![]() ![]() Good stability and friendly operation will let you enjoy the ride! Especially Designed for Bikers: 2 channel separated cameras with each standard 2.5 meters extension cable for front and rear view recording.Compared to sports action camera, VSYSTO professional dash cameras are equipped with dual front & rear sync recording cameras, allows you to capture the unexpected accident evidence, and amazing travel scenery. Aimed to simplify the use of cameras, for security, and pleasure. AAA provides a powerful framework to support the iterative and non-unique process of aircraft preliminary design.VSYSTO 2CH camera system is designed especially for motorcycles. The AAA program allows students and preliminary design engineers to take an aircraft configuration from early weight sizing through open loop and closed loop dynamic stability and sensitivity analysis, while working within regulatory and cost constraints.ĪAA can be used to design fighter style aircraft and high speed aircraft. The detailed drag module allows designers to go all the way to supersonic flow. The stability and control derivatives modules only deal with subsonic flow (up to about Mach=0.7) for most derivatives. It does not calculate the derivatives for transonic and supersonic flow. Most other modules do not have a speed dependency and can be used in any speed regime.ĪAA is used for preliminary and Class II design and stability and control analysis of new and existing aircraft. ![]() Class II design incorporates detailed weight & balance, aerodynamics, stability & control calculations including trim analysis and flying qualities used in conjunction with the preliminary design sequence. Class II uses more sophisticated methods than Class I and requires more detailed information of the airplane to be known.Ĭlass II design accounts for power plant installation, landing gear disposition and component locations on the airplane. Statistical relations between empty weight and take-off weight of existing similar aircraft.These parameters are estimated on the basis of the following input: Sensitivity of take-off weight to aerodynamic, propulsion and mission parameters.The purpose of the Weight Sizing module is to rapidly estimate the following weight components and/or sensitivity coefficients: The accuracy of Class II methods is therefore greater than Class I methods. Methods to establish this statistical relationship for any type of aircraft are included in the AAA software. The methods are based on Chapter 2, Sections 2.1 to 2.5 and Section 2.7 of Airplane Design Part I. The weight sizing module contains a plot feature which displays the weight iteration process as well as a Class I payload-range diagram. This module also contains methods to calculate the lift-to-drag ratios for the climb, cruise, turn and loiter segments based on corresponding segment weights. This process iterates between the Weight Sizing module and Class I Drag module to converge on a solution for the take-off weight.Ĭomponent Center of Gravity option allows the user to calculate the aircraft center of gravity by entering weight components and their locations in a preformatted table. Tables are available for structure weight, fixed equipment weight, powerplant weight and total weight. Center of gravity of wing, canard, horizontal tail, vertical tail, V-tail, fuselage, tailbooms, nacelles, stores, floats and ventral fins are calculated. These are based on geometry of the components and on the methods described in Chapter 8 of Airplane Design Part V.ĭetailed center of gravity calculations based on empty weight and various loading scenarios are included in the software. These calculations include the determination of the most forward and most aft center of gravity based on the minimum and maximum weights of passengers, fuel, baggage, cargo etc. and the total center of gravity based on a specific loading scenario. The software includes the option to plot the C.G. envelope based on all possible loading scenarios. The plot feature can also be used to plot the empty weight C.G. ![]() along with the empty weight component’s C.G. together with a side view of the aircraft. The Lift submodule can be used for estimating the lifting characteristics of aircraft lifting surfaces and high lift devices.
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