本研究前半部利用微機電系統技術製作拍撲式微飛行器之聚對二甲苯(parylene)機翼薄膜與鈦合金機翼，並結合非微機電製程製作之拍撲式傳動機構、機身骨架與尾翼，成為全機重6gw以下，翼展尺寸為16cm之拍撲式飛行器。並放置於風洞內進行升力及推力量測進行討論。 本研究另使用聚乙烯氟化物(PVDF)壓電薄膜材料，製作拍撲式機翼結構於風洞測試中進行現地量測(on-site lift measurement)，並將機翼之壓電輸出訊號與風洞測力計升力訊號，進行比對探討。 本研究後半部利用RF無線傳輸模組成功量測日常生活週遭溫度變化；並將傳輸模組置放於壓力測試機台腔體之中，達成對腔體內部進行溫度監控。未來寄望能夠搭載於微飛行器之上，於飛行時即時擷取空氣動力訊號與飛行姿態之掌握，進而實現空中監控的目標。 This research utilized MEMS technology layering parylene film as the wing skin and titanium alloy as the wing skeleton. The transmission system with reduction ratio of 26.6 is also fabricated. The total mass of the flapping MAV is less than 6 grams and the wing span is 16 cm. Then we measured and discussed the lift and thrust force of the MAV at the wind tunnel test. The signals from a load cell in the wind tunnel and a PVDF sensor embedded in parylene wings are acquired simultaneously. Both of the lift signals from the PVDF and the load cell are basically similar with the same flapping frequency and with the qualitative behavior. In addition, we successful measured the temperature changes byutilizing a commercial Radio frequency wireless transmission module in our daily living. We set the module and monitored temperture changes in a pressure test chamber. We expect this module to combine with our MAV, and receive the aerodynamic signals to detect the gesture of the MAV during flying. The final goal of this research is to accomplish the real time MAV monitoring in the sky.