Device and method for testing synthesis parameter of aviation piston engine

Abstract

The invention discloses an aviation piston engine all-purpose parameter test device and a method thereof, the test device includes: a control unit TCU, an IMS, a flight control computer, a servo-electric motor, a turbo-charger and an engine. The turbo-charger is driven by the engine discharge gas and supplies the turbo-charged air for the engine, the servo-electric motor is controlled by the control signal outputted from the turbo control unit TCU which senses and calculates correlation parameters, which causes the connected valve deflexion, in order to change the turbo-charged air pressure which is transferred from the turbo-charger to the aviation piston engine. The all-purpose parameter test system IMS, taken the singlechip as the kernel, obtains engines running status parameter and TCU controlling parameter, judges the two parts of parameters with overrun judgment and gives status code according to the fault mode, packs this two parts of parameters and status codes; transmits the packed parameters to the flight control computer; the flight control computer then carries the followed processing and transmits the data down to the ground.

Description

technical field [0001] The invention belongs to the technical field of aviation testing, and in particular relates to a comprehensive parameter testing device and method of an aviation piston engine. Background technique [0002] As we all know, the characteristic of UAV system is that there is no pilot. The state parameters of the engine and airborne equipment of ordinary manned aircraft are displayed on the pilot's operation panel through the instrument, while the unmanned aerial vehicle needs to convert all the measurement parameters through A / D and then download them to the ground through the measurement and control wireless link. Among them, the test parameters of the engine part are no exception. [0003] When the conventional UAV engine test parameters are downloaded from the ground, firstly, the test parameters and their sensors are determined according to the needs of the engine test, and then the sensor conditioning circuit is designed and manufactured. The adjust...

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Problems solved by technology

[0008] The purpose of the present invention is to solve the problems existing in the existing engine parameter test method, and adopt the comprehensive parameter test system IMS to complete the acquisition, conversion and temporary storage of the engine state parameters and TCU parameters, and these parameters are exceeded Inspection and failure mode judgment, finally integrate the data frame, and then transmit the integrated data frame containing the engine comprehensive test parameters to the flight control computer in the form of digital signal, so as to reduce the occupation of the flight control computer data acquisition channel by the engine measurement parameters , reduce the resource consumption of the flight control computer in the digital-to-analog conversion operation and processing of the engine measurement parameters, reduce the measurement error caused by interference in the analog signal transmission process, and improve the fault isolation rate and fault detection rate

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