Use of uncoupled, six-degree-of-freedom (6-DOF) motion is rapidly becoming state-of-the-art in terms of necessary flight control laws and aerodynamic capability. The next generation of aircraft may use uncoupled, 6-DOF control capability in conjunction with other new technologies such as Integrated Flight-Fire Control (IFFC). In order for future applications of 6-DOF control to be successful, the pilot must be able to command motion and acceleration magnitude with sufficiently good system response characteristics to accomplish particular missions or tasks. This study sought to develop design criteria and gather appropriate substantiating data for cockpit control devices for 6-DOF motion which will assure compatibility among the pilot, control device(s) and aircraft response and thus allow efficient implementation of the 6-DOF control capability. Phase I consisted of defining existing data on the design of of cockpit controllers for 6-DOF. Application of 6-DOF aircraft motion to aircraft mission requirements was examined. A set of tentative criteria was formulated and test plans developed to gather data necessary to validate and expand the tentative criteria. A simulation was conducted using the motion-based simulator at Wright-Patterson AFB. Results of the simulation were combined with results of the literature survey to form a set of design guidelines. Volume I (AD-A153 300) presents the results of the literature survey, Volume II is a detailed discussion of the simulation and analysis of the data.
Controller Requirements for Uncoupled Aircraft Motion. Volume 2
1984
558 pages
Report
Keine Angabe
Englisch
Avionics , Human Factors Engineering , Attitude control systems , Flight control systems , Man machine systems , Control theory , Military aircraft , Flight simulators , Flight , Quality , Acceleration , Response , Aerodynamics , Military requirements , Missions , Cockpits , Motion , 6-DEGREES OF FREEDOM , Uncoupled 6-DOF control , Flying qualities , Pilot vehicle interface , MIL-F8785
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