Multidisciplinary Optimization of Air breathing Hypersonic Vehicles

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```					Problem 5

Classification: I A 3

Title: Multidisciplinary optimization of Air breathing Hypersonic Vehicles

References: Kevin G. Bowcutt, The Boeing Company, Long Beach, California 90807-5309,

Journal of Power and Propulsion Vol. 17, No. 6, November–December 2001.

Description:

This problem deals with maximizing the range of a hypersonic cruise missile wherein there

is a high degree of interdependency between the airframe and the engine. This problem

deals with development and implementation of MDO in the conceptual design of a

hypersonic Air breathing Vehicle which combines propulsion and external aerodynamic

forces, mass properties and internal volumetric modeling in maximizing the range of the

vehicle.

System Representation:

Geometric Model

Stability and Control
Model

Optimizer
Mass Properties Model

Trajectory/Performance
Model

Objective Function
DSM MATRIX:

Geometric
Analysis

Stability and
Control Analysis

Mass Properties
Analysis

Trajectory
Analysis

Design variables:

D = drag
g = gravitational acceleration

Isp = specific impulse

Iyy = pitch moment of inertia

K = centrifugal relief factor

L = lift

L p = propulsive lift

lchine = chine length

lcowl = nozzle cowl length

M® = pitching-moment derivative

P q = pitch acceleration

R = range

T = thrust in flight direction

TQ = thrust magnitude

T2 = time to double

V = velocity

W = weight

W0 = weight modified by centrifugal relief

WQ = required cruise aerodynamic lift

wf = fuel flow rate

xeng = engine axial location

® = angle of attack

μcant = engine cant angle
μnose = upper-body nose angle

μT = thrust vector angle

Objective Function:

Maximize: R(range)

Constraints:

   L=W

   T=D(Thrust equal to drag during cruise)

   Height ≤ Heightmax

   Width ≤ Widthmax

   Length ≤ Lengthmax

```
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