Browse Topic: Lightweighting
The paper describes a method for optimal design of a helicopter tail shaft that considers rotordynamic effects from long shaft assembly. The tail shaft transmits power from the main gearbox (MGB) to the tail rotor of the helicopter and operates at high speeds that may exceed 6000 rpm. While higher speeds allow for weight reduction, they also pose risks associated with supercritical operation, necessitating careful design optimization. The objective of the optimization is to maximize the first three transverse natural frequencies with the constraint of the safety parameter (avoidance of the resonance/critical zone) while minimizing the weight of the system. A Non-Dominated Sorting Genetic Algorithm (NSGA-II) is used to obtain the solution to this multiobjective optimization problem, which involves shaft design variables such as length, outer diameter, and wall thickness. In addition, the optimization framework also incorporates system related design variables, including the stiffness of
Emerging microelectronic technologies are expanding functionalities for future decades of vertical lift platforms, enabling both manned and unmanned rotorcraft to fully and safely participate in the NextGen National Airspace System. Specifically, for rotorcraft, benefits from expanded multi-functionality and reduced weight and space requirements, for both mandatory and desired optional avionics, are entering advanced development and flight-testing stages prior to being available to all users. One has only to think about the incredible, multifunctional capabilities of a smartphone to imagine what is possible in avionics with today's advanced technology. This presentation discusses achievements that only a few years ago were beyond imagination – miniaturized avionics that fully employ tiny but powerful digital processors and software defined multi-functional systems on a single chip are rapidly obsoleting the "black boxes" of the past. For both manned and unmanned rotorcraft systems, the
The development of Vertical Take-off and Landing (VTOL) vehicles for the Urban Air Mobility (UAM) markets presents a need for light weight vehicle structures with effective occupant protection capabilities. The National Aeronautics and Space Administration (NASA) has been working to fill that need, recently developing a cadre of concept vehicles to help characterize UAM design feasibility. This paper describes a study, using these concept vehicles, to evaluate the use of advanced composite structure and energy attenuating designs in the UAM vehicle design space. A finite element model (FEM) of a single passenger quadrotor concept vehicle was developed in LS- Dyna® and simulated under nominal and off-nominal vertical impact conditions. A variety of energy attenuating design mechanisms were implemented within this model to quantify their effectiveness in improving occupant safety. The use of carbon composites in both the energy attenuation mechanisms and vehicle structure was evaluated
In order to maximize range, a substantial portion of the interior volume of aircraft is allocated for fuel containment. To ensure the safety of aircrew and passengers, these systems must contain fuel and retain critical structural integrity in the event of a crash, self-seal and retain structural capability in the event of penetration, and suppress fire in the event of proximate ignition. Traditionally, light weight aircraft such as rotorcraft have accomplished these functions with heavy self-sealing bladder offset and isolated from primary structure. Boeing and the US Army Combat Capabilities Development Command Aviation & Missile Center's Aviation Development Directorate (ADD), together with the Joint Aircraft Survivability Program Office, have developed and demonstrated a structurally integrated fuel containment system that efficiently tolerates crash, self-seals, and suppresses fire at a lower weight and volume than traditional systems, thus maximizing space and weight capacity for
The Mars Helicopter is a 1.8 kg coaxial rotorcraft designed to demonstrate aerial mobility at the surface of Mars after deployment from the Mars 2020 rover. In this paper, the authors present the development of the Mars Helicopter rotor system from preliminary design through fabrication and testing of the flight hardware. The vehicle has a 1.21 m counter-rotating coaxial rotor system which is driven by electric motors and which features collective and cyclic controls on both the upper and lower rotor sets. The rotor blade design is characterized by the low Reynolds number (∼104), high Mach number (∼0.7), high stiffness (first flap frequency ∼1.9/rev), and minimum mass. Airfoil design focused on minimizing drag at the low operating Reynolds number while maintaining sufficient spar depth for structural requirements, and the blade planform was based on a minimum induced loss profile with modifications to reduce mass of the outboard blade sections for increased flap frequency. The
There is a constant push within the rotorcraft community to increase performance while simultaneously reducing weight in all systems. For rolling element bearings, this translates to a demand for alternative materials with lower density and improved mechanical properties. This combination of new materials and increasingly demanding application conditions goes beyond historical experiences and defined design and analysis standards. A consequence of this is that tests of these new technologies occasionally result in failure. This was the case during a recent series of gearbox tests during which two different bearing designs failed due to cage issues. The two bearing designs included cages manufactured out of different materials, and the cages failed due to two distinct failure modes (wear and structural fatigue). These test results were used to validate computational results from SKF's proprietary multibody dynamics software, BEAST (BEAring Simulation Tool). A combination of elemental
This study develops an optimization technique for a sinusoidal interlock design of a hybrid spur gear consisting of a metallic outer ring to support high contact stress bonded to a composite inner web for weight reduction. Two objectives (mass and shear traction on the metal-composite interface under static loading conditions) were minimized for four design variables subject to two constraints. Borg MOEA, a multi-objective evolutionary algorithm developed at The Pennsylvania State University, and an in-house finite element solver were used to generate Pareto-optimal solutions to this design problem. Two of the designs were then analyzed in greater detail to determine stress distributions throughout the gear. In the future, this technique will be refined and applied to optimization of more representative rotorcraft gears, with the aim of reducing drive train weight and meeting performance requirements.
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