Ventral fin radiator suitable for aircraft

Abstract

The invention belongs to a ventral fin type radiator suitable for an aircraft, and discloses a ventral fin type radiator suitable for an aircraft, which comprises a flow guide body, a mounting bracketand a radiating main body, the radiating main body is connected with the flow guide body front and back, is integrally of an aircraft ventral fin structure, and is connected with the aircraft main body through the mounting bracket; the heat dissipation body comprises an upper cover plate, a lower cover plate, cooling fins, a lubricating oil inlet, a lubricating oil outlet and a lubricating oil channel, the upper cover plate and the lower cover plate are arranged on the upper sides and the lower sides of the cooling fins respectively, and the lubricating oil inlet and the lubricating oil outlet penetrate through the upper cover plate to extend out of the installation support and are connected with an inlet and an outlet of the lubricating oil channel. And the lubricating oil channel bypasses the interior of the cooling fin. The ventral fin type radiator does not occupy the internal space of a machine body and does not need an independent air inlet and outlet pipeline, so that the internal space is saved, and the structural weight is reduced; and the heat exchange power of the radiator is high, the dual-redundancy design of the main channel and the standby channel is adopted, and the working reliability of the product is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft design, and relates to an aircraft radiator structure, in particular to a ventral fin radiator suitable for aircraft. Background technique [0002] One of the oil cooling commonly used on aircraft is the air-oil radiator, which uses air as the cooling medium to exchange heat with the oil to cool the hot oil in the oil system and reduce the temperature of the oil to meet the requirements requirements for recycling. The air-lubricating oil radiator on the existing aircraft is mostly installed inside the fuselage as an independent component, and it is necessary to introduce one or more air streams from the front end of the aircraft or a certain position to dissipate heat from the radiator. This solution has the following aspects: question: [0003] 1. The size of the external structure is limited by the space inside the machine; [0004] 2. The intake and exhaust pipes need to be designed separat...

AI Technical Summary

Problems solved by technology

[0003]1. The size of the external structure is limited by the space inside the machine;

[0004]2. The intake and exhaust pipes need to be designed separately to introduce air outside the aircraft, which takes up a lot of space and increases the weight of the aircraft;

[0005]3. Affected by aircraft aerodynamics and other factors, problems such as limited air flow are introduced

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