A Nonlinear Six Degree-of-freedom Flight Simulation Model

A Nonlinear Six Degree-of-freedom Flight Simulation Model
Author: A. B. Markov
Publisher:
Total Pages: 0
Release: 1990
Genre: Cruise missiles
ISBN:

"Six degree-of-freedom, rigid body equations of motion are described suitable for modeling the dynamic characteristics of multistaged rocket-boosted maneuvering aerial targets such as the DRES developed ROBOT-X. These equations of motion form the core of a Fortran simulation package called FLISIM. FLISIM is currently installed on a VAX 11/780 computer and allows for modeling of vehicle thrust and structural asymmetries, time-varying mass and inertia characteristics, autopilot control laws, autopilot update rates, autopilot sensor non-idealities, nonlinear aerodynamic characteristics, variable wind conditions, turbulence, nonstandard atmospheric conditions, stage and individual motor failures, different rocket motor types, and parachute deceleration dynamics. The FLISIM software package has been developed in two versions (FLISIMV1 and FLISIMV2) using two different aerodynamic models. Both are written in VAX 11 Fortran and run under the VMS Operating System. FLISIM is fully supported with a plotting software package (PLTSIM) developed around Tektronix PLOT 10 core software"--abstract.

A Nonlinear Six Degree-of-Freedom Ballistic Aerial Target Simulation Model. Volume 1. Theoretical Development

A Nonlinear Six Degree-of-Freedom Ballistic Aerial Target Simulation Model. Volume 1. Theoretical Development
Author:
Publisher:
Total Pages: 51
Release: 1984
Genre:
ISBN:

Six degree-of-freedom, rigid body equations of motion are described suitable for modeling the dynamic characteristics of multistaged, free-flight, ballistic rockets such as the DRES developed aerial targets CRV7/BATS and ROBOT- 9. These equations of motion form the core of a FORTRAN simulation software package called BALSIM. This package allows for modeling of vehicle thrust and structural symmetries, time-varying mass and inertia characteristics, variable wind conditions, nonstandard atmospheric conditions, stage failures, and different rocket motor types. The BALSIM package has been written in IBM FORTRAN IV and has been tested on the IBM 3033 computer with the H-extended compiler. It is currently being adapted for use with the VAX11/780 and Honeywell DPS-8/70C computers.

Flight Dynamics

Flight Dynamics
Author: Robert F. Stengel
Publisher: Princeton University Press
Total Pages: 914
Release: 2022-11-01
Genre: Science
ISBN: 0691237042

An updated and expanded new edition of an authoritative book on flight dynamics and control system design for all types of current and future fixed-wing aircraft Since it was first published, Flight Dynamics has offered a new approach to the science and mathematics of aircraft flight, unifying principles of aeronautics with contemporary systems analysis. Now updated and expanded, this authoritative book by award-winning aeronautics engineer Robert Stengel presents traditional material in the context of modern computational tools and multivariable methods. Special attention is devoted to models and techniques for analysis, simulation, evaluation of flying qualities, and robust control system design. Using common notation and not assuming a strong background in aeronautics, Flight Dynamics will engage a wide variety of readers, including aircraft designers, flight test engineers, researchers, instructors, and students. It introduces principles, derivations, and equations of flight dynamics as well as methods of flight control design with frequent reference to MATLAB functions and examples. Topics include aerodynamics, propulsion, structures, flying qualities, flight control, and the atmospheric and gravitational environment. The second edition of Flight Dynamics features up-to-date examples; a new chapter on control law design for digital fly-by-wire systems; new material on propulsion, aerodynamics of control surfaces, and aeroelastic control; many more illustrations; and text boxes that introduce general mathematical concepts. Features a fluid, progressive presentation that aids informal and self-directed study Provides a clear, consistent notation that supports understanding, from elementary to complicated concepts Offers a comprehensive blend of aerodynamics, dynamics, and control Presents a unified introduction of control system design, from basics to complex methods Includes links to online MATLAB software written by the author that supports the material covered in the book

High Speed Civil Transport Aircraft Simulation

High Speed Civil Transport Aircraft Simulation
Author: National Aeronautics and Space Adm Nasa
Publisher:
Total Pages: 82
Release: 2018-09-23
Genre:
ISBN: 9781723955945

The mathematical model and associated code to simulate a high speed civil transport aircraft - the Boeing Reference H configuration - are described. The simulation was constructed in support of advanced control law research. In addition to providing time histories of the dynamic response, the code includes the capabilities for calculating trim solutions and for generating linear models. The simulation relies on the nonlinear, six-degree-of-freedom equations which govern the motion of a rigid aircraft in atmospheric flight. The 1962 Standard Atmosphere Tables are used along with a turbulence model to simulate the Earth atmosphere. The aircraft model has three parts - an aerodynamic model, an engine model, and a mass model. These models use the data from the Boeing Reference H cycle 1 simulation data base. Models for the actuator dynamics, landing gear, and flight control system are not included in this aircraft model. Dynamic responses generated by the nonlinear simulation are presented and compared with results generated from alternate simulations at Boeing Commercial Aircraft Company and NASA Langley Research Center. Also, dynamic responses generated using linear models are presented and compared with dynamic responses generated using the nonlinear simulation.Sotack, Robert A. and Chowdhry, Rajiv S. and Buttrill, Carey S.Langley Research CenterSUPERSONIC TRANSPORTS; TRANSPORT AIRCRAFT; BOEING AIRCRAFT; CIVIL AVIATION; AIRCRAFT MODELS; MATHEMATICAL MODELS; COMPUTERIZED SIMULATION; ALGORITHMS; AERODYNAMIC CHARACTERISTICS; DYNAMIC RESPONSE; FLIGHT CONTROL; CONTROL SYSTEMS DESIGN; LANDING GEAR; NONLINEAR EQUATIONS; EQUATIONS OF MOTION; UNSTEADY FLOW; STEADY FLOW...

Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail

Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail
Author: Paul T. Soderman
Publisher:
Total Pages: 108
Release: 1971
Genre: Airplanes
ISBN:

The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.