CN215285291U - Rotor unmanned aerial vehicle aircraft nacelle - Google Patents

Abstract

The utility model discloses a rotor unmanned aerial vehicle nacelle, relating to the technical field of airborne equipment; rotor unmanned aerial vehicle aircraft nacelle, including the cabin body, the cabin body is provided with drainage piece, when the cabin body hoist and mount were under rotor aircraft drainage piece is located the route of the air current that the rotor produced, can not increase under the heat radiating area of nacelle also adds the condition of fan, can normally dispel the heat to the unmanned aerial vehicle nacelle to ensure the normal work of the part in the nacelle.

Description

Rotor unmanned aerial vehicle aircraft nacelle

Technical Field

The utility model relates to an airborne equipment technical field, concretely relates to rotor unmanned aerial vehicle aircraft nacelle.

Background

Unmanned aerial vehicles have been widely used in many fields such as tactical reconnaissance, target positioning, target damage assessment, electronic countermeasure, communication relay, and the like. In order to meet the execution requirements of corresponding tasks, a pod is usually additionally arranged below the unmanned aerial vehicle, so that the unmanned aerial vehicle can perform various tasks such as detection, monitoring, search and rescue, identification, tracking, navigation and the like. Most of these pods require a fan inside the cabin to dissipate heat from the electronics, such as a lighting pod.

The existing unmanned aerial vehicle lighting pod has high power consumption and long working time, so that heat emitted by the lamp beads is transmitted to an external space in time by using lower resources in limited electric energy and space use scenes, and the unmanned aerial vehicle lighting pod is very important. The operating temperature of lamp pearl is inversely proportional with illumination brightness to high temperature influences the lamp pearl life-span, makes two key characteristics of luminance, the life-span of unmanned aerial vehicle illumination nacelle impaired. The existing unmanned aerial vehicle nacelle is provided with cooling fins outside the nacelle in order to meet the heat dissipation requirement, so that heat is taken away through air convection, or an active cooling fan is added in the nacelle, and the air flow speed is improved to take away the heat.

For the pod provided with the radiating fins, if the unmanned aerial vehicle has too long hovering time, the pod cannot be effectively radiated, so that electronic components in the pod cannot work normally; for the pod with the active heat dissipation fan arranged in the pod, as no person has natural wind in high-altitude operation, when the natural wind direction is opposite to the wind direction of the heat dissipation fan, the rotation resistance of the fan is increased, so that the air flow in the pod is reduced, the heat dissipation efficiency is low, or the purpose of heat dissipation cannot be achieved.

SUMMERY OF THE UTILITY MODEL

The technical problem that the existing unmanned aerial vehicle lighting pod cannot normally dissipate heat when in operation is solved; the utility model provides a rotor unmanned aerial vehicle aircraft nacelle can normally dispel the heat to the unmanned aerial vehicle nacelle to ensure that the part in the nacelle normally works.

The utility model discloses a following technical scheme realizes:

the utility model provides a rotor unmanned aerial vehicle aircraft nacelle, including the cabin body, the cabin body is provided with the drainage piece, cabin body hoist and mount are under rotor aircraft the drainage piece is located the route of the air current that the rotor produced.

The utility model discloses be provided with the drainage piece on the cabin body, and when the hoist and mount of the cabin body were under rotor craft the drainage piece is located the route of the air current that the rotor produced. When the rotor aircraft flies, natural wind energy blows to the cabin body, and partial airflow generated by the rotor is guided to the cabin body through the drainage piece, so that the nacelle can be normally cooled. When the rotorcraft hovers, part of the airflow generated by the rotor is guided to the cabin body through the drainage piece so as to dissipate heat of the nacelle. Therefore, the utility model discloses can be under the heat radiating area who neither increases the nacelle does not also add the condition of fan, can normally dispel the heat to the unmanned aerial vehicle nacelle to ensure the normal work of part in the nacelle.

Wherein, the nacelle is at work, and required heat dissipation amount of wind is less, consequently only need to lead the very few some of air current of rotor output to the nacelle, can not cause the influence to rotor craft's normal flight.

In an optional embodiment, the cabin body is provided with an air inlet, and the air inlet is located on the drainage path of the drainage member to introduce the airflow generated by the rotor into the cabin body, so that the heat dissipation efficiency is higher compared with the heat dissipation efficiency of the cabin body for arranging the heat dissipation fins.

In an alternative embodiment, the air inlet is located on one side of the cabin in the height direction, and the length of the air inlet is shorter than that of the air inlet drainage component arranged on the top of the cabin, so that the air flow can be more easily introduced into the cabin.

In an optional embodiment, an included angle between the length direction of the drainage member and the height direction of the cabin body is adjustable, so that the drainage angle of the airflow member is adjusted, and the wind resistance of airflow flowing into the cabin body is reduced.

In an optional embodiment, the cabin body is provided with a linear driver, the middle part of the drainage component is hinged to the cabin body, one end of the linear driver is hinged to the cabin body, and the other end of the linear driver is hinged to one end of the drainage component, so that the drainage angle of the drainage component can be automatically adjusted.

In an alternative embodiment, the chamber is provided with an air outlet, so that the airflow entering the chamber is discharged from the air outlet to reduce the resistance of the airflow entering the chamber.

In an optional embodiment, the air outlet is located cabin body below can ensure that the heat that the internal components and parts of cabin produced all can be taken away, ensures the radiating effect and improves the radiating efficiency, reduces the influence that drainage piece drainage caused to the flight lift of rotor craft simultaneously.

In an optional embodiment, a drainage groove is formed in one side, facing the cabin body, of the drainage piece, so that most of gas drained by the drainage piece flows in the drainage groove, interference of natural wind on the gas drained by the drainage piece is reduced, and normal heat dissipation of the cabin body is ensured.

The utility model discloses beneficial effect who has:

the utility model discloses be provided with the drainage piece on the cabin body, and when the hoist and mount of the cabin body were under rotor craft the drainage piece is located the route of the air current that the rotor produced, when rotor craft when flying, natural wind energy blows to the cabin body, the partial air current that the rotor produced causes the cabin body through the drainage piece, when rotor craft is hovering, the partial air current that the rotor produced causes the cabin body through the drainage piece, therefore, can be under the condition that the heat radiating area that neither increases the nacelle does not also add the fan, can normally dispel the heat to rotor unmanned aerial vehicle aircraft nacelle to ensure the normal work of the part in the nacelle.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive effort.

Figure 1 is the utility model discloses a structural schematic of rotor unmanned aerial vehicle aircraft nacelle.

Reference numerals:

1-cabin body, 11-air inlet, 12-air outlet, 2-drainage piece and 3-linear driver.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the embodiments of the present application, the terms "central," "upper," "lower," "left," "right," "vertical," "longitudinal," "lateral," "horizontal," "inner," "outer," "front," "rear," "top," "bottom," and the like refer to orientations or positional relationships that are conventionally used in the manufacture of the present application, or that are routinely understood by those of ordinary skill in the art, but are merely used to facilitate the description and to simplify the description and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be considered limiting of the present application.

In the description of the present invention, unless otherwise expressly specified or limited, the terms "disposed," "open," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.

Example 1

With reference to fig. 1, the present embodiment provides a pod for a rotor unmanned aerial vehicle, including a cabin body 1, where the cabin body 1 is provided with a drainage member 2, and the drainage member 2 is located on a path of an airflow generated by a rotor when the cabin body 1 is hung under the rotor unmanned aerial vehicle.

It can be understood that the cabin body can be a hollow box body with radiating fins arranged on the outer wall, in this embodiment, the cabin body 1 is provided with the air inlet 11, the air inlet 11 is located on the drainage path of the drainage member 2, so that the airflow generated by the rotor wing is introduced into the cabin body 1, and the radiating efficiency of the radiating fins is higher than that of the cabin body 1.

Preferably, the air inlet 11 is located at one side of the cabin 1 in the height direction, and is shorter than the length required by arranging the air inlet 11 on the top of the cabin 1 to guide the flow 2, so that the air flow can be more easily introduced into the cabin 1.

Further, the cabin 1 is provided with an air outlet 12, so that the airflow entering the cabin 1 is discharged from the air outlet 12, thereby reducing the resistance of the airflow entering the cabin 1.

In an optional embodiment, the air outlet 12 is located below the cabin body 1, so that heat generated by components in the cabin body 1 can be taken away, a heat dissipation effect and a heat dissipation efficiency can be ensured, and meanwhile, the influence of drainage of a drainage piece on the flight lift of the rotor craft is reduced.

In an optional embodiment, a drainage groove is formed in one side, facing the cabin body 1, of the drainage part 2, so that most of the gas drained by the drainage part 2 flows in the drainage groove, interference of natural wind on the gas drained by the drainage part 2 is reduced, and normal heat dissipation of the cabin body 1 is ensured.

Furthermore, the included angle between the length direction of the drainage component 2 and the height direction of the cabin body 1 is adjustable, so that the drainage angle of the airflow component is adjusted, and the wind resistance of airflow flowing into the cabin body 1 is reduced. For example, the drainage part 2 is driven to rotate around the length direction of the drainage part 2 by a rotary driver, or the drainage part 2 is driven to rotate around the hinge joint of the drainage part 2 and the cabin body by a linear driver.

Particularly, the cabin body 1 is provided with linear actuator 3, drainage piece 2 middle part with the cabin body 1 is articulated, 3 one end of linear actuator with the cabin body 1 is articulated, the 3 other ends of linear actuator with drainage piece 2 one end is articulated to in automatically regulated drainage piece 2's drainage angle. The linear actuator 3 can be an air push rod or an electric push rod, and in order to simplify the control of the linear actuator 3 and reduce the net weight of the cabin, the electric push rod is used to drive the drainage member 2 to rotate in the present embodiment.

When the aircraft is used, the cabin body 1 is hung below the body of the rotorcraft, and the projection distance between the cabin body 1 and a rotor of the rotorcraft is shortened as much as possible in the projection in the height direction.

When the rotor craft is in flight, calorific capacity of components and parts carried according to the cabin body 1, through the flexible inclination of adjustment drainage piece 2 of linear actuator 3, drainage piece 2 keeps vertical when can be direct, only blow cabin body 1 through the natural wind and dispel the heat, but when the supplementary heat dissipation of air current that needs the rotor to produce, make drainage piece 2 at least part be located the irradiation range of rotor air current through shrink linear actuator 3, make the partial air current that natural wind and rotor produced all blow to cabin body 1, can carry out normal heat dissipation to the nacelle.

When the rotor craft hovers, the contraction linear driver 3 is adjusted according to the heat dissipation air volume required by the nacelle, so that the drainage piece 2 is positioned in the area of the irradiation range of the rotor airflow, and partial airflow generated by the rotor wing is led to the nacelle body 1 through the drainage piece 2 to dissipate heat of the nacelle.

Therefore, the embodiment can carry out normal heat dissipation on the unmanned aerial vehicle nacelle under the condition that the heat dissipation area of the nacelle is not increased and a fan is not added, so that the normal work of components in the nacelle is ensured.

Wherein, most nacelle is at the during operation, and required heat dissipation amount of wind is less, consequently only need to lead the very few some of the air current of rotor output to the nacelle, and the air current through drainage piece 2 drainage gets into from the air intake 11 of the cabin body 1 and flows out through the cabin body 1 lower extreme, can not cause the influence to rotor craft's normal flight.

Example 2

Based on the structure and principle described in embodiment 1, the present embodiment provides a drone, including a body and a rotor drone aircraft pod as described in embodiment 1.

It can be understood that the nacelle 1 is located below the airframe and close to a rotor of the drone, so that when the linear actuator 3 is retracted, the flow guide 2 is at least partially located in the irradiation range of the rotor flow. And according to the task executed by the unmanned aerial vehicle, corresponding devices such as a camera, an illuminating lamp and the like are installed in the nacelle.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and the technical essence of the present invention is that within the spirit and principle of the present invention, any simple modification, equivalent replacement, and improvement made to the above embodiments are all within the protection scope of the technical solution of the present invention.

Claims (8)

1. The utility model provides a rotor unmanned aerial vehicle aircraft nacelle, includes cabin body (1), its characterized in that, cabin body (1) is provided with drainage piece (2), when cabin body (1) hoist and mount are under rotor aircraft drainage piece (2) are located the route of the air current that the rotor produced.

2. A rotorcraft unmanned aerial vehicle pod according to claim 1, wherein the nacelle (1) is provided with an air inlet (11), the air inlet (11) being located on a drainage path of the drainage member (2).

3. The rotorcraft aircraft pod of claim 2, wherein the air inlet (11) is located on one side of the nacelle (1) in the height direction.

4. The rotorcraft pod according to claim 2, wherein the angle between the length direction of the flow-directing member (2) and the height direction of the nacelle (1) is adjustable.

5. A rotorcraft unmanned aerial vehicle pod according to claim 4, wherein the pod (1) is provided with a linear actuator (3), the central portion of the flow guide (2) is articulated to the pod (1), one end of the linear actuator (3) is articulated to the pod (1), and the other end of the linear actuator (3) is articulated to one end of the flow guide (2).

6. A rotary wing drone aircraft pod according to any one of claims 2 to 5, characterised in that the nacelle (1) is provided with air outlets (12).

7. A rotary wing drone aircraft pod according to claim 6, characterised in that the air outlet (12) is located below the nacelle (1).

8. The rotorcraft nacelle according to claim 6, characterised in that the side of the drainage member (2) facing the nacelle (1) is provided with drainage slots.

Images