Mounting device and flight mounting system

Abstract

The invention discloses a mounting device and a flight mounting system, and relates to the field of aircraft equipment. The mounting device provided by the embodiment of the invention comprises a mounting mechanism and a connecting piece, the connecting piece is arranged on the airborne load, and a matching structure is arranged on the connecting piece. The mounting mechanism comprises a base, a driving assembly and a bearing assembly, the base is used for being connected with the aircraft, the driving assembly is arranged on the base, and the bearing assembly is in sliding fit with the base and is in transmission connection with the driving assembly. The driving assembly is used for driving the bearing assembly to move between the first position and the second position. The bearing assembly can be matched with the matching structure of the connecting piece at the first position so as to support the connecting piece; and the release structure can be separated from the matching structure at the second position so as to release the connecting piece. The mounting device provided by the invention is good in structural stability, and can efficiently and reliably realize mounting and putting of the airborne load. The flight mounting system provided by the invention adopts the mounting device to realize mounting and putting of the airborne load.

Description

Technical Field

[0001] This application relates to the field of aircraft equipment, and more specifically, to a mounting device and a flight mounting system. Background Technology

[0002] Currently, some aircraft carry onboard payloads for operations. For example, the onboard payload may be fire extinguishing bombs, which the aircraft carries and drops to the location of the fire to extinguish it. In existing technology, onboard payloads are typically mounted on the aircraft using mounting devices. However, existing mounting devices often suffer from poor reliability. Summary of the Invention

[0003] The purpose of this application is to provide a mounting device and a flight mounting system that have better reliability.

[0004] The embodiments of this application can be implemented as follows: In a first aspect, this application provides a mounting device for mounting and launching airborne loads. The mounting device includes a mounting mechanism and a connector. The connector is disposed on the airborne load and has a mating structure. The mounting mechanism includes a base, a drive assembly, and a load-bearing assembly. The base is used to connect the aircraft. The drive assembly is mounted on the base. The load-bearing assembly is slidably engaged with the base. The load-bearing assembly is drively connected to the drive assembly. The drive assembly is used to drive the load-bearing assembly to slide relative to the base so that the load-bearing assembly moves between a first position and a second position. A limit structure is provided on the base to prevent the connecting parts from moving with the load-bearing assembly. The load-bearing component can engage with the connecting structure in the first position to support the connecting component and enable the mounting of the airborne load; the load-bearing component can disengage from the connecting structure in the second position to release the connecting component and enable the release of the airborne load.

[0005] In an optional embodiment, the bearing component includes a bearing body and a sliding part and a bearing part disposed on the bearing body. A slide rail is disposed on the base, and the sliding part slides in cooperation with the slide rail. The bearing part is used to cooperate with the mating structure of the connector when the bearing component is in the first position to support the connector.

[0006] In an optional embodiment, the slide rail includes a strip-shaped boss protruding from the surface of the base, and a slide groove is provided on the sliding part, which slides in cooperation with the slide rail. Alternatively, the slide rail is a groove provided on the surface of the base, and at least a portion of the sliding part is embedded in the groove and slides in cooperation with the groove.

[0007] In an optional embodiment, the supporting body includes at least two pairs of connecting parts, which are spaced apart, and the two ends of the supporting body are respectively connected to the two pairs of connecting parts.

[0008] In an optional embodiment, the base includes a seat body having opposing first and second sides, a slide rail and a limiting structure located on the first and second sides of the seat body respectively, a connecting portion extending from the first side of the seat body to the second side of the seat body, and a bearing portion and a connector located on the second side of the seat body.

[0009] In an optional embodiment, a first clearance hole is provided on the base, and the connecting part passes through the first clearance hole through the base.

[0010] In an optional embodiment, the driving component is used to drive the bearing component to move in a first direction. The mating structure includes a mating groove, which includes a first segment and a second segment connected at an angle to form an L-shape. The first segment extends along the first direction, and the end of the second segment away from the first segment forms an opening in the mating groove. The bearing portion is a bearing pin, which is inserted into the mating groove along a second direction perpendicular to the first direction. When the bearing component is in the first position, the bearing portion can abut against the side wall of the first segment to support the connector. When the bearing component is in the second position, the bearing portion can move along the second segment relative to the connector to disengage from the opening of the mating groove.

[0011] In an optional implementation, the second segment extends along a third direction, which is perpendicular to the first and second directions.

[0012] In an optional embodiment, the connector is a plate extending in a first direction, and the mating groove penetrates the connector in a second direction.

[0013] In an optional embodiment, the support component includes at least two support portions spaced apart in a first direction; The connectors are provided with mating grooves that are equal in number and correspond one-to-one with the number of bearing parts, or the connectors are equal in number and correspond one-to-one with the number of bearing parts, and each connector is provided with a mating groove.

[0014] In an optional embodiment, the limiting structure forms a slot for inserting and engaging with the connector in a third direction, which is perpendicular to the first and second directions. The limiting structure is also provided with a second clearance hole for avoiding the bearing portion. The second clearance hole penetrates the side wall of the slot in the second direction, and the bearing portion extends into the slot through the second clearance hole and engages with the connecting structure.

[0015] In an optional embodiment, the slot has two second clearance holes on its two opposite sidewalls in the second direction, and the bearing portion passes through the two second clearance holes and the slot between the two second clearance holes.

[0016] In an optional embodiment, the mounting mechanism further includes a pretensioning assembly connected to the base, which is used to apply a pretensioning force to the airborne load to cause the airborne load to tend to move away from the mounting mechanism.

[0017] In an optional embodiment, the preload assembly includes an abutment and an elastic member, the abutment being movable relative to the base, and the elastic member being used to apply an elastic force to the abutment to cause the abutment to abut against the machine load.

[0018] In an optional embodiment, the pre-tightening assembly further includes a mounting member and a guide shaft. The mounting member is connected to the base, and the guide shaft is inserted into a hole on the mounting member. The end of the guide shaft away from the mounting member is connected to an abutment member. An elastic member is sleeved on the guide shaft, and the two ends of the elastic member abut against the mounting member and the abutment member, respectively.

[0019] In an optional embodiment, the abutment has an abutment surface for abutting the airborne load, the abutment surface being adapted to the surface shape of the airborne load.

[0020] In an optional embodiment, the base is connected to pretensioning components at both ends in the driving direction of the drive component, and the connector is located between the two pretensioning components.

[0021] In an optional embodiment, the mounting device further includes a connecting frame connected to the base, and the base is connected to the aircraft via the connecting frame.

[0022] In an optional embodiment, the connecting frame is provided with connecting holes and an adjustment hole group. The connecting holes are used to connect with the aircraft, and the adjustment hole group includes multiple adjustment holes. The adjustment hole group is used to connect with the aircraft through some of the adjustment holes to adjust the tilt angle of the mounting device relative to the aircraft, thereby adjusting the tilt angle of the airborne load relative to the aircraft.

[0023] In an optional embodiment, the mounting device further includes a control component disposed on the connecting frame and electrically connected to the drive component.

[0024] In an optional implementation, a limit switch is provided on the base, the limit switch is electrically connected to the control component, and the limit switch can be triggered when the carrier component moves to the second position.

[0025] In an optional implementation, the control component includes a mounting button and a throwing button. The mounting button is used to control the drive component to move the carrier component from the second position to the first position, and the throwing button is used to control the drive component to move the carrier component from the first position to the second position.

[0026] Secondly, this application provides a flight payload system, including an aircraft, an airborne payload, and a payload device according to any of the foregoing embodiments, wherein the connector of the payload device is connected to the airborne payload, and the payload mechanism of the payload device is connected to the aircraft.

[0027] The beneficial effects of the mounting device and flight mounting system provided in this application include: The mounting device provided in this application includes a mounting mechanism and a connector. The connector is mounted on the airborne load and has a mating structure. The mounting mechanism includes a base, a drive assembly, and a load-bearing assembly. The base is used to connect to the aircraft. The drive assembly is mounted on the base. The load-bearing assembly is slidably fitted with the base and is drively connected to the drive assembly. The drive assembly drives the load-bearing assembly to slide relative to the base, allowing the load-bearing assembly to move between a first position and a second position. A limit structure is provided on the base to prevent the connector from moving with the load-bearing assembly. The load-bearing assembly can engage with the mating structure of the connector in the first position to support the connector and achieve the mounting of the airborne load. The load-bearing assembly can disengage from the mating structure of the connector in the second position to release the connector and achieve the release of the airborne load. In the embodiments of this application, the base and the load-bearing assembly are slidably fitted, and the drive assembly drives the load-bearing assembly to move on the base. The base provides support and guidance for the load-bearing assembly. By using a limiting structure to prevent the connector from moving with the load-bearing assembly, the load-bearing assembly, while engaging with and supporting the connector through its mating structure, can still move relative to the connector under the drive of the drive assembly. Ultimately, this relative movement disengages the connector from the mating structure, releasing it and thus enabling the deployment of the airborne load. When installing the airborne load, the load-bearing assembly can be driven to the second position first, then the connector installed in the assembly position, and finally the load-bearing assembly driven to the first position to engage with the mating structure, thereby supporting the airborne load and achieving its mounting. The mounting device provided in this application embodiment has good structural stability and can efficiently and reliably achieve the mounting and deployment of airborne loads. The flight mounting system provided in this application embodiment, by employing the mounting device provided in this application embodiment, can efficiently and reliably achieve the mounting and deployment of airborne loads. Attached Figure Description

[0028] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0029] Figure 1 This is a schematic diagram of the assembly of the mounting device and the airborne load in one embodiment of this application; Figure 2 This is a schematic diagram of the assembly of the mounting device and the airborne load in another embodiment of this application; Figure 3 This is a schematic diagram of the assembly of the airborne load (partial) and the connecting parts in one embodiment of this application; Figure 4 This is a first exploded view of the mounting mechanism in one embodiment of this application; Figure 5 This is a second exploded view of the mounting mechanism in one embodiment of this application; Figure 6 This is a first schematic diagram of a base (slide rail omitted) in one embodiment of this application; Figure 7 This is a second schematic diagram of the base (slide rail omitted) in one embodiment of this application; Figure 8 This is a schematic diagram of a support component (sliding part omitted) in one embodiment of this application; Figure 9 This is a schematic diagram of a pre-tightening component in one embodiment of this application; Figure 10 for Figure 1 A magnified view of a local area X.

[0030] Icons: 100-Hanging device; 110-Base; 111-Seat body; 112-Slide rail; 113-First clearance hole; 114-Connecting bracket mounting hole; 115-Preload assembly mounting hole; 116-Slide rail mounting hole; 120-Limiting structure; 121-Slot; 122-Second clearance hole; 130-Drive assembly; 1301-Fixed end; 1302-Moving end; 131-Drive mounting base; 140-Bearing assembly; 141-Bearing body; 1411-Connecting part; 1412-Sliding part mounting hole; 142-Bearing part; 143-Sliding part; 144-Bearing; 145 - Limiting plate; 150 - Pre-tightening assembly; 151 - Abutting part; 152 - Elastic part; 153 - Mounting part; 154 - Guide shaft; 160 - Connecting bracket; 161 - Connecting hole; 162 - Adjusting hole group; 170 - Control assembly; 171 - First connector; 172 - Second connector; 173 - Mounting button; 174 - Throwing button; 175 - Limit switch; 176 - Switch mounting base; 180 - Connecting part; 181 - Mating groove; 1811 - First section; 1812 - Second section; 200 - Airborne load; 210 - Guide vane; 220 - Control wing; 230 - Wind dam. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. The components of the embodiments of this application described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0032] Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.

[0033] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0034] In the description of this application, it should be noted that if terms such as "upper," "lower," "inner," or "outer" are used to indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of the invention is usually placed during use, they are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0035] Furthermore, the terms "first" and "second" are used only to distinguish descriptions and should not be interpreted as indicating or implying relative importance.

[0036] It should be noted that, where there is no conflict, the features in the embodiments of this application can be combined with each other.

[0037] Currently, some aircraft carry airborne payloads that can be released in mid-air to land at target locations for corresponding operations. For example, if the airborne payload contains fire extinguishing materials, it can be dropped to the location of a fire for firefighting; if it contains insecticides, it can be dropped to a target location for pest control. Existing technology typically uses mounting devices to attach the airborne payload to the aircraft and release it. However, existing mounting devices often have poor reliability, are prone to release failures, and are inconvenient to install.

[0038] Therefore, this application provides a mounting device that achieves efficient mounting and reliable deployment of airborne loads through a stable structure.

[0039] Figure 1 This is a schematic diagram of the assembly of the mounting device and the airborne load in one embodiment of this application; Figure 2 This is a schematic diagram of the assembly of the mounting device and the airborne load in another embodiment of this application; Figure 3 This is a schematic diagram illustrating the assembly of the airborne load (partial) and connecting components in one embodiment of this application. Figures 1 to 3As shown, the mounting device 100 provided in this embodiment is used for mounting and deploying airborne loads 200. The mounting device 100 includes a mounting mechanism and a connector 180. The connector 180 is disposed on the airborne load 200, and a mating structure is provided on the connector 180. The mating structure is used to cooperate with the mounting mechanism to achieve the mounting of the airborne load 200. This application does not limit the specific structure of the airborne load 200; for example, Figure 1 The airborne payload 200 in this embodiment has a guide wing 210, a control wing 220, and a wind-resistant section 230. The guide wing 210 ensures stable flight of the airborne payload 200 and increases its maneuverability. The control wing 220 adjusts the attitude and direction of motion of the airborne payload 200, thereby controlling its landing point. The wind-resistant section 230 reduces the upward drag experienced by the airborne payload 200 during its descent after deployment, effectively reducing its descent speed and facilitating the control wing 220 to adjust its trajectory, allowing it to land more precisely at the target location. Figure 2 The airborne payload 200 in this embodiment does not have the function of actively adjusting the descent trajectory.

[0040] The mounting mechanism includes a base 110, a drive assembly 130, and a load-bearing assembly 140. The base 110 is used to connect to the aircraft. The drive assembly 130 is mounted on the base 110. The load-bearing assembly 140 is slidably engaged with the base 110 and is drive-connected to the drive assembly 130. The drive assembly 130 drives the load-bearing assembly 140 to slide relative to the base 110, allowing the load-bearing assembly 140 to move between a first position and a second position. A limit structure 120 is provided on the base 110 to prevent the connecting member 180 from moving with the load-bearing assembly 140. The load-bearing assembly 140 can engage with the connecting member 180 in the first position to support the connecting member 180 and achieve the mounting of the airborne payload 200. The load-bearing assembly 140 can disengage from the connecting member 180 in the second position to release the connecting member 180 and achieve the release of the airborne payload 200. In this embodiment, the mounting device 100 further includes a connecting frame 160 connected to the base 110, the connecting frame 160 being used to connect the aircraft; in other words, the base 110 is connected to the aircraft via the connecting frame 160. In other optional embodiments, the base 110 may also be directly connected to the aircraft.

[0041] It is understood that when the load-bearing component 140 is in the first position, it can apply an upward supporting force to the connector 180 to balance the weight of the connector 180 and the airborne load 200, thereby enabling the mounting of the airborne load 200. When the load-bearing component 140 is driven to move to the second position, the limiting structure 120 limits the connector 180, preventing the connector 180 from moving with the load-bearing component 140, and causing relative slippage between the connector 180 and the load-bearing component 140. When the load-bearing component 140 moves to the second position, it disengages from the mating structure, and finally separates from the connector 180. The connector 180 loses the support of the load-bearing component 140, causing the connector 180 and the airborne load 200 to fall under the influence of gravity, thus enabling the deployment of the airborne load 200. Therefore, in this embodiment, the first position of the bearing component 140 is equivalent to the locked position, which can support the connector 180 and ensure that the connector 180 and the airborne load 200 are stably mounted on the mounting mechanism; the second position is equivalent to the unlocked position, where the connector 180 and the airborne load 200 can be detached from the bearing component 140 under the action of gravity.

[0042] In this embodiment, the mounting mechanism further includes a pre-tensioning component 150, which is connected to the base 110. The pre-tensioning component 150 applies a pre-tensioning force to the airborne load 200, causing the airborne load 200 to tend to move away from the mounting mechanism. By setting the pre-tensioning component 150, a pre-tensioning force opposite to the supporting force can be applied to the airborne load 200 when the bearing component 140 supports it. This ensures that the connecting piece 180 on the airborne load 200 is tightly pressed against the bearing component 140, preventing the airborne load 200 from swaying relative to the bearing component 140 in the vertical or horizontal direction, thus improving the reliability of the mounting. Furthermore, when deploying the airborne load 200, the pre-tensioning force provided by the pre-tensioning component 150 allows the connecting piece 180 to quickly detach from the bearing component 140, making the airborne load 200 easier to deploy.

[0043] Figure 4 This is a first exploded view of the mounting mechanism in one embodiment of this application; Figure 5 This is a second exploded view of the mounting mechanism in one embodiment of this application; Figure 6 This is a first schematic diagram of a base (slide rail omitted) in one embodiment of this application; Figure 7 This is a second schematic diagram of the base (slide rail omitted) in one embodiment of this application. Figures 1 to 7As shown, in this embodiment, the driving component 130 is used to drive the bearing component 140 to move in a first direction (i.e., the direction indicated by arrow ab in the figure). In this embodiment, the mating structure includes a mating groove 181 formed on the connector 180. The mating groove 181 includes a first segment 1811 and a second segment 1812 connected at an included angle, so that the mating groove 181 is L-shaped. The first segment 1811 extends along the first direction, and the end of the second segment 1812 away from the first segment 1811 forms the opening of the mating groove 181. The bearing component 140 includes a bearing body 141 and a bearing portion 142 disposed on the bearing body 141. The bearing portion 142 is used to engage with the mating structure of the connector 180 when the bearing component 140 is in the first position to support the connector 180. In this embodiment, the bearing portion 142 is a bearing pin (see...). Figures 4 to 7 The support pin is inserted into the mating groove 181 along a second direction (i.e., the direction indicated by arrow cd in the figure), and the second direction is perpendicular to the first direction. When the support assembly 140 is in the first position, the support part 142 can abut against the side wall of the first section 1811 to support the connector 180. When the support assembly 140 is in the second position, the support part 142 can move relative to the connector 180 along the second section 1812 to disengage from the opening of the mating groove 181. In its normal mounting posture, the first segment 1811 of the mating groove 181 of the airborne load 200 has upper and lower sidewalls. When the bearing assembly 140 is in the first position, the bearing part 142 is located in the first segment 1811 and can abut against the upper sidewall of the first segment 1811 to support the connector 180. When the bearing assembly 140 is in the second position, the bearing part 142 is located at the connection position between the first segment 1811 and the second segment 1812. Since the second segment 1812 has a vertical extension and an upward opening at the end away from the first segment 1811, the bearing part 142 can slide along the second segment 1812 and eventually move out of the mating groove 181 from the opening, thus separating the connector 180 from the bearing assembly 140. In other optional embodiments, the bearing part 142 can also be any other structure that can mate with the connector 180 and bear the airborne load 200.

[0044] In this embodiment, the second segment 1812 extends along a third direction (indicated by arrow ef in the figure), which is perpendicular to the first and second directions. In practical applications, the first direction is the forward / backward direction of the aircraft or inclined to the forward / backward direction, the second direction is the left / right direction, and the third direction is the up / down direction of the aircraft or inclined to the up / down direction. Optionally, the connector 180 is a plate extending along the first direction, and the mating groove 181 penetrates the connector 180 along the second direction. By setting the connector 180 as a plate extending along the first direction, it is beneficial to reduce wind resistance during aircraft operation. Optionally, the load-bearing assembly 140 includes at least two load-bearing portions 142 spaced apart in the first direction; correspondingly, the connector 180 is provided with mating grooves 181 equal in number and corresponding one-to-one with the load-bearing portions 142, or the number of connectors 180 and load-bearing portions 142 are equal and corresponding one-to-one, and each connector 180 is provided with one mating groove 181. By providing multiple support pins and mating grooves 181, the support assembly 140 can provide multi-point support for the connector 180, thereby improving the stability of the airborne load 200 under load. In this embodiment, the connector 180 is provided with two mating grooves 181, and the support assembly 140 includes two support portions 142.

[0045] In this embodiment, the airborne load 200 is mounted by the cooperation of the first segment 1811 of the L-shaped mating groove 181 with the bearing part 142, and the airborne load 200 is released by driving the bearing part 142 to move to the second segment 1812 of the mating groove 181. In other optional embodiments, the structural shape of the mating groove 181 is not limited to this. For example, the mating groove 181 can be a groove extending along the first direction, with the opening also facing the first direction. When the bearing part 142 is inserted into the mating groove 181, it abuts against the upper wall of the mating groove 181. When the bearing part 142 moves out of the mating groove 181 along the first direction, unlocking is achieved. Alternatively, the mating groove 181 can be a groove with a wider bottom and a narrower opening (such as a dovetail groove). The mating groove 181 extends along the first direction and the opening faces upward. At least one end of the mating groove 181 is open in the first direction to form an opening. The bearing assembly 140 has a bearing part 142 that matches the shape of the mating groove 181. When the bearing part 142 is in the mating groove 181, it cannot be disengaged from the narrower opening. When the bearing part 142 slides along the mating groove 181 and moves out of the opening, the bearing part 142 is disengaged from the mating groove 181, thereby unlocking, that is, the airborne load 200 is deployed. In other optional embodiments, the support portion 142 can also be an L-shaped hook structure, with the mating structure including a pin. Specifically, the support portion 142 includes a vertical arm and a horizontal arm. When the support assembly 140 is in the first position, the horizontal arm can support the pin, and the support portion 142 "hooks" the pin as the mating structure. When the support assembly 140 moves to the second position, the pin will detach from the horizontal arm of the support portion 142 (i.e., "unhook"), thereby realizing the deployment of the airborne load 200. Optionally, the horizontal arm of the L-shaped hook structure has a recessed portion matching the shape of the pin at one end near the vertical arm, so that when the support assembly 140 is in the first position, the pin is located in the recessed portion of the L-shaped hook structure, preventing the pin from detaching from the horizontal arm of the support portion 142 when it is in the mounted state.

[0046] like Figure 4 and Figure 5As shown, the base 110 of the mounting mechanism in this embodiment includes a seat body 111 and a limiting structure 120 connected to the seat body 111, and a driving component 130 is disposed on the seat body 111. Specifically, the driving component 130 is connected to the seat body 111 through a driving mounting base 131. In this embodiment, the bearing component 140 further includes a sliding portion 143 disposed on the bearing body 141, and a slide rail 112 is disposed on the base 110. The sliding portion 143 is slidably engaged with the slide rail 112. The bearing portion 142 is used to engage with the engaging structure of the connector 180 when the bearing component 140 is in a first position to support the connector 180. In this embodiment, the slide rail 112 includes a strip-shaped boss protruding from the surface of the base 110. The strip-shaped boss extends along a first direction and can guide the bearing component 140. A sliding groove is provided on the sliding portion 143, and the sliding groove is slidably engaged with the slide rail 112. Optionally, the slide rail is a dovetail groove, and the cross-section of the slide rail 112 is a shape that matches the dovetail groove. This arrangement can prevent the sliding part 143 from falling off the slide rail 112. Alternatively, the cross-section of the slide rail 112 is rectangular, and the cross-sectional shape of the slide rail matches the cross-sectional shape of the slide rail 112. However, this application is not limited to this, and the cross-sectional shapes of the slide rail 112 and the slide rail can be appropriately adjusted according to actual needs, as long as their shapes match. Optionally, the slide rail 112 can be fixed to the base 111 by fasteners, including but not limited to screws.

[0047] In this embodiment, there are two sliding parts 143, which are respectively disposed at both ends of the supporting body 141 along the first direction. However, this application is not limited thereto, and the number and arrangement of the sliding parts 143 can be adjusted appropriately according to actual needs.

[0048] In this embodiment, the supporting body 141 is provided with a sliding part mounting hole 1412, and the sliding part 143 can be fixed to the supporting body 141 through the sliding part mounting hole 1412 and fasteners (such as screws).

[0049] In other optional embodiments, the slide rail 112 may also be a groove provided on the surface of the base 110, and at least a portion of the sliding part 143 is embedded in the groove and slides in cooperation with the groove.

[0050] Figure 8 This is a schematic diagram of a support component (sliding part omitted) in one embodiment of this application. (In conjunction with...) Figures 4 to 8In this embodiment, the supporting body 141 of the supporting component 140 includes at least two pairs of connecting portions 1411, which are spaced apart. The two ends of the supporting portion 142 are respectively connected to the two pairs of connecting portions 1411. The seat body 111 has opposing first and second sides. The slide rail 112 and the limiting structure 120 are respectively located on the first and second sides of the seat body 111. The connecting portion 1411 extends from the first side of the seat body 111 to the second side of the seat body 111. The supporting portion 142 and the connector 180 are located on the second side of the seat body 111. In this embodiment, the first and second sides of the seat body 111 are two opposing sides facing a third direction, wherein the first side is the side facing the aircraft, and the second side is the side away from the aircraft. Figure 6 In this embodiment, the first side of the seat 111 is the upper side of the seat 111, and the second side of the seat 111 is the lower side of the seat 111. Two connecting portions 1411 on the supporting body 141 are spaced apart in the second direction. In this embodiment, since the supporting assembly 140 includes two supporting portions 142, there are two pairs (four in total) of connecting portions 1411 on the supporting body 141.

[0051] In this embodiment, a first clearance hole 113 is provided on the base 111, and the connecting portion 1411 of the supporting body 141 passes through the base 111 through the first clearance hole 113. It should be noted that the first clearance hole 113 not only allows the connecting portion 1411 to pass through in a third direction, but its dimension in the first direction should also be larger than the dimension of the connecting portion 1411 in the first direction, so that when the supporting assembly 140 moves in the first direction, the first clearance hole 113 will not interfere with the movement of the connecting portion 1411. A slide rail mounting hole 116 is also provided on the first side of the base 111 for mounting a slide rail 112.

[0052] In this embodiment, the limiting structure 120 forms a slot 121, which is used to insert and engage with the connector 180 in the third direction. The limiting structure 120 also has a second clearance hole 122 for avoiding the support portion 142. The second clearance hole 122 penetrates the sidewall of the slot 121 in the second direction, and the support portion 142 extends into the slot 121 through the second clearance hole 122 and engages with the engaging structure (specifically, the engaging groove 181) of the connector 180. Furthermore, the slot 121 has two second clearance holes 122 on its two opposite sidewalls in the second direction, and the support portion 142 passes through the two second clearance holes 122 and the slot 121 between them. In this embodiment, since the connector 180 is inserted into the slot 121, the connector 180 can only move relative to the slot 121 in the depth direction (i.e., the third direction) when the support component 140 is in the second position. During the movement of the load-bearing component 140 from the first position to the second position, the connector 180 is restricted by the limiting structure 120 (specifically, by the inner wall of one end of the slot 121 in the first direction), preventing the connector 180 from moving with the load-bearing component 140 (specifically, the load-bearing part 142) in the first direction. Therefore, the connector 180 and the load-bearing component 140 can slide relative to each other, thus unlocking the connector. In this embodiment, the limiting structure 120 with the slot 121 not only restricts the movement of the connector 180 in the first direction but also restricts its movement in the second direction, improving the stability of the airborne load 200 in the mounted state. Furthermore, when the airborne load 200 is installed on the mounting mechanism, the slot 121 serves a positioning function, facilitating the operator to accurately locate the installation position of the connector 180, thereby improving installation efficiency. In this embodiment, the shape of the slot 121 is adapted to the connector 180, being a flat cavity extending along the first direction, thus better limiting the connector 180 and improving the stability of the connector 180 after insertion into the slot 121.

[0053] In this embodiment, when the bearing portion 142 is a bearing pin, the second clearance hole 122 is an oblong hole extending along the first direction. Therefore, when the bearing portion 142 moves along the first direction, the limiting structure 120 will not interfere with the bearing portion 142. However, this application is not limited to this. The bearing portion 142 can also be other structures suitable for the load-bearing capacity of the loader, as long as the shape of the second clearance hole 122 matches the shape of the bearing portion 142 and does not interfere with the movement of the bearing portion 142.

[0054] It should be understood that the limiting structure 120 can also be other structural forms. For example, the limiting structure 120 is a limiting plate provided on the base 111, which abuts against the connecting member 180 when the bearing component 140 moves from the first position to the second position, preventing it from moving with the bearing component 140.

[0055] In this embodiment, both ends of the bearing portion 142 can be rotatably connected to the connecting portion 1411 via bearings 144. This allows the bearing portion 142 to roll on the connecting portion 180 when it supports the connecting member 180 and moves relative to the connecting member 180 in the first direction, thereby reducing motion resistance, reducing the risk of jamming of the bearing assembly 140, and improving the success rate of airborne load 200 deployment. Optionally, the bearing assembly 140 also includes a limiting piece 145 disposed on the connecting portion 1411. The limiting piece 145 can block the bearing 144, preventing the bearing 144 from falling out of the hole in the connecting portion 1411 in the second direction.

[0056] The base 110 also has a preload assembly mounting hole 115 on its seat body 111. The preload assembly 150 can be connected to the seat body 111 of the base 110 via the preload assembly mounting hole 115 and fasteners (such as screws). Specifically, the preload assembly mounting hole 115 is located on the end faces of both ends of the seat body 111 in the first direction. The base 110 also has a connecting bracket mounting hole 114 on its seat body 111. The seat body 111 can be connected to the connecting bracket 160 via the connecting bracket mounting hole 114 and fasteners (such as screws). Optionally, the connecting bracket mounting hole 114 is located on opposite sides of the seat body 111 in the second direction.

[0057] Optionally, weight reduction holes or weight reduction grooves can be provided on the load-bearing body 141 and connecting part 1411 of the load-bearing component 140, the seat 111 and limiting structure 120 of the base 110, and / or connecting frame 160 to reduce the weight of the entire mounting mechanism and reduce the load on the aircraft.

[0058] In this embodiment, the drive assembly 130 may be an electric push rod, which has a fixed end 1301 and a movable end 1302. The fixed end 1301 is connected to the seat body 111 of the base 110 through the drive mounting seat 131; the movable end 1302 is connected to the bearing body 141 of the bearing assembly 140.

[0059] Figure 9 This is a schematic diagram of the pretensioning component 150 in one embodiment of this application. (In conjunction with...) Figure 5 and Figure 9 As shown, in this embodiment, the base 110 is connected to two pretensioning components 150 at both ends in the driving direction (i.e., the first direction) of the driving component 130, and the connector 180 is located between the two pretensioning components 150; in this embodiment, the limiting structure 120 is located between the two pretensioning components 150. By setting two pretensioning components 150 and placing the connector 180 and the limiting structure 120 between the two pretensioning components 150, the force application points of the two pretensioning components 150 on the airborne load 200 can be located on the front and rear sides of the connector 180, respectively, so that the airborne load 200 can be subjected to more balanced forces.

[0060] In this embodiment, the pretensioning assembly 150 includes an abutment 151 and an elastic member 152. The abutment 151 is movable relative to the base 110, and the elastic member 152 applies an elastic force to the abutment 151 to abut against the machine load 200. Further, the pretensioning assembly 150 also includes a mounting member 153 and a guide shaft 154. The mounting member 153 is connected to the base 110 (specifically, to the end of the seat body 111 in a first direction). The guide shaft 154 is inserted into a hole on the mounting member 153. One end of the guide shaft 154 away from the mounting member 153 is connected to the abutment 151. The elastic member 152 is sleeved on the guide shaft 154, and its two ends abut against the mounting member 153 and the abutment 151, respectively. The insertion and engagement of the guide shaft 154 with the hole in the mounting member 153 allows the abutment 151 to move only in a third direction relative to the mounting member 153. In this embodiment, a connecting member 151 connects two guide shafts 154, and two elastic members 152 are respectively sleeved on the outer sides of the two guide shafts 154. Optionally, the elastic members 152 include, but are not limited to, springs. In other embodiments, the number of guide shafts 154 can be one or three, but this application is not limited thereto. The specific number of guide shafts 154 can be appropriately adjusted according to actual needs, and the number of elastic members 152 matches the number of guide shafts 154.

[0061] In this embodiment, the abutment member 151 has an abutment surface for abutting the airborne load 200, and the abutment surface is adapted to the surface shape of the airborne load 200. Optionally, the abutment surface is an arc surface adapted to the surface shape of the airborne load 200, but this application is not limited to this. In other embodiments, the abutment surface may also be a plane or other shapes, as long as it is adapted to the surface shape of the airborne load 200.

[0062] Optionally, the abutment 151 includes a rubber pad that abuts against the machine load 200, which can play a role in anti-slip and cushioning. However, this application is not limited to this, and the rubber pad can also be replaced with a pad made of other materials with anti-slip and cushioning functions.

[0063] In this embodiment, when the bearing assembly 140 is in the first position and supports the connector 180, the pre-tensioning assembly 150 always applies a force along a third direction to the airborne load 200, causing the airborne load 200 to tend to move away from the aircraft. When the bearing assembly 140 moves to the second position, the connector 180 is in the unlocked state, and the pre-tensioning assembly 150 can push the airborne load 200, causing the connector 180 to disengage from the slot 121, that is, pushing the airborne load 200 away from the mounting mechanism, thereby realizing the deployment of the airborne load 200. The pre-tensioning assembly 150 can improve the problem of the airborne load 200 not deploying smoothly due to the connector 180 being too tightly fitted to the slot 121. Furthermore, the aircraft may not be in a horizontal attitude when releasing the airborne payload 200, and the opening of the slot 121 may not be facing vertically downward. Therefore, there is a possibility that the airborne payload 200 may not be able to fall off the slot 121 smoothly by gravity alone. However, setting the pre-tightening component 150 can avoid the problem of the airborne payload 200 failing to fall off the slot 121 smoothly under the above circumstances, reduce the risk of airborne payload 200 release failure, and improve the release efficiency and success rate of airborne payload 200.

[0064] Figure 10 for Figure 1 A magnified view of a portion of X in the middle. Please refer to [link / reference]. Figure 10 The mounting device 100 also includes a control component 170, which is electrically connected to the drive component 130. Optionally, the control component 170 is disposed on the connecting frame 160. The control component 170 is capable of controlling the operation of the drive component 130, including driving the load-bearing component 140 to move between a first position and a second position. Optionally, the control component 170 is capable of communicative and electrical connections with the aircraft, obtaining power from the aircraft and receiving control commands from the aircraft. Optionally, the control component 170 is also communicatively and electrically connected to the airborne payload 200, thereby enabling power supply and communication to the airborne payload 200. In this embodiment, the control component 170 includes a first connector 171 and a second connector 172, which is electrically and communicatively connected to the aircraft and the airborne payload 200 through the first connector 171, and electrically connected to the drive component 130 through the second connector 172.

[0065] In this embodiment, a limit switch 175 is provided on the base 110. The limit switch 175 is electrically connected to the control component 170 and can be triggered when the carrying component 140 moves to the second position. When the carrying component 140 moves to the second position, the limit switch 175 can feed back a signal to the control component 170, enabling the control component 170 to control the drive component 130 to stop. In this embodiment, the limit switch 175 is connected to the base 110 via a switch mounting base 176. Specifically, the switch mounting base 176 is disposed on the first side of the base body 111 of the base 110 and is disposed opposite to the drive mounting base 131; that is, the switch mounting base 176 and the drive mounting base 131 are disposed on the first side of the base body 111 and are respectively located at both ends of the base body 111 (specifically, respectively located at both ends of the base body 111 along the first direction). Optionally, the limit switch 175 is electrically connected to the first connector 171 of the control component 170.

[0066] In this embodiment, the control component 170 further includes a mounting button 173 and a dropping button 174. The mounting button 173 controls the drive component 130 to move the carrier component 140 from the second position to the first position, thereby mounting the airborne payload 200. The dropping button 174 controls the drive component 130 to move the carrier component 140 from the first position to the second position, thereby releasing the airborne payload 200. It should be understood that the mounting and dropping of the airborne payload 200 can be achieved not only through the mounting button 173 and the dropping button 174, but also by the aircraft and / or ground control equipment directly sending corresponding control commands to the control component 170. Therefore, the control component 170 may also include a wireless communication module to communicate with the aircraft or ground control equipment.

[0067] In this embodiment, there are two throwing buttons 174, and both throwing buttons 174 must be pressed simultaneously to trigger the throwing command. This design effectively prevents accidental activation. In other embodiments, the number of throwing buttons 174 and mounting buttons 173 can be adjusted as needed.

[0068] In this embodiment, the connecting frame 160 is provided with a connecting hole 161 and an adjustment hole group 162. The connecting hole 161 is used to connect with the aircraft, and the adjustment hole group 162 includes multiple adjustment holes. The adjustment hole group 162 is used to connect with the aircraft through some of the adjustment holes to adjust the tilt angle of the mounting device 100 relative to the aircraft, thereby adjusting the tilt angle of the airborne load 200 relative to the aircraft. Figure 4As shown, if the upper adjustment hole in the left adjustment hole group 162 is used to connect to the aircraft, and the lower adjustment hole in the right adjustment hole group 162 is used to connect to the aircraft, the first direction of the mounting device 100 can have an angle of inclination relative to the forward / backward direction of the aircraft, thereby causing the front end of the airborne payload 200 to have a downward tilt angle relative to the front end of the aircraft. When the airborne payload 200 is launched with its front end tilted downward, it can more quickly calibrate its attitude after launch, which is beneficial for improving the accuracy of the landing point. In other embodiments, the lower adjustment hole in the left adjustment hole group 162 can also be connected to the aircraft, and the upper adjustment hole in the right adjustment hole group 162 can be connected to the aircraft, thus causing the front end of the airborne payload 200 to have an upward tilt angle relative to the front end of the aircraft. It should be understood that in other embodiments, the number of adjustment holes in the adjustment hole group 162 can be further increased.

[0069] The method of using the mounting device 100 provided in this embodiment is as follows: When installing the airborne load 200, the drive assembly 130 is first controlled to move the bearing assembly 140 to the second position, and then the connector 180 on the airborne load 200 is inserted into the slot 121 of the limiting structure 120. Since the bearing part 142 is in the unlocked position at this time, the opening of the mating groove 181 of the connector 180 is directly opposite the bearing part 142. During the process of inserting the connector 180 into the slot 121, the bearing part 142 moves along the second segment 1812 of the mating groove 181 to the position where the first segment 1811 and the second segment 1812 meet. Then, the drive assembly 130 is controlled to drive the bearing assembly 140 to the first position. During this process, the bearing part 142 moves along the first direction into the first segment 1811 of the mating groove 181. After that, the bearing part 142 can abut against the inner sidewall of the first segment 1811 of the mating groove 181, thereby supporting the connector 180, thus realizing the mounting of the airborne load 200. During the process of the drive assembly 130 driving the load-bearing assembly 140 to move from the second position to the first position along the first direction, the drive assembly 130 only provides driving force in the first direction. That is, the electric push rod of the drive assembly 130 only generates axial driving force and does not need to provide radial force. The gravity of the airborne load 200 is transmitted to the base 110 by the load-bearing assembly 140. Therefore, the load on the drive assembly 130 can be reduced and its service life can be improved. When the airborne load 200 needs to be deployed, the control drive assembly 130 moves the bearing assembly 140 from the first position to the second position. During this process, the connector 180 will not move with the bearing assembly 140 under the limiting action of the slot 121 of the limiting structure 120. Therefore, the bearing part 142 can move to the second section 1812 of the mating groove 181. After that, the connector 180 can disengage from the slot 121 under the action of its own weight, the weight of the airborne load 200, and the pre-tightening force of the pre-tightening assembly 150. During this process, the bearing part 142 no longer supports the connector 180, but slides out of the mating groove 181 along the second section 1812. It can be seen that the mounting device 100 provided in this application embodiment can efficiently realize the mounting and deployment of the airborne load 200.

[0070] This application also provides a flight payload system, including an aircraft (not shown in the figure), an airborne payload 200, and a payload device 100 provided in the above embodiments. A connector 180 of the payload device 100 is connected to the airborne payload 200, and the payload mechanism of the payload device 100 is connected to the aircraft. The types of aircraft include unmanned aerial vehicles (UAVs) and manned aircraft. Unmanned aerial vehicles include, but are not limited to, unmanned helicopters, fixed-wing UAVs, multi-rotor UAVs, and compound-wing UAVs.

[0071] In summary, this application provides a mounting device 100 and a flight mounting system. The mounting device 100 provided in this application includes a mounting mechanism and a connector 180. The connector 180 is disposed on an airborne payload 200 and has a mating structure. The mounting mechanism includes a base 110, a drive assembly 130, and a load-bearing assembly 140. The base 110 is used to connect to the aircraft. The drive assembly 130 is disposed on the base 110. The load-bearing assembly 140 is slidably engaged with the base 110 and is drively connected to the drive assembly 130. The drive assembly 130 drives the load-bearing assembly 140 to slide relative to the base 110, causing the load-bearing assembly 140 to move between a first position and a second position. A limiting structure 120 is provided on the base 110 to prevent the connector 180 from moving with the load-bearing assembly 140. The load-bearing component 140 can engage with the connecting member 180 in a first position to support the connecting member 180 and enable the mounting of the airborne load 200. The load-bearing component 140 can disengage from the connecting member 180 in a second position to release the connecting member 180 and allow the airborne load 200 to be deployed. In this embodiment, the base 110 and the load-bearing component 140 are slidably engaged. The drive component 130 drives the load-bearing component 140 to move on the base 110, which provides support and guidance. The limiting structure 120 prevents the connecting member 180 from moving with the load-bearing component 140. This allows the load-bearing component 140 to move relative to the connecting member 180 even when engaged with and supporting the connecting member 180, under the drive of the drive component 130. Ultimately, this relative movement disengages the connecting member 180, releasing the connecting member and enabling the deployment of the airborne load 200. When installing the airborne payload 200, the load-bearing component 140 can be driven to the second position first, then the connector 180 can be installed in the assembly position, and then the load-bearing component 140 can be driven to the first position to cooperate with the mating structure, thereby supporting the airborne payload 200 and realizing the mounting of the airborne payload 200. The mounting device 100 provided in this application embodiment has good structural stability and can efficiently and reliably realize the mounting and deployment of the airborne payload 200. The flight mounting system provided in this application embodiment, by adopting the mounting device 100 provided in this application embodiment, can efficiently and reliably realize the mounting and deployment of the airborne payload 200.

[0072] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application.

Claims

1. A mounting device for mounting and deploying airborne loads, characterized in that, The mounting device includes a mounting mechanism and a connector, the connector being disposed on the airborne load, and the connector having a mating structure. The mounting mechanism includes a base, a drive assembly, and a load-bearing assembly. The base is used to connect to the aircraft. The drive assembly is disposed on the base. The load-bearing assembly is slidably engaged with the base. The load-bearing assembly is drively connected to the drive assembly. The drive assembly is used to drive the load-bearing assembly to slide relative to the base so that the load-bearing assembly moves between a first position and a second position. A limit structure is provided on the base to prevent the connecting member from moving with the load-bearing assembly. The load-bearing component can engage with the mating structure of the connector at the first position to support the connector and enable the mounting of the airborne load; the load-bearing component can disengage from the mating structure of the connector at the second position to release the connector and enable the deployment of the airborne load.

2. The mounting device according to claim 1, characterized in that, The bearing assembly includes a bearing body, a sliding part and a bearing part disposed on the bearing body, a slide rail disposed on the base, and the sliding part slidingly engaging with the slide rail; the bearing part is used to engage with the mating structure of the connector when the bearing assembly is in the first position to support the connector; The slide rail includes a strip-shaped boss protruding from the surface of the base, and the sliding part is provided with a sliding groove, which slides in cooperation with the slide rail. Alternatively, the slide rail is a groove provided on the surface of the base, and at least a portion of the sliding part is embedded in the groove and slides in cooperation with the groove.

3. The mounting device according to claim 2, characterized in that, The supporting body includes at least two pairs of connecting parts, the two connecting parts are spaced apart, and the two ends of the supporting part are respectively connected to the two pairs of connecting parts; The base includes a seat body having a first side and a second side opposite to each other. The slide rail and the limiting structure are located on the first side and the second side of the seat body, respectively. The connecting part extends from the first side of the seat body to the second side of the seat body. The bearing part and the connecting member are located on the second side of the seat body. The base is provided with a first clearance hole, and the connecting part passes through the base through the first clearance hole.

4. The mounting device according to claim 2, characterized in that, The driving component is used to drive the bearing component to move in a first direction. The mating structure includes a mating groove, which includes a first segment and a second segment connected at an angle to make the mating groove L-shaped. The first segment extends along the first direction, and the end of the second segment away from the first segment forms an opening in the mating groove. The bearing part is a bearing pin, which is inserted into the mating groove along a second direction, which is perpendicular to the first direction. When the support component is in the first position, the support portion can abut against the side wall of the first segment to support the connector. When the support component is in the second position, the support portion can move along the second segment relative to the connector to disengage from the opening of the mating groove.

5. The mounting device according to claim 4, characterized in that, The second segment extends along a third direction, which is perpendicular to both the first and second directions; The connector is a plate extending along the first direction, and the mating groove penetrates the connector along the second direction.

6. The mounting device according to claim 4, characterized in that, The load-bearing component includes at least two load-bearing portions spaced apart in the first direction; The connector is provided with a number of mating grooves that are equal to and correspond one-to-one with the number of the bearing parts; or, the number of connectors is equal to and corresponds one-to-one with the number of the bearing parts, and each connector is provided with a mating groove. The limiting structure forms a slot for inserting and engaging with the connector in a third direction, the third direction being perpendicular to the first and second directions; the limiting structure is also provided with a second clearance hole for avoiding the bearing portion, the second clearance hole penetrating the side wall of the slot in the second direction, the bearing portion extending into the slot through the second clearance hole and engaging with the engaging structure of the connector; The slot has two opposing sidewalls in the second direction each having a second clearance hole, and the bearing portion passes through the two second clearance holes and the slot between the two second clearance holes.

7. The mounting device according to any one of claims 1-6, characterized in that, The mounting mechanism also includes a pre-tensioning assembly connected to the base. The pre-tensioning assembly is used to apply a pre-tensioning force to the airborne load so that the airborne load tends to move away from the mounting mechanism. The pretensioning assembly includes an abutment and an elastic member. The abutment is movable relative to the base, and the elastic member is used to apply an elastic force to the abutment so that the abutment abuts against the airborne load. The pre-tightening assembly further includes a mounting component and a guide shaft. The mounting component is connected to the base, and the guide shaft is inserted into a hole on the mounting component. The end of the guide shaft away from the mounting component is connected to the abutment component. The elastic element is sleeved on the guide shaft, and the two ends of the elastic element abut against the mounting component and the abutment component, respectively. The abutment has an abutment surface for abutting the airborne load, the abutment surface being adapted to the surface shape of the airborne load; The base is connected to the pretensioning components at both ends in the driving direction of the driving component, and the connector is located between the two pretensioning components.

8. The mounting device according to any one of claims 1-6, characterized in that, The mounting device also includes a connecting frame connected to the base, and the base is connected to the aircraft via the connecting frame.

9. The mounting device according to claim 8, characterized in that, The connecting frame is provided with connecting holes and an adjustment hole group. The connecting holes are used to connect with the aircraft. The adjustment hole group includes multiple adjustment holes. The adjustment hole group is used to connect with the aircraft through some of the adjustment holes to adjust the tilt angle of the mounting device relative to the aircraft, thereby adjusting the tilt angle of the airborne load relative to the aircraft. The mounting device further includes a control component, which is disposed on the connecting frame and electrically connected to the drive component; A limit switch is provided on the base, and the limit switch is electrically connected to the control component. The limit switch can be triggered when the support component moves to the second position. The control component includes a mounting button and a throwing button. The mounting button is used to control the drive component to move the carrier component from the second position to the first position, and the throwing button is used to control the drive component to move the carrier component from the first position to the second position.

10. A flight payload system, characterized in that, It includes an aircraft, an airborne payload, and a mounting device according to any one of claims 1-9, wherein the mounting device's connector is connected to the airborne payload, and the mounting mechanism of the mounting device is connected to the aircraft.

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