A Method of Inductive Construction of Equivalent Microenvironment of Average Temperature Around a Fighter Pilot

Abstract

The invention relates to an inductive constructing method for an equivalent microenvironment of an average temperature around a fighter plane pilot. The inductive constructing method comprises the following steps: 1) confirming the position of an air temperature sensor: mounting the air temperature sensor (3) at any position in a flight deck; and 2) mounting a tubule and an ejector: mounting the tubule (2) at the part, close to the air temperature sensor (3), of an air conditioner pipeline (4), then connecting the ejector (1) to the port of the tubule (2), confirming the geometric dimension of the tubule (2), by acquiring a distance between the outlet of the ejector (1) and the air temperature sensor (3) in the manner of flight deck temperature flow-field simulation calculation or test surveying and mapping under the condition that the air temperature induced by the air temperature sensor (3) is equal to the average temperature around the fighter plane pilot. The method is used for realizing the equivalent inductive construction for the average temperature around the fighter plane pilot, thereby enabling the average temperature around the fighter plane pilot to become measurable and controllable and promoting the development of a flight deck temperature control technique.

Description

technical field [0001] The invention relates to the technical field of environmental control, in particular to the temperature control technology of a fighter cockpit. Background technique [0002] Generally, the aircraft adopts a conventional control method to control the ambient temperature around the pilot, that is, to select an installation point that best represents the average temperature of the cockpit by means of experiments, and install the temperature sensor at this position to provide temperature control system Cockpit air temperature signal. [0003] This method has a series of disadvantages. First of all, it is difficult to choose the installation position of the temperature sensor, because the cockpit space of general fighter jets is relatively limited, and it is necessary to measure a point in the cockpit flow field that best represents the average temperature of the cockpit through a large number of experiments. Whether the temperature sensor can be install...

AI Technical Summary

Problems solved by technology

First of all, it is difficult to choose the installation position of the temperature sensor, because the cockpit space of general fighter jets is relatively limited, and it is necessary to measure a point in the cockpit flow field that best represents the average temperature of the cockpit through a large number of experiments. Whether the temperature sensor can be installed at this point is still subject to the layout environment in the cockpit

In addition, the air flow in the cockpit is restricted by the layout of the air-conditioning pipelines, so it has a fixed flow field characteristic. However, it is extremely difficult to capture the average temperature around the driver due to the influence of the personnel in the cockpit and the thermal load of the equipment. Therefore, even It is still difficult to accurately represent the average temperature around the driver at the installation point of the temperature sensor through a large number of experimental mapping.

Secondly, affected by the temperature field changes in the cockpit, the temperature point responded by the temperature sensor is likely to form a temperature dead space, which reduces the control accuracy of the cockpit temperature control system and affects the response speed of the system.

Images