No-Failure Accelerated Life Test of Flap Actuating System using Weibull Distribution

Abstract

In this paper, we present some results on No-failure accelerated life test of aerial vehicle for reliability demonstration. The design of general accelerated life test consists of the three phases: 1) Estimating normal life test time of a single product from Weibull distribution model; 2) Determining the acceleration factor (AF) by utilizing the relation between the life of mechanical components and the applied torque; 3) Calculating the accelerated life test time, which comes from dividing the estimated normal life test time into AF. Then, we applied the calculated life test time to the real reliability test of the flap actuating system, while considering the requirement specification for mechanical components and operating environment of the actuation system. Real experimental processes and results are presented to validate the theory.

Numerical Evaluation of Structural Safety of Linear Actuator for Flap Control of Aircraft Based on Airworthiness Standard

“…The resulting coil spring constant is approximately 2253 N/mm. Figure 2 shows the operating profile of the linear actuator [14]. In the test rig, two linear actuators and a load simulator based on 16 coil springs were connected to the shaft, and the flap was controlled by the link as shown in Figure 1a.…”

“…The resulting coil spring constant is approximately 2253 N/mm. Figure 2 shows the operating profile of the linear actuator [14]. The initial stroke of the linear actuator is 70 mm, and the stroke reaches 0 mm in seven seconds, causing the flap surface to reach the maximum deflection angle (15.7°).…”