X-Git-Url: https://git.gag.com/?a=blobdiff_plain;ds=sidebyside;f=altosui%2Faltoslib%2Fsrc%2Forg%2Faltusmetrum%2FAltosLib%2FAltosConvert.java;fp=altosui%2Faltoslib%2Fsrc%2Forg%2Faltusmetrum%2FAltosLib%2FAltosConvert.java;h=df41a522ad956a967d2d103d65cb95ba8ad26a8f;hb=6510e8495fc5e8057b6092963def4d78978625a0;hp=0000000000000000000000000000000000000000;hpb=97663f922e236f4ee7bd08277ca80d419b5cd10f;p=fw%2Faltos diff --git a/altosui/altoslib/src/org/altusmetrum/AltosLib/AltosConvert.java b/altosui/altoslib/src/org/altusmetrum/AltosLib/AltosConvert.java new file mode 100644 index 00000000..df41a522 --- /dev/null +++ b/altosui/altoslib/src/org/altusmetrum/AltosLib/AltosConvert.java @@ -0,0 +1,259 @@ +/* + * Copyright © 2010 Keith Packard + * + * 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. + */ + +/* + * Sensor data conversion functions + */ +package altosui; + +public class AltosConvert { + /* + * Pressure Sensor Model, version 1.1 + * + * written by Holly Grimes + * + * Uses the International Standard Atmosphere as described in + * "A Quick Derivation relating altitude to air pressure" (version 1.03) + * from the Portland State Aerospace Society, except that the atmosphere + * is divided into layers with each layer having a different lapse rate. + * + * Lapse rate data for each layer was obtained from Wikipedia on Sept. 1, 2007 + * at site MAXIMUM_ALTITUDE) /* FIX ME: use sensor data to improve model */ + return 0; + + /* calculate the base temperature and pressure for the atmospheric layer + associated with the inputted altitude */ + for(layer_number = 0; layer_number < NUMBER_OF_LAYERS - 1 && altitude > base_altitude[layer_number + 1]; layer_number++) { + delta_z = base_altitude[layer_number + 1] - base_altitude[layer_number]; + if (lapse_rate[layer_number] == 0.0) { + exponent = GRAVITATIONAL_ACCELERATION * delta_z + / AIR_GAS_CONSTANT / base_temperature; + base_pressure *= Math.exp(exponent); + } + else { + base = (lapse_rate[layer_number] * delta_z / base_temperature) + 1.0; + exponent = GRAVITATIONAL_ACCELERATION / + (AIR_GAS_CONSTANT * lapse_rate[layer_number]); + base_pressure *= Math.pow(base, exponent); + } + base_temperature += delta_z * lapse_rate[layer_number]; + } + + /* calculate the pressure at the inputted altitude */ + delta_z = altitude - base_altitude[layer_number]; + if (lapse_rate[layer_number] == 0.0) { + exponent = GRAVITATIONAL_ACCELERATION * delta_z + / AIR_GAS_CONSTANT / base_temperature; + pressure = base_pressure * Math.exp(exponent); + } + else { + base = (lapse_rate[layer_number] * delta_z / base_temperature) + 1.0; + exponent = GRAVITATIONAL_ACCELERATION / + (AIR_GAS_CONSTANT * lapse_rate[layer_number]); + pressure = base_pressure * Math.pow(base, exponent); + } + + return pressure; + } + + +/* outputs the altitude associated with the given pressure. the altitude + returned is measured with respect to the mean sea level */ + static double + pressure_to_altitude(double pressure) + { + + double next_base_temperature = LAYER0_BASE_TEMPERATURE; + double next_base_pressure = LAYER0_BASE_PRESSURE; + + double altitude; + double base_pressure; + double base_temperature; + double base; /* base for function to determine base pressure of next layer */ + double exponent; /* exponent for function to determine base pressure + of next layer */ + double coefficient; + int layer_number; /* identifies layer in the atmosphere */ + int delta_z; /* difference between two altitudes */ + + if (pressure < 0) /* illegal pressure */ + return -1; + if (pressure < MINIMUM_PRESSURE) /* FIX ME: use sensor data to improve model */ + return MAXIMUM_ALTITUDE; + + /* calculate the base temperature and pressure for the atmospheric layer + associated with the inputted pressure. */ + layer_number = -1; + do { + layer_number++; + base_pressure = next_base_pressure; + base_temperature = next_base_temperature; + delta_z = base_altitude[layer_number + 1] - base_altitude[layer_number]; + if (lapse_rate[layer_number] == 0.0) { + exponent = GRAVITATIONAL_ACCELERATION * delta_z + / AIR_GAS_CONSTANT / base_temperature; + next_base_pressure *= Math.exp(exponent); + } + else { + base = (lapse_rate[layer_number] * delta_z / base_temperature) + 1.0; + exponent = GRAVITATIONAL_ACCELERATION / + (AIR_GAS_CONSTANT * lapse_rate[layer_number]); + next_base_pressure *= Math.pow(base, exponent); + } + next_base_temperature += delta_z * lapse_rate[layer_number]; + } + while(layer_number < NUMBER_OF_LAYERS - 1 && pressure < next_base_pressure); + + /* calculate the altitude associated with the inputted pressure */ + if (lapse_rate[layer_number] == 0.0) { + coefficient = (AIR_GAS_CONSTANT / GRAVITATIONAL_ACCELERATION) + * base_temperature; + altitude = base_altitude[layer_number] + + coefficient * Math.log(pressure / base_pressure); + } + else { + base = pressure / base_pressure; + exponent = AIR_GAS_CONSTANT * lapse_rate[layer_number] + / GRAVITATIONAL_ACCELERATION; + coefficient = base_temperature / lapse_rate[layer_number]; + altitude = base_altitude[layer_number] + + coefficient * (Math.pow(base, exponent) - 1); + } + + return altitude; + } + + static double + cc_battery_to_voltage(double battery) + { + return battery / 32767.0 * 5.0; + } + + static double + cc_ignitor_to_voltage(double ignite) + { + return ignite / 32767 * 15.0; + } + + static double radio_to_frequency(int freq, int setting, int cal, int channel) { + double f; + + if (freq > 0) + f = freq / 1000.0; + else { + if (setting <= 0) + setting = cal; + f = 434.550 * setting / cal; + /* Round to nearest 50KHz */ + f = Math.floor (20.0 * f + 0.5) / 20.0; + } + return f + channel * 0.100; + } + + static int radio_frequency_to_setting(double frequency, int cal) { + double set = frequency / 434.550 * cal; + + return (int) Math.floor (set + 0.5); + } + + static int radio_frequency_to_channel(double frequency) { + int channel = (int) Math.floor ((frequency - 434.550) / 0.100 + 0.5); + + if (channel < 0) + channel = 0; + if (channel > 9) + channel = 9; + return channel; + } + + static double radio_channel_to_frequency(int channel) { + return 434.550 + channel * 0.100; + } + + static int[] ParseHex(String line) { + String[] tokens = line.split("\\s+"); + int[] array = new int[tokens.length]; + + for (int i = 0; i < tokens.length; i++) + try { + array[i] = Integer.parseInt(tokens[i], 16); + } catch (NumberFormatException ne) { + return null; + } + return array; + } + + static double meters_to_feet(double meters) { + return meters * (100 / (2.54 * 12)); + } + + static double meters_to_mach(double meters) { + return meters / 343; /* something close to mach at usual rocket sites */ + } + + static double meters_to_g(double meters) { + return meters / 9.80665; + } + + static int checksum(int[] data, int start, int length) { + int csum = 0x5a; + for (int i = 0; i < length; i++) + csum += data[i + start]; + return csum & 0xff; + } +}