X-Git-Url: https://git.gag.com/?a=blobdiff_plain;ds=sidebyside;f=ao-tools%2Fao-fakeflight%2Fao-fakeflight.c;fp=ao-tools%2Fao-fakeflight%2Fao-fakeflight.c;h=8a9925934961f5798f1ccc34cbe7a330c3a31ce7;hb=248aaf5e76292c8e6bfa3600d2cf9b194bf66c86;hp=0000000000000000000000000000000000000000;hpb=4f2cbe0c537c9f417aae310cc3b89f84e0915103;p=fw%2Faltos

diff --git a/ao-tools/ao-fakeflight/ao-fakeflight.c b/ao-tools/ao-fakeflight/ao-fakeflight.c
new file mode 100644
index 00000000..8a992593
--- /dev/null
+++ b/ao-tools/ao-fakeflight/ao-fakeflight.c
@@ -0,0 +1,179 @@
+/*
+ * 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.
+ */
+
+#include "ao-fakeflight.h"
+
+char *state_name[] = {
+	[state_ascent] = "ascent",
+	[state_drogue] = "drogue",
+	[state_main] = "main",
+	[state_landed] = "landed",
+};
+
+struct rocket o5778 = {
+	.models = {
+		[state_ascent] = {
+			.cd = 0.5,
+			.diameter = .100
+		},
+		[state_drogue] = {
+			.cd = 1.3,
+			.diameter = .300
+		},
+		[state_main] = {
+			.cd = 1.3,
+			.diameter = 1.0
+		},
+	},
+	.empty_mass = 15.0,
+	.main_deploy = 250,
+	.motors = {
+		[0] = {
+			.fuel_mass = 18.021,
+			.average_thrust = 5778.0,
+			.burn_time = 8.52,
+			.delay = 0.0,
+		},
+		[1] = {
+			.fuel_mass = 18.021,
+			.average_thrust = 5778.0,
+			.burn_time = 0, /* 17.04 */
+			.delay = 18.0,
+		},
+	},
+};
+
+struct rocket n5778 = {
+	.models = {
+		[state_ascent] = {
+			.cd = 0.5,
+			.diameter = .100
+		},
+		[state_drogue] = {
+			.cd = 1.3,
+			.diameter = .300
+		},
+		[state_main] = {
+			.cd = 1.3,
+			.diameter = 1.0
+		},
+	},
+	.empty_mass = 15.0,
+	.main_deploy = 250,
+	.motors = {
+		[0] = {
+			.fuel_mass = 9.0105,
+			.average_thrust = 5778.0,
+			.burn_time = 4.26,
+			.delay = 0.0,
+		},
+	},
+};
+
+/*
+ * Move the flight one tick forward
+ */
+void
+step(struct flight *f, struct rocket *r)
+{
+	double	drag = rocket_drag(f, r);
+	double	thrust = rocket_thrust(f, r);
+	double	gravity = rocket_gravity(f, r);
+	double	mass = rocket_mass(f, r);
+	double	accel;
+
+	/* This is our acceleration relative to the earth */
+	accel = (drag + thrust - gravity) / mass;
+
+	/* Because the accelerometer is also affected by gravity, it
+	 * only measures *other* forces applied to the rocket
+	 */
+	f->accel = (drag + thrust) / mass;
+
+	f->altitude += f->speed * STEP + 0.5 * (accel * STEP) * (accel * STEP);
+	f->speed += accel * STEP;
+	f->time += STEP;
+}
+
+void
+init(struct flight *f, struct rocket *r)
+{
+	double gravity = rocket_gravity(f, r);
+
+	/* The pad is pushing up on the rocket to counter
+	 * gravity, so the accelerometer, which only measures
+	 * forces other than gravity, sees only this
+	 */
+	f->accel = gravity / rocket_mass(f, r);
+	f->speed = 0;
+	f->altitude = 0;
+	f->time += STEP;
+}
+
+void
+fly(FILE *file, struct rocket *r)
+{
+	struct flight f = {
+		.time = -1,
+		.altitude = 0,
+		.speed = 0,
+		.accel = 0,
+		.state = state_ascent,
+	};
+
+	double	max_speed = 0;
+	double	max_alt = 0;
+	double	max_accel = 0;
+
+
+	ao_show_header(file, r);
+	while (f.time < 0) {
+		init(&f, r);
+		ao_log(file, &f, r);
+	}
+	while (f.altitude >= 0) {
+		step(&f, r);
+		switch (f.state) {
+		case state_ascent:
+			if (f.speed >= 0)
+				break;
+			f.state = state_drogue;
+			/* fall through */
+		case state_drogue:
+			if (f.altitude > o5778.main_deploy)
+				break;
+			f.state = state_main;
+			/* fall through */
+		case state_main:
+			break;
+		}
+		ao_log(file, &f, r);
+		max_speed = fmax(max_speed, f.speed);
+		max_accel = fmax(max_accel, f.accel);
+		max_alt = fmax(max_alt, f.altitude);
+	}
+	fprintf(stderr, "max alt %9.1f speed %9.1f accel %9.1f\n",
+		max_alt, max_speed, max_accel);
+}
+
+int
+main(int argc, char **argv)
+{
+	fly(stdout, &o5778);
+//	fly(stdout, &n5778);
+	return 0;
+}