SIMULATION REQUIREMENTS
=======================



The simulation will be a 6DOF flight simulator of a fictional rocket that 
uses the designed hybrid engine in order to test the performance of the 
engine.  Monte Carlo (random) variables will be used.

Sections of the flight sim will be:
	DYNAMICS SECTION (y' = f(t,y))
	ENGINE MODEL
	AERO MODEL
	CONTROL SYSTEM MODEL
	ATMOSPHERE MODEL




SECTION CONSTANTS, INPUT, AND OUTPUT
------------------------------------

=========================================================================================
ENGINE SECTION:										|
=========================================================================================




	=================================================================================
	| ENGINE::GRAIN GEOMETRY:							|
	=================================================================================
	| SYMBOL	| VALUE		| UNITS		| DESCRIPTION			|
	================+===============+===============+================================
	| egLP		| 1.0		| m		| Length of the ports		|
	| egNP		| 7		| --		| Number of ports		|
	| egDP		| 0.4		| m		| Diameter of the grain		|
	| egCSGo	| data table	| --		| Grain cross-sect geom descr	|
	| egVG		| output	| M^2		| Volume of the fuel		|
	| egSABURN	| output	| inches^2	| Burnable surface area at t	|
	| egCSG		| output	| --		| Grain cross-sect geom descr	|
	================+===============+===============+================================

		MODULE THEORY:
		put in the geometry of the port, and have the geometry vary with time
		based on a geometric burn algorithm.  thermochemistry would have to be 
		a feedback input to make it more accurate (ie: areas of more intense 
		burning).
		


	=================================================================================
	| ENGINE::NOZZLE:								|
	=================================================================================
	| SYMBOL	| VALUE		| UNITS		| DESCRIPTION			|
	================+===============+===============+================================
	| enDTo		| 1.0		| inches	| Initial nozzle throat diameter|
	| enDEo		| 5.0		| inches	| Initial nozzle exit diameter	|
	| enLAMDAo	| 15.0		| degrees	| Initial nozzle lambda angle	|
	| enRRATE	| 0.05g0.02	| inches/s	| Nozzle regression rate	|
	| enAE		| output	| inches^2	| Nozzle exit area, Ae		|
	| enAT		| output	| inches^2	| Nozzle throat area, At	|
	| enEPSILON	| output	| --		| Ae/At				|
	================+===============+===============+================================

		MODULE THEORY:
		given the initial geometry, determine parameters for use in other modules
		and account for erosion of the throat.





	=================================================================================
	| ENGINE::OXIDIZER PARAMETERS:							|
	=================================================================================
	| SYMBOL	| VALUE		| UNITS		| DESCRIPTION			|
	================+===============+===============+================================
	| eoDINJ	| 0.053		| inches	| Diameter of an injector hole	|
	| eoNINJ	| 25		| --		| Number fo injector holes	|
	| eoLINJ	| 0.100		| inches	| Length of the injector holes	|
	| eoPOXo	| 1000g10	| psi		| Initial oxidizer tank pressure|
	| eoROXo	| 		| 		| Initial oxidizer density	|
	| eoTOXo	| 		| K		| Initial oxidizer temperature	|
	| eoMOXo	| 100g2		| kg		| Initial oxidizer mass		|
	| eoMOXDOT	| output	| kg/s		| Oxidizer mass flow rate	|
	| eoVOX		| output	| m^3		| Oxidizer volume		|
	| eoGO		| output	| --		| Oxidizer mass flux rate	|
	================+===============+===============+================================
		MODULE THEORY:
		this calculates the flow of the oxidizer into the engine.

	


	=================================================================================
	| ENGINE::GRAIN CHEMISTRY PARAMETERS:						|
	=================================================================================
	| SYMBOL	| VALUE		| UNITS		| DESCRIPTION			|
	================+===============+===============+================================
	| ecRHTPB	| 		| 		| Density of the HTPB		|
	| ecRIPDI	| 		| 		| Density of the IPDI		|
	| ecRCARBON	| 		| 		| Density of the CARBON BLACK	|
	| ecRCASTOR	| 		| 		| Density of the CASTOR OIL	|

	| ecVFUELo	| 		|m^3		| Initial volume of the fuel	|
	| ecRFUEL	| output	| 		| Density of the fuel		|
	================+===============+===============+================================
		MODULE THEORY:
		this module calculates the parameters of the fuel grains from the basic
		chemistry.





	=================================================================================
	| ENGINE::COMBUSTION/THERMOCHEMISTRY PARAMETERS:				|
	=================================================================================
	| SYMBOL	| VALUE		| UNITS		| DESCRIPTION			|
	================+===============+===============+================================
	| etA		| 0.7g0.3	| --		| 				|
	| etN		| 0.7g0.3	| --		|				|
	| etM		| 0.7g0.3	| --		|				|
	| etRRATE	| 0.2g0.05	| in/s		| Regression rate of the fuel	|
	| etISP		| output	| --		| Isp of the engine		|
	| etGAMMA	| output	| 		| Gammma for combustion products|
	| etMW 		| output	| 		| Molecular weight of comb prods|
	| etR		| output	|		| ?				|
	| etCSTAR	| output	| --		| ?				|
	| etPC		| output	|		| Chamber pressure		|
	| etMFDOT	| output	| kg/s		| Fuel mass flow rate		|
	| etOF		| output	| --		| Oxidizer to Fuel flow ratio	|
	| etTHRUST	| output	| N		| Engine thrust			|
	================+===============+===============+================================
		MODULE THEORY:
		this module calculates the combustion of the engine with time.
			Pc is a function of Pox
			Tf, k, M, R are calculated from either tables or as a 
			 function of O/F

		




=========================================================================================
ATMOSPHERE SECTION:									|
=========================================================================================


	=================================================================================
	| ATMOSPHERE::WEATHER:								|
	=================================================================================
	| SYMBOL	| VALUE		| UNITS		| DESCRIPTION			|
	================+===============+===============+================================
	| awTAIRo	| 293.0		| K		| Air temperature		|
	| awVWIND	| 0u20		| m/s		| Wind velocity			|
	| awDWIND	| 0u180		| degrees	| Wind direction		|
	| awPAIR	| output	| psi		| Air pressure			|
	| awRAIR	| output	| 		| Air density			|
	================+===============+===============+================================





=========================================================================================
CONTROL SYSTEM SECTION:									|
=========================================================================================


	=================================================================================
	| CONTROL::									|
	=================================================================================
	| SYMBOL	| VALUE		| UNITS		| DESCRIPTION			|
	================+===============+===============+================================
	| etFHISTo	| data table	| 		| Desired thrust history vs time|
	================+===============+===============+================================




=========================================================================================
AERODYNAMICS SECTION:									|
=========================================================================================



=========================================================================================
FLIGHT SECTION:										|
=========================================================================================


	INITIAL ALTITUDE