![]() The Lift submodule can be used for estimating the lifting characteristics of aircraft lifting surfaces and high lift devices. together with a side view of the aircraft. along with the empty weight component’s C.G. The plot feature can also be used to plot the empty weight C.G. envelope based on all possible loading scenarios. The software includes the option to plot the C.G. and the total center of gravity based on a specific loading scenario. 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. 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. Center of gravity of wing, canard, horizontal tail, vertical tail, V-tail, fuselage, tailbooms, nacelles, stores, floats and ventral fins are calculated. Tables are available for structure weight, fixed equipment weight, powerplant weight and total weight. 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. 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. The weight sizing module contains a plot feature which displays the weight iteration process as well as a Class I payload-range diagram. The methods are based on Chapter 2, Sections 2.1 to 2.5 and Section 2.7 of Airplane Design Part I. Methods to establish this statistical relationship for any type of aircraft are included in the AAA software. 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. Class II uses more sophisticated methods than Class I and requires more detailed information of the airplane to be known. Class II design accounts for power plant installation, landing gear disposition and component locations on the airplane. 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. 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. It does not calculate the derivatives for transonic and supersonic flow. The stability and control derivatives modules only deal with subsonic flow (up to about Mach=0.7) for most derivatives. The detailed drag module allows designers to go all the way to supersonic flow. 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. AAA provides a powerful framework to support the iterative and non-unique process of aircraft preliminary design.
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