Design and Integration Tools
Vehicle/Payload Modeling and Analysis, Component and Integrated System Simulation
Architecture Adaptive Computing Environment (ACE)
The Architecture Adaptive Computing Environment (ACE) is a parallel computing language, compiler, and runtime library. The purpose of ACE is to allow a programmer to more easily write parallel programs for a wide variety of parallel computer architectures.
NASA.rb (formerly fUnit)
NASA.rb (formerly fUnit) is a collection of Fortran modules that provide a framework for automating the construction, execution, and reporting of unit tests for Fortran software applications. Support is provided for several aspects of unit testing that are peculiar to scientific technical computing including distributing jparallel applications and parameterized behavior.
NASA STRuctrual ANalysis (NASTRAN)
NASTRAN is a finite element analysis program that was originally developed for NASA in the late 1960s under U.S. government funding for the aerospace industry. The software suite provides engineers a comprehensive simulation solution for insight into structural behavior. NASTRAN source code is integrated in a number of different software packages, which are distributed by a range of companies.
Flight Dynamics Simulation of a Generic Transport Model
This software is a flight dynamics simulation of a transport aircraft. It implements general rigid body equations of motion for the vehicle dynamics and draws aerodynamic forces from a standard coefficient expansion implemented as table lookups. Dynamics of actuator servos and bandwidth of sensors are also included. The simulation is coded in Simulink, a model-based environment using a commercial simulation package from Mathworks, Inc. The software is not stand-alone; it must be run from inside this commercial environment, making use of numerical libraries for basic operations as well as the overall time-stepping and numerical integration routines.
Incompressible Navier-Stokes CFD Solver (INS3D)
The INS3D code solves the incompressible Naiver-Stokes equations in three-dimensional generalized coordinates for both steady-state and time varying flow. The equations are formulated using the method of artificial compressibility. The convective terms are differenced using an upwind biased flux-difference splitting. The equations are solved using an implicit line-relaxation scheme. The code is written for single or multiple-zone calculations. It can utilize either pointwise continuous zonal interfaces, or overset zonal interfaces if a PEGASUS interpolation database is supplied. The INS3D code is written in Fortran77 and C. The code only runs in a serial execution mode. This code was developed in the 1990s and is no longer under development at NASA.
U.S. Release Only
42: A Comprehensive General-Purpose Simulation of Attitude and Trajectory Dynamics and Control of Multiple Spacecraft Composed of Multiple Rigid or Flexible Bodies
Simulator of spacecraft attitude, orbit dynamics, and environmental models. Spacecraft models composed of multiple bodies are supported. The environment models include ephemerides for all planets and major moons in the solar system. Supports geometrical visualization through an OpenGL interface. The simulator is opensource and portable across computing platforms, making it customizable and extensible. It is written to support the entire GNC design cycle, from rapid prototyping and design analysis, to high-fidelity flight code verification.
Computational Fluids Laboratory 3-Dimensional (CFL3D)
CFL3D is a structured-grid, cell-centered, upwind-biased, Reynolds-averaged Navier-Stokes (RANS) code. It can be run in parallel on multiple grid zones with point-matched, patched, overset, or embedded connectivities. Both multigrid and mesh sequencing are available in time-accurate or steady-state modes.
Weight Analysis of Turbine Engine - an Object-Oriented Version (WATE )
WATE is an object-oriented computer code for gas turbine engine weight estimation; it calculates the weight and dimension of each major gas turbine engine component. It is used to create engine architecture that could achieve an engine thermodynamic cycle produced by a thermodynamic cycle code. The thermodynamic cycle data, the material properties, and design rules for geometric, stress, and turbo-machinery stage-loading limits were used to determine an acceptable engine flowpath and weight. The code was converted from the structured FORTRAN version of the code, originally developed by Boeing Aircraft for NASA, to improve its maintainability and extensibility. The conversion was done within the NASAs NPSS (Numerical Propulsion System Simulation) framework. This enables WATE to interact seamlessly with the thermodynamic cycle model which provides component flow data such as airflows, temperatures, and pressures, etc. that are also required for sizing the components and weight calculations. The tight integration between the NPSS and WATE greatly enhances system-level analysis and optimization capabilities.
U.S. Release Only
NPSS Electrical Power System Analysis Toolbox
An electrical power system analysis tool that can integrate with traditional combustion based propulsion models to analyze the potential benefits of aircraft electrification in the NPSS environment. This toolbox basic (text book based) electrical power system component models and an electrical port which connects these component models together to ensure the correct data is available to each model. The toolbox sizes the electrical power system based on required load demand at the design point and determines the power available to the loads in off-design.
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