Power supply pod for aircraft

Abstract

The utility model discloses a power supply pod for an aircraft. The power supply pod comprises a pod shell, a power distribution management system, a fuel tank, a power generation control system, an engine and a generator, a power distribution management cabin, a fuel cabin and a power cabin are arranged in the pod shell, the power distribution management system is arranged in the power distribution management cabin, the fuel tank is arranged in the fuel cabin, and the engine and the generator are arranged in the power cabin; the fuel cabin is located in the middle of the pod shell, and the fuel tank and the power generation control system are distributed in the fuel cabin in the vertical direction. According to the scheme, the problems that in the prior art, the gravity center change amplitude of a power supply pod is large, and adverse effects are easily generated on an aircraft are solved.

Description

Technical Field

[0001] This utility model relates to power supply equipment for unmanned aerial vehicles, specifically a power supply pod for aircraft. Background Technology

[0002] An aircraft power supply pod is a device that is externally attached to an aircraft to provide electrical power.

[0003] Chinese patent document CN114633890A discloses a power supply pod, including an air guide shroud, an electrical system compartment, a fuel tank, and an engine compartment. The air guide shroud, electrical system compartment, fuel tank, and engine compartment are sequentially connected. The air guide shroud has an air inlet. The fuel tank contains a fuel container, and a cooling channel is formed between the outer wall of the fuel container and the inner wall of the fuel compartment. Airflow entering through the air inlet passes through the electrical system compartment and the cooling channel into the engine compartment to dissipate heat from the engine. This prior art power supply pod also includes an air guide shroud, electrical system compartment, fuel tank, and engine compartment, wherein the air guide shroud, electrical system compartment, fuel tank, and engine compartment are sequentially connected. The air guide shroud has an air inlet, and the fuel tank contains a fuel container. A cooling channel is formed between the outer wall of the fuel container and the inner wall of the fuel compartment. Thus, airflow entering through the air inlet into the air guide shroud passes through the electrical system compartment and the cooling channel into the engine compartment to dissipate heat from the engine. Compared to traditional power supply pods, the power supply pod provided in this embodiment places the fuel tank between the electrical system compartment and the engine compartment. Simultaneously, a fuel container is installed within the fuel tank, and a cooling channel is formed between the outer wall of the fuel container and the inner wall of the fuel tank. This cooling channel allows airflow entering through the air inlet of the air deflector to flow towards the engine compartment for engine cooling. In other words, the cooling channel allows external cooling airflow to flow directionally into the engine compartment. This improves the heat dissipation performance of the power supply pod under the cooling effect of the external cooling airflow flowing in through the air inlet, increasing the cooling effect on the working components within the power supply pod. This maintains a stable internal temperature, preventing overheating due to rapid temperature increases, thereby reducing instability in UAV signals caused by excessive temperature and improving the stability and reliability of the system operation.

[0004] The above-mentioned existing technologies have the following problems when in use: the cross-section of the pod is circular, and in order to match the center of gravity of the aircraft, an additional connecting frame is required for mounting, which increases the structural complexity; the engine uses air cooling, which makes it difficult to control the airflow at the air inlet, and the large variety of parts makes assembly more difficult; the fuel tank occupies most of the space in the fuel compartment, causing the center of gravity of the power supply pod to change significantly as the fuel in the fuel tank is consumed, which can easily have an adverse effect on the aircraft. Utility Model Content

[0005] The purpose of this invention is to provide a power supply pod for aircraft, in order to solve the problem that the center of gravity of the power supply pod in the prior art changes significantly, which can easily have an adverse effect on the aircraft.

[0006] To achieve the above objectives, the basic solution of this utility model provides a power supply pod for aircraft, including a pod shell, a power distribution management system, a fuel tank, a power generation control system, an engine, and a generator; the pod shell is internally provided with a power distribution management compartment, a fuel compartment, and a power compartment, the power distribution management system is located in the power distribution management compartment, the fuel tank is located in the fuel compartment, and the engine and generator are located in the power compartment; the fuel compartment is located in the middle of the pod shell, and the fuel tank and the power generation control system are vertically distributed within the fuel compartment.

[0007] The beneficial effects of this basic scheme are as follows: by adopting this configuration, the center of gravity of the fuel tank is close to the center above the center of the power supply pod, and the weight of the fuel tank is increased by using the power generation control system. At the same time, the range of change of the center of gravity of the fuel tank is reduced, which helps to reduce the change of the center of gravity of the power supply pod caused by the consumption of fuel, thereby reducing the adverse effects of the change of the center of gravity of the power supply pod on the aircraft.

[0008] Preferably, the fuel tank is located in the upper part of the fuel compartment, and the power generation control system is located in the lower part of the fuel compartment. With this arrangement, the center of gravity of the fuel tank gradually decreases as fuel is consumed, and the direction of the movement of the center of gravity of the fuel tank is towards the direction of the power generation control system. This results in a relatively small change in the center of gravity of the entire pod, which helps to further reduce the adverse effects of the change in the center of gravity of the power supply pod on the aircraft.

[0009] Preferably, the power distribution management compartment, fuel compartment, and power compartment are arranged sequentially along the length of the pod's outer shell. This arrangement helps to reduce the cross-sectional area of ​​the power supply pod, thereby reducing drag.

[0010] Preferably, the pod's outer shell has a rectangular cross-section. This design increases the contact area between the pod's outer shell and the aircraft, facilitating the installation and connection of the power supply pod and reducing the complexity of the structural design.

[0011] Preferably, the generator is an integrated starter-generator motor. This configuration allows the generator to function as a starter motor during engine startup and as a generator once the engine is running smoothly, thus simplifying the structure and improving the power supply capacity of the power pod.

[0012] Preferably, the engine is a water-cooled engine. This configuration improves the engine's cooling effect, thereby reducing the heat dissipation pressure on the power supply pod and promoting its stable operation.

[0013] Preferably, the water-cooled radiator of the engine's cooling system is located at the bottom of the fuel tank, near the electrical control compartment. This arrangement ensures the water-cooled radiator is in contact with the external cooling airflow from the electrical control compartment as early as possible, thereby improving the radiator's heat dissipation effect and consequently enhancing the engine's water-cooling performance, which is beneficial for stable engine operation.

[0014] Preferably, the power distribution management system includes a T-BOX remote monitoring system. The T-BOX remote monitoring system refers to a system with remote communication capabilities. This setup facilitates remote monitoring of the power supply pod's equipment status via backend devices and allows for timely access to the pod's information, thereby improving the practicality of the power supply pod. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of an embodiment of a power supply pod for an aircraft according to the present invention;

[0016] Figure 2 for Figure 1 A schematic diagram of the interior of the pod's outer shell;

[0017] Figure 3 for Figure 1 The left view. Detailed Implementation

[0018] The following detailed description illustrates the specific implementation method:

[0019] The reference numerals in the accompanying drawings include: pod outer shell 1, power distribution management compartment 2, fuel tank 3, power compartment 4, power distribution management system 5, fuel tank 6, power generation control system 7, engine 8, exhaust port 9.

[0020] The basic implementation examples are as follows: Figure 1 , Figure 2 and Figure 3 As shown: An aircraft power supply pod includes a pod shell 1, a power distribution management system 5, a fuel tank 6, a power generation control system 7, an engine 8, and a generator. In this embodiment, the pod shell 1 has a rectangular cross-section. Inside the pod shell 1, along its length, are arranged a power distribution management compartment 2, a fuel tank 3, and a power compartment 4. A cooling air inlet is provided at the bottom of the power distribution management compartment 2, facilitating the entry of external cooling airflow into the interior of the power distribution management compartment 2.

[0021] The power distribution management system 5 is located within the power distribution management compartment 2. The power distribution management system 5 also includes a T-BOX remote monitoring system, facilitating remote monitoring of equipment status and other operations. The fuel tank 6 is located within the fuel compartment 3, as is the power generation control system 7. Specifically, the fuel tank 6 is located at the top of the fuel compartment 3, and the power generation control system 7 is located at the bottom. The engine 8 and generator are located within the power compartment 4. An exhaust port 9 is located at the bottom of the power compartment 4, facilitating the installation of the engine 8's exhaust pipe for discharging exhaust gases.

[0022] In this embodiment, the generator is an integrated starter-generator motor; the engine 8 is a water-cooled engine 8. The water-cooled radiator of the engine 8's cooling system is located at the bottom of the fuel tank 3, near the power distribution management compartment 2. This allows the water-cooled radiator to come into contact with the external cooling airflow from the power distribution management compartment 2 as early as possible, thereby improving the radiator's heat dissipation effect and thus improving the water-cooling effect of the engine 8. This design positions the center of gravity of the fuel tank 6 closer to the center of the power supply pod, and utilizes the power generation control system 7 to increase the weight at the fuel tank 3. This also reduces the range of changes in the center of gravity of the fuel tank 6, thus minimizing the impact of changes in the power supply pod's center of gravity on the aircraft.

[0023] The above description is merely an embodiment of this utility model, and common knowledge such as specific structures and characteristics of the solution is not described in detail here. It should be noted that those skilled in the art can make several modifications and improvements without departing from the structure of this utility model, and these should also be considered within the protection scope of this utility model. These modifications and improvements will not affect the effectiveness of the implementation of this utility model or the practicality of the patent.

Claims

1. A power supply pod for an aircraft, comprising a pod shell, a power distribution management system, a fuel tank, a power generation control system, an engine, and a generator; the pod shell houses a power distribution management compartment, a fuel tank, and a power compartment, the power distribution management system being located within the power distribution management compartment, the fuel tank within the fuel tank, and the engine and generator within the power compartment; the fuel tank is located in the middle of the pod shell, characterized in that: The fuel tank and power generation control system are arranged vertically within the fuel compartment.

2. The power supply pod for an aircraft according to claim 1, characterized in that: The fuel tank is located in the upper part of the fuel compartment, and the power generation control system is located in the lower part of the fuel compartment.

3. The power supply pod for an aircraft according to claim 2, characterized in that: The power distribution management compartment, fuel compartment, and power compartment are arranged sequentially along the length of the pod's outer shell.

4. The power supply pod for an aircraft according to claim 3, characterized in that: The pod's outer shell has a rectangular cross-section.

5. The power supply pod for an aircraft according to claim 4, characterized in that: The generator is a starter-generator integrated motor.

6. The power supply pod for an aircraft according to claim 5, characterized in that: The engine is a water-cooled engine.

7. The power supply pod for an aircraft according to claim 6, characterized in that: The engine's cooling system has a water-cooled radiator located at the bottom of the fuel tank on the side near the power distribution management compartment.

8. The power supply pod for an aircraft according to claim 7, characterized in that: The power distribution management system includes the T-BOX remote monitoring system.

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