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 *
170 lines
2.3 KiB
C
170 lines
2.3 KiB
C
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#ifndef __state_h__
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#define __state_h__
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typedef double real;
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typedef real scalar_t;
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typedef real vector_t[3];
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typedef real matrix_t[3][3];
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typedef enum
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{
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_CONSTANT,
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_FUNCTION,
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_TABLE
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} val_t;
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typedef enum
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{
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ALT,
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MACH,
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AOA,
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TIME
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} parameter_t;
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typedef struct _function
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{
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char *name;
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val_t type;
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/* if type is _CONSTANT */
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float constant_value;
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/* if type is _TABLE */
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int n_point;
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parameter_t independant_var;
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float *x, *y;
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/* if type is _FUNCTION */
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char *function;
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} function_t;
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typedef struct state
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{
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int s; /* active stage */
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scalar_t m; /* mass of the rocket */
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scalar_t g; /* gravitational acceleration */
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scalar_t Ix;
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scalar_t Iy;
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scalar_t Iz;
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/* */
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scalar_t alt;
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scalar_t aoa;
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scalar_t mach;
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/* aerodynamic coefficients */
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scalar_t Cd;
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scalar_t CL;
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scalar_t CB;
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scalar_t Cspin;
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scalar_t Cmoment;
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scalar_t Cdamping;
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scalar_t D; /* Diameter of the rocket */
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scalar_t A; /* reference area (m^2) */
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scalar_t C; /* reference distance */
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/* aerodynamic forces */
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vector_t Faero; /* (X, Y, Z) */
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/* moments */
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vector_t Maero; /* (L, M, N) */
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/* engine forces and moments */
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vector_t Feng;
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vector_t Meng;
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/* component of centripetal acceleration in F_B */
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scalar_t Cx;
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scalar_t Cy;
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scalar_t Cz;
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/* earth angular velocity in F_B */
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scalar_t pE;
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scalar_t qE;
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scalar_t rE;
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/* relative angular velocity of F_B to F_V */
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scalar_t P;
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scalar_t Q;
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scalar_t R;
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matrix_t L_BV;
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matrix_t L_VB;
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} state_t;
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typedef struct engine
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{
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float propellant_mass;
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float dry_mass;
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function_t thrust;
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float c;
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float mass_flow;
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float start_time;
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float burn_time;
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float drop_time;
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float position[3];
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float direction[3];
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} engine_t;
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typedef struct rocket_properties
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{
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float dry_mass;
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function_t Ix;
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function_t Iy;
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function_t Iz;
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function_t Cd;
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function_t CL;
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function_t CB;
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float Cspin;
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float Cmoment;
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float Cdamping;
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float Diameter;
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float active_time;
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int n_engine;
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engine_t *engines;
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} rocket_properties_t;
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typedef struct rocket
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{
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int n_stage;
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rocket_properties_t *stage_properties;
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state_t state;
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} rocket_t;
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typedef struct solution
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{
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float duration;
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float dt;
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float precision;
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} solution_t;
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#endif /* __state_h__ */
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