward bracket second end. The nose bracket 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 bracket including a rear bracket first end and a rear bracket second end. The rear bracket first end is pivotably coupled to the nose landing gear bay about a second pivot axis, and the rear bracket second end is pivotably coupled to the oleo strut. The 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 bracket. An actuator is configured to selectively move the nose landing gear assembly between a retracted position (inclusive) and an extended position (inclusive).

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 an oleo strut, a forward bracket, an aft bracket, and an actuator. The method includes pivotably coupling a first end of a nose bracket to a nose landing gear bay about a second pivot axis. The method further comprises the following steps: pivotally coupling a second end of the rear bracket to the hydraulic strut; coupling a first end of an actuator to a nose landing gear bay; a second end of the actuator is coupled to the front bracket. An actuator is configured to selectively move the nose landing gear assembly between a retracted position (inclusive) and an extended position (inclusive).

Drawings

FIG. 1 is a schematic illustration of an exemplary aircraft with an exemplary nose landing gear assembly.

FIG. 2 is a schematic view of the nose landing gear assembly illustrated in FIG. 1 in a gear well of an exemplary aircraft.

FIG. 3 is a side view of the nose landing gear assembly illustrated in FIG. 2 in an extended position.

FIG. 4 is a perspective view of the nose landing gear assembly illustrated in FIG. 2 in an extended position.

FIG. 5 is a front view of the nose landing gear assembly illustrated in FIG. 2 in an extended position.

FIG. 6 is a rear view of the nose landing gear assembly illustrated in FIG. 2 in an extended position.

FIG. 7 is a top view of the nose landing gear assembly illustrated in FIG. 2 in an extended position.

FIG. 8 is a bottom view of the nose landing gear assembly illustrated in FIG. 2 in an extended position.

Figures 9A-9F are perspective views of the nose landing gear assembly illustrated in figure 2 moving from an extended position to a retracted position.

Figure 10 is a side view of the nose landing gear assembly illustrated in figure 2 in a retracted position.

FIG. 11 is a perspective view of the nose landing gear assembly illustrated in FIG. 2 in a retracted position.

FIG. 12 is a front view of the nose landing gear assembly illustrated in FIG. 2 in a retracted position.

FIG. 13 is a rear view of the nose landing gear assembly illustrated in FIG. 2 in a retracted position.

FIG. 14 is a top view of the nose landing gear assembly illustrated in FIG. 2 in a retracted position.

FIG. 15 is a bottom view of the nose landing gear assembly illustrated in FIG. 2 in a retracted position.

FIG. 16 is a front perspective view of an exemplary nose landing gear assembly in an extended position.

FIG. 17 is a right side view and a left side view is a mirror image of the right side view of the nose landing gear assembly shown in FIG. 16 in an extended position.

FIG. 18 is a front view of the nose landing gear assembly shown in FIG. 16 in an extended position.

FIG. 19 is a rear view of the nose landing gear assembly shown in FIG. 16 in an extended position.

Figure 20 is a top view of the nose landing gear assembly shown in figure 16 in an extended position.

Figure 21 is a bottom view of the nose landing gear assembly shown in figure 16 in an extended position.

FIG. 22 is a front perspective view of the nose landing gear assembly shown in FIG. 16 in a retracted position.

FIG. 23 is a right side view and a left side view that is a mirror image of the right side view of the nose landing gear assembly shown in FIG. 16 in a retracted position.

FIG. 24 is a front view of the nose landing gear assembly shown in FIG. 16 in a retracted position.

FIG. 25 is a rear view of the nose landing gear assembly shown in FIG. 16 in a retracted position.

Figure 26 is a top view of the nose landing gear assembly shown in figure 16 in a retracted position.

Figure 27 is a bottom view of the nose landing gear assembly shown in figure 16 in a retracted position.

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

Detailed Description

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 landing gear bay. More specifically, in the exemplary embodiment, a nose mounted landing gear assembly includes an oleo strut, a forward bracket including a forward bracket first end and a forward bracket second end. The nose bracket first end is pivotably coupled to a nose landing gear bay of the high wing aircraft about a first pivot axis. The nose mounted landing gear assembly also includes a rear bracket having a rear bracket first end and a rear bracket second end. The rear bracket first end is pivotably coupled to the nose landing gear bay about a second pivot axis, and the rear bracket second end is pivotably coupled to the oleo strut. The 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 bracket. An actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

The assemblies and methods described herein facilitate folding nose landing gear assemblies into a more compact configuration to allow storage in a reduced volume nose landing gear bay. Generally, the nose landing gear assembly described herein is for use with cargo aircraft that do not have passenger compartments and enlarged cargo compartments. In such aircraft, the cargo compartment floor is positioned as close as possible to the bottom of the aircraft to enable the maximum amount of cargo to be stored. In this manner, the available volume for storing the nose landing gear assembly is reduced. The nose landing gear assembly described herein allows the retracted configuration to occupy only a small percentage of the space required when it is in the extended configuration, and therefore can be stored in a relatively small nose landing gear well volume. As a result, the cargo tanks are made larger than the cargo tanks of known cargo aircraft to enable the transport of larger volumes of cargo.

Fig. 1 is a schematic illustration of an aircraft 100. In the exemplary embodiment, aircraft 100 is a high wing cargo aircraft that includes a cargo compartment 102 and a cargo compartment floor 104. In addition, a nose landing gear bay 106 is positioned below the cargo bay floor and selectively receives a nose landing gear assembly 108 therein. FIG. 2 is a schematic view of a nose landing gear assembly 108 positioned in a nose landing gear bay 106. The configuration of the aircraft 100 gives a limited volume below the cargo bay floor 104 to stow the nose landing gear assembly 108. As described herein, nose landing gear assembly 108 includes a folding mechanism that allows the support trunnions to be placed in close proximity to one another, allowing for a more compact nose landing gear well 106. Specifically, as shown in fig. 2, nose landing gear bay 106 includes a first side panel 107, a second side panel 109, a front panel 111 extending between side panel 107 and side panel 109, and a rear panel 113 extending between side panel 107 and side panel 109. Face plate 107, face plate 109, face plate 111, and face plate 113 define an interior volume in which nose landing gear assembly 108 is stored during flight.

Fig. 3 is a side view of nose landing gear assembly 108 in an extended position, fig. 4 is a perspective view of nose landing gear assembly 108 in an extended position, and fig. 5 is a front view of nose landing gear assembly 108 in an extended position. Figure 6 is a rear view of nose landing gear assembly 108 in an extended position and figure 7 is a top view of nose landing gear assembly 108 in an extended position. Figure 8 is a bottom view of nose landing gear assembly 108 in an extended position.

In the exemplary embodiment, nose landing gear assembly 108 includes a forward carrier 110 having a forward carrier first end 112 and a forward carrier second end 114. The forward bracket first end 112 is coupled to the nose gear bay 106 about a first pivot axis 116. Specifically, the front bracket 110 is pivotally coupled to the side panels 107 and 109 of the nose landing gear bay 106 at a first pivot axis 116. Nose landing gear assembly 108 also includes a rear bracket 118 having a rear bracket first end 120 and a rear bracket second end 124. The rear bracket first end 120 is coupled to the nose gear bay 106 about a second pivot axis 122. Specifically, the rear bracket 118 is pivotably coupled to the side panels 107 and 109 of the nose landing gear bay 106 at a second pivot axis 122. As best shown in fig. 5, the first pivot axis 116 is positioned higher than the second pivot axis 122 within the nose landing gear bay 106 such that the first pivot axis 116 and the second pivot axis 122 are vertically offset by a distance D1 of between about 1.50 inches and about 3.50 inches. More specifically, the first pivot axis 116 and the second pivot axis 122 are vertically offset by a distance D1 of approximately 2.50 inches. This relatively small offset distance allows nose gear assembly 108 to fold into a smaller volume nose gear well 106.

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

As best shown in fig. 3 and 5, nose landing gear assembly 108 also includes an oleo strut 136 pivotally coupled to rear bracket second end 124. A shock strut 138 is telescopically coupled to the oil 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 oil strut 136 when the head landing gear assembly 108 is in the retracted configuration. Additionally, the shock strut 138 is configured to extend from the oleo strut 136 when the head landing gear assembly 108 is in the expanded configuration.

In the exemplary embodiment, a pair of lower links 144 are coupled between oleo strut 136 and front carrier 110. More specifically, the lower link 144 includes a lower link first end 146 pivotally coupled to the oleo strut 136 and a lower link second end 148 pivotally coupled to the front bracket second end 144. The lower link 144 enables the nose landing gear assembly 108 to be collapsed into a smaller volume to fit within the available volume of the nose landing gear bay 106.

As best shown in fig. 4 and 5, the front brace 110 includes a front brace first leg 150, a front brace second leg 152, and a front brace cross member 154, the front brace cross member 154 being coupled to and extending between the legs 150 and 152. In the exemplary embodiment, legs 150 and 152 are oriented obliquely with respect to each other such that a width of front brace 110 gradually narrows from front brace first end 112 to front brace second end 114. The front bracket cross member 154 is positioned approximately midway between the front bracket first end 112 and the front bracket second end 114, and the actuator first end 128 is coupled to the front bracket cross member 154. In operation, actuator 126 pulls forward bracket 110 to facilitate transitioning nose landing gear assembly 108 from the extended position to the retracted position. Specifically, actuator 126 pulls front brace cross member 154 to cause front brace second end 114 to move toward actuator second end 130.

Similarly, in the exemplary embodiment, rear brace 118 includes a rear brace first leg 156, a rear brace second leg 158, and a rear brace cross member 160 that is coupled to legs 156 and 158 and extends between legs 156 and 158. In the exemplary embodiment, legs 156 and 158 are oriented obliquely with respect to each other such that a width of rear brace 118 gradually narrows from rear brace first end 120 to rear brace second end 124. The rear bracket cross member 160 is positioned approximately midway between the bracket first end 120 and the rear bracket second end. In this configuration, the actuator outer cylinder 132 extends between and is spaced apart from the first end 120 of the rear bracket first leg 156 and the first end 120 of the rear bracket second leg 158.

In the exemplary embodiment, nose landing gear assembly 108 also includes a pair of side links 162 that are coupled to forward support 110 and aft support 118 and between forward support 110 and aft support 118, as shown at 162. Each side link 162 includes a side link first end 164 coupled to front bracket 110 and positioned between front bracket cross member 154 and front bracket second end 114. Each side link 162 also includes a side link second end 166, the side link second end 166 being coupled to the rear bracket 118 and positioned between the rear bracket cross member 160 and the rear bracket second end 124.

As best shown in fig. 3 and 5, the front support 110 is larger than the rear support 118. More specifically, in the exemplary embodiment, legs 150 and 152 of front bracket 110 are longer than legs 156 and 158 of rear bracket 118. Additionally, the first ends 112 of the legs 150 and 152 of the front bracket 110 are spaced apart a distance similar to the first ends 120 of the legs 156 and 158 of the rear bracket 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 bracket 118 are more obliquely oriented relative to each other than the legs 150 and 152 of the front bracket 110. As shown in fig. 3, when the head truck assembly 108 is in the extended position, the rear bracket 118 is aligned with the oil strut 136 and the shock strut 138, and the rear bracket 118, the oil strut 136, and the shock strut 138 are all oriented obliquely relative to a vertical plane perpendicular to the ground surface. In addition, in the extended position, the side links 162 are oriented substantially parallel to the outer cylinder 132 and the inner cylinder 134.

Figures 9A-9F are perspective views of nose landing gear assembly 108 moving from an extended position to a retracted position. In the exemplary embodiment, the inner cylinder 134 of the actuator 126 retracts into the outer cylinder 132, which causes the first end 112 of the forward bracket 110 to pivot about the first pivot axis 116 and the second end 114 of the forward bracket 110 to move rearward and upward toward the nose gear well 106. As the second end 114 of the front bracket 110 moves rearward, the side links 162 also push the second end 124 of the rear bracket 118 rearward and upward. Further, as the second end 114 of the front bracket 110 moves rearward, the lower link 144 pivots relative to the front bracket 110. Specifically, the second end 114 of the front bracket 110 pushes the second end 148 of the lower link 144 rearward. Further, as the second end 124 of the rear bracket 118 moves rearward, the top end of the oleo strut 136 pivots relative to the second end 124, and the lower link 144 begins to raise the oleo strut 136, shock strut 138 and wheels 140 toward the nose gear bay 106.

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

As best shown in fig. 10, when the nose landing gear assembly 108 is in the retracted position, the first end 120 of the rear support 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 bracket 110, the rear bracket 118, the oil 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.

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

Similarly, as best shown in fig. 3, when the nose landing gear assembly 108 is in the extended position, the first pivot axis 116 is positioned at a third height H3, the third height H3 being between about 75.0 inches (inclusive) and about 81.0 inches (inclusive) above the ground surface. 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 surface. The relatively small ground clearance between the first pivot axis 116 and the ground surface allows for a larger cargo compartment 102.

Further, as shown in fig. 1, the landing gear bay includes a forward end 103 and a rearward end 105. In one embodiment, the front end 103 includes a height H4 of between about 33.0 inches (inclusive) and about 36.0 inches (inclusive). More specifically, the front end 103 includes a height H4 of approximately 34.5.0 inches. Similarly, the rear end 105 includes a height H5 of between about 36.0 inches (inclusive) and about 40.0 inches (inclusive). More specifically, the rear end 105 includes a height H5 of approximately 38.0 inches. In such a configuration, nose landing gear bay 106 includes a volume of between 70,000 cubic inches (inclusive) and about 75,000 cubic inches (inclusive). More specifically, in one embodiment, nose landing gear bay 106 includes a volume of approximately 72,626 cubic inches. The relatively small volume of nose landing gear bay 106 requires nose landing gear assembly 108 to fold sufficiently to fit within nose landing gear bay 106. As described herein, the aircraft 100 provides a limited volume below the cargo bay floor 104 to store the nose landing gear assembly 108 to allow for a large volume cargo bay 102.

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 nacelle. More specifically, in the exemplary embodiment, a nose mounted landing gear assembly includes an oleo strut, a forward bracket including a forward bracket first end and a forward bracket second end. The nose bracket first end is pivotably coupled to a nose landing gear bay of the high wing aircraft about a first pivot axis. The nose mounted landing gear assembly also includes a rear bracket having a rear bracket first end and a rear bracket second end. The rear bracket first end is pivotably coupled to the nose landing gear bay about a second pivot axis, and the rear bracket second end is pivotably coupled to the oleo strut. The 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 bracket. An actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

The assemblies and methods described herein facilitate folding nose landing gear assemblies into a more compact configuration to allow storage in a reduced volume nose landing gear bay. Generally, the nose landing gear assembly described herein is for use with cargo aircraft that do not have passenger compartments and enlarged cargo compartments. In such aircraft, the cargo compartment floor is located as close as possible to the bottom of the aircraft to enable the maximum amount of cargo to be stored. In this way, the available volume for storing the nose landing gear assembly is reduced. The nose landing gear assembly described herein allows the retracted configuration to occupy only a small percentage of the space required when it is in the extended configuration, and therefore can be stored in a relatively small nose landing gear well volume. As a result, the cargo tanks are made larger than the cargo tanks of known cargo aircraft to enable the transport of larger volumes of cargo.

The systems and methods described herein are not limited to the specific embodiments described herein, but rather, components of systems and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein.

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

As used herein, an element or step recited in the singular and proceeded with the word "a" or "an" should be understood as not excluding plural elements or steps, unless such exclusion is explicitly recited. Furthermore, references to "one embodiment" or "an exemplary embodiment" of the present invention are not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the recited features.

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

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:

the oil strut 136;

a forward bracket 110 including a forward bracket first end 112 and a forward bracket second end 114, the forward bracket first end 112 being pivotably coupled to the nose landing gear bay 106 about a first pivot axis 116;

a rear bracket 118 including a rear bracket first end 120 and a rear bracket second end 124, the rear bracket first end 120 being pivotably coupled to the nose gear bay 106 about a second pivot axis 122, and the rear bracket second end 124 being pivotably coupled to the oleo strut 136; 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 landing gear bay 106, and the actuator first end 128 coupled to the forward support 110, wherein the actuator 126 is configured to selectively move the nose landing gear assembly 108 between a retracted position (inclusive) and an extended position (inclusive).

Clause 2. the nose landing gear assembly 108 of clause 1, wherein the forward carrier includes a forward carrier first leg 150, a forward carrier second leg 152, and a forward carrier cross member 154 extending therebetween, wherein the actuator first end 128 is coupled to the forward carrier cross member 154.

Clause 3. the nose landing gear assembly 108 according to clause 2, wherein the forward bracket second leg 152 is oriented obliquely relative to the forward bracket first leg 150.

Clause 4. the nose landing gear assembly 108 according to clause 2, wherein the forward bracket cross member 154 is positioned approximately midway between the forward bracket first end 112 and the forward bracket second end 114.

Clause 5. the nose landing gear assembly 108 according to clause 2, wherein the rear bracket 118 includes a rear bracket first leg 156, a rear bracket second leg 158, and a rear bracket cross member 160 extending therebetween.

Clause 6. the nose landing gear assembly 108 of clause 5, further comprising a pair of side links 162 coupled between the forward support 110 and the aft support 118.

Clause 7. the nose landing gear assembly 108 according to clause 6, wherein each side link 162 of the pair of side links includes a side link first end 162 coupled to the forward bracket 114 between the forward bracket cross member 154 and the forward bracket second end 114 bracket, and wherein each side link 162 of the side links includes a side link second end 166 coupled to the aft bracket 118 between the aft bracket cross member 160 and the aft bracket second end 124 bracket.

Clause 8. the nose landing gear assembly 108 according to clause 5, wherein the actuator 126 extends between a rear bracket first leg 156 and a rear bracket second leg 158.

Clause 9. the nose landing gear assembly 108 according to 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.

Clause 10. the nose landing gear assembly 108 according to 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.

Clause 11, an aircraft 100, comprising:

a cargo compartment 102 including a cargo compartment floor 104;

a nose gear bay 106 positioned below the cargo bay floor 104; and

a nose landing gear assembly 108 selectively positionable within the nose landing gear bay 106, the nose landing gear assembly 108 comprising:

the oil strut 136;

a forward bracket 110 including a forward bracket first end 112 and a forward bracket second end 114, the forward bracket first end 112 being pivotably coupled to the nose landing gear bay 106 about a first pivot axis 116.

A rear bracket 118 including a rear bracket first end 120 and a rear bracket second end 124, the rear bracket first end 120 being pivotably coupled to the nose gear bay 106 about a second pivot axis 122, and the rear bracket second end 124 being pivotably coupled to the oleo strut 136; 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 landing gear bay 106, and the actuator first end 128 coupled to the forward bracket 110, wherein the actuator 126 is configured to selectively move the nose landing gear assembly 106 between a retracted position (inclusive) and an extended position (inclusive).

Clause 12. the aircraft 100 of clause 11, wherein the forward leg 110 comprises a forward leg width that tapers from the forward leg first end 112 to the forward leg second end 114, and wherein the aft leg 118 comprises an aft leg width that tapers from the aft leg first end 120 to the aft leg second end 124.

Clause 13. the aircraft 100 of clause 11, wherein the forward bracket 110, the aft bracket 118, the oleo strut 136, and the actuator 126 at least partially overlap in a vertical direction when in the retracted position.

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

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.

Clause 16 the aircraft 100 according to 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.

Clause 17 the aircraft 100 of clause 11, wherein:

the front bracket 110 includes a front bracket first leg 150, a front bracket second leg 152, and a front bracket cross member 154 extending therebetween, wherein the first end 128 of the actuator is coupled to the front bracket cross member 154; and

wherein the rear bracket 118 includes a rear bracket first leg 156, a rear bracket second leg 158, and a rear bracket cross member 160 extending therebetween.

Clause 18. the aircraft 100 of clause 11, further comprising a pair of side links 162 coupled between the forward support 110 and the aft support 118.

Clause 19. a method of assembling a nose landing gear assembly 108 of a high wing aircraft 100 for defining a nose landing gear bay 106, wherein the nose landing gear assembly 108 includes an oleo strut 136, a forward bracket 110, an aft bracket 118, and an actuator 126, the method comprising:

pivotally coupling a first end 112 of the nose bracket 110 to the nose gear bay 106 about a first pivot axis 116;

pivotally coupling a first end 120 of the rear bracket 118 to the nose gear bay 106 about a second pivot axis 122;

pivotally coupling the second end 124 of the rear bracket 118 to the oleo strut 136;

coupling a first end 128 of the actuator 126 to the nose gear bay 106; and

a second end 130 of the actuator 126 is coupled to the forward bracket 110, wherein the actuator 126 is configured to selectively move the nose landing gear assembly 108 between a retracted position (inclusive) and an extended position (inclusive).

Clause 20. the method of clause 19, further comprising:

a pair of side links 162 is coupled between the front bracket 110 and the rear bracket 118; and

a pair of lower links 144 are coupled between the second end 114 of the front bracket 110 and the oleo strut 136.

LULIT-annotated claim from 19-0896-US-NP [2] (thank you for description):

1. a folding assembly 100 movable between a compressed configuration 138 and an extended configuration 136, the folding assembly 100 comprising:

a first rotating 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;

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

a first connecting link 116 pivotably coupled between the first rotating link 102 and the second rotating link 108;

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 rotating link second end 106; and

a support link 126 including a first end 128 and a second end 130, wherein the first end 126 is pivotably coupled to the first rotating link second end 106 and the support link second end 130 is configured to be coupled to a member 132 to be moved, wherein the support link 126 is configured to selectively move the member 132 between a compressed position 20 (inclusive) and an expanded position 12 (inclusive).

2. The folding assembly 100 of claim 1 wherein the first rotation link 102 is parallel to the first connection link 116 in the extended configuration 136.

3. The folding assembly 100 of claim 1 wherein the second rotation link 108 is parallel to the support link 126 in the extended configuration 136.

4. The folding assembly 100 of 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 an extended configuration 136.

5. The folding assembly 100 of claim 1 wherein the second connecting link second end 134 is coupled to the support link 126 at about a midpoint 140 of the support link 126.

6. The folding assembly 100 of claim 1 wherein the first connecting link second end 120 is coupled to the second rotation link 108 closer to the second rotation link second end 112 than the second rotation link first end 110.

7. The folding assembly 100 of claim 1 wherein first connecting link first end 118 is coupled to the first rotating link 102 at a first pivot point 142 that is closer to the first rotating link second end 106 than the first rotating link first end 104.

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

9. The folding assembly 100 of claim 7 wherein the first rotation link first end 104 and the second rotation link first end 110 define a third distance therebetween.

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

11. The folding assembly 100 of claim 10 wherein a fifth distance defined between the second rotation link first end 110 and the first pivot point 142 is substantially similar to the third distance and the fourth distance.

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

13. The folding assembly 100 of claim 1 wherein the second rotation link first end 110 and the second rotation link second end 112 define a distance that is substantially similar to a distance defined between the support link first end 128 and the support link midpoint 140.

14. A method of assembling a folding assembly 100 movable between a compressed configuration 138 and an extended configuration 136, the method comprising:

pivotally coupling the first end 104 of the first rotating link 102 to the structural member/frame 114;

pivotally coupling the first end 110 of the second rotation link 108 to the structural member/frame 114;

a first connecting link 116 pivotably coupled between the first rotational connection 102 and the second rotational connection 108;

pivotally coupling a first end 124 of a second connecting link 122 to the first rotating link second end 106;

pivotally coupling a first end 128 of a support link 126 to the second rotating link second end 112; and

a second connecting link second end 134 is pivotably coupled to the support link 126, wherein the support link second end 130 is configured to be coupled to a member 132 to be moved such that the support link 126 is configured to selectively move the member 132 between the retracted position 20 (inclusive) and the deployed position 12 (inclusive).

15. The method of claim 14, wherein the first rotation link 102 is parallel to the first connection link 116 in the extended configuration 136, and wherein the second rotation link 108 is parallel to the support link 126 in the extended configuration 136.

16. The method of claim 14, wherein the second connecting link second end 134 is coupled to the support link 126 at approximately a midpoint 140 of the support link 126.

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

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

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

wherein a fourth distance is defined between the first rotating link first end 104 and the first pivot point 142;

wherein a fifth distance is defined between the second rotating link first end 110 and the first pivot point 142; and

wherein a sixth distance is defined between the first pivot point 142 and the second connecting link second end 134, the third distance, the fourth distance, the fifth distance, and the sixth distance being substantially all similar to one another.

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

This written description 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 performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be 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 include equivalent structural elements with insubstantial differences from the literal languages of the claims.