Acceptance testing of Electro Hydraulic based Aircraft Actuator Using LabVIEW

1
Karthik SP
Karthik SP
2
Vijay Desai
Vijay Desai
1 National Institute of Technology, Karnataka.

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This paper presents an approach to perform aircraft actuator Acceptance Testing capability. Efforts include design and development of Test system for Electro Hydraulic aircraft actuator, in nominal condition that may be used along with measurement data to generate effective test results. LabVIEW platform is used for developing the test system.To develop communication between the LabVIEW based Test software and Actuator, Portable Test Controller (PTC), is used.

7 Cites in Articles

References

  1. A Goldenberg,S Habibi (1999). A Mechatronics Approach for the Design of a New High Performance Electro Hydraulic Actuator.
  2. G Daneker (1973). Army View of Acceptance Tests.
  3. G Mcgrath (1964). What Is Acceptable Service Life?.
  4. H Moon,W Knowles (1970). Acceptance Criteria for Demonstrating System Safety Requirement.
  5. Pawel Rzucidlo (2006). Laboratory and Preliminary In-Flight Tests of Electromechanical Actuators.
  6. Pawel Rzucidlo (2006). Laboratory and Preliminary In-Flight Tests of Electromechanical Actuators.
  7. Shrinath S V Londhe,E M Jois,Peethambaran (1999). Vehicle Evaluation and Test System.

Funding

No external funding was declared for this work.

Conflict of Interest

The authors declare no conflict of interest.

Ethical Approval

No ethics committee approval was required for this article type.

Data Availability

Not applicable for this article.

Karthik SP. 2014. \u201cAcceptance testing of Electro Hydraulic based Aircraft Actuator Using LabVIEW\u201d. Global Journal of Research in Engineering - A : Mechanical & Mechanics GJRE-A Volume 14 (GJRE Volume 14 Issue A1): .

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Journal Specifications

Crossref Journal DOI 10.17406/gjre

Print ISSN 0975-5861

e-ISSN 2249-4596

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v1.2

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March 2, 2014

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English

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This paper presents an approach to perform aircraft actuator Acceptance Testing capability. Efforts include design and development of Test system for Electro Hydraulic aircraft actuator, in nominal condition that may be used along with measurement data to generate effective test results. LabVIEW platform is used for developing the test system.To develop communication between the LabVIEW based Test software and Actuator, Portable Test Controller (PTC), is used.

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Acceptance testing of Electro Hydraulic based Aircraft Actuator Using LabVIEW

Karthik SP
Karthik SP
Vijay Desai
Vijay Desai

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