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| Author | : Peter D. Talbot |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1977 |
| Genre | : |
| ISBN | : |
| Author | : K. B. Hilbert |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1984 |
| Genre | : Helicopters |
| ISBN | : |
This report documents the revisions made to a mathematical model of a single main rotor helicopter. These revisions were necessary to model the UH-60 helicopter accurately. The major modifications to the model include fuselage aerodynamic force and moment equations that are specific to the UH-60, a canted tail rotor, a horizontal stabilator with variable incidence, and a pitch bias actuator (PBA). In addition, the model requires a full set of parameters which describe the helicopter configuration and its physical characteristics.
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 30 |
| Release | : 2018-07-25 |
| Genre | : |
| ISBN | : 9781724220202 |
The model was developed for real-time pilot-in-the-loop investigation of helicopter flying qualities. The mathematical model included the tip-path plane dynamics and several primary rotor design parameters, such as flapping hinge restraint, flapping hinge offset, blade Lock number, and pitch-flap coupling. The model was used in several exploratory studies of the flying qualities of helicopters with a variety of rotor systems. The basic assumptions used and the major steps involved in the development of the set of equations listed are described. The equations consisted of the tip-path plane dynamic equation, the equations for the main rotor forces and moments, and the equation for control phasing required to achieve decoupling in pitch and roll due to cyclic inputs. Chen, R. T. N. Ames Research Center NASA-TM-78575, A-7538 RTOP 505-10-23
| Author | : Peter D. Talbot |
| Publisher | : |
| Total Pages | : 58 |
| Release | : 1982 |
| Genre | : Helicopters |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 1134 |
| Release | : 1989 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Monte Ung |
| Publisher | : |
| Total Pages | : 248 |
| Release | : 1984 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 604 |
| Release | : 1988 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1986 |
| Genre | : |
| ISBN | : |
Current approved terminal instrument procedures (TERPS) do not permit the full exploitation of the helicopter's unique flying characteristics. Enhanced TERPS need to be developed for a host of non-standard landing sites and navigation aids. Precision navigation systems such as MLS and GPS open the possibility of curved paths, steep glide slopes, and decelerating helicopter approaches. This study evaluated the feasibility, benefits, and liabilities of using helicopter cockpit simulators in place of flight testing to develop enhanced TERPS criteria for non-standard flight profiles and navigation equipment. Near-term (2-5 year) requirements for conducting simulator studies to verify that they produce suitable data comparable to that obtained from previous flight tests are discussed. The long-term (5-10 year) research and development requirements to provide necessary modeling for continued simulator-based testing to develop enhanced TERPS criteria are also outlined. (Author).
| Author | : |
| Publisher | : |
| Total Pages | : 336 |
| Release | : 1982 |
| Genre | : |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 54 |
| Release | : 1983 |
| Genre | : |
| ISBN | : |
A helicopter in-flight simulation was conducted to determine the effects of variations in roll damping, roll sensitivity, and pitch- and roll-rate cross-coupling on helicopter flying qualities in a low-altitude maneuver. The experiment utilized the Ames UH-1H helicopter in-flight simulator, which is equipped with the V/STOLAND avionics system. The response envelope of this vehicle allowed simulation of configurations with low-to-moderate damping and sensitivity. A visual, low-level slalom course was set up, consisting of constant-speed and constant-altitude S-turns around the 1000-ft markers of an 8000-ft runway. Results are shown in terms of Cooper-Harper pilot ratings, pilot commentary, and statistical and frequency analyses of the lateral characteristics. These results show good consistency with previous ground-simulator results and are compared with existing flying-qualities criteria, such as those set forth in MIL-F-83300 and MIL-H-8501A. (Author).
