Helicopter torsional vibration excitation test method based on fadec control system

A technology of a control system and a test method, applied in the field of aviation applications, to achieve the effect of large excitation frequency range and good response effect

CN107792391BActive Publication Date: 2020-12-29CHINESE FLIGHT TEST ESTAB
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Publication Date
2020-12-29

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Abstract

The invention belongs to the field of aviation application, and relates to a helicopter torsional vibration stimulating test method based on a FADEC control system. The helicopter torsional vibrationstimulating test method selects the stimulating mode, designs the stimulating system, and gives out the stimulating method. An effective stimulating implementation means is provided for a helicopter torsional vibration test, so that the helicopter torsional vibration system generates an appropriate structural dynamics response, test analysis data for determining the helicopter torsional vibrationsystem frequency and evaluating the coupling stability of the torsional vibration system and the FADEC control system are provided for engineers, and accordingly the problem that the stimulating modeof the torsional vibration test is simplex in the development of helicopter versions in China is solved. The helicopter torsional vibration stimulating test method firstly proposes the torsional vibration test stimulating system based on the FADEC engine control system, and the stimulating system is completely different from a traditional stimulating mode through the propeller pitch. The helicopter torsional vibration stimulating test method adds a stimulating signal into a helicopter system through the FADEC engine control system and stimulates a helicopter to respond by treating a power turbine rotation speed signal as the stimulating signal.
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Description

technical field

[0001] The invention belongs to the field of aviation applications, and relates to an excitation system and an excitation method for a helicopter torsional vibration test based on a FADEC control system. Background technique

[0002] The development process of helicopters reflects the development process of my country's aviation industry. It has experienced from the introduction of imitation, learning and digestion to the final independent research and development. On the basis of accumulating certain capabilities, helicopters with independent intellectual property rights are gradually designed. In the early days, the introduction of imitation in my country mainly adopted the means of surveying and mapping to design and develop helicopters. In this process, due to the constraints of surveying and mapping technology and the limitation of technological level, the helicopters produced will have some problems that the prototype does not have, such as torsional vib...

Examples

Embodiment Construction

[0030] Technical principle

[0031] The technical principle of the helicopter torsional vibration test excitation system and excitation method based on the FADEC control system: By adding the power turbine speed disturbance excitation signal to the helicopter FADEC engine control system, the torsional vibration system composed of the rotor / tail rotor / transmission system and the engine Controls coupled system response. Among them, the FADEC control system is the engine control system.

[0032] In order to analyze the inherent characteristics of the torsional vibration system and the coupling stability characteristics between the torsional vibration system and the engine control system, it is necessary to obtain test data with a high signal-to-noise ratio.

[0033] By adding the power turbine speed excitation signal to the helicopter FADEC control system, high-quality response data is obtained, and then the characteristics of the helicopter torsional vibration system are evalua...