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1612 | dongfang | 1 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
2 | // + Copyright (c) 04.2007 Holger Buss |
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3 | // + Nur für den privaten Gebrauch |
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4 | // + www.MikroKopter.com |
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5 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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6 | // + Es gilt für das gesamte Projekt (Hardware, Software, Binärfiles, Sourcecode und Dokumentation), |
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7 | // + dass eine Nutzung (auch auszugsweise) nur für den privaten (nicht-kommerziellen) Gebrauch zulässig ist. |
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8 | // + Sollten direkte oder indirekte kommerzielle Absichten verfolgt werden, ist mit uns (info@mikrokopter.de) Kontakt |
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9 | // + bzgl. der Nutzungsbedingungen aufzunehmen. |
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10 | // + Eine kommerzielle Nutzung ist z.B.Verkauf von MikroKoptern, Bestückung und Verkauf von Platinen oder Bausätzen, |
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11 | // + Verkauf von Luftbildaufnahmen, usw. |
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12 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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13 | // + Werden Teile des Quellcodes (mit oder ohne Modifikation) weiterverwendet oder veröffentlicht, |
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14 | // + unterliegen sie auch diesen Nutzungsbedingungen und diese Nutzungsbedingungen incl. Copyright müssen dann beiliegen |
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15 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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16 | // + Sollte die Software (auch auszugesweise) oder sonstige Informationen des MikroKopter-Projekts |
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17 | // + auf anderen Webseiten oder sonstigen Medien veröffentlicht werden, muss unsere Webseite "http://www.mikrokopter.de" |
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18 | // + eindeutig als Ursprung verlinkt werden |
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19 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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20 | // + Keine Gewähr auf Fehlerfreiheit, Vollständigkeit oder Funktion |
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21 | // + Benutzung auf eigene Gefahr |
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22 | // + Wir übernehmen keinerlei Haftung für direkte oder indirekte Personen- oder Sachschäden |
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23 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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24 | // + Die Portierung der Software (oder Teile davon) auf andere Systeme (ausser der Hardware von www.mikrokopter.de) ist nur |
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25 | // + mit unserer Zustimmung zulässig |
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26 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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27 | // + Die Funktion printf_P() unterliegt ihrer eigenen Lizenz und ist hiervon nicht betroffen |
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28 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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29 | // + Redistributions of source code (with or without modifications) must retain the above copyright notice, |
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30 | // + this list of conditions and the following disclaimer. |
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31 | // + * Neither the name of the copyright holders nor the names of contributors may be used to endorse or promote products derived |
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32 | // + from this software without specific prior written permission. |
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33 | // + * The use of this project (hardware, software, binary files, sources and documentation) is only permittet |
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34 | // + for non-commercial use (directly or indirectly) |
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1868 | - | 35 | // + Commercial use (for example: selling of MikroKopters, selling of PCBs, assembly, ...) is only permitted |
1612 | dongfang | 36 | // + with our written permission |
37 | // + * If sources or documentations are redistributet on other webpages, out webpage (http://www.MikroKopter.de) must be |
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38 | // + clearly linked as origin |
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39 | // + * porting to systems other than hardware from www.mikrokopter.de is not allowed |
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40 | // + THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS "AS IS" |
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41 | // + AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT LIMITED TO, THE |
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42 | // + IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS FOR A PARTICULAR PURPOSE |
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43 | // + ARE DISCLAIMED. IN NO EVENT SHALL THE COPYRIGHT OWNER OR CONTRIBUTORS BE |
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44 | // + LIABLE FOR ANY DIRECT, INDIRECT, INCIDENTAL, SPECIAL, EXEMPLARY, OR |
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45 | // + CONSEQUENTIAL DAMAGES (INCLUDING, BUT NOT LIMITED TO, PROCUREMENT OF |
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46 | // + SUBSTITUTE GOODS OR SERVICES; LOSS OF USE, DATA, OR PROFITS; OR BUSINESS |
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47 | // + INTERRUPTION) HOWEVER CAUSED AND ON ANY THEORY OF LIABILITY, WHETHER IN// + CONTRACT, STRICT LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) |
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48 | // + ARISING IN ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE |
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49 | // + POSSIBILITY OF SUCH DAMAGE. |
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50 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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51 | #include <avr/io.h> |
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52 | #include <avr/interrupt.h> |
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53 | #include <avr/pgmspace.h> |
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1864 | - | 54 | |
1612 | dongfang | 55 | #include "analog.h" |
1864 | - | 56 | #include "attitude.h" |
1612 | dongfang | 57 | #include "sensors.h" |
58 | |||
59 | // for Delay functions |
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60 | #include "timer0.h" |
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61 | |||
62 | // For DebugOut |
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63 | #include "uart0.h" |
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64 | |||
65 | // For reading and writing acc. meter offsets. |
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66 | #include "eeprom.h" |
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67 | |||
1796 | - | 68 | // For DebugOut.Digital |
69 | #include "output.h" |
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70 | |||
1854 | - | 71 | /* |
72 | * For each A/D conversion cycle, each analog channel is sampled a number of times |
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73 | * (see array channelsForStates), and the results for each channel are summed. |
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1645 | - | 74 | * Here are those for the gyros and the acc. meters. They are not zero-offset. |
1612 | dongfang | 75 | * They are exported in the analog.h file - but please do not use them! The only |
76 | * reason for the export is that the ENC-03_FC1.3 modules needs them for calibrating |
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77 | * the offsets with the DAC. |
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78 | */ |
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1646 | - | 79 | volatile int16_t rawGyroSum[3]; |
80 | volatile int16_t acc[3]; |
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1869 | - | 81 | volatile int16_t filteredAcc[2] = { 0,0 }; |
82 | volatile int32_t stronglyFilteredAcc[3] = { 0,0,0 }; |
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1612 | dongfang | 83 | |
84 | /* |
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1645 | - | 85 | * These 4 exported variables are zero-offset. The "PID" ones are used |
86 | * in the attitude control as rotation rates. The "ATT" ones are for |
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1854 | - | 87 | * integration to angles. |
1612 | dongfang | 88 | */ |
1645 | - | 89 | volatile int16_t gyro_PID[2]; |
90 | volatile int16_t gyro_ATT[2]; |
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91 | volatile int16_t gyroD[2]; |
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1646 | - | 92 | volatile int16_t yawGyro; |
1612 | dongfang | 93 | |
94 | /* |
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95 | * Offset values. These are the raw gyro and acc. meter sums when the copter is |
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96 | * standing still. They are used for adjusting the gyro and acc. meter values |
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1645 | - | 97 | * to be centered on zero. |
1612 | dongfang | 98 | */ |
1821 | - | 99 | volatile int16_t gyroOffset[3] = { 512 * GYRO_SUMMATION_FACTOR_PITCHROLL, 512 |
100 | * GYRO_SUMMATION_FACTOR_PITCHROLL, 512 * GYRO_SUMMATION_FACTOR_YAW }; |
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1612 | dongfang | 101 | |
1821 | - | 102 | volatile int16_t accOffset[3] = { 512 * ACC_SUMMATION_FACTOR_PITCHROLL, 512 |
103 | * ACC_SUMMATION_FACTOR_PITCHROLL, 512 * ACC_SUMMATION_FACTOR_Z }; |
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1646 | - | 104 | |
1612 | dongfang | 105 | /* |
106 | * This allows some experimentation with the gyro filters. |
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107 | * Should be replaced by #define's later on... |
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108 | */ |
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1646 | - | 109 | volatile uint8_t GYROS_PID_FILTER; |
110 | volatile uint8_t GYROS_ATT_FILTER; |
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111 | volatile uint8_t GYROS_D_FILTER; |
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1612 | dongfang | 112 | volatile uint8_t ACC_FILTER; |
113 | |||
1645 | - | 114 | /* |
1775 | - | 115 | * Air pressure |
1645 | - | 116 | */ |
1775 | - | 117 | volatile uint8_t rangewidth = 106; |
1612 | dongfang | 118 | |
1775 | - | 119 | // Direct from sensor, irrespective of range. |
120 | // volatile uint16_t rawAirPressure; |
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121 | |||
122 | // Value of 2 samples, with range. |
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123 | volatile uint16_t simpleAirPressure; |
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124 | |||
125 | // Value of AIRPRESSURE_SUMMATION_FACTOR samples, with range, filtered. |
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126 | volatile int32_t filteredAirPressure; |
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127 | |||
128 | // Partial sum of AIRPRESSURE_SUMMATION_FACTOR samples. |
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129 | volatile int32_t airPressureSum; |
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130 | |||
131 | // The number of samples summed into airPressureSum so far. |
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132 | volatile uint8_t pressureMeasurementCount; |
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133 | |||
1612 | dongfang | 134 | /* |
1854 | - | 135 | * Battery voltage, in units of: 1k/11k / 3V * 1024 = 31.03 per volt. |
1612 | dongfang | 136 | * That is divided by 3 below, for a final 10.34 per volt. |
137 | * So the initial value of 100 is for 9.7 volts. |
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138 | */ |
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139 | volatile int16_t UBat = 100; |
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140 | |||
141 | /* |
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142 | * Control and status. |
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143 | */ |
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144 | volatile uint16_t ADCycleCount = 0; |
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145 | volatile uint8_t analogDataReady = 1; |
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146 | |||
147 | /* |
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148 | * Experiment: Measuring vibration-induced sensor noise. |
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149 | */ |
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1645 | - | 150 | volatile uint16_t gyroNoisePeak[2]; |
151 | volatile uint16_t accNoisePeak[2]; |
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1612 | dongfang | 152 | |
153 | // ADC channels |
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1645 | - | 154 | #define AD_GYRO_YAW 0 |
155 | #define AD_GYRO_ROLL 1 |
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1634 | - | 156 | #define AD_GYRO_PITCH 2 |
157 | #define AD_AIRPRESSURE 3 |
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1645 | - | 158 | #define AD_UBAT 4 |
159 | #define AD_ACC_Z 5 |
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160 | #define AD_ACC_ROLL 6 |
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161 | #define AD_ACC_PITCH 7 |
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1612 | dongfang | 162 | |
163 | /* |
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164 | * Table of AD converter inputs for each state. |
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1854 | - | 165 | * The number of samples summed for each channel is equal to |
1612 | dongfang | 166 | * the number of times the channel appears in the array. |
167 | * The max. number of samples that can be taken in 2 ms is: |
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1854 | - | 168 | * 20e6 / 128 / 13 / (1/2e-3) = 24. Since the main control |
169 | * loop needs a little time between reading AD values and |
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1612 | dongfang | 170 | * re-enabling ADC, the real limit is (how much?) lower. |
171 | * The acc. sensor is sampled even if not used - or installed |
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172 | * at all. The cost is not significant. |
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173 | */ |
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174 | |||
1870 | - | 175 | const uint8_t channelsForStates[] PROGMEM = { |
176 | AD_GYRO_PITCH, AD_GYRO_ROLL, AD_GYRO_YAW, |
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177 | AD_ACC_PITCH, AD_ACC_ROLL, AD_AIRPRESSURE, |
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1612 | dongfang | 178 | |
1870 | - | 179 | AD_GYRO_PITCH, AD_GYRO_ROLL, AD_ACC_Z, // at 8, measure Z acc. |
180 | AD_GYRO_PITCH, AD_GYRO_ROLL, AD_GYRO_YAW, // at 11, finish yaw gyro |
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181 | |||
182 | AD_ACC_PITCH, // at 12, finish pitch axis acc. |
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183 | AD_ACC_ROLL, // at 13, finish roll axis acc. |
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184 | AD_AIRPRESSURE, // at 14, finish air pressure. |
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185 | |||
186 | AD_GYRO_PITCH, // at 15, finish pitch gyro |
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187 | AD_GYRO_ROLL, // at 16, finish roll gyro |
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188 | AD_UBAT // at 17, measure battery. |
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189 | }; |
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1612 | dongfang | 190 | |
191 | // Feature removed. Could be reintroduced later - but should work for all gyro types then. |
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192 | // uint8_t GyroDefectPitch = 0, GyroDefectRoll = 0, GyroDefectYaw = 0; |
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193 | |||
194 | void analog_init(void) { |
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1821 | - | 195 | uint8_t sreg = SREG; |
196 | // disable all interrupts before reconfiguration |
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197 | cli(); |
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1612 | dongfang | 198 | |
1821 | - | 199 | //ADC0 ... ADC7 is connected to PortA pin 0 ... 7 |
200 | DDRA = 0x00; |
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201 | PORTA = 0x00; |
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202 | // Digital Input Disable Register 0 |
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203 | // Disable digital input buffer for analog adc_channel pins |
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204 | DIDR0 = 0xFF; |
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205 | // external reference, adjust data to the right |
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206 | ADMUX &= ~((1 << REFS1) | (1 << REFS0) | (1 << ADLAR)); |
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207 | // set muxer to ADC adc_channel 0 (0 to 7 is a valid choice) |
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208 | ADMUX = (ADMUX & 0xE0) | AD_GYRO_PITCH; |
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209 | //Set ADC Control and Status Register A |
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210 | //Auto Trigger Enable, Prescaler Select Bits to Division Factor 128, i.e. ADC clock = SYSCKL/128 = 156.25 kHz |
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211 | ADCSRA = (0 << ADEN) | (0 << ADSC) | (0 << ADATE) | (1 << ADPS2) | (1 |
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212 | << ADPS1) | (1 << ADPS0) | (0 << ADIE); |
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213 | //Set ADC Control and Status Register B |
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214 | //Trigger Source to Free Running Mode |
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215 | ADCSRB &= ~((1 << ADTS2) | (1 << ADTS1) | (1 << ADTS0)); |
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216 | // Start AD conversion |
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217 | analog_start(); |
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218 | // restore global interrupt flags |
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219 | SREG = sreg; |
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1612 | dongfang | 220 | } |
221 | |||
1821 | - | 222 | void measureNoise(const int16_t sensor, |
223 | volatile uint16_t* const noiseMeasurement, const uint8_t damping) { |
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224 | if (sensor > (int16_t) (*noiseMeasurement)) { |
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225 | *noiseMeasurement = sensor; |
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226 | } else if (-sensor > (int16_t) (*noiseMeasurement)) { |
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227 | *noiseMeasurement = -sensor; |
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228 | } else if (*noiseMeasurement > damping) { |
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229 | *noiseMeasurement -= damping; |
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230 | } else { |
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231 | *noiseMeasurement = 0; |
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232 | } |
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1612 | dongfang | 233 | } |
234 | |||
1796 | - | 235 | /* |
236 | * Min.: 0 |
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237 | * Max: About 106 * 240 + 2047 = 27487; it is OK with just a 16 bit type. |
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238 | */ |
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1775 | - | 239 | uint16_t getSimplePressure(int advalue) { |
1821 | - | 240 | return (uint16_t) OCR0A * (uint16_t) rangewidth + advalue; |
1634 | - | 241 | } |
242 | |||
1645 | - | 243 | /***************************************************** |
1854 | - | 244 | * Interrupt Service Routine for ADC |
245 | * Runs at 312.5 kHz or 3.2 µs. When all states are |
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246 | * processed the interrupt is disabled and further |
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1645 | - | 247 | * AD conversions are stopped. |
248 | *****************************************************/ |
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1870 | - | 249 | ISR(ADC_vect) { |
1821 | - | 250 | static uint8_t ad_channel = AD_GYRO_PITCH, state = 0; |
251 | static uint16_t sensorInputs[8] = { 0, 0, 0, 0, 0, 0, 0, 0 }; |
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252 | static uint16_t pressureAutorangingWait = 25; |
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253 | uint16_t rawAirPressure; |
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254 | uint8_t i, axis; |
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255 | int16_t newrange; |
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1612 | dongfang | 256 | |
1870 | - | 257 | J5HIGH; |
258 | |||
1821 | - | 259 | // for various filters... |
260 | int16_t tempOffsetGyro, tempGyro; |
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1775 | - | 261 | |
1821 | - | 262 | sensorInputs[ad_channel] += ADC; |
1646 | - | 263 | |
1821 | - | 264 | /* |
265 | * Actually we don't need this "switch". We could do all the sampling into the |
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266 | * sensorInputs array first, and all the processing after the last sample. |
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267 | */ |
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268 | switch (state++) { |
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1645 | - | 269 | |
1821 | - | 270 | case 8: // Z acc |
271 | if (ACC_REVERSED[Z]) |
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272 | acc[Z] = accOffset[Z] - sensorInputs[AD_ACC_Z]; |
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273 | else |
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274 | acc[Z] = sensorInputs[AD_ACC_Z] - accOffset[Z]; |
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1869 | - | 275 | |
276 | stronglyFilteredAcc[Z] = |
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277 | (stronglyFilteredAcc[Z] * 99 + acc[Z] * 10) / 100; |
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278 | |||
1821 | - | 279 | break; |
1796 | - | 280 | |
1821 | - | 281 | case 11: // yaw gyro |
282 | rawGyroSum[YAW] = sensorInputs[AD_GYRO_YAW]; |
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283 | if (GYRO_REVERSED[YAW]) |
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284 | yawGyro = gyroOffset[YAW] - sensorInputs[AD_GYRO_YAW]; |
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285 | else |
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286 | yawGyro = sensorInputs[AD_GYRO_YAW] - gyroOffset[YAW]; |
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287 | break; |
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1775 | - | 288 | |
1821 | - | 289 | case 12: // pitch axis acc. |
290 | if (ACC_REVERSED[PITCH]) |
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291 | acc[PITCH] = accOffset[PITCH] - sensorInputs[AD_ACC_PITCH]; |
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292 | else |
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293 | acc[PITCH] = sensorInputs[AD_ACC_PITCH] - accOffset[PITCH]; |
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1796 | - | 294 | |
1869 | - | 295 | filteredAcc[PITCH] = |
296 | (filteredAcc[PITCH] * (ACC_FILTER - 1) + acc[PITCH]) / ACC_FILTER; |
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297 | |||
298 | stronglyFilteredAcc[PITCH] = |
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299 | (stronglyFilteredAcc[PITCH] * 99 + acc[PITCH] * 10) / 100; |
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300 | |||
301 | |||
1821 | - | 302 | measureNoise(acc[PITCH], &accNoisePeak[PITCH], 1); |
303 | break; |
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1796 | - | 304 | |
1821 | - | 305 | case 13: // roll axis acc. |
306 | if (ACC_REVERSED[ROLL]) |
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307 | acc[ROLL] = accOffset[ROLL] - sensorInputs[AD_ACC_ROLL]; |
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308 | else |
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309 | acc[ROLL] = sensorInputs[AD_ACC_ROLL] - accOffset[ROLL]; |
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1869 | - | 310 | filteredAcc[ROLL] = |
311 | (filteredAcc[ROLL] * (ACC_FILTER - 1) + acc[ROLL]) / ACC_FILTER; |
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312 | |||
313 | stronglyFilteredAcc[ROLL] = |
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314 | (stronglyFilteredAcc[ROLL] * 99 + acc[ROLL] * 10) / 100; |
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315 | |||
1821 | - | 316 | measureNoise(acc[ROLL], &accNoisePeak[ROLL], 1); |
317 | break; |
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1775 | - | 318 | |
1821 | - | 319 | case 14: // air pressure |
320 | if (pressureAutorangingWait) { |
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321 | //A range switch was done recently. Wait for steadying. |
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322 | pressureAutorangingWait--; |
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323 | DebugOut.Analog[27] = (uint16_t) OCR0A; |
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324 | DebugOut.Analog[31] = simpleAirPressure; |
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325 | break; |
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326 | } |
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1634 | - | 327 | |
1821 | - | 328 | rawAirPressure = sensorInputs[AD_AIRPRESSURE]; |
329 | if (rawAirPressure < MIN_RAWPRESSURE) { |
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330 | // value is too low, so decrease voltage on the op amp minus input, making the value higher. |
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331 | newrange = OCR0A - (MAX_RAWPRESSURE - MIN_RAWPRESSURE) / (rangewidth * 4); // 4; // (MAX_RAWPRESSURE - rawAirPressure) / (rangewidth * 2) + 1; |
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332 | if (newrange > MIN_RANGES_EXTRAPOLATION) { |
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333 | pressureAutorangingWait = (OCR0A - newrange) * AUTORANGE_WAIT_FACTOR; // = OCRA0 - OCRA0 + |
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334 | OCR0A = newrange; |
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335 | } else { |
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336 | if (OCR0A) { |
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337 | OCR0A--; |
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338 | pressureAutorangingWait = AUTORANGE_WAIT_FACTOR; |
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339 | } |
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340 | } |
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341 | } else if (rawAirPressure > MAX_RAWPRESSURE) { |
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342 | // value is too high, so increase voltage on the op amp minus input, making the value lower. |
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343 | // If near the end, make a limited increase |
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344 | newrange = OCR0A + (MAX_RAWPRESSURE - MIN_RAWPRESSURE) / (rangewidth * 4); // 4; // (rawAirPressure - MIN_RAWPRESSURE) / (rangewidth * 2) - 1; |
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345 | if (newrange < MAX_RANGES_EXTRAPOLATION) { |
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346 | pressureAutorangingWait = (newrange - OCR0A) * AUTORANGE_WAIT_FACTOR; |
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347 | OCR0A = newrange; |
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348 | } else { |
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349 | if (OCR0A < 254) { |
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350 | OCR0A++; |
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351 | pressureAutorangingWait = AUTORANGE_WAIT_FACTOR; |
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352 | } |
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353 | } |
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354 | } |
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1645 | - | 355 | |
1821 | - | 356 | // Even if the sample is off-range, use it. |
357 | simpleAirPressure = getSimplePressure(rawAirPressure); |
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358 | DebugOut.Analog[27] = (uint16_t) OCR0A; |
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359 | DebugOut.Analog[31] = simpleAirPressure; |
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1645 | - | 360 | |
1821 | - | 361 | if (simpleAirPressure < MIN_RANGES_EXTRAPOLATION * rangewidth) { |
362 | // Danger: pressure near lower end of range. If the measurement saturates, the |
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363 | // copter may climb uncontrolledly... Simulate a drastic reduction in pressure. |
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1854 | - | 364 | DebugOut.Digital[1] |= DEBUG_SENSORLIMIT; |
1821 | - | 365 | airPressureSum += (int16_t) MIN_RANGES_EXTRAPOLATION * rangewidth |
366 | + (simpleAirPressure - (int16_t) MIN_RANGES_EXTRAPOLATION |
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367 | * rangewidth) * PRESSURE_EXTRAPOLATION_COEFF; |
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368 | } else if (simpleAirPressure > MAX_RANGES_EXTRAPOLATION * rangewidth) { |
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369 | // Danger: pressure near upper end of range. If the measurement saturates, the |
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370 | // copter may descend uncontrolledly... Simulate a drastic increase in pressure. |
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1854 | - | 371 | DebugOut.Digital[1] |= DEBUG_SENSORLIMIT; |
1821 | - | 372 | airPressureSum += (int16_t) MAX_RANGES_EXTRAPOLATION * rangewidth |
373 | + (simpleAirPressure - (int16_t) MAX_RANGES_EXTRAPOLATION |
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374 | * rangewidth) * PRESSURE_EXTRAPOLATION_COEFF; |
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375 | } else { |
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376 | // normal case. |
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377 | // If AIRPRESSURE_SUMMATION_FACTOR is an odd number we only want to add half the double sample. |
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378 | // The 2 cases above (end of range) are ignored for this. |
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1854 | - | 379 | DebugOut.Digital[1] &= ~DEBUG_SENSORLIMIT; |
1821 | - | 380 | if (pressureMeasurementCount == AIRPRESSURE_SUMMATION_FACTOR - 1) |
381 | airPressureSum += simpleAirPressure / 2; |
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382 | else |
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383 | airPressureSum += simpleAirPressure; |
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384 | } |
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1645 | - | 385 | |
1821 | - | 386 | // 2 samples were added. |
387 | pressureMeasurementCount += 2; |
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388 | if (pressureMeasurementCount >= AIRPRESSURE_SUMMATION_FACTOR) { |
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389 | filteredAirPressure = (filteredAirPressure * (AIRPRESSURE_FILTER - 1) |
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390 | + airPressureSum + AIRPRESSURE_FILTER / 2) / AIRPRESSURE_FILTER; |
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391 | pressureMeasurementCount = airPressureSum = 0; |
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392 | } |
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1645 | - | 393 | |
1821 | - | 394 | break; |
1645 | - | 395 | |
1821 | - | 396 | case 15: |
397 | case 16: // pitch or roll gyro. |
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398 | axis = state - 16; |
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399 | tempGyro = rawGyroSum[axis] = sensorInputs[AD_GYRO_PITCH - axis]; |
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400 | // DebugOut.Analog[6 + 3 * axis ] = tempGyro; |
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401 | /* |
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402 | * Process the gyro data for the PID controller. |
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403 | */ |
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404 | // 1) Extrapolate: Near the ends of the range, we boost the input significantly. This simulates a |
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405 | // gyro with a wider range, and helps counter saturation at full control. |
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1645 | - | 406 | |
1821 | - | 407 | if (staticParams.GlobalConfig & CFG_ROTARY_RATE_LIMITER) { |
408 | if (tempGyro < SENSOR_MIN_PITCHROLL) { |
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1854 | - | 409 | DebugOut.Digital[0] |= DEBUG_SENSORLIMIT; |
1821 | - | 410 | tempGyro = tempGyro * EXTRAPOLATION_SLOPE - EXTRAPOLATION_LIMIT; |
411 | } else if (tempGyro > SENSOR_MAX_PITCHROLL) { |
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1854 | - | 412 | DebugOut.Digital[0] |= DEBUG_SENSORLIMIT; |
1821 | - | 413 | tempGyro = (tempGyro - SENSOR_MAX_PITCHROLL) * EXTRAPOLATION_SLOPE |
414 | + SENSOR_MAX_PITCHROLL; |
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1854 | - | 415 | } else { |
416 | DebugOut.Digital[0] &= ~DEBUG_SENSORLIMIT; |
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1821 | - | 417 | } |
418 | } |
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1645 | - | 419 | |
1821 | - | 420 | // 2) Apply sign and offset, scale before filtering. |
421 | if (GYRO_REVERSED[axis]) { |
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422 | tempOffsetGyro = (gyroOffset[axis] - tempGyro) * GYRO_FACTOR_PITCHROLL; |
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423 | } else { |
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424 | tempOffsetGyro = (tempGyro - gyroOffset[axis]) * GYRO_FACTOR_PITCHROLL; |
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425 | } |
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1612 | dongfang | 426 | |
1821 | - | 427 | // 3) Scale and filter. |
428 | tempOffsetGyro = (gyro_PID[axis] * (GYROS_PID_FILTER - 1) + tempOffsetGyro) |
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429 | / GYROS_PID_FILTER; |
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430 | |||
431 | // 4) Measure noise. |
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432 | measureNoise(tempOffsetGyro, &gyroNoisePeak[axis], |
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433 | GYRO_NOISE_MEASUREMENT_DAMPING); |
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434 | |||
435 | // 5) Differential measurement. |
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436 | gyroD[axis] = (gyroD[axis] * (GYROS_D_FILTER - 1) + (tempOffsetGyro |
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437 | - gyro_PID[axis])) / GYROS_D_FILTER; |
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438 | |||
439 | // 6) Done. |
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440 | gyro_PID[axis] = tempOffsetGyro; |
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441 | |||
442 | /* |
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443 | * Now process the data for attitude angles. |
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444 | */ |
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445 | tempGyro = rawGyroSum[axis]; |
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446 | |||
447 | // 1) Apply sign and offset, scale before filtering. |
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448 | if (GYRO_REVERSED[axis]) { |
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449 | tempOffsetGyro = (gyroOffset[axis] - tempGyro) * GYRO_FACTOR_PITCHROLL; |
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450 | } else { |
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451 | tempOffsetGyro = (tempGyro - gyroOffset[axis]) * GYRO_FACTOR_PITCHROLL; |
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452 | } |
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453 | |||
454 | // 2) Filter. |
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455 | gyro_ATT[axis] = (gyro_ATT[axis] * (GYROS_ATT_FILTER - 1) + tempOffsetGyro) |
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456 | / GYROS_ATT_FILTER; |
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457 | break; |
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458 | |||
459 | case 17: |
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460 | // Battery. The measured value is: (V * 1k/11k)/3v * 1024 = 31.03 counts per volt (max. measurable is 33v). |
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461 | // This is divided by 3 --> 10.34 counts per volt. |
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462 | UBat = (3 * UBat + sensorInputs[AD_UBAT] / 3) / 4; |
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1866 | - | 463 | DebugOut.Analog[11] = UBat; |
1821 | - | 464 | analogDataReady = 1; // mark |
465 | ADCycleCount++; |
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466 | // Stop the sampling. Cycle is over. |
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467 | state = 0; |
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468 | for (i = 0; i < 8; i++) { |
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469 | sensorInputs[i] = 0; |
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470 | } |
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471 | break; |
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472 | default: { |
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473 | } // do nothing. |
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474 | } |
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475 | |||
476 | // set up for next state. |
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477 | ad_channel = pgm_read_byte(&channelsForStates[state]); |
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478 | // ad_channel = channelsForStates[state]; |
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479 | |||
480 | // set adc muxer to next ad_channel |
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481 | ADMUX = (ADMUX & 0xE0) | ad_channel; |
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482 | // after full cycle stop further interrupts |
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483 | if (state) |
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484 | analog_start(); |
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1870 | - | 485 | else |
486 | J4LOW; |
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487 | |||
488 | J5LOW; |
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1612 | dongfang | 489 | } |
490 | |||
491 | void analog_calibrate(void) { |
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492 | #define GYRO_OFFSET_CYCLES 32 |
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1821 | - | 493 | uint8_t i, axis; |
494 | int32_t deltaOffsets[3] = { 0, 0, 0 }; |
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1612 | dongfang | 495 | |
1821 | - | 496 | // Set the filters... to be removed again, once some good settings are found. |
497 | GYROS_PID_FILTER = (dynamicParams.UserParams[4] & 0b00000011) + 1; |
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498 | GYROS_ATT_FILTER = ((dynamicParams.UserParams[4] & 0b00001100) >> 2) + 1; |
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499 | GYROS_D_FILTER = ((dynamicParams.UserParams[4] & 0b00110000) >> 4) + 1; |
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500 | ACC_FILTER = ((dynamicParams.UserParams[4] & 0b11000000) >> 6) + 1; |
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1612 | dongfang | 501 | |
1821 | - | 502 | gyro_calibrate(); |
1612 | dongfang | 503 | |
1821 | - | 504 | // determine gyro bias by averaging (requires that the copter does not rotate around any axis!) |
505 | for (i = 0; i < GYRO_OFFSET_CYCLES; i++) { |
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506 | Delay_ms_Mess(20); |
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507 | for (axis = PITCH; axis <= YAW; axis++) { |
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508 | deltaOffsets[axis] += rawGyroSum[axis]; |
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509 | } |
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510 | } |
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1646 | - | 511 | |
1821 | - | 512 | for (axis = PITCH; axis <= YAW; axis++) { |
1866 | - | 513 | gyroOffset[axis] = (deltaOffsets[axis] + GYRO_OFFSET_CYCLES / 2) / GYRO_OFFSET_CYCLES; |
514 | // DebugOut.Analog[20 + axis] = gyroOffset[axis]; |
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1821 | - | 515 | } |
1646 | - | 516 | |
1869 | - | 517 | // Noise is relativ to offset. So, reset noise measurements when changing offsets. |
1821 | - | 518 | gyroNoisePeak[PITCH] = gyroNoisePeak[ROLL] = 0; |
1612 | dongfang | 519 | |
1821 | - | 520 | accOffset[PITCH] = GetParamWord(PID_ACC_PITCH); |
521 | accOffset[ROLL] = GetParamWord(PID_ACC_ROLL); |
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522 | accOffset[Z] = GetParamWord(PID_ACC_Z); |
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1646 | - | 523 | |
1821 | - | 524 | // Rough estimate. Hmm no nothing happens at calibration anyway. |
525 | // airPressureSum = simpleAirPressure * (AIRPRESSURE_SUMMATION_FACTOR/2); |
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526 | // pressureMeasurementCount = 0; |
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1775 | - | 527 | |
1821 | - | 528 | Delay_ms_Mess(100); |
1612 | dongfang | 529 | } |
530 | |||
531 | /* |
||
532 | * Find acc. offsets for a neutral reading, and write them to EEPROM. |
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533 | * Does not (!} update the local variables. This must be done with a |
||
534 | * call to analog_calibrate() - this always (?) is done by the caller |
||
535 | * anyway. There would be nothing wrong with updating the variables |
||
536 | * directly from here, though. |
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537 | */ |
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538 | void analog_calibrateAcc(void) { |
||
539 | #define ACC_OFFSET_CYCLES 10 |
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1821 | - | 540 | uint8_t i, axis; |
541 | int32_t deltaOffset[3] = { 0, 0, 0 }; |
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542 | int16_t filteredDelta; |
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543 | // int16_t pressureDiff, savedRawAirPressure; |
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1612 | dongfang | 544 | |
1821 | - | 545 | for (i = 0; i < ACC_OFFSET_CYCLES; i++) { |
546 | Delay_ms_Mess(10); |
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547 | for (axis = PITCH; axis <= YAW; axis++) { |
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548 | deltaOffset[axis] += acc[axis]; |
||
549 | } |
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550 | } |
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1612 | dongfang | 551 | |
1821 | - | 552 | for (axis = PITCH; axis <= YAW; axis++) { |
553 | filteredDelta = (deltaOffset[axis] + ACC_OFFSET_CYCLES / 2) |
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554 | / ACC_OFFSET_CYCLES; |
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555 | accOffset[axis] += ACC_REVERSED[axis] ? -filteredDelta : filteredDelta; |
||
556 | } |
||
1646 | - | 557 | |
1821 | - | 558 | // Save ACC neutral settings to eeprom |
559 | SetParamWord(PID_ACC_PITCH, accOffset[PITCH]); |
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560 | SetParamWord(PID_ACC_ROLL, accOffset[ROLL]); |
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561 | SetParamWord(PID_ACC_Z, accOffset[Z]); |
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1612 | dongfang | 562 | |
1821 | - | 563 | // Noise is relative to offset. So, reset noise measurements when |
564 | // changing offsets. |
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565 | accNoisePeak[PITCH] = accNoisePeak[ROLL] = 0; |
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1645 | - | 566 | |
1821 | - | 567 | // Setting offset values has an influence in the analog.c ISR |
568 | // Therefore run measurement for 100ms to achive stable readings |
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569 | Delay_ms_Mess(100); |
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570 | |||
571 | // Set the feedback so that air pressure ends up in the middle of the range. |
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572 | // (raw pressure high --> OCR0A also high...) |
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573 | /* |
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574 | OCR0A += ((rawAirPressure - 1024) / rangewidth) - 1; |
||
575 | Delay_ms_Mess(1000); |
||
576 | |||
577 | pressureDiff = 0; |
||
578 | // DebugOut.Analog[16] = rawAirPressure; |
||
579 | |||
580 | #define PRESSURE_CAL_CYCLE_COUNT 5 |
||
581 | for (i=0; i<PRESSURE_CAL_CYCLE_COUNT; i++) { |
||
582 | savedRawAirPressure = rawAirPressure; |
||
583 | OCR0A+=2; |
||
584 | Delay_ms_Mess(500); |
||
585 | // raw pressure will decrease. |
||
586 | pressureDiff += (savedRawAirPressure - rawAirPressure); |
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587 | savedRawAirPressure = rawAirPressure; |
||
588 | OCR0A-=2; |
||
589 | Delay_ms_Mess(500); |
||
590 | // raw pressure will increase. |
||
591 | pressureDiff += (rawAirPressure - savedRawAirPressure); |
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592 | } |
||
593 | |||
594 | rangewidth = (pressureDiff + PRESSURE_CAL_CYCLE_COUNT * 2 * 2 - 1) / (PRESSURE_CAL_CYCLE_COUNT * 2 * 2); |
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595 | DebugOut.Analog[27] = rangewidth; |
||
596 | */ |
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1612 | dongfang | 597 | } |