Controllable engine heat management unmanned aerial vehicle cover

Abstract

The utility model discloses a controllable engine thermal management unmanned aerial vehicle hood. The overall structure comprises a fuselage, an engine hood, an engine, an air inlet spoiler, a servo, an engine hood air inlet and an engine hood air outlet. The engine cover is fixed to the installation position of an engine, and hole sites on the periphery of the engine cover are connected with holes reserved in an engine body; an air inlet spoiler is designed at the position of an air inlet of the engine hood, and the air inlet spoiler is fixed on the engine hood through a hinge; the air inlet spoiler is connected with the servo machine through a connecting rod, the servo machine controls the angle of a rocker arm of the servo machine through a PWM signal, the rocker arm of the servo machine rotates by a corresponding angle to control the air inlet spoiler to increase or reduce the air inflow of the engine hood, and therefore heat management of the engine of the unmanned aerial vehicle is achieved. Through effective heat management, the unmanned aerial vehicle can be helped to keep the normal working temperature in the high-temperature environment, and the performance and efficiency of the engine are improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of thermal management of unmanned aerial vehicle engines, and in particular relates to a unmanned aerial vehicle cover with controllable engine thermal management. Background Art

[0002] With the widespread application of drones in various fields, the requirements for drone performance are also increasing. Drones are mainly composed of airframe structure, power system, flight control system, and avionics system. The airframe structure is an important part of drones. In the airframe structure, the load-bearing structure is mainly used to bear various loads during the flight of the drone. The performance of the load-bearing structure directly affects the flight safety of the drone.

[0003] Most of the existing UAV power systems use piston engines as the main power form. In order to ensure the stability of the engine working at high altitude and low temperature, insulation measures need to be taken for the engine cooling duct. Insulation measures will not only increase the overall weight of the UAV, reduce the flight performance and endurance of the UAV, and affect its flight efficiency and operational flexibility; it will also make it difficult for the engine to dissipate heat, causing the engine to run at high temperature, reducing fuel combustion efficiency, increasing fuel consumption, and thus reducing the endurance of the UAV. Insulation measures also increase the complexity of the UAV power system, making maintenance and repair more difficult.

[0004] Based on this situation, the functional requirements for engine thermal management are particularly prominent. The present application provides a controllable thermal management UAV engine hood. The engine hood is fixed to the position where the engine is installed, and is interconnected with the holes reserved in the fuselage through the holes around the engine hood; the engine hood includes an air inlet and an air outlet, and an air inlet spoiler is designed at the air inlet position, and the air inlet spoiler is fixed to the engine hood through a hinge. The air inlet spoiler is connected to the servo through a connecting rod, and the servo controls the angle of the servo rocker arm through a PWM signal. The servo rocker arm rotates the corresponding angle to control the air inlet spoiler to increase or decrease the air intake of the engine hood, thereby realizing the thermal management of the UAV engine. Summary of the invention

[0005] The present invention provides a controllable engine thermal management unmanned aerial vehicle cover, which solves the problems of heavy fuselage weight and insufficient stability by designing a novel load-bearing bulkhead structure.

[0006] To achieve the above objectives, this application provides the following solutions:

[0007] A controllable thermal management UAV engine cover. It includes: fuselage, engine cover, engine;

[0008] The engine is fixed at the tail of the aircraft, and the aircraft uses the engine as a tail thruster. The engine cover is fixed at the tail of the fuselage to wrap the engine; the holes around the engine cover are connected to the holes reserved in the fuselage.

[0009] The engine comprises a heat sink; the engine hood comprises an engine hood air inlet and an engine hood air outlet.

[0010] Furthermore, the heat sink is arranged at the cylinder head position of the engine, and the engine hood air inlet and the engine hood air outlet are respectively arranged at the bottom of the heat sink; during the flight of the drone, the generated air flow passes through the cylinder head position of the engine from the engine hood air inlet and the engine hood air outlet.

[0011] Furthermore, an air inlet spoiler is provided at the air inlet position of the engine hood, and the air inlet spoiler is connected to the engine hood via a hinge.

[0012] Furthermore, a servo is provided at the bottom of the engine hood, and the servo is connected to the air inlet spoiler via a connecting rod.

[0013] Furthermore, the engine hood is made of composite materials and will not deform or change in quality under harsh environments such as high temperature and low temperature; the air inlet spoiler and the engine hood are fixed to the hinge with screws; the servo and the engine hood are fixed with screws, and the servo controls the rotation angle through the avionics system of the fuselage, and the servo controls the angle of the servo rocker arm through a PWM signal, and the servo rocker arm rotates the corresponding angle to control the air inlet spoiler to increase or decrease the air intake of the engine hood and control the air intake of the engine hood air inlet; thereby controlling the air volume of the engine cylinder body passing through the aircraft during flight, and realizing thermal management of the engine.

[0014] Beneficial effects of the technical solution of this application:

[0015] The controllable engine thermal management hood in the present application can effectively manage and control the heat of the engine by controlling the air intake of the engine hood air intake, preventing overheating from causing equipment failure or performance degradation.

[0016] Through effective thermal management, this application can help drones maintain normal operating temperatures in high temperature environments and improve engine performance and efficiency; this is very important for long-term flights, high-load missions, and operations in extreme climate conditions.

[0017] The engine hood of the present application is a composite material and will not deform or change in quality under harsh environments such as high and low temperatures. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative labor.

[0019] Figure 1 It is a schematic diagram of the structure of a controllable engine thermal management UAV cover;

[0020] Figure 2 It is a schematic diagram of the rotation of the air inlet spoiler of a controllable engine thermal management UAV cover;

[0021] Reference numerals:

[0022] 1. Fuselage; 2. Engine hood; 3. Engine; 4. Air inlet spoiler; 5. Hinge; 6. Connecting rod; 7. Servo; 21. Engine hood air inlet; 22. Engine hood air outlet. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of this application.

[0024] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the present application is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0025] like Figure 1 As shown, a controllable thermal management UAV engine cover comprises: a fuselage 1, an engine cover 2, and an engine 3;

[0026] The engine 3 is fixed at the tail of the aircraft, and the aircraft uses the engine 3 as a tail thrust power. The engine cover 2 is fixed at the tail of the fuselage 1 to wrap the engine 3; the holes around the engine cover 2 are connected to the holes reserved in the fuselage 1.

[0027] The engine 3 includes a heat sink; the engine hood 2 includes a engine hood air inlet 21 and an engine hood air outlet 22; the heat sink is arranged at the cylinder head position of the engine 3, and the engine hood air inlet 21 and the engine hood air outlet 22 are respectively arranged at the bottom of the heat sink; during the flight of the drone, the air flow generated passes through the cylinder head position of the engine 3 through the engine hood air inlet 21 and the engine hood air outlet 22; an air inlet spoiler 4 is arranged at the position of the engine hood air inlet 21, and the air inlet spoiler 4 is connected to the engine hood 2 through a hinge 5; a servo 7 is arranged at the bottom of the engine hood 2, and the servo 7 is connected to the air inlet spoiler 4 through a connecting rod 6.

[0028] The engine hood 2 is made of composite materials and will not deform or change in quality under harsh environments such as high temperature and low temperature; the air inlet spoiler 4 is fixed to the engine hood 2 by hinges 5 using screws; the servo 7 is fixed to the engine hood 2 by screws, and the servo 7 controls the rotation angle through the avionics system of the fuselage 1, and controls the angle of the servo 7 rocker arm through a PWM signal. The servo 7 rocker arm rotates the corresponding angle to control the air inlet spoiler 4 to increase or decrease the air intake of the engine hood 2, and control the air intake of the engine hood air inlet 21; thereby controlling the air volume of the engine 3 cylinder body passing through the aircraft during flight, and realizing thermal management of the engine 3.

[0029] like Figure 2 As shown, when the heat of the engine 3 is too high, the servo 7 controls the air inlet spoiler 4 as shown in FIG. Figure 2 With the rotation angle in the direction of the arrow shown, the airflow flows from the engine hood air inlet 21 in the direction A to the engine hood air outlet 22 in the direction B, thereby achieving thermal management of the engine 3 .

[0030] It is worth noting that this embodiment only shows a structural layout of a controllable engine thermal management UAV cover, but it does not mean that the controllable engine thermal management UAV cover provided by this application has only this one form, and the specific structural form can be adjusted according to the specific UAV structure.

[0031] In the description of the present application, it should be understood that the terms "front", "back", "up", "down", "outside", "inside", "horizontal", "top", "bottom", "surface", "bottom layer", "top layer", "upper", "lower", "bottom", "top", "inside", "surface", "center", "right", "middle" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0032] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "connected", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be the internal connection of two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0033] The embodiments described above are only descriptions of the preferred methods of the present application, and are not intended to limit the scope of the present application. Without departing from the design spirit of the present application, various modifications and improvements made to the technical solutions of the present application by those skilled in the art should all fall within the scope of protection determined by the claims of the present application.

Claims

1. A controllable engine thermal management drone cover, characterized in that: The aircraft includes a fuselage, an engine cover, and an engine; The engine is fixed to the tail of the aircraft, the aircraft uses the engine as a tail thruster, and the engine cover is fixed to the tail of the fuselage to wrap the engine; The engine comprises a heat sink; the engine hood comprises an engine hood air inlet and an engine hood air outlet.

2. The controllable engine thermal management drone cover according to claim 1, characterized in that: The heat sink is arranged at the cylinder head position of the engine, and the engine hood air inlet and the engine hood air outlet are respectively arranged at the bottom of the heat sink; during the flight of the drone, the generated air flow passes through the cylinder head position of the engine from the engine hood air inlet and the engine hood air outlet.

3. The controllable engine thermal management drone cover according to claim 1, characterized in that: An air inlet spoiler is provided at the air inlet position of the engine hood, and the air inlet spoiler is connected to the engine hood via a hinge.

4. The controllable engine thermal management drone cover according to claim 3, characterized in that: A servo is provided at the bottom of the engine hood, and the servo is connected to the air inlet spoiler through a connecting rod.

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