Actuators
With our advanced capabilities in utility and flight control systems, we develop all types of motion control actuators in aerospace, including both primary and secondary flight control system actuators.
Our motion control systems are meticulously designed in accordance with internationally recognized aerospace standards to optimize the flight performance of aerial platforms, ensure safety, and deliver high-performance maneuverability. Our innovative engineering solutions offer reliable, precise, and fully automated systems integrated with the latest technologies.
Our utility and flight control system actuators, which meet superior quality standards and fully comply with international aviation regulations, are combined with the latest industry developments to deliver exceptional performance and reliability.
Flight Control Actuation Systems
The Flight Control Actuator is designed to move the aircraft's control surfaces during flight in order to steer the aircraft along various axes and optimize takeoff/landing performance by altering the wing profile. These actuators are engineered to respond rapidly to signals from the aircraft, enabling the movement of aerodynamic surfaces that provide the high maneuverability required.
Electro-hydraulic actuators are specifically designed to deliver fast and precise responses to control inputs, allowing the aircraft to achieve desired maneuverability and flight characteristics. By receiving signals from the aircraft, they contribute to the aircraft's safe and efficient operation under various flight conditions.
Application Area
FLIGHT CONTROL
SYSTEMS
Failure Detection and Troubleshooting Capability
The subsystem features built-in mechanisms to detect failures or malfunctions in the actuators. This ensures that any issues arising during operation are identified in a timely manner, resolved when possible, or isolated if necessary—thereby maintaining the reliability and safety of the flight control system.
Low Response Time
The actuators are designed with fast response times, enabling them to quickly and accurately translate input signals from the flight control computer into the desired movements of the control surfaces.
Synchronous/Independent Operation
The actuators are capable of operating either synchronously or independently, allowing for coordinated control of multiple control surfaces or individual control based on specific flight requirements.
Flight Control Actuation Systems Features
| Electro-Hydraulic Actuators | |
| Stroke [mm] | 60-250 |
| Load Capacity[kN] | 80-300 |
| Drive [mm] | Electro-Hydraulic Servo Valve |
| Power [kW] | < 300 |
| DAL (ARP 4754A) | A |
Utility Actuation Systems
Utility Actuation Systems are electromechanical actuators that enables positioning hardware/equipment related to utility systems on the aircraft, based on inputs from the pilot or flight control system. When necessary, they can also be operated manually without an electrical power source.
Application Area
UTILITY SYSTEMS
Electromechanical Drive System
The system utilizes an electromechanical drive mechanism for operation.
Fast Extract and Retract Time
The system offers fast and efficient extract and retract times, enabling rapid operation.
Manual Drive and Braking During Power Loss
The system features a braking function for deceleration even in the event of a power loss and can be operated manually when electrical power is unavailable.
Lightweight and Compact Design
The system features a lightweight and compact design, providing optimized performance in terms of space and weight efficiency.
Utility Actuation Systems Features
| Parameter | Typical / Max Value | Unit |
| Operational Load | < 12,500 | N |
| Limit Load | < 20,000 | N |
| Ultimate Load | < 45,000 | N |
| Velocity | < 30 | mm/s |
| Stroke Range | 60 – 250 | mm |
| Pin To Pin Length [A] | < 500 | mm |
| Power Consumption (Nominal) | 560 (Peak: 6 sec) | W |
| Input Voltage | 28 | VDC |
| Overall Dimensions | < 150 × 200 × 600 | mm |
| Weight | < 7.5 | kg |
| Manual Drive Torque | < 8 | Nm |
| Operational Temperature | -46 to +70 | °C |
| Interface | CAN Bus 2.0 B | - |
| Communication Protocols | ARINC 825, ARINC 826 | - |
