Abstract
Integrated electric hydrostatic actuator (EHA) system has the advantages of both traditional hydraulic system and direct drive electromechanical system, and it can be modularized easily. This paper describes the structure and operating principle of EHA, and it gives the specific requirements of the system design and selective principles of the motor, pump and hydraulic cylinder. Furthermore, it creates the mathematical model of each module. Simulation results show that the EHA can meet modern aircraft requirements to the actuator system, and it can be used widely in the future power by wire (PBW) flight control system.
| Original language | English |
|---|---|
| Pages (from-to) | 79-83 |
| Number of pages | 5 |
| Journal | Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica |
| Volume | 26 |
| Issue number | 1 |
| State | Published - Jan 2005 |
Keywords
- Electric hydrostatic actuator
- Hydraulic
- Integration
- Power by wire
- Simulation
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