CN108088599A - A kind of helicopter electromagnetic actuator power output variation characteristic test method - Google Patents
A kind of helicopter electromagnetic actuator power output variation characteristic test method Download PDFInfo
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- CN108088599A CN108088599A CN201711250368.3A CN201711250368A CN108088599A CN 108088599 A CN108088599 A CN 108088599A CN 201711250368 A CN201711250368 A CN 201711250368A CN 108088599 A CN108088599 A CN 108088599A
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- Prior art keywords
- electromagnetic actuator
- helicopter
- power output
- variation characteristic
- test method
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
Abstract
The invention discloses a kind of helicopter electromagnetic actuator power output variation characteristic test methods.The helicopter electromagnetic actuator output force test method includes the following steps：Step 1：Force snesor is installed in helicopter electromagnetic actuator in vibration active control system；Step 2：Signal receiving end and signal sending end are connected with each other；Step 3：Data acquisition sending device is controlled to send multiple sinusoidal scanning signal f under different voltages to the helicopter electromagnetic actuator in vibration active control system；Step 4：Data acquisition sending device gathers each force value F of the force snesor under each different voltages；Step 5：The amplitude-frequency rate response curve and power output under different voltages are analyzed, draws the resonant electromagnetic actuator power output of active vibration control with frequency and the variation characteristic of input voltage.The helicopter electromagnetic actuator power output variation characteristic test method of the application can design for helicopter vibration active control system and provide direction.
Description
Technical field
The present invention relates to helicopter electromagnetic actuator technical field of measurement and test, more particularly to a kind of helicopter electromagnetic actuator
Power output variation characteristic test method.
Background technology
With the development of helicopter model and the progress of technology, around helicopter damping technology, rotor is successively developed and has moved
The passive damping technologies such as mechanics designing technique, dynamic absorber technology, focusing flexible vibration isolation technique.User is to helicopter vibration water
The increasingly raising of flat control requirement, traditional technology are difficult to meet damping requirements.
The main advantage of helicopter application vibration active control system (AVCS) be save weight, be applicable in wide frequency range,
Flexible arrangement.AVCS substitutes traditional passive type damper, and helicopter weight is made to reduce up to 150Ib.Followed by comparing
Vibration performance and parts longer fatigue life are improved in wide frequency range.The basic principle of AVCS is to pass through survey
The vibration on helicopter key position is measured, and control force is applied by active actuator and is offseted therewith, final realize reduces
The purpose of body vibration level.Active vibration control actuator is one of core component of AVCS, its performance will be determined directly
The actual effect that AVCS controls body vibration.
The prior art during exemplary position vibration environmental problem, can not also detect in helicopter simulating cabin and go straight up to electromechanics
Magnetic actuator power output variation characteristic.
Thus, it is desirable to have a kind of technical solution is come at least one drawbacks described above for overcoming or at least mitigating the prior art.
The content of the invention
It is an object of the invention to provide a kind of helicopter electromagnetic actuator power output variation characteristic test methods to overcome
Or at least mitigate at least one drawbacks described above of the prior art.
To achieve the above object, the present invention provides a kind of helicopter electromagnetic actuator power output variation characteristic test method,
The helicopter electromagnetic actuator output force test method includes the following steps：
Step 1：Force snesor is installed on helicopter electromagnetic actuator in vibration active control system is vertical；
Step 2：The signal receiving end of helicopter electromagnetic actuator in vibration active control system and data acquisition are sent out
The signal sending end of equipment is sent to be connected with each other；
Step 3：Data acquisition sending device is controlled to send multiple sinusoidal scanning signal f under different voltages to vibration active
Helicopter electromagnetic actuator in control system；
Step 4：Data acquisition sending device gathers each force value F of the force snesor under each different voltages；
Step 5：The amplitude-frequency rate response curve and power output under different voltages are analyzed, draws the resonant of active vibration control
Electromagnetic actuator power output is with frequency and the variation characteristic of input voltage.
Preferably, the helicopter electromagnetic actuator is multi-layer stacks spring resonance formula electromagnetic actuator.
The helicopter electromagnetic actuator power output variation characteristic test method of the application can be used for domestic all structures at present
The multi-layer stacks spring resonance formula electromagnetic actuator power output test of the active vibration control of type, is helicopter vibration active control
System design provides direction.
Description of the drawings
Fig. 1 is that the flow of the helicopter electromagnetic actuator power output variation characteristic test method of the application first embodiment is shown
It is intended to.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown is for only for ease of the description present invention and simplifies description rather than instruction or imply signified dress
It puts or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
Fig. 1 is that the flow of the helicopter electromagnetic actuator power output variation characteristic test method of the application first embodiment is shown
It is intended to.
Helicopter electromagnetic actuator output force test method as shown in Figure 1 includes the following steps：
Step 1：Force snesor is installed on helicopter electromagnetic actuator in vibration active control system is vertical；
Step 2：The signal receiving end of helicopter electromagnetic actuator in vibration active control system and data acquisition are sent out
The signal sending end of equipment is sent to be connected with each other；
Step 3：Data acquisition sending device is controlled to send multiple sinusoidal scanning signal f under different voltages to vibration active
Helicopter electromagnetic actuator in control system；
Step 4：Data acquisition sending device gathers each force value F of the force snesor under each different voltages；
Step 5：The amplitude-frequency rate response curve and power output under different voltages are analyzed, draws the resonant of active vibration control
Electromagnetic actuator power output is with frequency and the variation characteristic of input voltage.
The helicopter electromagnetic actuator power output variation characteristic test method of the application can be used for domestic all structures at present
The multi-layer stacks spring resonance formula electromagnetic actuator power output test of the active vibration control of type, is helicopter vibration active control
System design provides direction.
In the present embodiment, helicopter electromagnetic actuator is multi-layer stacks spring resonance formula electromagnetic actuator.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still
It can modify to the technical solution recorded in foregoing embodiments or which part technical characteristic is equally replaced
It changes；And these modifications or replacement, the essence of appropriate technical solution is not made to depart from the essence of various embodiments of the present invention technical solution
God and scope.
Claims (2)
1. a kind of helicopter electromagnetic actuator power output variation characteristic test method, which is characterized in that the helicopter electromagnetic is made
Dynamic device output force test method includes the following steps：
Step 1：Force snesor is installed on helicopter electromagnetic actuator in vibration active control system is vertical；
Step 2：The signal receiving end of helicopter electromagnetic actuator in vibration active control system and data acquisition transmission are set
Standby signal sending end is connected with each other；
Step 3：Data acquisition sending device is controlled to send multiple sinusoidal scanning signal f under different voltages to active vibration control
Helicopter electromagnetic actuator in system；
Step 4：Data acquisition sending device gathers each force value F of the force snesor under each different voltages；
Step 5：The amplitude-frequency rate response curve and power output under different voltages are analyzed, draws the resonant electromagnetism of active vibration control
Actuator power output is with frequency and the variation characteristic of input voltage.
2. helicopter electromagnetic actuator power output variation characteristic test method as described in claim 1, which is characterized in that described
Helicopter electromagnetic actuator is multi-layer stacks spring resonance formula electromagnetic actuator.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711250368.3A CN108088599A (en) | 2017-12-01 | 2017-12-01 | A kind of helicopter electromagnetic actuator power output variation characteristic test method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711250368.3A CN108088599A (en) | 2017-12-01 | 2017-12-01 | A kind of helicopter electromagnetic actuator power output variation characteristic test method |
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| CN108088599A true CN108088599A (en) | 2018-05-29 |
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| CN201711250368.3A Pending CN108088599A (en) | 2017-12-01 | 2017-12-01 | A kind of helicopter electromagnetic actuator power output variation characteristic test method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110908282A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | Modeling method for secondary passage of helicopter vibration active control system |
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| CN101526121A (en) * | 2009-04-17 | 2009-09-09 | 哈尔滨工程大学 | Redundant variable pitch structure semiactive vibration-isolating actuator |
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| DE102010024805A1 (en) * | 2010-06-23 | 2011-12-29 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Actuator device for electro-hydraulic system of e.g. airplane, has piezoresistive transducers that detect force received or delivered by actuator and transmit output signal to control unit that controls actuator based on output signal |
| CN102795334A (en) * | 2011-05-25 | 2012-11-28 | 尤洛考普特公司 | Method of determining the static force developed by a servo-control |
| JP6041309B2 (en) * | 2013-03-08 | 2016-12-07 | セイコーインスツル株式会社 | Pressure sensor |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110908282A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | Modeling method for secondary passage of helicopter vibration active control system |
| CN110908282B (en) * | 2019-12-04 | 2022-06-21 | 中国直升机设计研究所 | Modeling method for secondary passage of helicopter vibration active control system |
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