eb05416991
Taken from sources in CVS at:
https://sourceforge.net/projects/rocketworkbench/
Sources extracted in two steps:
1. Pull entire project tree into a subdir "rwb" via "rsync":
rsync -a a.cvs.sourceforge.net::cvsroot/rocketworkbench/ rwb/.
2. Export sources:
export CVSROOT=$(pwd)/rwb
SUBDIRS="analyser cpropep cpropep-web CVSROOT data libcompat libcpropep libnum libsimulation libthermo prop rocketworkbench rockflight"
mkdir rwbx; cd rwbx
cvs export -D now ${SUBDIRS}
After this (and some backups for safety), the directory content was
added to a Git repo:
git init .
git add *
73 lines
2.5 KiB
C
73 lines
2.5 KiB
C
#ifndef lrd_h
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#define lrd_h
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#include "libcpropep/include/type.h"
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typedef struct _design_param_t
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{
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/* Design criteria */
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double chamber_pressure; /* Operating pressure of the motor (atm) */
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double thrust; /* Thrust of the motor (N) */
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double Lstar; /* Cracteristic chamber lengtgh */
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double Dc_Dt; /* Chamber diameter / Throat diameter */
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double R_Rt; /* Ratio of nozzle contour arc radius
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to throat radius */
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double theta; /* Convergent half angle (deg) */
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} design_param_t;
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typedef struct _motor_t
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{
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/* Unknown that will be compute */
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double mass_flow_rate; /* Total mass flow (kg/s) */
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double ox_flow_rate; /* Oxidant mass flow rate */
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double fu_flow_rate; /* Fuel mass flow rate */
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double throat_area; /* (m^2) */
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double throat_diameter; /* (m) */
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double throat_radius; /* (m) */
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double exit_area; /* (m^2) */
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double exit_diameter; /* (m) */
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double exit_radius; /* (m) */
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double Ac_At; /* Chamber area / throat area */
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/* total */
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double chamber_volume; /* (m^3) */
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double chamber_area; /* (m^2) */
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double chamber_diameter; /* (m) */
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double chamber_radius; /* (m) */
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double chamber_length; /* (m) */
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/* conical section */
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double convergent_volume; /* (m^3) */
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double convergent_length; /* (m) */
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/* cylindrical section */
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double cylinder_volume; /* (m^3) */
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double cylinder_length; /* (m) */
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double walls_area; /* total surface area of the
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combustion chamber walls
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excluding injector face */
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} motor_t;
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typedef struct _liquid_propellant_t
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{
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int oxidant;
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int fuel;
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double o_f_ratio;
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} liquid_propellant_t;
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int LRD_compute_caracteristics(equilibrium_t *e, design_param_t *d,
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motor_t *m, liquid_propellant_t *p);
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int LRD_print_propellant_info(liquid_propellant_t *p);
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int LRD_print_design_criteria(design_param_t *c);
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int LRD_print_design_information(motor_t *mf, motor_t *ms);
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#endif
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