CN114435581A

CN114435581A - Radome housing and opening kinematics

Info

Publication number: CN114435581A
Application number: CN202011233643.2A
Authority: CN
Inventors: 扬·伯梅; 扬·勒卡代; 马丁·拉扎克
Original assignee: Airbus Helicopters Deutschland GmbH
Current assignee: Airbus Helicopters Deutschland GmbH
Priority date: 2020-11-06
Filing date: 2020-11-06
Publication date: 2022-05-06

Abstract

The present embodiment relates to an aircraft (100) having an aircraft structure, comprising a radome opening kinematics (200) and a radome housing (112), the radome housing (112) being adapted to enclose a device (115) in a nose region (110) of the aircraft (100) in a closed position. The radome opening kinematics (200) may move the radome housing (112) between a closed position and an open position, and vice versa. The radome opening kinematics 200 may comprise a guide rail (210) attached to the radome housing (112) and at least three rollers (230) attached to the aircraft structure (103), wherein a first roller (230a) and a second roller (230b) are arranged on opposite sides of the guide rail (210), and wherein a second roller (230b) and a third roller (230c) are arranged on the same side of the guide rail (210).

Description

Radome housing and opening kinematics

Technical Field

The present embodiments relate to an aircraft having an aircraft structure, and more particularly to an aircraft having an aircraft structure including a radar antenna cover housing and an opening kinematics.

Background

Radomes are typically located in the nose area of an aircraft and include equipment located in a particular area of the aircraft and a radome cover. A radome is a composite curved shell structure for enclosing or protecting equipment housed within the nose area of an aircraft. The radome cover may be formed in various shapes according to the type of aircraft with which the radome cover is used. One common shape is the near conical shape found on many jet aircraft or helicopters. The conical shape is sometimes supplemented by pointed or needle-like protrusions extending beyond the conical shape.

The radome cover generally includes a radome cover housing and radome cover opening kinematics. Typically, the radome housing is attached to the aircraft structure by radome opening kinematics, and the radome opening kinematics should allow easy access to the enclosed equipment. The radome opening kinematics typically include a fixed hinge that attaches the radome housing to the aircraft structure. However, conventional hinge mechanisms that simply rotate about a fixed axis can interfere with the enclosed device during rotational movement.

Thus, most radome opening kinematics slide the radome forward before rotating it around a fixed axis. For example, the airbus helicopter company's H155 helicopter has an opening mechanism that includes a sliding mechanism having a rod that is movable along a rod axis within a guide tube and a hinge attached to the radome housing and intermediate the rod. During the opening operation, the rod must be pulled out of the guide tube with a sliding movement until the hinge is free to rotate. The next rotation then rotates the radome housing upward. During the closing operation, the radome cover housing is rotated downwards, and then the rod can be pushed back into the guide tube by means of a sliding movement.

However, the sliding mechanism is often sensitive to dirt and must be accurately adjusted during installation to avoid twisting and snagging of the rod within the guide tube. Further, the above-described sliding mechanism introduces a high bending moment and load into the guide tube when the rod is pulled out of the guide tube. Therefore, a lightweight design of the sliding mechanism with the rod and the guide tube is difficult to achieve and requires a large amount of space.

Document CN207565827U describes a radome coupling mechanism. It includes radar antenna shroud, hinge, hook lock and vaulting pole. The radome cover is disposed at the front of the body. It provides an opening portion that can seal the opening. The side of the radar antenna cover close to the belly passes through the hook lock and is connected with the machine body. The vaulting pole sets up inside the fuselage, and its one end is connected with radar mounting platform, and the other end is connected with radar antenna shroud. The stay bar is provided with a self-locking device. After the radar antenna cover is completely opened, the length of the stay bar is kept unchanged through the self-locking device.

This document therefore discloses an easily detachable radome cover. However, the radome covers are not complete domes, but rather half domes and/or aircraft have no equipment mounted at the foremost part of the dome. Thus, the radome cover can perform only a simple rotation without a forward longitudinal movement.

Other prior art include radar antenna covers with opening kinematics that perform simple rotations or perform rotations after longitudinal movements involving a rod.

For example, document US9,608,320B2 describes a method for opening a dome for protecting a device to be protected, the dome being fitted in a portion described as fixed, wherein in an initial position before opening, a substantially planar interface separates the dome from the fixed portion. The method includes connecting the dome to the fixed portion by at least two independent double-stranded section connectors that are rotationally movable between the dome and the fixed portion. The links of the single link are jointly fitted to the dome and to the fixed part to form, as a whole, a telescopic device (pantograph) in the shape of an isosceles trapezium which, during opening, opens by pivoting until reaching a maximum opening, so that the dome is moved away from the fixed part by a combination of translational and rotational movements.

In practice, the connection pair and the two telescopic rods are fixed at their ends by means of suitable hinges on the inner edge of the radome cover and on the face of the radome cover and are used for the rotational connection. Each telescoping pole is positioned vertically onto the common fitting of a corresponding connecting pair at a distance greater than the length of the connecting pair. In addition, each connection pair is shorter than the corresponding telescopic rod due to the positioning on the common fitting and at the periphery of the radome. In addition, the telescopic rod has an automatic locking position corresponding to the maximum final opening of the radome relative to the fuselage face.

Document US6,796,529B1 describes a stay for bracing an aircraft door, the stay comprising an outer tube connected at one end to the aircraft and a telescopic inner member connected to the aircraft door. When the door is fully opened and automatically locked in place, the inner member extends from the outer tube. The stay can be unlocked by holding a sleeve mounted on the outer tube, pulling it down while rotating it clockwise. The stay bar remains locked until the door is lifted up until it stops, unlocking the stay. Lowering the door returns the stay to its stowed position with the result that the inner member is received within the outer tube.

Document US5,820,077A describes a radome structure with an integrally attached attachment structure for attachment to an aircraft, which is affixed to the rear of the radome.

Document US2,943,756A describes a radome of generally hemispherical configuration which is pivotally mounted at the upper edge of the airframe of an aircraft by a common two-leaf hinge, one of which is secured to the radome cover and the other to the airframe of the aircraft by nuts or bolts or any other conventional means. Carried by the shaft are two triangular truss assemblies, each consisting of a pair of struts extending from the connection with the torque shaft at their inner ends to join at an apex. The struts are secured to each other at their V-shaped junctions at their outer ends by welding and are secured to the torque shaft by welding for common movement therewith. As shown, in their connection to the torque shaft, the first struts are located on one side of the bearing block and the second struts are located on the opposite side. At the V-shaped junction of each truss assembly, a slot is formed in which a plate is secured by welding. Each of a pair of plates extends beyond the outer ends of its trusses and into the space provided between a pair of track engaging or sliding members, and is each pivotally connected to its associated pair of members by bolts and nuts.

Document US2017062920 describes a radome covering a radar system positioned under the fuselage of a fixed-wing aircraft. The radar system is positioned in an inner volume of the housing in which a radome covering the radar system is formed. The track attached to the radome engages with a corresponding track attached to the aircraft structure for sliding interengagement. The bearing as a ball or ball bearing is positioned relative to the track to allow the radome to slide linearly. The radome may reach the extended position only when slid to the axially extended position. When in the extended position, the articulated arm may be oriented at an angle relative to the axial direction of the track. This is to fully deploy the radome. Bearings are provided on opposite sides of the guide rail.

Document US3374972 describes a door for a cargo compartment of an aircraft, which door forms an aerodynamic rear part of the fuselage and is vertically swung from the fuselage in the manner of a sun visor into a top position. The door is hinged to the body by a hinge. The free end of the door is connected to the fuselage by a powered actuator arrangement. Furthermore, on each side of the fuselage there are symmetrically arranged fixed hinge connections in the form of pivots, which are fixed to the structure of the aircraft. The door is also connected to the fixed aircraft structure by means of a mechanism that can be forcibly driven at various positions. The door carries on the inside a fixed structural rib, which is curved, describing an arc drawn around the hinge connection. The structural ribs are secured to the interior surface of the door and the exterior surface of the aircraft structure by the bulkhead. The structural ribs carry gear tracks on each side for constant meshing co-action with a drive gear projecting from the wall of the structure. The gears are symmetrically arranged around the transverse centre of the aircraft and are driven together in opposite directions inside the aircraft by conventional drive means. Guides are provided in parallel on the ribs adjacent each track to engage a pair of rollers across each gear. Each pair of rollers is carried by a support fixed to and projecting from the structure, ensuring constant engagement of the gears in their respective tracks and preventing relative lateral movement of the door during its vertical swinging movement.

Documents CN207565827, FR2379434 or US4174609 and DE1481684 are also cited.

In summary, many prior art aircraft have a radome having a radome housing and radome opening kinematics using either hinges for rotational movement only or using hinges in combination with rods for rotational movement after longitudinal movement during opening of the radome housing and longitudinal movement after rotational movement during closing of the radome housing. A radome having a radome with a radome opening kinematics that eliminates longitudinal movement cannot accommodate equipment at the front-most portion of the radome, wasting space. Radomes having a radome with a radome opening kinematics that perform a longitudinal movement typically rely on a sliding mechanism that includes a rod that performs a longitudinal movement within a guide tube.

However, as mentioned above, such sliding mechanisms are sensitive to dirt and must be adjusted accurately during installation to avoid twisting and snagging of the rod within the guide tube. Furthermore, the sliding mechanism introduces high bending moments and loads into the guide tube when pulling the rod out of the guide tube. Therefore, a lightweight design of the sliding mechanism with the rod and the guide tube is difficult to achieve and requires a large amount of space.

Disclosure of Invention

It is therefore an object to provide an aircraft with a new radome cover housing and opening kinematics. The new radome housing and opening kinematics should have a light weight design, require little space, and be robust, easy to install and less sensitive to dirt.

The above object is solved by an aircraft comprising the features of claim 1. More specifically, an aircraft having an aircraft structure may include a radome housing and a radome housing opening kinematics. The radome housing may be adapted to enclose the device in the nose area of the aircraft in the closed position. The radome opening kinematics may enable a first movement of the radome housing from the closed position to the open position and a second movement of the radome housing from the open position to the closed position. The radome opening kinematics comprises a guide rail attached to the radome housing and at least three rollers attached to the aircraft structure, wherein a first roller and a second roller of the at least three rollers are arranged on opposite sides of the guide rail, and wherein the second roller and a third roller of the at least three rollers are arranged on the same side of the guide rail.

Illustratively, the radome opening kinematics includes a guide rail mounted at the radome housing and guided by rollers mounted on the frame structure.

The radome opening kinematics enables sequential longitudinal and rotational movement of the radome housing during opening of the radome housing to avoid contact with equipment mounted in the aircraft recess and covered by the radome housing when the radome housing is in the closed position.

Thus, any longitudinal movement of the radome housing is guided by the rollers rather than sliding. For this purpose, three rollers guide the movement link via guide rails. The kinematic linkage may be moved and secured to the radome housing while the roller remains in its position.

The rollers reduce friction and ensure smooth movement during longitudinal movement. The distance between the rollers results in a better load distribution and a lower force on the guide rail.

The attack point of the operating force for opening and closing does not have to be centered between the two hinges; the tolerance for asymmetric push-pull forces is much wider.

The guidance perpendicular to the plane of movement is improved during the longitudinal movement.

The space required for the radome to open the kinematics is smaller in length compared to prior art solutions with rods and guide tubes, since there is no need for the necessary residual rod length behind the hinge point as in prior art solutions.

The operation of the radar antenna cover opening kinematics at very high or very low temperatures is improved compared to prior art solutions.

The radar antenna cover opening movement member is less susceptible to dirt and dust. The motion link with attached movable portion can be easily detached and reinstalled with the guide rail without adjustment.

According to one aspect, the aircraft further comprises a radome attachment surface attached to the radome opening kinematics and receiving the radome housing.

According to one aspect, the aircraft further comprises a roller support bracket attached to the aircraft structure and receiving the at least three rollers.

According to one aspect, the aircraft further comprises a plurality of latches adapted to hold the radome housing in a closed position.

According to one aspect, the latch of the plurality of latches further comprises: a latch attached to the radome housing; a latch hook engaged with the latch pin in a closed position; and a biasing device biasing the latch hook to maintain it in engagement with the bolt.

According to one aspect, the latch of the plurality of latches further comprises a detent pin and a detent fork, wherein the detent pin and the detent fork guide the striker pin toward the latch hook during at least a portion of a second movement of the radome housing from the open position to the closed position.

According to one aspect, the first movement of the radar antenna cover housing from the closed position to the open position includes a longitudinal movement from the closed position to a first partially open position, a first rotational movement from the first partially open position to a second partially open position, and a second rotational movement from the second partially open position to a fully open position, and wherein the guide rail further includes a curved end portion that engages the first roller to form a guide rail rear stop that stops the longitudinal movement of the radar antenna cover housing at the first partially open position.

According to one aspect, the radome opening kinematics further comprises a radome housing rotation limiter that stops the second rotational movement of the radome housing at the fully open position.

According to one aspect, the first roller defines an axis of rotation about which the radome housing rotates during the first and second rotational movements of the radome housing.

According to one aspect, the aircraft further comprises a roller guide attached to the radome housing, wherein at least a third roller of the at least three rollers is disposed between the guide rail and the roller guide when the radome housing is in the closed position.

According to one aspect, the roller guide further comprises a first portion parallel to the guide rail; and a second portion kinked away from the guide rail at a predetermined angle.

According to one aspect, the third roller is in contact with the second portion of the roller guide during the first rotational movement of the radome housing.

According to one aspect, the roller guide is removed from the third roller during the second rotational movement of the radome housing.

According to one aspect, the aircraft further comprises: a rod having a first end and a second end, wherein the first end is attached to the aircraft structure; and a rod holder bracket mounted on the radome housing and adapted to receive the second end of the rod when the radome housing is in the fully open position.

According to one aspect, the aircraft further comprises a pole holder bracket mounted on the aircraft structure and adapted to receive the second end of the pole when the radome housing is in the closed position.

Drawings

Embodiments are summarized by way of example in the following description with reference to the drawings. In these figures, identical or functionally identical parts and elements are denoted by the same reference numerals and symbols and are therefore described only once in the following description.

Figure 1 shows a perspective view of an illustrative aircraft having a radome with a radome having a radome cover including a radome cover housing and a radome opening kinematic, in accordance with some embodiments,

FIG. 2A is a diagram of an illustrative radar antenna cover including a radar antenna cover housing and a radar antenna cover opening kinematic, in accordance with some embodiments,

FIG. 2B is a diagram of an illustrative radar antenna cover having a radar antenna cover housing and a radar antenna cover opening kinematic according to some embodiments at the end of longitudinal movement from the closed position of FIG. 2A to a first partially open position,

FIG. 2C is a diagram of an illustrative radar antenna cover having a radar antenna cover housing and a radar antenna cover opening kinematic, during a first rotational movement from a first partially open position to a second partially open position of FIG. 2B, according to some embodiments,

FIG. 2D is a diagram of an illustrative radome having radome housing and radome opening kinematics according to some embodiments during a second rotational movement from a second partially open position to a fully open position,

FIG. 3 shows an isometric view of an illustrative radar antenna cover having a radar antenna cover, a radar antenna cover opening kinematics, a latch, a lock, a rod and a rod holder mount according to some embodiments,

figure 4 shows a three-dimensional view of a portion of an illustrative radar antenna cover opening kinematics moving according to some embodiments,

FIG. 5 shows a three-dimensional view of the interior of an illustrative radar antenna cover having a radar antenna cover opening kinematic and a radar antenna cover housing in a closed position, according to some embodiments,

figure 6A shows a three-dimensional view of an illustrative radome opening kinematic when a corresponding radome cover housing is in a closed position according to some embodiments,

figure 6B shows a three-dimensional view of the illustrative radar antenna cover opening kinematics of figure 6A at the end of the longitudinal movement of the radar antenna cover housing from the closed position of figure 6A to the first partially open position according to some embodiments,

figure 6C shows a three-dimensional view of the illustrative radome opening kinematics of figure 6B during rotational movement of the radome housing from the first partially open position of figure 6B to a fully open position in accordance with some embodiments,

FIG. 6D shows a three-dimensional view of an illustrative radome cover having a radome cover housing attached to the radome cover opening kinematics of FIG. 6C with the radome cover housing in a fully open position, in accordance with some embodiments,

figure 7A is a diagram of a portion of an illustrative lower latch and locking mechanism for a radome cover visible inside the radome cover according to some embodiments,

FIG. 7B is a view of a portion of the illustrative lower latch and locking mechanism of FIG. 7A visible outside of a radome cover, in accordance with some embodiments, an

Figure 8 is a diagram of an illustrative upper latch and locking mechanism for a radar antenna cover visible inside the radar antenna cover, according to some embodiments.

Detailed Description

Fig. 1 shows an aircraft 100 having an aircraft frame 102, the aircraft frame 102 sometimes also being referred to as a fuselage 102. Illustratively, aircraft 100 is an airplane. However, the present embodiment is not limited to an aircraft. Alternatively, any vehicle having a radome is also contemplated, such as a vertical take-off and landing (VTOL) aircraft, helicopter, drone, and the like.

If desired, aircraft 100 may be accessed through a plurality of aircraft doors 104, which plurality of aircraft doors 104 illustratively includes a plurality of

cabin access doors

104a, 104b, 104c, and 104d and one or more cargo compartment access doors 104 e.

The plurality of aircraft doors 104 may be adapted to close the aircraft frame 102 (i.e., the fuselage 102 of the aircraft 100) in a fluid-tight manner.

Fuselage 102 may include an aircraft structure 103 and an aircraft skin 109 attached to aircraft structure 103. For example, the aircraft 100 may include a radome with a radome cover located in a nose area of the aircraft 100. The radome cover may include radome cover housing 112 and radome cover opening kinematics. Radome housing 112 may be part of aircraft skin 109.

If desired, the radome housing 112 may enclose a device 115 in the nose region 110 of the aircraft 100. For example, if desired, the radome cover housing 112 may enclose a device 115 such as a radome.

Fig. 2A is a diagram of an illustrative radar antenna cover having a radar antenna cover opening kinematic 200 and a radar antenna cover housing 112 in a closed position. Radome housing 112 is adapted to enclose device 115 in a nose region of an aircraft (e.g., nose region 110 of aircraft 100 of fig. 1) in the closed position shown in fig. 2A.

Illustratively, radome opening kinematics 200 may include a guide rail 210 and at least three rollers 230. The radome opening kinematics 200 may include roller guides 220, if desired. The roller guide 220 may include a first portion 222 parallel to the guide rail 210. If desired, the roller guide 220 may include a second portion 224, the second portion 224 being twisted away from the guide rail 210 at a predetermined angle.

As shown in fig. 2A to 2D, the radome opening kinematics 200 may comprise three

rollers

230a, 230b, 230 c. However, if desired, radome opening kinematics 200 may include more than three rollers. For example, radome opening kinematics 200 may include an additional roller between

rollers

230b and 230 c.

For example, guide rail 210 and roller guide 220 may both be attached to radome housing 112. At least three rollers 230 may be attached to the aircraft structure 103.

Illustratively, a first roller 230a and a second roller 230b of the at least three rollers 230 may be disposed on opposite sides of the guide rail 210. The second roller 230b and the third roller 230c of the at least three rollers 230 may be disposed on the same side of the guide rail 210.

During longitudinal movement of radome housing 112 from the closed position shown in fig. 2A to the first partially open position shown in fig. 2B, at least a third roller 230c may be positioned between guide rail 210 and first portion 222 of roller guide 220. Accordingly, when the roller 230c is between the guide rail 210 and the first portion 222 of the roller guide 220 (i.e., during longitudinal movement of the radome housing 112), the first portion 222 of the roller guide 220 and the roller 230c may prevent rotational movement of the radome housing 112.

The guide rail 210 may have a straight portion to enable the radar antenna cover housing 112 to move longitudinally along the plurality of rollers 230. If desired, the guide rail 210 may include a curved end 215. The curved end 215 may engage the first roller 230a to form a guide rail rear stop 217 that stops longitudinal movement of the radar antenna cover housing 112 in the first partially open position.

Placing

rollers

230a and 230b opposite each other on opposite sides of guide rail 210 may prevent rotational movement of radome housing 112 until curved end 215 engages first roller 230 a.

Fig. 2B is a diagram of an illustrative radar antenna cover having radar antenna cover opening kinematics 200 and a radar antenna cover housing 112 at the end of a longitudinal movement from the closed position of fig. 2A to a first partially open position, according to some embodiments.

As shown in fig. 2B, the curved end 215 engages the first roller 230a to form the guide rail rear stop 217. The guide rail rear stop 217 (i.e., the curved end 215 along with the roller 230a) stops longitudinal movement of the radar antenna cover housing 112 in the first partially open position and prevents any further longitudinal movement of the radar antenna cover housing 112.

In the first partially open position, the roller 230c is no longer located between the guide rail 210 and the first portion 222 of the roller guide 220. Thus, in the first partially open position, roller 230c may no longer prevent rotational movement of radome housing 112 about an axis defined by roller 230a (i.e., counterclockwise rotation of radome housing 112 about roller 230a as shown in fig. 2B). However, in the first partially open position, roller 230c still prevents rotational movement of radome housing 112 about an axis defined by roller 230B (i.e., clockwise rotation of radome housing 112 about roller 230B as shown in fig. 2B).

Indeed, upon reaching the first partially open position, the radome housing 112 is free to perform a first rotational movement from the first partially open position to a second partially open position as shown in fig. 2C.

As shown in fig. 2C, roller 230a defines an axis of rotation about which radome housing 112 rotates during a first rotational movement of radome housing 112. If desired, the roller 230c may contact the second portion 224 of the roller guide 220 during at least a portion of the first rotational movement of the radome housing 112 from the first partially open position to the second partially open position.

In other words, roller 230a and curved end 215 may at least partially define a first rotational movement of radome housing 112, and second portion 224 of roller guide 220 and roller 230c may support the definition of the first rotational movement of radome housing 112. If desired, the second portion 224 of the roller guide 220, along with the roller 230c, may guide the radome housing 112 during the closing movement between the second partially open position and the first partially open position.

If desired, the radome housing 112 may perform a second rotational movement from the second partially open position to the fully open position. Fig. 2D shows radome housing 112 in a fully open position.

Illustratively, during the second rotational motion, the roller 230c may not be in contact with the second portion 224 of the roller guide 220. If desired, radome housing opening kinematics 210 may include a radome housing rotation limiter that stops the second rotational movement of radome housing 112 at the fully open position.

Fig. 3 shows an isometric view of an illustrative radar antenna cover. The radome cover may include radome cover housing 112, radome cover opening kinematics 200, and latches and/or locks 300. If desired, the radome cover may include one or more posts 410 and corresponding one or more post retainer brackets 420 to retain radome cover housing 112 in the fully open position.

The latch and/or lock 300 may be adapted to hold the radome cover housing 112 in the closed position. Illustratively, latch and/or lock 300 may include a bolt attached to radome housing 112 and a latch hook attached to an aircraft structure (e.g., aircraft structure 103 of fig. 1). If desired, the latch and/or the latch of lock 300 may be attached to the aircraft structure, while the latch hook is attached to radome housing 112.

The latch hook may engage the latch pin in the closed position of radome housing 112. The illustrative latch and/or lock 300 may include a detent pin and/or detent prong 340. The locating pin and/or locating prong 340 may guide the plug pin toward the latch hook during at least a portion of a second movement of the radome housing 112 from the open position to the closed position.

If desired, the latch and/or lock may include a biasing device that biases the latch hook to remain engaged with the shoot bolt. For example, the biasing means may comprise a spring.

During movement of radome housing 112 from the open position to the closed position, the latch pin may push the latch hook against a spring force from its biased position. When radome housing 112 has reached the closed position, the spring may push the latch hook back to its biased position in which it engages the latch pin to hold radome housing 112 in its closed position.

If desired, the latch and/or lock 300 may include a release button 350 and/or an unlatch handle 360. The release button 350 and/or the release handle 360 may be adapted to disengage the latch hook from the deadbolt. For example, releasing the button 350 and/or the release handle 360 may push and move the latch hook against the force of the biasing device from its biased position.

As shown in fig. 3, the radome cover may include four latches and/or locks 300. The radome cover may have a different number of latches and/or locks 300, if desired. For example, the radome cover may include one, two, three, five, six, or any other number of latches and/or locks 300. The latch and/or lock 300 is described in more detail in fig. 7A, 7B, and 8.

For example, the radome cover may include one or more opening handles 380. One or more opening handles 380 may be adapted to provide a handle to an operator moving radome housing 112 from a closed position to an open position and/or from an open position to a closed position.

For example, one or more rods 410 may have a first end 412 and a second end 415. The second end 415 of the rod 410 may be attached to the aircraft structure 103.

A corresponding one or more rod holder brackets 420 may be mounted to the radome housing 112 and adapted to receive a corresponding second end 415 of a corresponding rod 410 when the radome housing 112 is in the fully open position. Thus, one or more rods 410 and corresponding one or more rod retainer brackets 420 may retain radome housing 112 in a fully open position.

One or more rod holder brackets 430 may be mounted on the aircraft structure 103, if desired. One or more rod holder brackets 430 may be adapted to receive a respective second end 415 of a corresponding rod 410 when the radome housing 112 is in the closed position. Thus, when the radome cover housing 112 is in the closed position, the respective second ends 415 of the rods 410 may be safely stowed.

Illustratively, the roller support bracket 250 may be attached to the aircraft structure 103. The roller support bracket 250 is depicted in greater detail in fig. 4.

Fig. 4 shows a three-dimensional view of a portion of an illustrative radar antenna cover opening kinematic 200 with a roller support bracket 250 in accordance with some embodiments.

The roller support bracket 250 may receive at least three rollers 230, such as

rollers

230a, 230b, and 230 c. Illustratively, the roller support bracket 250 may receive a guide rail rear restraint 260. Thus, the portion of radome opening kinematics 200 attached to roller support bracket 250 may be quickly and easily replaced by replacing roller support bracket 250 with all the attached parts.

Illustratively, the roller support bracket 250 may be closed to prevent water penetration and thereby reduce the risk of corrosion. If desired, the roller support bracket 250 may be angled to drain water so that water cannot accumulate, further reducing the risk of corrosion.

For example, the roller support bracket 250 may include a frame that surrounds a truss. The truss may include a plurality of beams to provide increased stability. The roller 230c may be mounted to the frame if desired. One beam may connect the

rollers

230b and 230c and the other beam may connect the

rollers

230a and 230 b.

The frame may have an irregular hexagonal shape. At least some of the vertices of the hexagon may have first stiffeners. The first reinforcement may protrude toward the inside of the frame.

Illustratively, the roller support bracket 250 may have second stiffeners at least at some locations where the beams of the truss intersect each other. The first reinforcement and the second reinforcement may have any shape. For example, the stiffeners may be circular, triangular, rectangular, etc.

If desired, the roller support bracket 250 may be attached to the aircraft structure through at least some of the vertices of the frame and/or through some of the first and/or second stiffeners.

Fig. 5 shows a three-dimensional view of the interior of an illustrative radar antenna cover having a radar antenna cover opening kinematic and a radar antenna cover housing in a closed position, in accordance with some embodiments.

The illustrative radome cover may include radome cover attachment surface 240. Radome attachment surface 240 may be attached to radome opening kinematics 200. Radome attachment surface 240 may receive radome housing 112, if desired.

For example, radome attachment surface 240 may include a bore 242, and radome housing 112 may be attached to radome attachment surface 240 by fasteners that attach to bore 242.

Any type of fastener may be used to attach radome housing 112 to radome attachment surface 240. The fasteners may include screws, bolts and nuts, pins, rivets, nails, clips, clamps, brackets, or any other type of fastener that may be suitable for attaching radome cover housing 112 to radome cover attachment surface 240. If desired, radome housing 112 may be welded and/or glued to radome attachment surface 240.

The radome opening kinematics 200 may include guide rails 210. The guide rail 210 may be straight and have a curved end 215. As shown in fig. 5, the guide rail 210 may have a U-shaped profile, and at least one roller (e.g., roller 230a) of the plurality of rollers 230 may move within the U-shaped profile.

If desired, the guide rail 210 may have an H-shaped profile, and all of the plurality of rollers 230 (e.g.,

rollers

230a, 230b, 230c) may move on either side within the H-shaped profile of the guide rail 210.

Illustratively, the radome opening kinematics 200 may include a roller guide 220. The roller guide 220 may have a first portion 222 parallel to the guide rail 210 and a second portion 224 twisted away from the guide rail 210 at a predetermined angle.

The first portion 222 and/or the second portion 224 of the roller guide 220 may have a U-shaped profile, if desired. For example, at least one roller (e.g., roller 230c) of the plurality of rollers 230 can move within a U-shaped profile.

As shown in fig. 5, the illustrative radome cover may include a latch and/or lock 300 adapted to retain radome cover housing 112 in the closed position. Illustratively, latch and/or lock 300 may include a latch 310 attached to radome cover housing 112.

The latch hook 320 may be attached to an aircraft structure. The latch hook 320 may engage the latch 310 in the closed position. If desired, latch hooks 320 may be attached to radome housing 112 and latch pins 310 may be attached to the aircraft structure.

Fig. 6A shows a three-dimensional view of an illustrative radome opening kinematic when a corresponding radome housing (e.g., radome housing 112 of fig. 1-3) is in a closed position, in accordance with some embodiments.

Illustratively, the roller support bracket 250 may have a plate to which the truss of fig. 4 may be attached. The roller support bracket 250 may be attached to the aircraft structure by a plate, if desired.

The roller support bracket 250 may be at least partially made of a composite material. The roller support bracket 250 may be at least partially made of metal, if desired.

As shown in fig. 6A, a radome attachment surface 240 may be attached to the radome opening kinematics 200. If desired, radome attachment surface 240 may include a bore 242, and radome housing may be attached to radome attachment surface 240 by fasteners that attach to bore 242.

Fig. 6B shows a three-dimensional view of the illustrative radar antenna cover opening mover of fig. 6A at the end of the longitudinal movement of the radar antenna cover housing from the closed position of fig. 6A to the first partially open position, in accordance with some embodiments.

As shown in fig. 6B, the curved end 215 of the guide rail 210 engages the first roller 230a to form a guide rail rear stop 217. The guide rail rear stop 217 (i.e., the curved end 215 along with the roller 230a) stops longitudinal movement of the radome housing at the first partially open position and prevents any further longitudinal movement of the radome housing other than the return longitudinal movement toward the closed position of fig. 6A.

The guide rail rear stop 217 may include a roller 230b, if desired, in addition to the curved end 215 and the roller 230 a. Thus, the guide rail rear stop 217 may prevent any movement other than rotational movement about an axis defined by the roller 230a or longitudinal movement of the radar antenna cover housing toward the closed position of fig. 6A.

Upon reaching the first partially open position, the radome housing is free to perform a rotational movement.

Fig. 6C shows a three-dimensional view of the illustrative radome opening kinematics of fig. 6B during rotational movement of the radome housing from the first partially open position of fig. 6B to a fully open position, in accordance with some embodiments.

In the fully open position, the radome housing rotation limiter 260 stops the second rotational movement of the radome housing. For example, during the second rotational movement, the guide rail 210 may reach the radome housing rotation limiter 260, which may prevent the guide rail 210 from performing any further rotational movement.

Fig. 6D shows a three-dimensional view of an illustrative radome cover having a radome cover housing attached to the radome cover opening kinematics of fig. 6C with the radome cover housing in a fully open position, in accordance with some embodiments.

As shown in fig. 6D, the radome cover may include at least two latches and/or locks 300. The latch and/or lock 300 is described in more detail in fig. 7A, 7B, and 8.

For example, the radome cover may include one or more opening handles 380. The one or more opening handles 380 may be adapted to provide a grip for an operator moving the radome housing 112 from the closed position to the open position and/or from the open position to the closed position.

Fig. 7A is a diagram of a portion of an illustrative lower latch and/or lock for a radome cover visible inside of the radome cover, according to some embodiments.

As shown in fig. 7A, the portion 305 of the latch and/or lock 300 may include a latch hook 320, a biasing device 330, a positioning fork 340, an unlatching handle 360, and a release hook 370. The latch and/or lock 300 may include a portion 305 of the latch and/or lock 300 and a mating portion of the latch and/or lock 300. The latch and/or lock 300 may be adapted to hold the radome cover housing 112 in the closed position.

A portion 305 of the latch and/or lock 300 may be attached to the radome housing 112 and a mating portion of the latch and/or lock 300 may be attached to an aircraft structure (e.g., the aircraft structure 103 of fig. 1). If desired, a portion 305 of the latch and/or lock 300 may be attached to the aircraft structure, while a corresponding portion of the latch and/or lock may be attached to the radome cover housing 112.

Illustratively, the latch and/or the mating portion of the lock 300 may include a bolt. The latch and/or portion 305 of the lock 300 may be adapted to receive a bolt. For example, the latch hook 320 may engage a latch in a closed position.

If desired, the latch and/or the portion 305 of the lock 300 may include a biasing device 330. The biasing device 330 may bias the latch hook 320 to a predetermined position. For example, the biasing device 330 may bias the latch hook 320 to remain engaged with the shoot bolt.

The exterior of the latching hook 320 may be shaped such that a cross pin can move the latching hook 320 out of a biased position during movement of the radome housing 112 to the closed position. For example, the exterior of the latch hook 320 may have a kink.

For example, the biasing device 330 may include a spring that urges the latching hook 320 in the direction of the positioning fork 340. The release handle 360 may be adapted to move the latch hook 320 out of the biased position to release the latch from the latch hook 320. Thus, the release handle 360 may be pushed directly or indirectly against the biasing device 330 and/or the latch hook 320 such that the latch hook 320 moves out of the biased position.

Release hook 370 may block release handle 360 when latch and/or lock 300 is locked. When the latch and/or lock 300 is unlocked, the release hook 370 may allow the release handle 360 to release the latch and/or lock 300. In other words, releasing the hook 370 may cause the latch and/or lock 300 to transition from the locked state to the unlocked state, and vice versa.

During movement of radome housing 112 to the closed position, positioning prongs 340 may guide the plug toward latch hooks 320. For example, the mating portion of the latch and/or lock 300 may include a pin oriented perpendicular to the positioning fork 340, and the positioning fork 340 may receive the pin between two prongs of the positioning fork 340.

Fig. 7B is a diagram of a portion of the illustrative lower latch and locking mechanism of fig. 7A visible outside of a radome cover, according to some embodiments. As shown in fig. 7B, the portion 305 of the latch and/or lock 300 may include a latch hook 320, a positioning fork 340, a release button 350, and a release handle 360.

Illustratively, release button 350 may act on release hook 370. For example, when the latch and/or lock 300 is in the unlocked state, the release button 350 may cause the release hook 370 to block the release handle 360, thereby transitioning the latch and/or lock 300 to the locked state. For another example, when the latch and/or lock 300 is in the locked state, the release button 350 may cause the release hook 370 to allow the release handle 360 to disengage the latch and/or lock 300, thereby transitioning the latch and/or lock 300 to the unlocked state.

When the latch and/or lock 300 is in the unlocked state, the release handle 360 may be adapted to move the latch hook 320 out of the biased position to release the shoot bolt from the latch hook 320.

Fig. 8 is a diagram of an illustrative upper latch and locking mechanism for a radar antenna cover visible inside of the radar antenna cover, according to some embodiments. Fig. 8 shows the latch and/or lock 300 in a closed state. In the closed state, the latch hook 320 has latched onto the latch 310. Thus, the latch and/or lock 300 holds the radome cover in a closed state.

Illustratively, the release button 350 may act on a release hook adapted to block the release handle 360. For example, when the latch and/or lock 300 is in the locked state, the release button 350 may cause the release hook to allow the release handle 360 to disengage the latch and/or lock 300. In other words, the release button 350 may cause the latch and/or the lock 300 to transition from the locked state to the unlocked state via the release hook.

If desired, the release button 350 may cause the release hook to block the release handle 360 when the latch and/or lock 300 is in the unlocked state. In other words, the release button 350 may cause the latch and/or the lock 300 to transition from the unlocked state to the locked state via the release hook.

The latch and/or lock 300 may include a locating pin 840. The locating pin 840 may guide the plug pin 310 toward the latch hook 320 during movement of the radome housing from the open position to the closed position.

For example, the locating pin 840 may be located on a portion of the latch and/or lock 300 (e.g., on the portion 305 of the latch and/or lock 300 of fig. 7A and 7B). The funnel may be located on a mating portion of the latch and/or lock 300. The funnel can guide the insert pin 310 toward the latch hook 320 together with the set pin 840, if desired.

Illustratively, the latch and/or lock 300 may have a locating fork. If desired, both the locating pin 840 and the locating prongs may guide the latch pin 310 toward the latch hook 320 during movement of the radome housing from the open position to the closed position.

It should be noted that modifications to the above described embodiments are within the knowledge of a person skilled in the art and are therefore also considered to be part of the present invention.

For example, the latch and/or lock 300 of fig. 7A is shown with the latch hook 320 engaged with the bolt in the closed position of the radome housing 112. However, any other means of engaging the latch in the closed position is also contemplated. For example, latch and/or lock 300 may include a pair of pliers instead of latch hook 320. The pair of pliers may have a slot that may engage a latch. Further, the biasing device 330 of fig. 7A can push the prongs of the pair of pliers together, rather than pushing the latch hook 320 in the direction of the positioning fork 340.

Further, a second portion 224 of the roller guide 220 is shown in fig. 6A-6D, which includes a rectangular plate without any side walls. However, the second portion 224 of the roller guide 220 may have a trapezoidal shape, with the shorter of the two parallel sides attached to the first portion 222 of the roller guide 220. Also, the second portion 224 of the roller guide 220 may have a sidewall. The sidewalls may help guide the movement of the radome housing 112 from the fully open position to the closed position.

List of reference numerals

100 aircraft

102 aircraft frame, fuselage

103 aircraft structure

104 aircraft door

104a, 104b, 104c, 104d cabin access doors

104e cargo compartment access door

109 aircraft skin

110 nose area

112 radar antenna cover casing

115 device

200 radar antenna cover opening kinematics

210 guide rail

215 bent end portion

217 guide rail rear limiter

220 roller guide

222 first part

224 second portion

230 multiple rollers

230a, 230b, 230c roller

240 radar antenna cover attachment surface

242 drilling a hole

250 roller supporting bracket

260 radar antenna cover housing rotation limiter

300 latch, lock

305 latching and/or locking portion

310 bolt

320 latching hook

330 biasing device

340 positioning fork

350 Release button

360 unlock handle

370 release hook

380 opening handle

410 rod

412 first end portion

415 second end portion

420 rod holder bracket

430 pole holder bracket

840 locating pin

Claims

1. An aircraft (100) having an aircraft structure (103), comprising:

a radome housing (112) adapted to enclose a device (115) in a nose region (110) of the aircraft (100) in a closed position; and

a radome opening kinematics (200) that enables a first movement of the radome housing (112) from the closed position to an open position and a second movement of the radome housing (112) from the open position to the closed position, wherein the radome opening kinematics (200) comprises:

a guide rail (210) attached to the radome housing (112), and

at least three rollers (230) attached to the aircraft structure (103), wherein a first roller (230a) and a second roller (230b) of the at least three rollers (230) are arranged on opposite sides of the guide rail (210), and wherein the second roller (230b) and a third roller (230c) of the at least three rollers (230) are arranged on the same side of the guide rail (210).

2. The aircraft (100) of claim 1, further comprising:

a radome attachment surface (240) attached to the radome opening kinematics (200) and receiving the radome housing (112).

3. The aircraft (100) of any preceding claim, further comprising:

a roller support bracket (250) attached to the aircraft structure (103) and receiving the at least three rollers (230).

4. The aircraft (100) of any preceding claim, further comprising:

a plurality of latches (300) adapted to retain the radome housing (112) in the closed position.

5. The aircraft (100) of claim 4, wherein a latch (300) of the plurality of latches (300) further comprises:

a latch (310) attached to the radome housing (112);

a latching hook (320) engaged with the latch pin (310) in the closed position; and

a biasing device (330) biasing the latch hook (320) to maintain it engaged with the latch pin (310).

6. The aircraft (100) of claim 5, wherein the latch (300) of the plurality of latches (300) further comprises:

a locating pin (840); and

a positioning fork (340), wherein the positioning pin (840) and the positioning fork (340) guide the bolt (310) toward the latch hook (320) during at least a portion of a second movement of the radome housing (112) from the open position to the closed position.

7. The aircraft (100) of any preceding claim, wherein the first movement of the radar antenna cover housing (112) from the closed position to the open position comprises a longitudinal movement from the closed position to a first partially open position, a first rotational movement from the first partially open position to a second partially open position, and a second rotational movement from the second partially open position to a fully open position, and wherein the guide rail (210) further comprises:

a curved end (215) that engages the first roller (230a) to form a guide-rail rear limiter (217) that stops longitudinal movement of the radome housing (112) at the first partially open position.

8. The aircraft (100) of claim 7, wherein the radar antenna enclosure opening kinematics (210) further comprise:

a radome housing rotation limiter (260) that stops a second rotational movement of the radome housing (112) in the fully open position.

9. The aircraft (100) of claim 8, wherein the first roller (230a) defines an axis of rotation about which the radome housing (112) rotates during the first and second rotational motions of the radome housing (112).

10. The aircraft (100) of claim 8, further comprising:

a roller guide (220) attached to the radome housing (112), wherein at least the third roller (230c) of the at least three rollers (230) is disposed between the guide rail (210) and the roller guide (220) when the radome housing (112) is in the closed position.

11. The aircraft (100) of claim 10, wherein the roller guide (220) further comprises:

a first portion (222) parallel to the guide rail (210); and

a second portion (224) kinked away from the guide rail (210) at a predetermined angle.

12. The aircraft (100) of claim 11, wherein the third roller (230c) is in contact with the second portion (224) of the roller guide (220) during the first rotational movement of the radome housing (112).

13. The aircraft (100) of claim 11, wherein the roller guide (220) is removed from the third roller (230c) during the second rotational movement of the radome housing (112).

14. The aircraft (100) of any preceding claim, further comprising:

a rod (410) having a first end (412) and a second end (415), wherein the first end (412) is attached to the aircraft structure (103); and

a rod holder bracket (420) mounted on the radome housing (112) and adapted to receive the second end (415) of the rod (410) when the radome housing (112) is in the fully open position.

15. The aircraft (100) of claim 14, further comprising:

a pole holder bracket (430) mounted on the aircraft structure (103) and adapted to receive the second end (415) of the pole (410) when the radome housing (112) is in the closed position.