Orbital research proposes to design, optimize and demonstrate a lightweight swashplateless helicopter rotor collective control system. Design and performance prediction of swashplateless. The axstream rotor design tool allows users to import a newexisting optimized flow path design from any axstream project. Dynamics research on actively controlled swashplateless rotor no access. Light weight collective pitch control systems for swashplateless rotors. Thrust, roll, pitch, and yaw from only two motors we derive thrust, roll, and pitch authority from a single propeller and single motor through an underactuated mechanism. A helicopter flight control system with rotorstate feedback to improve turbulence. Top view of swashplateless rotor wake with flap trailers at 0. The method is evaluated using softwareintheloop and flight evaluations on the georgia. Modern helicopters still suffer from many problems that hinder a further increase in their efficiency, acceptance and hence their market share. Trim code analysis of a swashplateless rotor for a utility helicopter modeled on a uh60a, to include incorporation of a cfdgenerated database of uh60 rotor blade airloads for.
Download scientific diagram swashplateless rotor concept with integral airfoil. If you have the appropriate software installed, you can download article citation. Hunter pgp rotor 22ft52ft gear drive rotor the grass is greener where you water it keeping your lawn and garden healthy and strong is as easy as. A blade actuation system comprises at least one motor coupled to a rotor blade for changing the pitch angle of the rotor blade.
The swashplateless control system integrated into the raven, which includes the onblade actuators, cables. The method is evaluated using softwareintheloop and flight evaluations on the. The axstream rotor design tool allows users to import a newexistingoptimized flow path design from any axstream project. Important trailing edge ap and tab design features including index angle, aerodynamic overhang, chord and length are identi ed through examination of coupled trim solutions in wind tunnel conditions at high speed. Low cyclic pitch is a necessity to implement the swashplateless rotor concept using. The modeling of the swashplateless teetering rotor with.
A parametric design study for a swashplateless helicopter rotor with trailingedge flaps jinwei shen inderjit chopra graduate research assistant alfred gessow professor and director. The high level of vibrations and the noise generated by the rotor are the most important reasons for this. Pdf design and performance prediction of swashplateless. The resulting blade pitch changes, rotor flapping response, and aircraft flight. This study presents the design, dynamic model, and dynamics research of a new cyclic pitch control strategy in motordriven rotorcraft.
Download scientific diagram swashplateless rotor concept with integral airfoil actuator. Design and performance prediction of swashplateless helicopter. The pennsylvania state university the graduate school. Rotorstate feedback control design to improve helicopter turbulence. A parametric design study for a swashplateless helicopter. Raven sar rotorcraft advanced rotor control concept. Development of integrated rotorcraft design and virtual manufacturing framework. This work studies the design of trailing edge controls for swashplateless helicopter primary control, and examines the impact of those controls on the performance of the rotor. The rotorcraft was modeled with ideas cad software.
Vibrations are problematic not only for pilot and passenger comfort, but also give rise to an increase in maintenance effort. The motor is configured to wirelessly communicate with at least one flight control computer to modulate the pitch angle. The pennsylvania state university the graduate school college of engineering design and analysis of rotor systems with multiple trailing edge flaps and resonant. Hover testing of a swashplateless rotor with compact brushless motor actuated flaps for primary control. Performance of swashplateless ultralight helicopter rotor with. The swashplate, which comprises a nonrotating lower plate movably connected to a rotating upper plate by bearings, is typically located just below the rotor head on the axis of the main rotor shaft, and is itself typically actuated by hydraulic cylinders mounted to the chassis. Design and performance prediction of swashplateless helicopter rotors with. Performance of swashplateless ultralight helicopter rotor. In this strategy, the control response and flapping feature of conventional rotor systems can be obtained by imposing 1 a lagpitch coupling on rotor blade and 2 an additional sinusoidal rotational speed of rotor shaft without any actuators or swashplate. Important trailing edge flap and tab design features including index angle.
Dynamics research on actively controlled swashplateless rotor. At least one generator may be mounted on a rotor shaft to generate power during rotation of the rotor shaft. Rotorcraft ippd framework at konkuk university download. Light weight collective pitch control systems for swashplateless. Pdf hover testing of a swashplateless rotor with compact. Onshape is the only product development platform that unites cad, data management, collaboration tools and realtime analytics. Rotor design software turbomachinery design software softinway. Ke and electrical resistant rohm and software defined proportional and integral. Swashplateless helicopter rotor system with trailingedge. Inclusion of rotor dynamics in controller design for helicopters. Swashplateless rotor concept with integral airfoil actuator.578 617 1343 124 541 1360 1227 16 257 297 769 115 717 436 1485 283 85 1174 1294 1429 1515 1515 1288 24 32 9 1388 763 1071 114 47 863 175 516 1260 749 341 1157