Browse Topic: Terminology
This SAE Information Report contains definitions for hydrogen fuel cell powered vehicle terminology. It is intended that this document be a resource for those writing other hydrogen fuel cell vehicle documents, specifically, Standards or Recommended Practices.
This digital data model for the AS9100D aerospace quality management standard provides a structured, machine‑readable representation of the requirements, definitions, and industry‑specific enhancements that distinguish AS9100D from its ISO 9001:2015 foundation. Designed to support interoperability across aviation, space, and defense organizations, the model encapsulates the standard’s clause hierarchy, terminology, and compliance attributes in a format optimized for automated processing, validation, and lifecycle management. The model incorporates the revised clause structure introduced with ISO 9001:2015 and extends it with aerospace‑specific obligations, risk‑based considerations, and supply‑chain expectations defined by the International Aerospace Quality Group (IAQG). It captures the relationships between core quality management system elements—such as leadership, planning, operational control, and performance evaluation—while embedding additional AS9100D requirements related to
Axial velocity measurements were performed in the wake of a hovering rotor with constant and sinusoidal cyclic pitch inputs ranging from 0.05/rev to 0.4/rev using a fixed, 2D-3C PIV system. Measurements were taken at 36 azimuths of the rotor with a constant cyclic input producing a pitching moment of CM = -0.00037. Using a Pitt-Peters definition, a longitudinal inflow state of λ1c = 0.0059 was extracted from the velocity measurements. A phase-resolved, undersampling approach was used to reconstruct the time history of the wake for the dynamic inputs. Simultaneous rotor hub loads measurements were used to obtain the frequency response of the longitudinal inflow state to pitching moment perturbations. The pitching moment perturbations ranged from ΔCM = 0.00027 at f=0.05/rev to 0.00046 at f=0.4/rev. The inflow perturbations ranged from Δλ1c = 0.0085 at f=0.1/rev to 0.0085 at f=0.4/rev. A first order transfer function was fit to the frequency response to compute Pitt-Peters dynamic inflow
As military organizations internationally assess life extension and replacement actions for current legacy helicopter fleets and next generation rotorcraft are under development, novel rotor system technologies are required to fulfill challenging low-speed and high-speed flight envelopes and mission requirements. Proposed by the Department of National Defense (DND) and in collaboration with the National Research Council of Canada (NRC), a TTCP AER CP13A.1 Collaborative Project (CP) has been initiated supporting multi-nation development of numerical methods for optimizing and designing next generation main rotor blades. Four NRC laboratories collaborated to assemble a data set comprising design, performance, aerodynamics, structures, dynamics, and flight sciences elements. Acquired through research and testing, this information provides reference, technical, and engineering knowledge to support aero-structural model definition, model output validation, and the numerical optimization
Launch, recovery, and deck handling operational performance on smaller ship platforms like Corvettes, Frigates and Destroyers are qualified as the most challenging tasks in the UAS ship-deployment of a VTOL Uncrewed Air System (UAS). One of the main hurdles is the random nature of seaway-created deck motions coupled with ship structure disturbed air wake patterns. The MoD has supported a range of work aimed at bringing Quiescent Period Prediction (QPP) technology to fruition. QPP firstly requires Wave Profiling RADAR to measure the sea wave system out to approximately 2km in the region around a vessel. Secondly these measurements are employed in a wave propagation model to predict the actual wave forces acting on a vessel. Using the wave predictions as inputs to a vessel model makes possible to predict the actual (deterministic as opposed to statistical) motions of a vessel. Wave systems naturally alternate groups of large waves with smaller waves, this property, combined with the
In over actuated aircrafts a simple relationship between control inputs and forces/moments generated does not exist, however they have become very attractive for their wide range of applications. Control allocation aims at finding a unique surface control distribution as function of flight condition to perform the desired maneuver. The goal of this paper is to present a control allocation methodology applied on a generic over actuated aircraft aimed to determine the surface gearing matrix weights in different operative conditions to minimize the total power consumption. First, the non-linear model of the control forces and moments is derived for an over actuated aircraft. Then, two different optimization problems are introduced: the first to compute the trim equilibrium for any flight condition to minimize power consumption by the aircraft; the second to minimize the surface deflections required to produce desired control forces/moments starting from the trim point previously found
ABSTRACT
This SAE Recommended Practice covers the safety alert symbol intended for use on construction and industrial equipment as defined in SAE J1116 and on agricultural tractors and machinery as defined in ASABE S390.
This SAE Standard applies to cranes which are equipped to adjust the boom angle by hoisting and lowering means through rope reeving.
This SAE Information Report contains definitions for HEV, PHEV, and EV terminology. It is intended that this document be a resource for those writing other HEV, PHEV, and EV documents, specifications, standards, or recommended practices.
Illustrations used here are not intended to include all existing industrial or agricultural machines, or to be exactly descriptive of any particular machine. They have been picked to describe the principles to be used in applying this standard.
With the market introduction of the EC135 the bearingless main rotor (BMR) as a novel main rotor system was put into series production. Since then a chain of interconnected research programs led to the next generation of BMR. It now enhances the qualities of the H145 regarding the aspects of useful load, comfort of ride, purchase and maintenance cost as well as operational features. The design targets definition and their implementation by innovative solutions are summarized hereafter. The focus is put on the modular design of the main rotor system which is realized by an integrated flexbeam and control cuff assembly and a separate rotor blade joined together by a bolted connection using flat laminate lay-up instead of fiber loops. A detailed view is given on the development of the novel blade attachment from design considerations and manufacturing aspects over parametric subcomponent tests to full scale testing.
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