The fourth phase is given of a continuing program to develop the means to stabilize and control aircraft without moving parts or a separate source of power. Previous phases have demonstrated the feasibility of (1) generating adequate control forces on a standard airfoil, (2) controlling those forces with a fluidic amplifier and (3) cascading non-vented fluidic amplifiers operating on ram air supply pressure. The foremost objectives of the fourth phase covered under Part I of this report were to demonstrate a complete force-control system in a wind tunnel environment and to measure its static and dynamic control characteristics. Secondary objectives, covered under Part II, were to evaluate alternate configurations for lift control. The results demonstrate an overall response time of 150 msec, confirming this technology as a viable means for implementing low-cost reliable flight control systems.
Wind tunnel tests of the dynamic characteristics of the fluidic rudder
1976-12-01
Report
No indication
English
Wind tunnel tests of various servo rudder systems
SLUB | 1929
|Development of a fluidic rudder
NTRS | 1976
|Development of a fluidic rudder
AIAA | 1976
|Design and test of the 172K fluidic rudder
NTRS | 1978
|Design and Test of the 172K Fluidic Rudder
NTIS | 1978
|