Aeronautics and astronautics are two closely related disciplines, sometimes found under the joint term aerospace, that have progressed at a formidable pace during the 20th century. Their im...

Aeronautics and astronautics: Recent progress and future trends

Assessment on critical technologies for conceptual design of blended-wing-body civil aircraft

Transient Performance Simulation of Aircraft Engine Integrated with Fuel and Control Systems

Dynamic performance simulation and control of gas turbines used for hybrid gas/wind energy applications

A transient two-stream engine model has been developed. Individual component models developed exclusively in MATLAB/Simulink including the fan, high pressure compressor, combustor, high pressure turbine, low pressure turbine, plenum volumes, and exit nozzle have been combined to investigate the behavior of a turbofan two-stream engine. Special attention has been paid to the development of transient capabilities throughout the model, increasing physics model, eliminating algebraic constraints, and reducing simulation time through enabling the use of advanced numerical solvers. The lessening of computation time is paramount for conducting future aircraft system-level design trade studies and optimization. The new engine model is simulated for a fuel perturbation and a specified mission while tracking critical parameters. These results, as well as the simulation times, are presented. The new approach significantly reduces the simulation time.

/pdf/modeling-techniques-for-a-computational-efficient-dynamic-2e4jwltxxl.pdf

Modeling Techniques for a Computational Efficient Dynamic Turbofan Engine Model

This paper presents a transient three-spool turbofan engine simulation model that uses a combination of intercomponent volume and iterative techniques. The engine model runs in real time and has been implemented in MATLAB /SIMULINK environment. The main advantage of this hybrid approach is that it preserves the accuracy of the iterative method while maintaining the simplicity of the intercomponent volume method. The iterative approach is applied at each engine subsystem to solve algebraic thermodynamic equations for exit enthalpy, entropy, and temperature, whereas the intercomponent volume method is used to calculate pressures derivatives and hence pressures at corresponding engine stations. This allows the engine state vector to be updated at each pass through the engine calculations. This technique was applied as a test case on the Rolls Royce Trent 500 three-spool turbofan engine, and the results were compared with an iterative method. As the engine state vector is updated during each cycle, the model lends itself for easy integration into nonlinear aircraft simulations, real-time engine diagnostics/prognostics, and jet engine control applications.

Real-Time Transient Three Spool Turbofan Engine Simulation: A Hybrid Approach

A real time simulation model has been developed to investigate the effect of variable engine bleed on steady state and transient performance of a single-spool turbojet engine. The bleed air...

/pdf/a-numerical-investigation-into-the-effect-of-engine-bleed-on-2y3mtu9n9t.pdf

A numerical investigation into the effect of engine bleed on performance of a single-spool turbojet engine

Design of a longitudinal flight control system for a Blended Wing Body (BWB) tailless aircraft is presented. The BWB aircraft is assumed to be operating with a reduced static margin and is marginally stable. After trimming, the linear model is obtained by evaluating the dimensional derivatives for a low speed terminal flight condition. The linear model is then augmented with actuator dynamics. The longitudinal short period and phugoid dynamics are initially analyzed for the open loop case. The short period mode was restored artificially to nominal values by incidence and pitch rate feedback. Once the conventional short period is restored a pitch rate command attitude-hold (RCAH) flight control system was designed to improve the handling qualities of the aircraft. The Gibson Dropback handling qualities assessment criteria [1] was applied to evaluate the pilot opinion rating. The handling qualities were assessed for both the augmented and un-augmented case. For this tailless configuration, the handling qualities improved from Level 2 to Level 1 when the rate command attitude hold longitudinal flight control system was engaged.

http://ieeexplore.ieee.org/iel5/5585908/5596161/05596389.pdf

Longitudinal control system design and handling qualities assessment of a Blended Wing Body aircraft

While operating at low airspeeds with nominal static margins, the controls on a blended-wing-body aircraft begin to saturate, and the dynamic performance gets sluggish. Augmentation of aerodynamic controls with the propulsion system is therefore considered in this research. Two aspects were of interest: namely, thrust vectoring and flap blowing. An aerodynamic model for a large blended-wing-body transport aircraft with blown flap effects was formulated using empirical and vortex lattice methods and then integrated with a Trent 500 turbofan engine model. To enhance control effectiveness, both internally and externally blown flaps were simulated. For a full-span internally blown flap arrangement using intermediate compressor flow, the amount of engine bleed and the resulting blowing coefficients were limited. However, even with a reduced bleed mass flow, the pitch control effectiveness increases by 15.9% at 85% fan revolutions per minute. For an externally blown flap arrangement using bypass air, much higher blowing coefficients can be achieved. For instance, at 100% fan revolutions per minute, there is a 44% increase in pitch control authority at low dynamic pressures. The main benefit occurs during takeoff, where both thrust vectoring and flap blowing help in achieving early pitch rotation, reducing takeoff field length and liftoff speed considerably. With central flap blowing and a limited thrust vectoring of 10°, the liftoff range reduces by 48%, and liftoff speed reduces by almost 26%.

Propulsion and Flight Controls Integration for a Blended-Wing-Body Transport Aircraft

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Real-Time Transient Three Spool Turbofan Engine Simulation: A Hybrid Approach

A numerical investigation into the effect of engine bleed on performance of a single-spool turbojet engine

Longitudinal control system design and handling qualities assessment of a Blended Wing Body aircraft

Propulsion and Flight Controls Integration for a Blended-Wing-Body Transport Aircraft