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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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2017 | - | 7 | // + dass eine Nutzung (auch auszugsweise) nur für den privaten und nicht-kommerziellen Gebrauch zulässig ist. |
1612 | dongfang | 8 | // + Sollten direkte oder indirekte kommerzielle Absichten verfolgt werden, ist mit uns (info@mikrokopter.de) Kontakt |
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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1963 | - | 17 | // + auf anderen Webseiten oder Medien veröffentlicht werden, muss unsere Webseite "http://www.mikrokopter.de" |
18 | // + eindeutig als Ursprung verlinkt und genannt werden |
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1612 | dongfang | 19 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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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1963 | - | 47 | // + INTERRUPTION) HOWEVER CAUSED AND ON ANY THEORY OF LIABILITY, WHETHER IN |
48 | // + CONTRACT, STRICT LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) |
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1612 | dongfang | 49 | // + ARISING IN ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE |
50 | // + POSSIBILITY OF SUCH DAMAGE. |
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51 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
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52 | #include <avr/io.h> |
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53 | #include <avr/interrupt.h> |
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54 | #include <avr/pgmspace.h> |
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1864 | - | 55 | |
1612 | dongfang | 56 | #include "analog.h" |
1864 | - | 57 | #include "attitude.h" |
1612 | dongfang | 58 | #include "sensors.h" |
1964 | - | 59 | #include "printf_P.h" |
1612 | dongfang | 60 | |
61 | // for Delay functions |
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62 | #include "timer0.h" |
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63 | |||
1955 | - | 64 | // For debugOut |
1612 | dongfang | 65 | #include "uart0.h" |
66 | |||
67 | // For reading and writing acc. meter offsets. |
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68 | #include "eeprom.h" |
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69 | |||
1955 | - | 70 | // For debugOut.digital |
1796 | - | 71 | #include "output.h" |
72 | |||
1952 | - | 73 | // set ADC enable & ADC Start Conversion & ADC Interrupt Enable bit |
74 | #define startADC() (ADCSRA |= (1<<ADEN)|(1<<ADSC)|(1<<ADIE)) |
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75 | |||
1969 | - | 76 | const char* recal = ", recalibration needed."; |
77 | |||
1854 | - | 78 | /* |
79 | * For each A/D conversion cycle, each analog channel is sampled a number of times |
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80 | * (see array channelsForStates), and the results for each channel are summed. |
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1645 | - | 81 | * Here are those for the gyros and the acc. meters. They are not zero-offset. |
1612 | dongfang | 82 | * They are exported in the analog.h file - but please do not use them! The only |
83 | * reason for the export is that the ENC-03_FC1.3 modules needs them for calibrating |
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84 | * the offsets with the DAC. |
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85 | */ |
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1952 | - | 86 | volatile uint16_t sensorInputs[8]; |
2015 | - | 87 | int16_t acc[3]; |
88 | int16_t filteredAcc[3] = { 0,0,0 }; |
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1612 | dongfang | 89 | |
90 | /* |
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1645 | - | 91 | * These 4 exported variables are zero-offset. The "PID" ones are used |
92 | * in the attitude control as rotation rates. The "ATT" ones are for |
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1854 | - | 93 | * integration to angles. |
1612 | dongfang | 94 | */ |
2015 | - | 95 | int16_t gyro_PID[2]; |
96 | int16_t gyro_ATT[2]; |
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97 | int16_t gyroD[2]; |
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98 | int16_t yawGyro; |
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1612 | dongfang | 99 | |
100 | /* |
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101 | * Offset values. These are the raw gyro and acc. meter sums when the copter is |
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102 | * standing still. They are used for adjusting the gyro and acc. meter values |
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1645 | - | 103 | * to be centered on zero. |
1612 | dongfang | 104 | */ |
105 | |||
1969 | - | 106 | sensorOffset_t gyroOffset; |
107 | sensorOffset_t accOffset; |
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108 | sensorOffset_t gyroAmplifierOffset; |
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1960 | - | 109 | |
1612 | dongfang | 110 | /* |
2015 | - | 111 | * In the MK coordinate system, nose-down is positive and left-roll is positive. |
112 | * If a sensor is used in an orientation where one but not both of the axes has |
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113 | * an opposite sign, PR_ORIENTATION_REVERSED is set to 1 (true). |
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114 | * Transform: |
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115 | * pitch <- pp*pitch + pr*roll |
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116 | * roll <- rp*pitch + rr*roll |
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117 | * Not reversed, GYRO_QUADRANT: |
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118 | * 0: pp=1, pr=0, rp=0, rr=1 // 0 degrees |
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119 | * 1: pp=1, pr=-1,rp=1, rr=1 // +45 degrees |
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120 | * 2: pp=0, pr=-1,rp=1, rr=0 // +90 degrees |
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121 | * 3: pp=-1,pr=-1,rp=1, rr=1 // +135 degrees |
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122 | * 4: pp=-1,pr=0, rp=0, rr=-1 // +180 degrees |
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123 | * 5: pp=-1,pr=1, rp=-1,rr=-1 // +225 degrees |
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124 | * 6: pp=0, pr=1, rp=-1,rr=0 // +270 degrees |
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125 | * 7: pp=1, pr=1, rp=-1,rr=1 // +315 degrees |
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126 | * Reversed, GYRO_QUADRANT: |
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127 | * 0: pp=-1,pr=0, rp=0, rr=1 // 0 degrees with pitch reversed |
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128 | * 1: pp=-1,pr=-1,rp=-1,rr=1 // +45 degrees with pitch reversed |
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129 | * 2: pp=0, pr=-1,rp=-1,rr=0 // +90 degrees with pitch reversed |
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130 | * 3: pp=1, pr=-1,rp=-1,rr=1 // +135 degrees with pitch reversed |
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131 | * 4: pp=1, pr=0, rp=0, rr=-1 // +180 degrees with pitch reversed |
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132 | * 5: pp=1, pr=1, rp=1, rr=-1 // +225 degrees with pitch reversed |
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133 | * 6: pp=0, pr=1, rp=1, rr=0 // +270 degrees with pitch reversed |
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134 | * 7: pp=-1,pr=1, rp=1, rr=1 // +315 degrees with pitch reversed |
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1612 | dongfang | 135 | */ |
136 | |||
2015 | - | 137 | void rotate(int16_t* result, uint8_t quadrant, uint8_t reverse) { |
138 | static const int8_t rotationTab[] = {1,1,0,-1,-1,-1,0,1}; |
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139 | // Pitch to Pitch part |
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2020 | - | 140 | int8_t xx = reverse ? rotationTab[(quadrant+4)%8] : rotationTab[quadrant]; |
2015 | - | 141 | // Roll to Pitch part |
142 | int8_t xy = rotationTab[(quadrant+2)%8]; |
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143 | // Pitch to Roll part |
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144 | int8_t yx = reverse ? rotationTab[(quadrant+2)%8] : rotationTab[(quadrant+6)%8]; |
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145 | // Roll to Roll part |
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146 | int8_t yy = rotationTab[quadrant]; |
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147 | |||
148 | int16_t xIn = result[0]; |
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2019 | - | 149 | result[0] = xx*xIn + xy*result[1]; |
2015 | - | 150 | result[1] = yx*xIn + yy*result[1]; |
151 | |||
152 | if (quadrant & 1) { |
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153 | // A rotation was used above, where the factors were too large by sqrt(2). |
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154 | // So, we multiply by 2^n/sqt(2) and right shift n bits, as to divide by sqrt(2). |
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155 | // A suitable value for n: Sample is 11 bits. After transformation it is the sum |
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156 | // of 2 11 bit numbers, so 12 bits. We have 4 bits left... |
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157 | result[0] = (result[0]*11) >> 4; |
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158 | result[1] = (result[1]*11) >> 4; |
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159 | } |
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160 | } |
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2019 | - | 161 | |
1645 | - | 162 | /* |
1775 | - | 163 | * Air pressure |
1645 | - | 164 | */ |
1970 | - | 165 | volatile uint8_t rangewidth = 105; |
1612 | dongfang | 166 | |
1775 | - | 167 | // Direct from sensor, irrespective of range. |
168 | // volatile uint16_t rawAirPressure; |
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169 | |||
170 | // Value of 2 samples, with range. |
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2015 | - | 171 | uint16_t simpleAirPressure; |
1775 | - | 172 | |
2019 | - | 173 | // Value of AIRPRESSURE_OVERSAMPLING samples, with range, filtered. |
2015 | - | 174 | int32_t filteredAirPressure; |
1775 | - | 175 | |
2026 | - | 176 | #define MAX_AIRPRESSURE_WINDOW_LENGTH 64 |
177 | int16_t airPressureWindow[MAX_AIRPRESSURE_WINDOW_LENGTH]; |
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178 | int32_t windowedAirPressure; |
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179 | uint8_t windowPtr; |
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180 | |||
1775 | - | 181 | // Partial sum of AIRPRESSURE_SUMMATION_FACTOR samples. |
2015 | - | 182 | int32_t airPressureSum; |
1775 | - | 183 | |
184 | // The number of samples summed into airPressureSum so far. |
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2015 | - | 185 | uint8_t pressureMeasurementCount; |
1775 | - | 186 | |
1612 | dongfang | 187 | /* |
1854 | - | 188 | * Battery voltage, in units of: 1k/11k / 3V * 1024 = 31.03 per volt. |
1612 | dongfang | 189 | * That is divided by 3 below, for a final 10.34 per volt. |
190 | * So the initial value of 100 is for 9.7 volts. |
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191 | */ |
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2015 | - | 192 | int16_t UBat = 100; |
1612 | dongfang | 193 | |
194 | /* |
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195 | * Control and status. |
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196 | */ |
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197 | volatile uint16_t ADCycleCount = 0; |
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198 | volatile uint8_t analogDataReady = 1; |
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199 | |||
200 | /* |
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201 | * Experiment: Measuring vibration-induced sensor noise. |
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202 | */ |
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2015 | - | 203 | uint16_t gyroNoisePeak[3]; |
204 | uint16_t accNoisePeak[3]; |
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1612 | dongfang | 205 | |
1986 | - | 206 | volatile uint8_t adState; |
1987 | - | 207 | volatile uint8_t adChannel; |
1986 | - | 208 | |
1612 | dongfang | 209 | // ADC channels |
1645 | - | 210 | #define AD_GYRO_YAW 0 |
211 | #define AD_GYRO_ROLL 1 |
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1634 | - | 212 | #define AD_GYRO_PITCH 2 |
213 | #define AD_AIRPRESSURE 3 |
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1645 | - | 214 | #define AD_UBAT 4 |
215 | #define AD_ACC_Z 5 |
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216 | #define AD_ACC_ROLL 6 |
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217 | #define AD_ACC_PITCH 7 |
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1612 | dongfang | 218 | |
219 | /* |
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220 | * Table of AD converter inputs for each state. |
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1854 | - | 221 | * The number of samples summed for each channel is equal to |
1612 | dongfang | 222 | * the number of times the channel appears in the array. |
223 | * The max. number of samples that can be taken in 2 ms is: |
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1854 | - | 224 | * 20e6 / 128 / 13 / (1/2e-3) = 24. Since the main control |
225 | * loop needs a little time between reading AD values and |
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1612 | dongfang | 226 | * re-enabling ADC, the real limit is (how much?) lower. |
227 | * The acc. sensor is sampled even if not used - or installed |
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228 | * at all. The cost is not significant. |
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229 | */ |
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230 | |||
1870 | - | 231 | const uint8_t channelsForStates[] PROGMEM = { |
232 | AD_GYRO_PITCH, AD_GYRO_ROLL, AD_GYRO_YAW, |
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233 | AD_ACC_PITCH, AD_ACC_ROLL, AD_AIRPRESSURE, |
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1612 | dongfang | 234 | |
1870 | - | 235 | AD_GYRO_PITCH, AD_GYRO_ROLL, AD_ACC_Z, // at 8, measure Z acc. |
236 | AD_GYRO_PITCH, AD_GYRO_ROLL, AD_GYRO_YAW, // at 11, finish yaw gyro |
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237 | |||
238 | AD_ACC_PITCH, // at 12, finish pitch axis acc. |
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239 | AD_ACC_ROLL, // at 13, finish roll axis acc. |
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240 | AD_AIRPRESSURE, // at 14, finish air pressure. |
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241 | |||
242 | AD_GYRO_PITCH, // at 15, finish pitch gyro |
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243 | AD_GYRO_ROLL, // at 16, finish roll gyro |
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244 | AD_UBAT // at 17, measure battery. |
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245 | }; |
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1612 | dongfang | 246 | |
247 | // Feature removed. Could be reintroduced later - but should work for all gyro types then. |
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248 | // uint8_t GyroDefectPitch = 0, GyroDefectRoll = 0, GyroDefectYaw = 0; |
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249 | |||
250 | void analog_init(void) { |
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1821 | - | 251 | uint8_t sreg = SREG; |
252 | // disable all interrupts before reconfiguration |
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253 | cli(); |
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1612 | dongfang | 254 | |
1821 | - | 255 | //ADC0 ... ADC7 is connected to PortA pin 0 ... 7 |
256 | DDRA = 0x00; |
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257 | PORTA = 0x00; |
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258 | // Digital Input Disable Register 0 |
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259 | // Disable digital input buffer for analog adc_channel pins |
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260 | DIDR0 = 0xFF; |
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261 | // external reference, adjust data to the right |
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1952 | - | 262 | ADMUX &= ~((1<<REFS1)|(1<<REFS0)|(1<<ADLAR)); |
1821 | - | 263 | // set muxer to ADC adc_channel 0 (0 to 7 is a valid choice) |
1987 | - | 264 | ADMUX = (ADMUX & 0xE0); |
1821 | - | 265 | //Set ADC Control and Status Register A |
266 | //Auto Trigger Enable, Prescaler Select Bits to Division Factor 128, i.e. ADC clock = SYSCKL/128 = 156.25 kHz |
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1952 | - | 267 | ADCSRA = (1<<ADPS2)|(1<<ADPS1)|(1<<ADPS0); |
1821 | - | 268 | //Set ADC Control and Status Register B |
269 | //Trigger Source to Free Running Mode |
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1952 | - | 270 | ADCSRB &= ~((1<<ADTS2)|(1<<ADTS1)|(1<<ADTS0)); |
271 | |||
2026 | - | 272 | for (uint8_t i=0; i<MAX_AIRPRESSURE_WINDOW_LENGTH; i++) { |
273 | airPressureWindow[i] = 0; |
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274 | } |
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275 | |||
276 | windowedAirPressure = 0; |
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277 | |||
1952 | - | 278 | startAnalogConversionCycle(); |
279 | |||
1821 | - | 280 | // restore global interrupt flags |
281 | SREG = sreg; |
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1612 | dongfang | 282 | } |
283 | |||
2015 | - | 284 | uint16_t rawGyroValue(uint8_t axis) { |
285 | return sensorInputs[AD_GYRO_PITCH-axis]; |
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286 | } |
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287 | |||
288 | uint16_t rawAccValue(uint8_t axis) { |
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289 | return sensorInputs[AD_ACC_PITCH-axis]; |
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290 | } |
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291 | |||
1821 | - | 292 | void measureNoise(const int16_t sensor, |
293 | volatile uint16_t* const noiseMeasurement, const uint8_t damping) { |
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294 | if (sensor > (int16_t) (*noiseMeasurement)) { |
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295 | *noiseMeasurement = sensor; |
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296 | } else if (-sensor > (int16_t) (*noiseMeasurement)) { |
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297 | *noiseMeasurement = -sensor; |
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298 | } else if (*noiseMeasurement > damping) { |
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299 | *noiseMeasurement -= damping; |
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300 | } else { |
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301 | *noiseMeasurement = 0; |
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302 | } |
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1612 | dongfang | 303 | } |
304 | |||
1796 | - | 305 | /* |
306 | * Min.: 0 |
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307 | * Max: About 106 * 240 + 2047 = 27487; it is OK with just a 16 bit type. |
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308 | */ |
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1775 | - | 309 | uint16_t getSimplePressure(int advalue) { |
2026 | - | 310 | uint16_t result = (uint16_t) OCR0A * (uint16_t) rangewidth + advalue; |
311 | result += (acc[Z] * (staticParams.airpressureAccZCorrection-128)) >> 10; |
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312 | return result; |
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1634 | - | 313 | } |
314 | |||
1952 | - | 315 | void startAnalogConversionCycle(void) { |
1960 | - | 316 | analogDataReady = 0; |
2017 | - | 317 | |
1952 | - | 318 | // Stop the sampling. Cycle is over. |
319 | for (uint8_t i = 0; i < 8; i++) { |
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320 | sensorInputs[i] = 0; |
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321 | } |
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1986 | - | 322 | adState = 0; |
1987 | - | 323 | adChannel = AD_GYRO_PITCH; |
324 | ADMUX = (ADMUX & 0xE0) | adChannel; |
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1952 | - | 325 | startADC(); |
326 | } |
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327 | |||
1645 | - | 328 | /***************************************************** |
1854 | - | 329 | * Interrupt Service Routine for ADC |
1963 | - | 330 | * Runs at 312.5 kHz or 3.2 �s. When all states are |
1952 | - | 331 | * processed further conversions are stopped. |
1645 | - | 332 | *****************************************************/ |
1870 | - | 333 | ISR(ADC_vect) { |
1986 | - | 334 | sensorInputs[adChannel] += ADC; |
1952 | - | 335 | // set up for next state. |
1986 | - | 336 | adState++; |
337 | if (adState < sizeof(channelsForStates)) { |
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338 | adChannel = pgm_read_byte(&channelsForStates[adState]); |
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339 | // set adc muxer to next adChannel |
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340 | ADMUX = (ADMUX & 0xE0) | adChannel; |
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1952 | - | 341 | // after full cycle stop further interrupts |
342 | startADC(); |
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343 | } else { |
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344 | ADCycleCount++; |
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345 | analogDataReady = 1; |
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346 | // do not restart ADC converter. |
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347 | } |
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348 | } |
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1612 | dongfang | 349 | |
1952 | - | 350 | void analog_updateGyros(void) { |
351 | // for various filters... |
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2015 | - | 352 | int16_t tempOffsetGyro[2], tempGyro; |
1952 | - | 353 | |
1991 | - | 354 | debugOut.digital[0] &= ~DEBUG_SENSORLIMIT; |
1952 | - | 355 | for (uint8_t axis=0; axis<2; axis++) { |
2015 | - | 356 | tempGyro = rawGyroValue(axis); |
1952 | - | 357 | /* |
358 | * Process the gyro data for the PID controller. |
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359 | */ |
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360 | // 1) Extrapolate: Near the ends of the range, we boost the input significantly. This simulates a |
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361 | // gyro with a wider range, and helps counter saturation at full control. |
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362 | |||
1960 | - | 363 | if (staticParams.bitConfig & CFG_GYRO_SATURATION_PREVENTION) { |
1952 | - | 364 | if (tempGyro < SENSOR_MIN_PITCHROLL) { |
2015 | - | 365 | debugOut.digital[0] |= DEBUG_SENSORLIMIT; |
366 | tempGyro = tempGyro * EXTRAPOLATION_SLOPE - EXTRAPOLATION_LIMIT; |
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1952 | - | 367 | } else if (tempGyro > SENSOR_MAX_PITCHROLL) { |
2015 | - | 368 | debugOut.digital[0] |= DEBUG_SENSORLIMIT; |
369 | tempGyro = (tempGyro - SENSOR_MAX_PITCHROLL) * EXTRAPOLATION_SLOPE + SENSOR_MAX_PITCHROLL; |
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1952 | - | 370 | } |
371 | } |
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2015 | - | 372 | |
1952 | - | 373 | // 2) Apply sign and offset, scale before filtering. |
2015 | - | 374 | tempOffsetGyro[axis] = (tempGyro - gyroOffset.offsets[axis]) * GYRO_FACTOR_PITCHROLL; |
375 | } |
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376 | |||
377 | // 2.1: Transform axes. |
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2020 | - | 378 | rotate(tempOffsetGyro, staticParams.gyroQuadrant, staticParams.imuReversedFlags & IMU_REVERSE_GYRO_PR); |
2015 | - | 379 | |
380 | for (uint8_t axis=0; axis<2; axis++) { |
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381 | // 3) Filter. |
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382 | tempOffsetGyro[axis] = (gyro_PID[axis] * (staticParams.gyroPIDFilterConstant - 1) + tempOffsetGyro[axis]) / staticParams.gyroPIDFilterConstant; |
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383 | |||
1952 | - | 384 | // 4) Measure noise. |
2015 | - | 385 | measureNoise(tempOffsetGyro[axis], &gyroNoisePeak[axis], GYRO_NOISE_MEASUREMENT_DAMPING); |
386 | |||
1952 | - | 387 | // 5) Differential measurement. |
2015 | - | 388 | gyroD[axis] = (gyroD[axis] * (staticParams.gyroDFilterConstant - 1) + (tempOffsetGyro[axis] - gyro_PID[axis])) / staticParams.gyroDFilterConstant; |
389 | |||
1952 | - | 390 | // 6) Done. |
2015 | - | 391 | gyro_PID[axis] = tempOffsetGyro[axis]; |
392 | |||
393 | // Prepare tempOffsetGyro for next calculation below... |
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394 | tempOffsetGyro[axis] = (rawGyroValue(axis) - gyroOffset.offsets[axis]) * GYRO_FACTOR_PITCHROLL; |
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1952 | - | 395 | } |
396 | |||
2015 | - | 397 | /* |
398 | * Now process the data for attitude angles. |
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399 | */ |
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2020 | - | 400 | rotate(tempOffsetGyro, staticParams.gyroQuadrant, staticParams.imuReversedFlags & IMU_REVERSE_GYRO_PR); |
2015 | - | 401 | |
2017 | - | 402 | gyro_ATT[PITCH] = tempOffsetGyro[PITCH]; |
403 | gyro_ATT[ROLL] = tempOffsetGyro[ROLL]; |
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404 | |||
405 | debugOut.analog[22 + 0] = gyro_PID[0]; |
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406 | debugOut.analog[22 + 1] = gyro_PID[1]; |
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407 | |||
408 | debugOut.analog[24 + 0] = gyro_ATT[0]; |
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409 | debugOut.analog[24 + 1] = gyro_ATT[1]; |
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410 | |||
2015 | - | 411 | // 2) Filter. This should really be quite unnecessary. The integration should gobble up any noise anyway and the values are not used for anything else. |
412 | // gyro_ATT[PITCH] = (gyro_ATT[PITCH] * (staticParams.attitudeGyroFilter - 1) + tempOffsetGyro[PITCH]) / staticParams.attitudeGyroFilter; |
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413 | // gyro_ATT[ROLL] = (gyro_ATT[ROLL] * (staticParams.attitudeGyroFilter - 1) + tempOffsetGyro[ROLL]) / staticParams.attitudeGyroFilter; |
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414 | |||
1952 | - | 415 | // Yaw gyro. |
2020 | - | 416 | if (staticParams.imuReversedFlags & IMU_REVERSE_GYRO_YAW) |
1960 | - | 417 | yawGyro = gyroOffset.offsets[YAW] - sensorInputs[AD_GYRO_YAW]; |
1952 | - | 418 | else |
1960 | - | 419 | yawGyro = sensorInputs[AD_GYRO_YAW] - gyroOffset.offsets[YAW]; |
1952 | - | 420 | } |
1775 | - | 421 | |
1952 | - | 422 | void analog_updateAccelerometers(void) { |
423 | // Pitch and roll axis accelerations. |
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424 | for (uint8_t axis=0; axis<2; axis++) { |
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2015 | - | 425 | acc[axis] = rawAccValue(axis) - accOffset.offsets[axis]; |
1979 | - | 426 | } |
2015 | - | 427 | |
2020 | - | 428 | rotate(acc, staticParams.accQuadrant, staticParams.imuReversedFlags & IMU_REVERSE_ACC_XY); |
2015 | - | 429 | |
430 | for(uint8_t axis=0; axis<3; axis++) { |
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1960 | - | 431 | filteredAcc[axis] = (filteredAcc[axis] * (staticParams.accFilterConstant - 1) + acc[axis]) / staticParams.accFilterConstant; |
1952 | - | 432 | measureNoise(acc[axis], &accNoisePeak[axis], 1); |
433 | } |
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2015 | - | 434 | |
435 | // Z acc. |
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436 | if (staticParams.imuReversedFlags & 8) |
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437 | acc[Z] = accOffset.offsets[Z] - sensorInputs[AD_ACC_Z]; |
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438 | else |
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439 | acc[Z] = sensorInputs[AD_ACC_Z] - accOffset.offsets[Z]; |
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1952 | - | 440 | } |
1645 | - | 441 | |
1952 | - | 442 | void analog_updateAirPressure(void) { |
443 | static uint16_t pressureAutorangingWait = 25; |
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444 | uint16_t rawAirPressure; |
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445 | int16_t newrange; |
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446 | // air pressure |
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447 | if (pressureAutorangingWait) { |
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448 | //A range switch was done recently. Wait for steadying. |
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449 | pressureAutorangingWait--; |
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450 | } else { |
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451 | rawAirPressure = sensorInputs[AD_AIRPRESSURE]; |
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452 | if (rawAirPressure < MIN_RAWPRESSURE) { |
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453 | // value is too low, so decrease voltage on the op amp minus input, making the value higher. |
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454 | newrange = OCR0A - (MAX_RAWPRESSURE - MIN_RAWPRESSURE) / (rangewidth * 4); // 4; // (MAX_RAWPRESSURE - rawAirPressure) / (rangewidth * 2) + 1; |
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455 | if (newrange > MIN_RANGES_EXTRAPOLATION) { |
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456 | pressureAutorangingWait = (OCR0A - newrange) * AUTORANGE_WAIT_FACTOR; // = OCRA0 - OCRA0 + |
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457 | OCR0A = newrange; |
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458 | } else { |
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459 | if (OCR0A) { |
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460 | OCR0A--; |
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461 | pressureAutorangingWait = AUTORANGE_WAIT_FACTOR; |
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1821 | - | 462 | } |
1952 | - | 463 | } |
464 | } else if (rawAirPressure > MAX_RAWPRESSURE) { |
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465 | // value is too high, so increase voltage on the op amp minus input, making the value lower. |
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466 | // If near the end, make a limited increase |
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467 | newrange = OCR0A + (MAX_RAWPRESSURE - MIN_RAWPRESSURE) / (rangewidth * 4); // 4; // (rawAirPressure - MIN_RAWPRESSURE) / (rangewidth * 2) - 1; |
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468 | if (newrange < MAX_RANGES_EXTRAPOLATION) { |
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469 | pressureAutorangingWait = (newrange - OCR0A) * AUTORANGE_WAIT_FACTOR; |
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470 | OCR0A = newrange; |
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471 | } else { |
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472 | if (OCR0A < 254) { |
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473 | OCR0A++; |
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474 | pressureAutorangingWait = AUTORANGE_WAIT_FACTOR; |
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475 | } |
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476 | } |
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477 | } |
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478 | |||
479 | // Even if the sample is off-range, use it. |
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480 | simpleAirPressure = getSimplePressure(rawAirPressure); |
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481 | |||
482 | if (simpleAirPressure < MIN_RANGES_EXTRAPOLATION * rangewidth) { |
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483 | // Danger: pressure near lower end of range. If the measurement saturates, the |
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484 | // copter may climb uncontrolledly... Simulate a drastic reduction in pressure. |
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1955 | - | 485 | debugOut.digital[1] |= DEBUG_SENSORLIMIT; |
1952 | - | 486 | airPressureSum += (int16_t) MIN_RANGES_EXTRAPOLATION * rangewidth |
487 | + (simpleAirPressure - (int16_t) MIN_RANGES_EXTRAPOLATION |
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488 | * rangewidth) * PRESSURE_EXTRAPOLATION_COEFF; |
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489 | } else if (simpleAirPressure > MAX_RANGES_EXTRAPOLATION * rangewidth) { |
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490 | // Danger: pressure near upper end of range. If the measurement saturates, the |
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491 | // copter may descend uncontrolledly... Simulate a drastic increase in pressure. |
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1955 | - | 492 | debugOut.digital[1] |= DEBUG_SENSORLIMIT; |
1952 | - | 493 | airPressureSum += (int16_t) MAX_RANGES_EXTRAPOLATION * rangewidth |
494 | + (simpleAirPressure - (int16_t) MAX_RANGES_EXTRAPOLATION |
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495 | * rangewidth) * PRESSURE_EXTRAPOLATION_COEFF; |
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496 | } else { |
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497 | // normal case. |
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2026 | - | 498 | // If AIRPRESSURE_OVERSAMPLING is an odd number we only want to add half the double sample. |
1952 | - | 499 | // The 2 cases above (end of range) are ignored for this. |
1955 | - | 500 | debugOut.digital[1] &= ~DEBUG_SENSORLIMIT; |
2019 | - | 501 | if (pressureMeasurementCount == AIRPRESSURE_OVERSAMPLING - 1) |
1952 | - | 502 | airPressureSum += simpleAirPressure / 2; |
503 | else |
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504 | airPressureSum += simpleAirPressure; |
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505 | } |
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506 | |||
507 | // 2 samples were added. |
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508 | pressureMeasurementCount += 2; |
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2019 | - | 509 | if (pressureMeasurementCount >= AIRPRESSURE_OVERSAMPLING) { |
1952 | - | 510 | filteredAirPressure = (filteredAirPressure * (AIRPRESSURE_FILTER - 1) |
511 | + airPressureSum + AIRPRESSURE_FILTER / 2) / AIRPRESSURE_FILTER; |
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512 | pressureMeasurementCount = airPressureSum = 0; |
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513 | } |
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2026 | - | 514 | //int16_t airPressureWindow[MAX_AIRPRESSURE_WINDOW_LENGTH]; |
515 | //int32_t windowedAirPressure = 0; |
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516 | //uint8_t windowPtr; |
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517 | windowedAirPressure += simpleAirPressure; |
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518 | windowedAirPressure -= airPressureWindow[windowPtr]; |
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519 | airPressureWindow[windowPtr] = simpleAirPressure; |
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520 | windowPtr = (windowPtr+1) % MAX_AIRPRESSURE_WINDOW_LENGTH; |
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1952 | - | 521 | } |
522 | } |
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1821 | - | 523 | |
1952 | - | 524 | void analog_updateBatteryVoltage(void) { |
525 | // Battery. The measured value is: (V * 1k/11k)/3v * 1024 = 31.03 counts per volt (max. measurable is 33v). |
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526 | // This is divided by 3 --> 10.34 counts per volt. |
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527 | UBat = (3 * UBat + sensorInputs[AD_UBAT] / 3) / 4; |
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1955 | - | 528 | debugOut.analog[11] = UBat; |
1952 | - | 529 | } |
1821 | - | 530 | |
1952 | - | 531 | void analog_update(void) { |
532 | analog_updateGyros(); |
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533 | analog_updateAccelerometers(); |
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534 | analog_updateAirPressure(); |
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535 | analog_updateBatteryVoltage(); |
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1612 | dongfang | 536 | } |
537 | |||
1961 | - | 538 | void analog_setNeutral() { |
2018 | - | 539 | gyro_init(); |
540 | |||
1961 | - | 541 | if (gyroOffset_readFromEEProm()) { |
1969 | - | 542 | printf("gyro offsets invalid%s",recal); |
2019 | - | 543 | gyroOffset.offsets[PITCH] = gyroOffset.offsets[ROLL] = 512 * GYRO_OVERSAMPLING_PITCHROLL; |
544 | gyroOffset.offsets[YAW] = 512 * GYRO_OVERSAMPLING_YAW; |
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1961 | - | 545 | } |
1964 | - | 546 | |
1961 | - | 547 | if (accOffset_readFromEEProm()) { |
1969 | - | 548 | printf("acc. meter offsets invalid%s",recal); |
2019 | - | 549 | accOffset.offsets[PITCH] = accOffset.offsets[ROLL] = 512 * ACC_OVERSAMPLING_XY; |
550 | accOffset.offsets[Z] = 717 * ACC_OVERSAMPLING_Z; |
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1961 | - | 551 | } |
552 | |||
553 | // Noise is relative to offset. So, reset noise measurements when changing offsets. |
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554 | gyroNoisePeak[PITCH] = gyroNoisePeak[ROLL] = 0; |
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555 | accNoisePeak[PITCH] = accNoisePeak[ROLL] = 0; |
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556 | |||
557 | // Setting offset values has an influence in the analog.c ISR |
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558 | // Therefore run measurement for 100ms to achive stable readings |
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2015 | - | 559 | delay_ms_with_adc_measurement(100, 0); |
1961 | - | 560 | |
561 | // Rough estimate. Hmm no nothing happens at calibration anyway. |
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2019 | - | 562 | // airPressureSum = simpleAirPressure * (AIRPRESSURE_OVERSAMPLING/2); |
1961 | - | 563 | // pressureMeasurementCount = 0; |
564 | } |
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565 | |||
566 | void analog_calibrateGyros(void) { |
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1612 | dongfang | 567 | #define GYRO_OFFSET_CYCLES 32 |
1952 | - | 568 | uint8_t i, axis; |
1963 | - | 569 | int32_t offsets[3] = { 0, 0, 0 }; |
1952 | - | 570 | gyro_calibrate(); |
571 | |||
572 | // determine gyro bias by averaging (requires that the copter does not rotate around any axis!) |
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573 | for (i = 0; i < GYRO_OFFSET_CYCLES; i++) { |
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2015 | - | 574 | delay_ms_with_adc_measurement(10, 1); |
1952 | - | 575 | for (axis = PITCH; axis <= YAW; axis++) { |
2015 | - | 576 | offsets[axis] += rawGyroValue(axis); |
1952 | - | 577 | } |
578 | } |
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579 | |||
580 | for (axis = PITCH; axis <= YAW; axis++) { |
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1963 | - | 581 | gyroOffset.offsets[axis] = (offsets[axis] + GYRO_OFFSET_CYCLES / 2) / GYRO_OFFSET_CYCLES; |
2018 | - | 582 | |
2019 | - | 583 | int16_t min = (512-200) * (axis==YAW) ? GYRO_OVERSAMPLING_YAW : GYRO_OVERSAMPLING_PITCHROLL; |
584 | int16_t max = (512+200) * (axis==YAW) ? GYRO_OVERSAMPLING_YAW : GYRO_OVERSAMPLING_PITCHROLL; |
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2018 | - | 585 | if(gyroOffset.offsets[axis] < min || gyroOffset.offsets[axis] > max) |
586 | versionInfo.hardwareErrors[0] |= FC_ERROR0_GYRO_PITCH << axis; |
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1952 | - | 587 | } |
1961 | - | 588 | |
589 | gyroOffset_writeToEEProm(); |
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2015 | - | 590 | startAnalogConversionCycle(); |
1612 | dongfang | 591 | } |
592 | |||
593 | /* |
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594 | * Find acc. offsets for a neutral reading, and write them to EEPROM. |
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595 | * Does not (!} update the local variables. This must be done with a |
||
596 | * call to analog_calibrate() - this always (?) is done by the caller |
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597 | * anyway. There would be nothing wrong with updating the variables |
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598 | * directly from here, though. |
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599 | */ |
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600 | void analog_calibrateAcc(void) { |
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2015 | - | 601 | #define ACC_OFFSET_CYCLES 32 |
1960 | - | 602 | uint8_t i, axis; |
2015 | - | 603 | int32_t offsets[3] = { 0, 0, 0 }; |
604 | |||
1960 | - | 605 | for (i = 0; i < ACC_OFFSET_CYCLES; i++) { |
2015 | - | 606 | delay_ms_with_adc_measurement(10, 1); |
1960 | - | 607 | for (axis = PITCH; axis <= YAW; axis++) { |
2015 | - | 608 | offsets[axis] += rawAccValue(axis); |
1960 | - | 609 | } |
610 | } |
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2015 | - | 611 | |
1960 | - | 612 | for (axis = PITCH; axis <= YAW; axis++) { |
2015 | - | 613 | accOffset.offsets[axis] = (offsets[axis] + ACC_OFFSET_CYCLES / 2) / ACC_OFFSET_CYCLES; |
2018 | - | 614 | int16_t min,max; |
615 | if (axis==Z) { |
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2020 | - | 616 | if (staticParams.imuReversedFlags & IMU_REVERSE_ACC_Z) { |
2018 | - | 617 | // TODO: This assumes a sensitivity of +/- 2g. |
2019 | - | 618 | min = (256-200) * ACC_OVERSAMPLING_Z; |
619 | max = (256+200) * ACC_OVERSAMPLING_Z; |
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2018 | - | 620 | } else { |
621 | // TODO: This assumes a sensitivity of +/- 2g. |
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2019 | - | 622 | min = (768-200) * ACC_OVERSAMPLING_Z; |
623 | max = (768+200) * ACC_OVERSAMPLING_Z; |
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2018 | - | 624 | } |
625 | } else { |
||
2019 | - | 626 | min = (512-200) * ACC_OVERSAMPLING_XY; |
627 | max = (512+200) * ACC_OVERSAMPLING_XY; |
||
2018 | - | 628 | } |
629 | if(gyroOffset.offsets[axis] < min || gyroOffset.offsets[axis] > max) { |
||
630 | versionInfo.hardwareErrors[0] |= FC_ERROR0_ACC_X << axis; |
||
631 | } |
||
1960 | - | 632 | } |
1961 | - | 633 | |
2015 | - | 634 | accOffset_writeToEEProm(); |
635 | startAnalogConversionCycle(); |
||
1612 | dongfang | 636 | } |