AAA applies to most fixed wing configurations (civil, military and transport aircraft) and allows design engineers to rapidly evolve an aircraft configuration from weight sizing through detailed performance calculations and cost estimations. All applicable performance and flying quality regulations are available in the AAA program. This provides the designer with an instant appraisal of the status of the design relative to these regulations.
Raymer 5th Ed Aircraft Design Torrent
AAA provides a powerful framework to support the iterative and non-unique process of aircraft preliminary design. 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.
AAA 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.
AAA 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 design accounts for power plant installation, landing gear disposition and component locations on the airplane. Class II uses more sophisticated methods than Class I and requires more detailed information of the airplane to be known. The accuracy of Class II methods is therefore greater than Class I methods.
The purpose of this module is to present a Class II method for estimating aircraft component weights. The Class II estimation methods used in this module are based on those described in Airplane Design Part V. These methods employ empirical equations, which relate component weights to aircraft design characteristics. In the Class II weight estimate module, the weight estimation methods are identified as follows:
The purpose of the Class II Drag submodule is to supply a Class II method for predicting drag polars of aircraft during the preliminary design phase. A detailed drag polar can be calculated for the subsonic, transonic and supersonic flow regimes. The following drag calculations can be performed:
The purpose of the Performance Sizing module is to allow for a rapid estimation of those aircraft design parameters which have a major impact on aircraft performance. Aircraft are usually required to meet performance objectives in different categories depending on the mission profile. Meeting these performance objectives normally results in the determination of a range of values for:
The purpose of this module is to estimate loads placed on aircraft components and to determine important information for structural design and sizing. The Loads module consists of three submodules: V-n Diagram, Structural Loads and Lateral Gust Loads. The purpose of the V-n Diagram submodule is to determine load factors and their corresponding speeds. The purpose of the Structural Loads submodule is to calculate the internal forces and moments in the structural components of an aircraft. Use of the Loads module options will be described in the following sections.
We use AAA for our aircraft design consulting services. We are constantly updating and refining the methods used, based on our research and wind tunnel tests that we perform. This leads to regular software version updates, which benefits all of our software clients. 2ff7e9595c
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