民用飞机复合材料尾翼舵面作动器选型研究

A comparative study of control surface actuators for commercial aircraft composite empennage

民用飞机复合材料尾翼舵面作动器选型时,除需考察作动器系统及自身性能外,还需考察作动器对结构产生的载荷和重量影响。以结构减载和减重为出发点,对复合材料尾翼舵面的作动器开展选型研究。分析了在铰链轴布置位置不同的情况下,两种液压作动器,即点对点作动器和返力连杆作动器对尾翼结构的作动反力及结构重量的影响。研究发现：铰链轴居中布置时,舵面连接点处集中力比采用点对点作动器减少约40.2%～55.18%,安定面连接点处集中力减少约87.23%～88.7%;铰链轴非居中布置时,安定面连接点处集中力比采用点对点作动器减小约75.98～97.81%。重量对比分析发现,采用返力连杆作动器对尾翼结构的减重非常有利,返力连杆作动器在民用飞机复合材料尾翼结构上具有明显的应用优势。

Besides the system and properties of itself, choosing control surface actuators for composite commercial aircraft should study the effects on load and weight of structure from actuator. To reduce the structural load and weight, a comparative study is performed on the actuator type of control surfaces for the empennage structure of commercial aircraft. The reaction forces of point to point actuator and reaction link actuator are analyzed as the hinge axis location varies. The effects of reaction forces on the structural weight are also analyzed. It is found that when the hinge axis is located in the middle, the applied load from reaction link actuator to the control surface is lower than that from pin to pin actuator by 40.2%~55.18%, and the applied load from reaction link actuator to the stabilizer is lower than that from pin to pin actuator by 87.23%~88.7%; When the hinge axis is located not in the middle, the applied load from reaction link actuator to the stabilizer is lower than that from pin to pin actuator by 75.98%~97.81%. After weight analysis, it is found that the empennage structure gains benefits by using reaction link actuator. The reaction link actuator application has an obvious advantage on composite empennage structure of commercial aircraft.