Patent ID: 6164596
Filing Date: 2000-12-26
Classification: B64C,B64G,F02K,G06F,Y02T

Abstract:
A computer implemented method of designing a space vehicle, comprising the steps of:determining a characteristic of a flow field;selecting a Radial Deviation Parameter numerical value consistent with the characteristic of the flow field;determining a shape of an inlet based on the Radial Deviation Parameter numerical value;determining a first exit property of the inlet;configuring a shape of an isolator based on the first exit property;determining a second exit property of the isolator;configuring a shape of a combustor based on the second exit property;determining a third exit property of the combustor;configuring a shape of a nozzle based on the third exit property;configuring an external surface based on the flow field;determining a lower wing and an upper wing based on a lifting characteristic provided by the flow field;displaying a graphical representation of the designed space vehicle.