The invention belongs to the technical field of airworthiness verification of aircrafts, and particularly relates to a test flight method for verifying longitudinal static stability of a civil helicopter instrument. Comprising the following steps: S1, determining a relation between a longitudinal control lever force and a longitudinal control position of a control lever; s2, verifying the longitudinal joystick force gradient of the acceleration section of the helicopter through a flight test; s3, verifying the longitudinal joystick force gradient of the helicopter deceleration section through a flight test; s4, verifying the balancing speed recovery characteristic of the acceleration section of the helicopter through a flight test; and S5, verifying the balancing speed recovery characteristic of the deceleration section of the helicopter through a flight test.
本发明属于航空器适航验证技术领域,尤其涉及一种民用直升机仪表纵向静稳定性验证试飞方法。包括:S1,确定驾驶杆的纵向操纵杆力与纵向操纵位置之间的关系;S2,通过飞行试验验证直升机加速段的纵向操纵杆力梯度;S3,通过飞行试验验证直升机减速段的纵向操纵杆力梯度;S4,通过飞行试验验证直升机加速段的配平速度恢复特性;S5,通过飞行试验验证直升机减速段的配平速度恢复特性。
Civil helicopter instrument longitudinal static stability verification flight test method
一种民用直升机仪表纵向静稳定性验证试飞方法
04.03.2025
Patent
Elektronische Ressource
Chinesisch
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
Civil helicopter flight research
NTRS | 1976
|Civil helicopter flight research
AIAA | 1976
|Civil helicopter ground joint test bed coupling stability test method
Europäisches Patentamt | 2024
|Helicopter longitudinal stability
Engineering Index Backfile | 1957
|