1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
90
91
92
93
94
95
96
97
98
99
100
101
102
103
104
105
106
107
108
109
110
111
112
113
114
115
116
117
118
119
120
121
122
123
124
125
126
127
128
129
130
131
132
133
134
135
136
137
138
139
140
|
/*
* Copyright © 2014 Keith Packard <keithp@keithp.com>
*
* This program is free software; you can redistribute it and/or modify
* it under the terms of the GNU General Public License as published by
* the Free Software Foundation; version 2 of the License.
*
* This program is distributed in the hope that it will be useful, but
* WITHOUT ANY WARRANTY; without even the implied warranty of
* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
* General Public License for more details.
*
* You should have received a copy of the GNU General Public License along
* with this program; if not, write to the Free Software Foundation, Inc.,
* 59 Temple Place, Suite 330, Boston, MA 02111-1307 USA.
*/
#ifndef _AO_FAKEFLIGHT_H_
#define _AO_FAKEFLIGHT_H_
#define __xdata
#include <stdint.h>
#include <ao_ms5607.h>
#include <math.h>
#include <stdio.h>
#include "cc.h"
#define GAS_CONSTANT 287.05
#define STEP 0.01
#define GRAVITATIONAL_CONSTANT 6.67384e-11
#define GRAVITY 9.807
#define EARTH_MASS 5.9726e24
#define EARTH_RADIUS 6375313
enum flight_state {
state_ascent,
state_drogue,
state_main,
state_landed,
state_num
};
extern char *state_name[];
struct model {
double cd;
double diameter;
};
struct motor {
double fuel_mass;
double average_thrust;
double burn_time;
double delay;
};
#define MAX_MOTORS 12
struct rocket {
struct model models[state_num];
double empty_mass;
double main_deploy;
struct motor motors[MAX_MOTORS];
};
/* Flight state */
struct flight {
double time;
double altitude;
double speed;
double accel;
enum flight_state state;
};
/* ao-physics.c */
/* Density of dry air in kg/m³ for a given pressure and temperature. */
/* Density of dry air in kg/m³ for a given pressure and temperature. */
double
density_air(double pressure, /* Pa */
double temperature); /* °C */
/* Area of a circle */
double
area_circle(double diameter);
/* Force due to drag (N) */
double
force_drag(double speed, /* m/s */
double rho, /* kg/m³ */
double cd, /* unitless */
double area); /* m² */
/* Force due to gravity (N) */
double
force_gravity(double mass, /* kg */
double altitude); /* m */
/* ao-rocket.c */
/* Mass (kg) of the airframe */
double
rocket_mass(struct flight *f, struct rocket *r);
/* Force (N) due to thrust */
double
rocket_thrust(struct flight *f, struct rocket *r);
/* Drag (N) due to air resistance */
double
rocket_drag(struct flight *f, struct rocket *r);
/* Force (N) due to gravity */
double
rocket_gravity(struct flight *f, struct rocket *r);
/* ao-fake-convert.c */
void
ao_ms5607_unconvert(double altitude,
struct ao_ms5607_sample *ret);
int16_t
ao_accel_unconvert(double accel);
void
ao_show_header(FILE *f, struct rocket *r);
/* ao-fake-log.c */
void
ao_log_flight(FILE *file, struct flight *f, struct rocket *r);
void
ao_log_sensor(FILE *file, struct flight *f, struct rocket *r);
void
ao_log_state(FILE *file, struct flight *f, struct rocket *r);
#endif
|
