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1 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
1 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
2 | // + Copyright (c) 04.2007 Holger Buss |
2 | // + Copyright (c) 04.2007 Holger Buss |
3 | // + Nur für den privaten Gebrauch |
3 | // + Nur für den privaten Gebrauch |
4 | // + www.MikroKopter.com |
4 | // + www.MikroKopter.com |
5 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
5 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
6 | // + Es gilt für das gesamte Projekt (Hardware, Software, Binärfiles, Sourcecode und Dokumentation), |
6 | // + Es gilt für das gesamte Projekt (Hardware, Software, Binärfiles, Sourcecode und Dokumentation), |
7 | // + dass eine Nutzung (auch auszugsweise) nur für den privaten (nicht-kommerziellen) Gebrauch zulässig ist. |
7 | // + dass eine Nutzung (auch auszugsweise) nur für den privaten (nicht-kommerziellen) Gebrauch zulässig ist. |
8 | // + Sollten direkte oder indirekte kommerzielle Absichten verfolgt werden, ist mit uns (info@mikrokopter.de) Kontakt |
8 | // + Sollten direkte oder indirekte kommerzielle Absichten verfolgt werden, ist mit uns (info@mikrokopter.de) Kontakt |
9 | // + bzgl. der Nutzungsbedingungen aufzunehmen. |
9 | // + bzgl. der Nutzungsbedingungen aufzunehmen. |
10 | // + Eine kommerzielle Nutzung ist z.B.Verkauf von MikroKoptern, Bestückung und Verkauf von Platinen oder Bausätzen, |
10 | // + Eine kommerzielle Nutzung ist z.B.Verkauf von MikroKoptern, Bestückung und Verkauf von Platinen oder Bausätzen, |
11 | // + Verkauf von Luftbildaufnahmen, usw. |
11 | // + Verkauf von Luftbildaufnahmen, usw. |
12 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
12 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
13 | // + Werden Teile des Quellcodes (mit oder ohne Modifikation) weiterverwendet oder veröffentlicht, |
13 | // + Werden Teile des Quellcodes (mit oder ohne Modifikation) weiterverwendet oder veröffentlicht, |
14 | // + unterliegen sie auch diesen Nutzungsbedingungen und diese Nutzungsbedingungen incl. Copyright müssen dann beiliegen |
14 | // + unterliegen sie auch diesen Nutzungsbedingungen und diese Nutzungsbedingungen incl. Copyright müssen dann beiliegen |
15 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
15 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
16 | // + Sollte die Software (auch auszugesweise) oder sonstige Informationen des MikroKopter-Projekts |
16 | // + Sollte die Software (auch auszugesweise) oder sonstige Informationen des MikroKopter-Projekts |
17 | // + auf anderen Webseiten oder sonstigen Medien veröffentlicht werden, muss unsere Webseite "http://www.mikrokopter.de" |
17 | // + auf anderen Webseiten oder sonstigen Medien veröffentlicht werden, muss unsere Webseite "http://www.mikrokopter.de" |
18 | // + eindeutig als Ursprung verlinkt werden |
18 | // + eindeutig als Ursprung verlinkt werden |
19 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
19 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
20 | // + Keine Gewähr auf Fehlerfreiheit, Vollständigkeit oder Funktion |
20 | // + Keine Gewähr auf Fehlerfreiheit, Vollständigkeit oder Funktion |
21 | // + Benutzung auf eigene Gefahr |
21 | // + Benutzung auf eigene Gefahr |
22 | // + Wir übernehmen keinerlei Haftung für direkte oder indirekte Personen- oder Sachschäden |
22 | // + Wir übernehmen keinerlei Haftung für direkte oder indirekte Personen- oder Sachschäden |
23 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
23 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
24 | // + Die Portierung der Software (oder Teile davon) auf andere Systeme (ausser der Hardware von www.mikrokopter.de) ist nur |
24 | // + Die Portierung der Software (oder Teile davon) auf andere Systeme (ausser der Hardware von www.mikrokopter.de) ist nur |
25 | // + mit unserer Zustimmung zulässig |
25 | // + mit unserer Zustimmung zulässig |
26 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
26 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
27 | // + Die Funktion printf_P() unterliegt ihrer eigenen Lizenz und ist hiervon nicht betroffen |
27 | // + Die Funktion printf_P() unterliegt ihrer eigenen Lizenz und ist hiervon nicht betroffen |
28 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
28 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
29 | // + Redistributions of source code (with or without modifications) must retain the above copyright notice, |
29 | // + Redistributions of source code (with or without modifications) must retain the above copyright notice, |
30 | // + this list of conditions and the following disclaimer. |
30 | // + this list of conditions and the following disclaimer. |
31 | // + * Neither the name of the copyright holders nor the names of contributors may be used to endorse or promote products derived |
31 | // + * Neither the name of the copyright holders nor the names of contributors may be used to endorse or promote products derived |
32 | // + from this software without specific prior written permission. |
32 | // + from this software without specific prior written permission. |
33 | // + * The use of this project (hardware, software, binary files, sources and documentation) is only permittet |
33 | // + * The use of this project (hardware, software, binary files, sources and documentation) is only permittet |
34 | // + for non-commercial use (directly or indirectly) |
34 | // + for non-commercial use (directly or indirectly) |
35 | // + Commercial use (for example: selling of MikroKopters, selling of PCBs, assembly, ...) is only permitted |
35 | // + Commercial use (for example: selling of MikroKopters, selling of PCBs, assembly, ...) is only permitted |
36 | // + with our written permission |
36 | // + with our written permission |
37 | // + * If sources or documentations are redistributet on other webpages, out webpage (http://www.MikroKopter.de) must be |
37 | // + * If sources or documentations are redistributet on other webpages, out webpage (http://www.MikroKopter.de) must be |
38 | // + clearly linked as origin |
38 | // + clearly linked as origin |
39 | // + * porting to systems other than hardware from www.mikrokopter.de is not allowed |
39 | // + * porting to systems other than hardware from www.mikrokopter.de is not allowed |
40 | // + THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS "AS IS" |
40 | // + THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS "AS IS" |
41 | // + AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT LIMITED TO, THE |
41 | // + AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT LIMITED TO, THE |
42 | // + IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS FOR A PARTICULAR PURPOSE |
42 | // + IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS FOR A PARTICULAR PURPOSE |
43 | // + ARE DISCLAIMED. IN NO EVENT SHALL THE COPYRIGHT OWNER OR CONTRIBUTORS BE |
43 | // + ARE DISCLAIMED. IN NO EVENT SHALL THE COPYRIGHT OWNER OR CONTRIBUTORS BE |
44 | // + LIABLE FOR ANY DIRECT, INDIRECT, INCIDENTAL, SPECIAL, EXEMPLARY, OR |
44 | // + LIABLE FOR ANY DIRECT, INDIRECT, INCIDENTAL, SPECIAL, EXEMPLARY, OR |
45 | // + CONSEQUENTIAL DAMAGES (INCLUDING, BUT NOT LIMITED TO, PROCUREMENT OF |
45 | // + CONSEQUENTIAL DAMAGES (INCLUDING, BUT NOT LIMITED TO, PROCUREMENT OF |
46 | // + SUBSTITUTE GOODS OR SERVICES; LOSS OF USE, DATA, OR PROFITS; OR BUSINESS |
46 | // + SUBSTITUTE GOODS OR SERVICES; LOSS OF USE, DATA, OR PROFITS; OR BUSINESS |
47 | // + INTERRUPTION) HOWEVER CAUSED AND ON ANY THEORY OF LIABILITY, WHETHER IN// + CONTRACT, STRICT LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) |
47 | // + INTERRUPTION) HOWEVER CAUSED AND ON ANY THEORY OF LIABILITY, WHETHER IN// + CONTRACT, STRICT LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) |
48 | // + ARISING IN ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE |
48 | // + ARISING IN ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE |
49 | // + POSSIBILITY OF SUCH DAMAGE. |
49 | // + POSSIBILITY OF SUCH DAMAGE. |
50 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
50 | // ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
51 | 51 | ||
52 | #include <stdlib.h> |
52 | #include <stdlib.h> |
53 | #include <avr/io.h> |
53 | #include <avr/io.h> |
54 | #include "eeprom.h" |
54 | #include "eeprom.h" |
55 | #include "flight.h" |
55 | #include "flight.h" |
56 | #include "output.h" |
56 | #include "output.h" |
57 | 57 | ||
58 | // Only for debug. Remove. |
58 | // Only for debug. Remove. |
59 | //#include "analog.h" |
59 | //#include "analog.h" |
60 | //#include "rc.h" |
60 | //#include "rc.h" |
61 | 61 | ||
62 | // Necessary for external control and motor test |
62 | // Necessary for external control and motor test |
63 | #include "uart0.h" |
63 | #include "uart0.h" |
64 | #include "twimaster.h" |
64 | #include "twimaster.h" |
65 | #include "attitude.h" |
65 | #include "attitude.h" |
66 | #include "controlMixer.h" |
66 | #include "controlMixer.h" |
67 | #include "commands.h" |
67 | #include "commands.h" |
68 | #ifdef USE_MK3MAG |
68 | #ifdef USE_MK3MAG |
69 | #include "gps.h" |
69 | #include "gps.h" |
70 | #endif |
70 | #endif |
71 | 71 | ||
72 | #define CHECK_MIN_MAX(value, min, max) {if(value < min) value = min; else if(value > max) value = max;} |
72 | #define CHECK_MIN_MAX(value, min, max) {if(value < min) value = min; else if(value > max) value = max;} |
73 | 73 | ||
74 | /* |
74 | /* |
75 | * These are no longer maintained, just left at 0. The original implementation just summed the acc. |
75 | * These are no longer maintained, just left at 0. The original implementation just summed the acc. |
76 | * value to them every 2 ms. No filtering or anything. Just a case for an eventual overflow?? Hey??? |
76 | * value to them every 2 ms. No filtering or anything. Just a case for an eventual overflow?? Hey??? |
77 | */ |
77 | */ |
78 | // int16_t naviAccPitch = 0, naviAccRoll = 0, naviCntAcc = 0; |
78 | // int16_t naviAccPitch = 0, naviAccRoll = 0, naviCntAcc = 0; |
79 | 79 | ||
80 | uint8_t gyroPFactor, gyroIFactor; // the PD factors for the attitude control |
80 | uint8_t gyroPFactor, gyroIFactor; // the PD factors for the attitude control |
81 | uint8_t yawPFactor, yawIFactor; // the PD factors for the yaw control |
81 | uint8_t yawPFactor, yawIFactor; // the PD factors for the yaw control |
82 | 82 | ||
83 | // Some integral weight constant... |
83 | // Some integral weight constant... |
84 | uint16_t Ki = 10300 / 33; |
84 | uint16_t Ki = 10300 / 33; |
85 | 85 | ||
86 | /************************************************************************/ |
86 | /************************************************************************/ |
87 | /* Filter for motor value smoothing (necessary???) */ |
87 | /* Filter for motor value smoothing (necessary???) */ |
88 | /************************************************************************/ |
88 | /************************************************************************/ |
89 | int16_t motorFilter(int16_t newvalue, int16_t oldvalue) { |
89 | int16_t motorFilter(int16_t newvalue, int16_t oldvalue) { |
90 | switch (staticParams.motorSmoothing) { |
90 | switch (staticParams.motorSmoothing) { |
91 | case 0: |
91 | case 0: |
92 | return newvalue; |
92 | return newvalue; |
93 | case 1: |
93 | case 1: |
94 | return (oldvalue + newvalue) / 2; |
94 | return (oldvalue + newvalue) / 2; |
95 | case 2: |
95 | case 2: |
96 | if (newvalue > oldvalue) |
96 | if (newvalue > oldvalue) |
97 | return (1 * (int16_t) oldvalue + newvalue) / 2; //mean of old and new |
97 | return (1 * (int16_t) oldvalue + newvalue) / 2; //mean of old and new |
98 | else |
98 | else |
99 | return newvalue - (oldvalue - newvalue) * 1; // 2 * new - old |
99 | return newvalue - (oldvalue - newvalue) * 1; // 2 * new - old |
100 | case 3: |
100 | case 3: |
101 | if (newvalue < oldvalue) |
101 | if (newvalue < oldvalue) |
102 | return (1 * (int16_t) oldvalue + newvalue) / 2; //mean of old and new |
102 | return (1 * (int16_t) oldvalue + newvalue) / 2; //mean of old and new |
103 | else |
103 | else |
104 | return newvalue - (oldvalue - newvalue) * 1; // 2 * new - old |
104 | return newvalue - (oldvalue - newvalue) * 1; // 2 * new - old |
105 | default: |
105 | default: |
106 | return newvalue; |
106 | return newvalue; |
107 | } |
107 | } |
108 | } |
108 | } |
109 | 109 | ||
110 | /************************************************************************/ |
110 | /************************************************************************/ |
111 | /* Neutral Readings */ |
111 | /* Neutral Readings */ |
112 | /************************************************************************/ |
112 | /************************************************************************/ |
113 | void flight_setNeutral() { |
113 | void flight_setNeutral() { |
114 | MKFlags |= MKFLAG_CALIBRATE; |
114 | MKFlags |= MKFLAG_CALIBRATE; |
115 | // not really used here any more. |
115 | // not really used here any more. |
116 | /* |
116 | /* |
117 | dynamicParams.KalmanK = -1; |
117 | dynamicParams.KalmanK = -1; |
118 | dynamicParams.KalmanMaxDrift = 0; |
118 | dynamicParams.KalmanMaxDrift = 0; |
119 | dynamicParams.KalmanMaxFusion = 32; |
119 | dynamicParams.KalmanMaxFusion = 32; |
120 | */ |
120 | */ |
121 | controlMixer_initVariables(); |
121 | controlMixer_initVariables(); |
122 | } |
122 | } |
123 | 123 | ||
124 | void setFlightParameters(uint8_t _Ki, uint8_t _gyroPFactor, |
124 | void setFlightParameters(uint8_t _Ki, uint8_t _gyroPFactor, |
125 | uint8_t _gyroIFactor, uint8_t _yawPFactor, uint8_t _yawIFactor) { |
125 | uint8_t _gyroIFactor, uint8_t _yawPFactor, uint8_t _yawIFactor) { |
126 | Ki = 10300 / _Ki; |
126 | Ki = 10300 / _Ki; |
127 | gyroPFactor = _gyroPFactor; |
127 | gyroPFactor = _gyroPFactor; |
128 | gyroIFactor = _gyroIFactor; |
128 | gyroIFactor = _gyroIFactor; |
129 | yawPFactor = _yawPFactor; |
129 | yawPFactor = _yawPFactor; |
130 | yawIFactor = _yawIFactor; |
130 | yawIFactor = _yawIFactor; |
131 | } |
131 | } |
132 | 132 | ||
133 | void setNormalFlightParameters(void) { |
133 | void setNormalFlightParameters(void) { |
134 | setFlightParameters( |
134 | setFlightParameters( |
135 | dynamicParams.IFactor, |
135 | dynamicParams.IFactor, |
136 | dynamicParams.gyroP, |
136 | dynamicParams.gyroP, |
137 | staticParams.bitConfig & CFG_HEADING_HOLD ? 0 : dynamicParams.gyroI, |
137 | staticParams.bitConfig & CFG_HEADING_HOLD ? 0 : dynamicParams.gyroI, |
138 | dynamicParams.gyroP, |
138 | dynamicParams.gyroP, |
139 | dynamicParams.yawIFactor |
139 | dynamicParams.yawIFactor |
140 | ); |
140 | ); |
141 | } |
141 | } |
142 | 142 | ||
143 | void setStableFlightParameters(void) { |
143 | void setStableFlightParameters(void) { |
144 | setFlightParameters(33, 90, 120, 90, 120); |
144 | setFlightParameters(33, 90, 120, 90, 120); |
145 | } |
145 | } |
146 | 146 | ||
147 | /************************************************************************/ |
147 | /************************************************************************/ |
148 | /* Main Flight Control */ |
148 | /* Main Flight Control */ |
149 | /************************************************************************/ |
149 | /************************************************************************/ |
150 | void flight_control(void) { |
150 | void flight_control(void) { |
151 | int16_t tmp_int; |
151 | int16_t tmp_int; |
152 | // Mixer Fractions that are combined for Motor Control |
152 | // Mixer Fractions that are combined for Motor Control |
153 | int16_t yawTerm, throttleTerm, term[2]; |
153 | int16_t yawTerm, throttleTerm, term[2]; |
154 | 154 | ||
155 | // PID controller variables |
155 | // PID controller variables |
156 | int16_t PDPart[2], PDPartYaw, PPart[2]; |
156 | int16_t PPArt[2], DPart[2], PPartYaw, DPartYaw; |
157 | static int32_t IPart[2] = { 0, 0 }; |
157 | static int32_t IPart[2] = { 0, 0 }; |
158 | // static int32_t yawControlRate = 0; |
- | |
159 | - | ||
160 | // Removed. Too complicated, and apparently not necessary with MEMS gyros anyway. |
- | |
161 | // static int32_t IntegralGyroPitchError = 0, IntegralGyroRollError = 0; |
- | |
162 | // static int32_t CorrectionPitch, CorrectionRoll; |
- | |
163 | - | ||
164 | static uint16_t emergencyFlightTime; |
158 | static uint16_t emergencyFlightTime; |
165 | static int8_t debugDataTimer = 1; |
159 | static int8_t debugDataTimer = 1; |
166 | 160 | ||
167 | // High resolution motor values for smoothing of PID motor outputs |
161 | // High resolution motor values for smoothing of PID motor outputs |
168 | static int16_t motorFilters[MAX_MOTORS]; |
162 | static int16_t motorFilters[MAX_MOTORS]; |
169 | 163 | ||
170 | uint8_t i, axis; |
164 | uint8_t i, axis; |
171 | 165 | ||
172 | // Fire the main flight attitude calculation, including integration of angles. |
166 | // Fire the main flight attitude calculation, including integration of angles. |
173 | // We want that to kick as early as possible, not to delay new AD sampling further. |
167 | // We want that to kick as early as possible, not to delay new AD sampling further. |
174 | calculateFlightAttitude(); |
168 | calculateFlightAttitude(); |
175 | controlMixer_update(); |
169 | controlMixer_update(); |
176 | throttleTerm = controls[CONTROL_THROTTLE]; |
170 | throttleTerm = controls[CONTROL_THROTTLE]; |
177 | 171 | ||
178 | // This check removed. Is done on a per-motor basis, after output matrix multiplication. |
172 | // This check removed. Is done on a per-motor basis, after output matrix multiplication. |
179 | if (throttleTerm < staticParams.minThrottle + 10) |
173 | if (throttleTerm < staticParams.minThrottle + 10) |
180 | throttleTerm = staticParams.minThrottle + 10; |
174 | throttleTerm = staticParams.minThrottle + 10; |
181 | else if (throttleTerm > staticParams.maxThrottle - 20) |
175 | else if (throttleTerm > staticParams.maxThrottle - 20) |
182 | throttleTerm = (staticParams.maxThrottle - 20); |
176 | throttleTerm = (staticParams.maxThrottle - 20); |
183 | 177 | ||
184 | /************************************************************************/ |
178 | /************************************************************************/ |
185 | /* RC-signal is bad */ |
179 | /* RC-signal is bad */ |
186 | /* This part could be abstracted, as having yet another control input */ |
180 | /* This part could be abstracted, as having yet another control input */ |
187 | /* to the control mixer: An emergency autopilot control. */ |
181 | /* to the control mixer: An emergency autopilot control. */ |
188 | /************************************************************************/ |
182 | /************************************************************************/ |
189 | 183 | ||
190 | if (controlMixer_getSignalQuality() <= SIGNAL_BAD) { // the rc-frame signal is not reveived or noisy |
184 | if (controlMixer_getSignalQuality() <= SIGNAL_BAD) { // the rc-frame signal is not reveived or noisy |
191 | beepRCAlarm(); |
185 | beepRCAlarm(); |
192 | 186 | ||
193 | if (emergencyFlightTime) { |
187 | if (emergencyFlightTime) { |
194 | // continue emergency flight |
188 | // continue emergency flight |
195 | emergencyFlightTime--; |
189 | emergencyFlightTime--; |
196 | if (isFlying > 256) { |
190 | if (isFlying > 256) { |
197 | // We're probably still flying. Descend slowly. |
191 | // We're probably still flying. Descend slowly. |
198 | throttleTerm = staticParams.emergencyThrottle; // Set emergency throttle |
192 | throttleTerm = staticParams.emergencyThrottle; // Set emergency throttle |
199 | MKFlags |= (MKFLAG_EMERGENCY_FLIGHT); // Set flag for emergency landing |
193 | MKFlags |= (MKFLAG_EMERGENCY_FLIGHT); // Set flag for emergency landing |
200 | setStableFlightParameters(); |
194 | setStableFlightParameters(); |
201 | } else { |
195 | } else { |
202 | MKFlags &= ~(MKFLAG_MOTOR_RUN); // Probably not flying, and bad R/C signal. Kill motors. |
196 | MKFlags &= ~(MKFLAG_MOTOR_RUN); // Probably not flying, and bad R/C signal. Kill motors. |
203 | } |
197 | } |
204 | } else { |
198 | } else { |
205 | // end emergency flight (just cut the motors???) |
199 | // end emergency flight (just cut the motors???) |
206 | MKFlags &= ~(MKFLAG_MOTOR_RUN | MKFLAG_EMERGENCY_FLIGHT); |
200 | MKFlags &= ~(MKFLAG_MOTOR_RUN | MKFLAG_EMERGENCY_FLIGHT); |
207 | } |
201 | } |
208 | } else { |
202 | } else { |
209 | // signal is acceptable |
203 | // signal is acceptable |
210 | if (controlMixer_getSignalQuality() > SIGNAL_BAD) { |
204 | if (controlMixer_getSignalQuality() > SIGNAL_BAD) { |
211 | // Reset emergency landing control variables. |
205 | // Reset emergency landing control variables. |
212 | MKFlags &= ~(MKFLAG_EMERGENCY_FLIGHT); // clear flag for emergency landing |
206 | MKFlags &= ~(MKFLAG_EMERGENCY_FLIGHT); // clear flag for emergency landing |
213 | // The time is in whole seconds. |
207 | // The time is in whole seconds. |
214 | emergencyFlightTime = (uint16_t) staticParams.emergencyFlightDuration * 488; |
208 | emergencyFlightTime = (uint16_t) staticParams.emergencyFlightDuration * 488; |
215 | } |
209 | } |
216 | 210 | ||
217 | // If some throttle is given, and the motor-run flag is on, increase the probability that we are flying. |
211 | // If some throttle is given, and the motor-run flag is on, increase the probability that we are flying. |
218 | if (throttleTerm > 40 && (MKFlags & MKFLAG_MOTOR_RUN)) { |
212 | if (throttleTerm > 40 && (MKFlags & MKFLAG_MOTOR_RUN)) { |
219 | // increment flight-time counter until overflow. |
213 | // increment flight-time counter until overflow. |
220 | if (isFlying != 0xFFFF) |
214 | if (isFlying != 0xFFFF) |
221 | isFlying++; |
215 | isFlying++; |
222 | } else |
216 | } else |
223 | /* |
217 | /* |
224 | * When standing on the ground, do not apply I controls and zero the yaw stick. |
218 | * When standing on the ground, do not apply I controls and zero the yaw stick. |
225 | * Probably to avoid integration effects that will cause the copter to spin |
219 | * Probably to avoid integration effects that will cause the copter to spin |
226 | * or flip when taking off. |
220 | * or flip when taking off. |
227 | */ |
221 | */ |
228 | if (isFlying < 256) { |
222 | if (isFlying < 256) { |
229 | IPart[PITCH] = IPart[ROLL] = 0; |
223 | IPart[PITCH] = IPart[ROLL] = 0; |
230 | // TODO: Don't stomp on other modules' variables!!! |
224 | // TODO: Don't stomp on other modules' variables!!! |
231 | // controlYaw = 0; |
225 | // controlYaw = 0; |
232 | PDPartYaw = 0; // instead. |
226 | PDPartYaw = 0; // instead. |
233 | if (isFlying == 250) { |
227 | if (isFlying == 250) { |
234 | // HC_setGround(); |
228 | // HC_setGround(); |
235 | updateCompassCourse = 1; |
229 | updateCompassCourse = 1; |
236 | yawAngleDiff = 0; |
230 | yawAngleDiff = 0; |
237 | } |
231 | } |
238 | } else { |
232 | } else { |
239 | // Set fly flag. TODO: Hmmm what can we trust - the isFlying counter or the flag? |
233 | // Set fly flag. TODO: Hmmm what can we trust - the isFlying counter or the flag? |
240 | // Answer: The counter. The flag is not read from anywhere anyway... except the NC maybe. |
234 | // Answer: The counter. The flag is not read from anywhere anyway... except the NC maybe. |
241 | MKFlags |= (MKFLAG_FLY); |
235 | MKFlags |= (MKFLAG_FLY); |
242 | } |
236 | } |
243 | 237 | ||
244 | commands_handleCommands(); |
238 | commands_handleCommands(); |
245 | setNormalFlightParameters(); |
239 | setNormalFlightParameters(); |
246 | } // end else (not bad signal case) |
240 | } // end else (not bad signal case) |
247 | 241 | ||
248 | /************************************************************************/ |
242 | /************************************************************************/ |
249 | /* Yawing */ |
243 | /* Yawing */ |
250 | /************************************************************************/ |
244 | /************************************************************************/ |
251 | if (abs(controls[CONTROL_YAW]) > 4 * staticParams.stickYawP) { // yaw stick is activated |
245 | if (abs(controls[CONTROL_YAW]) > 4 * staticParams.stickYawP) { // yaw stick is activated |
252 | ignoreCompassTimer = 1000; |
246 | ignoreCompassTimer = 1000; |
253 | if (!(staticParams.bitConfig & CFG_COMPASS_FIX)) { |
247 | if (!(staticParams.bitConfig & CFG_COMPASS_FIX)) { |
254 | updateCompassCourse = 1; |
248 | updateCompassCourse = 1; |
255 | } |
249 | } |
256 | } |
250 | } |
257 | 251 | ||
258 | // yawControlRate = controlYaw; |
252 | // yawControlRate = controlYaw; |
259 | // Trim drift of yawAngleDiff with controlYaw. |
253 | // Trim drift of yawAngleDiff with controlYaw. |
260 | // TODO: We want NO feedback of control related stuff to the attitude related stuff. |
254 | // TODO: We want NO feedback of control related stuff to the attitude related stuff. |
261 | // This seems to be used as: Difference desired <--> real heading. |
255 | // This seems to be used as: Difference desired <--> real heading. |
262 | yawAngleDiff -= controls[CONTROL_YAW]; |
256 | yawAngleDiff -= controls[CONTROL_YAW]; |
263 | 257 | ||
264 | // limit the effect |
258 | // limit the effect |
265 | CHECK_MIN_MAX(yawAngleDiff, -50000, 50000); |
259 | CHECK_MIN_MAX(yawAngleDiff, -50000, 50000); |
266 | 260 | ||
267 | /************************************************************************/ |
261 | /************************************************************************/ |
268 | /* Compass is currently not supported. */ |
262 | /* Compass is currently not supported. */ |
269 | /************************************************************************/ |
263 | /************************************************************************/ |
270 | if (staticParams.bitConfig & (CFG_COMPASS_ACTIVE | CFG_GPS_ACTIVE)) { |
264 | if (staticParams.bitConfig & (CFG_COMPASS_ACTIVE | CFG_GPS_ACTIVE)) { |
271 | updateCompass(); |
265 | updateCompass(); |
272 | } |
266 | } |
273 | 267 | ||
274 | #if defined (USE_NAVICTRL) |
268 | #if defined (USE_NAVICTRL) |
275 | /************************************************************************/ |
269 | /************************************************************************/ |
276 | /* GPS is currently not supported. */ |
270 | /* GPS is currently not supported. */ |
277 | /************************************************************************/ |
271 | /************************************************************************/ |
278 | if(staticParams.GlobalConfig & CFG_GPS_ACTIVE) { |
272 | if(staticParams.GlobalConfig & CFG_GPS_ACTIVE) { |
279 | GPS_Main(); |
273 | GPS_Main(); |
280 | MKFlags &= ~(MKFLAG_CALIBRATE | MKFLAG_START); |
274 | MKFlags &= ~(MKFLAG_CALIBRATE | MKFLAG_START); |
281 | } else { |
275 | } else { |
282 | } |
276 | } |
283 | #endif |
277 | #endif |
284 | // end part 1: 750-800 usec. |
278 | // end part 1: 750-800 usec. |
285 | // start part 3: 350 - 400 usec. |
279 | // start part 3: 350 - 400 usec. |
286 | #define SENSOR_LIMIT (4096 * 4) |
280 | #define SENSOR_LIMIT (4096 * 4) |
287 | /************************************************************************/ |
281 | /************************************************************************/ |
288 | 282 | ||
289 | /* Calculate control feedback from angle (gyro integral) */ |
283 | /* Calculate control feedback from angle (gyro integral) */ |
290 | /* and angular velocity (gyro signal) */ |
284 | /* and angular velocity (gyro signal) */ |
291 | /************************************************************************/ |
285 | /************************************************************************/ |
292 | // The P-part is the P of the PID controller. That's the angle integrals (not rates). |
286 | // The P-part is the P of the PID controller. That's the angle integrals (not rates). |
293 | - | ||
294 | for (axis = PITCH; axis <= ROLL; axis++) { |
287 | for (axis = PITCH; axis <= ROLL; axis++) { |
295 | PPart[axis] = angle[axis] * gyroIFactor / (44000 / CONTROL_SCALING); // P-Part - Proportional to Integral |
288 | PPart[axis] = angle[axis] * gyroIFactor / (44000 / CONTROL_SCALING); // P-Part - Proportional to Integral |
296 | 289 | ||
297 | /* |
290 | /* |
298 | * Now blend in the D-part - proportional to the Differential of the integral = the rate. |
291 | * Now blend in the D-part - proportional to the Differential of the integral = the rate. |
299 | * Read this as: PDPart = PPart + rate_PID * pfactor * CONTROL_SCALING |
292 | * Read this as: PDPart = PPart + rate_PID * pfactor * CONTROL_SCALING |
300 | * where pfactor is in [0..1]. |
293 | * where pfactor is in [0..1]. |
301 | */ |
294 | */ |
302 | PDPart[axis] = PPart[axis] + (int32_t) ((int32_t) rate_PID[axis] * gyroPFactor / (256L / CONTROL_SCALING)) + (differential[axis] |
295 | DPart[axis] = (int32_t) ((int32_t) rate_PID[axis] * gyroPFactor / (256L / CONTROL_SCALING)) + (differential[axis] * (int16_t) dynamicParams.gyroD) / 16; |
303 | * (int16_t) dynamicParams.gyroD) / 16; |
- | |
304 | - | ||
305 | CHECK_MIN_MAX(PDPart[axis], -SENSOR_LIMIT, SENSOR_LIMIT); |
296 | CHECK_MIN_MAX(PDPart[axis], -SENSOR_LIMIT, SENSOR_LIMIT); |
306 | } |
297 | } |
307 | 298 | ||
308 | PDPartYaw = (int32_t) (yawRate * 2 * (int32_t) yawPFactor) / (256L |
299 | PPartYaw = (int32_t) (yawAngleDiff * yawIFactor) / (2 * (44000 / CONTROL_SCALING)); |
309 | / CONTROL_SCALING) + (int32_t) (yawAngleDiff * yawIFactor) / (2 * (44000 |
- | |
310 | / CONTROL_SCALING)); |
300 | DPartYaw = (int32_t) (yawRate * 2 * (int32_t) yawPFactor) / (256L / CONTROL_SCALING); |
311 | 301 | ||
312 | // limit control feedback |
302 | // limit control feedback |
313 | CHECK_MIN_MAX(PDPartYaw, -SENSOR_LIMIT, SENSOR_LIMIT); |
303 | // CHECK_MIN_MAX(PDPartYaw, -SENSOR_LIMIT, SENSOR_LIMIT); |
314 | 304 | ||
315 | /* |
305 | /* |
316 | * Compose throttle term. |
306 | * Compose throttle term. |
317 | * If a Bl-Ctrl is missing, prevent takeoff. |
307 | * If a Bl-Ctrl is missing, prevent takeoff. |
318 | */ |
308 | */ |
319 | if (missingMotor) { |
309 | if (missingMotor) { |
320 | // if we are in the lift off condition. Hmmmmmm when is throttleTerm == 0 anyway??? |
310 | // if we are in the lift off condition. Hmmmmmm when is throttleTerm == 0 anyway??? |
321 | if (isFlying > 1 && isFlying < 50 && throttleTerm > 0) |
311 | if (isFlying > 1 && isFlying < 50 && throttleTerm > 0) |
322 | isFlying = 1; // keep within lift off condition |
312 | isFlying = 1; // keep within lift off condition |
323 | throttleTerm = staticParams.minThrottle; // reduce gas to min to avoid lift of |
313 | throttleTerm = staticParams.minThrottle; // reduce gas to min to avoid lift of |
324 | } |
314 | } |
325 | 315 | ||
326 | // Scale up to higher resolution. Hmm why is it not (from controlMixer and down) scaled already? |
316 | // Scale up to higher resolution. Hmm why is it not (from controlMixer and down) scaled already? |
327 | throttleTerm *= CONTROL_SCALING; |
317 | throttleTerm *= CONTROL_SCALING; |
328 | 318 | ||
329 | /* |
319 | /* |
330 | * Compose yaw term. |
320 | * Compose yaw term. |
331 | * The yaw term is limited: Absolute value is max. = the throttle term / 2. |
321 | * The yaw term is limited: Absolute value is max. = the throttle term / 2. |
332 | * However, at low throttle the yaw term is limited to a fixed value, |
322 | * However, at low throttle the yaw term is limited to a fixed value, |
333 | * and at high throttle it is limited by the throttle reserve (the difference |
323 | * and at high throttle it is limited by the throttle reserve (the difference |
334 | * between current throttle and maximum throttle). |
324 | * between current throttle and maximum throttle). |
335 | */ |
325 | */ |
336 | #define MIN_YAWGAS (40 * CONTROL_SCALING) // yaw also below this gas value |
326 | #define MIN_YAWGAS (40 * CONTROL_SCALING) // yaw also below this gas value |
337 | yawTerm = PDPartYaw - controls[CONTROL_YAW] * CONTROL_SCALING; |
327 | yawTerm = PDPartYaw - controls[CONTROL_YAW] * CONTROL_SCALING; |
338 | // Limit yawTerm |
328 | // Limit yawTerm |
339 | debugOut.digital[0] &= ~DEBUG_CLIP; |
329 | debugOut.digital[0] &= ~DEBUG_CLIP; |
340 | if (throttleTerm > MIN_YAWGAS) { |
330 | if (throttleTerm > MIN_YAWGAS) { |
341 | if (yawTerm < -throttleTerm / 2) { |
331 | if (yawTerm < -throttleTerm / 2) { |
342 | debugOut.digital[0] |= DEBUG_CLIP; |
332 | debugOut.digital[0] |= DEBUG_CLIP; |
343 | yawTerm = -throttleTerm / 2; |
333 | yawTerm = -throttleTerm / 2; |
344 | } else if (yawTerm > throttleTerm / 2) { |
334 | } else if (yawTerm > throttleTerm / 2) { |
345 | debugOut.digital[0] |= DEBUG_CLIP; |
335 | debugOut.digital[0] |= DEBUG_CLIP; |
346 | yawTerm = throttleTerm / 2; |
336 | yawTerm = throttleTerm / 2; |
347 | } |
337 | } |
348 | //CHECK_MIN_MAX(yawTerm, - (throttleTerm / 2), (throttleTerm / 2)); |
338 | //CHECK_MIN_MAX(yawTerm, - (throttleTerm / 2), (throttleTerm / 2)); |
349 | } else { |
339 | } else { |
350 | if (yawTerm < -MIN_YAWGAS / 2) { |
340 | if (yawTerm < -MIN_YAWGAS / 2) { |
351 | debugOut.digital[0] |= DEBUG_CLIP; |
341 | debugOut.digital[0] |= DEBUG_CLIP; |
352 | yawTerm = -MIN_YAWGAS / 2; |
342 | yawTerm = -MIN_YAWGAS / 2; |
353 | } else if (yawTerm > MIN_YAWGAS / 2) { |
343 | } else if (yawTerm > MIN_YAWGAS / 2) { |
354 | debugOut.digital[0] |= DEBUG_CLIP; |
344 | debugOut.digital[0] |= DEBUG_CLIP; |
355 | yawTerm = MIN_YAWGAS / 2; |
345 | yawTerm = MIN_YAWGAS / 2; |
356 | } |
346 | } |
357 | //CHECK_MIN_MAX(yawTerm, - (MIN_YAWGAS / 2), (MIN_YAWGAS / 2)); |
347 | //CHECK_MIN_MAX(yawTerm, - (MIN_YAWGAS / 2), (MIN_YAWGAS / 2)); |
358 | } |
348 | } |
359 | 349 | ||
360 | // FIXME: Throttle may exceed maxThrottle (there is no check no more). |
350 | // FIXME: Throttle may exceed maxThrottle (there is no check no more). |
361 | tmp_int = staticParams.maxThrottle * CONTROL_SCALING; |
351 | tmp_int = staticParams.maxThrottle * CONTROL_SCALING; |
362 | if (yawTerm < -(tmp_int - throttleTerm)) { |
352 | if (yawTerm < -(tmp_int - throttleTerm)) { |
363 | yawTerm = -(tmp_int - throttleTerm); |
353 | yawTerm = -(tmp_int - throttleTerm); |
364 | debugOut.digital[0] |= DEBUG_CLIP; |
354 | debugOut.digital[0] |= DEBUG_CLIP; |
365 | } else if (yawTerm > (tmp_int - throttleTerm)) { |
355 | } else if (yawTerm > (tmp_int - throttleTerm)) { |
366 | yawTerm = (tmp_int - throttleTerm); |
356 | yawTerm = (tmp_int - throttleTerm); |
367 | debugOut.digital[0] |= DEBUG_CLIP; |
357 | debugOut.digital[0] |= DEBUG_CLIP; |
368 | } |
358 | } |
369 | 359 | ||
370 | // CHECK_MIN_MAX(yawTerm, -(tmp_int - throttleTerm), (tmp_int - throttleTerm)); |
360 | // CHECK_MIN_MAX(yawTerm, -(tmp_int - throttleTerm), (tmp_int - throttleTerm)); |
371 | debugOut.digital[1] &= ~DEBUG_CLIP; |
361 | debugOut.digital[1] &= ~DEBUG_CLIP; |
372 | for (axis = PITCH; axis <= ROLL; axis++) { |
362 | for (axis = PITCH; axis <= ROLL; axis++) { |
373 | /* |
363 | /* |
374 | * Compose pitch and roll terms. This is finally where the sticks come into play. |
364 | * Compose pitch and roll terms. This is finally where the sticks come into play. |
375 | */ |
365 | */ |
376 | if (gyroIFactor) { |
366 | if (gyroIFactor) { |
377 | // Integration mode: Integrate (angle - stick) = the difference between angle and stick pos. |
367 | // Integration mode: Integrate (angle - stick) = the difference between angle and stick pos. |
378 | // That means: Holding the stick a little forward will, at constant flight attitude, cause this to grow (decline??) over time. |
368 | // That means: Holding the stick a little forward will, at constant flight attitude, cause this to grow (decline??) over time. |
379 | // TODO: Find out why this seems to be proportional to stick position - not integrating it at all. |
369 | // TODO: Find out why this seems to be proportional to stick position - not integrating it at all. |
380 | IPart[axis] += PPart[axis] - controls[axis]; // Integrate difference between P part (the angle) and the stick pos. |
370 | IPart[axis] += PPart[axis] - controls[axis]; // Integrate difference between P part (the angle) and the stick pos. |
381 | } else { |
371 | } else { |
382 | // "HH" mode: Integrate (rate - stick) = the difference between rotation rate and stick pos. |
372 | // "HH" mode: Integrate (rate - stick) = the difference between rotation rate and stick pos. |
383 | // To keep up with a full stick PDPart should be about 156... |
373 | // To keep up with a full stick PDPart should be about 156... |
384 | IPart[axis] += PDPart[axis] - controls[axis]; // With gyroIFactor == 0, PDPart is really just a D-part. Integrate D-part (the rot. rate) and the stick pos. |
374 | IPart[axis] += PDPart[axis] - controls[axis]; // With gyroIFactor == 0, PDPart is really just a D-part. Integrate D-part (the rot. rate) and the stick pos. |
385 | } |
375 | } |
386 | 376 | ||
387 | tmp_int = (int32_t) ((int32_t) dynamicParams.dynamicStability |
377 | tmp_int = (int32_t) ((int32_t) dynamicParams.dynamicStability |
388 | * (int32_t) (throttleTerm + abs(yawTerm) / 2)) / 64; |
378 | * (int32_t) (throttleTerm + abs(yawTerm) / 2)) / 64; |
389 | 379 | ||
390 | // TODO: From which planet comes the 16000? |
380 | // TODO: From which planet comes the 16000? |
391 | CHECK_MIN_MAX(IPart[axis], -(CONTROL_SCALING * 16000L), (CONTROL_SCALING * 16000L)); |
381 | CHECK_MIN_MAX(IPart[axis], -(CONTROL_SCALING * 16000L), (CONTROL_SCALING * 16000L)); |
392 | // Add (P, D) parts minus stick pos. to the scaled-down I part. |
382 | // Add (P, D) parts minus stick pos. to the scaled-down I part. |
393 | term[axis] = PDPart[axis] - controls[axis] + IPart[axis] / Ki; // PID-controller for pitch |
383 | term[axis] = PDPart[axis] - controls[axis] + IPart[axis] / Ki; // PID-controller for pitch |
394 | term[axis] += (dynamicParams.levelCorrection[axis] - 128); |
384 | term[axis] += (dynamicParams.levelCorrection[axis] - 128); |
395 | /* |
385 | /* |
396 | * Apply "dynamic stability" - that is: Limit pitch and roll terms to a growing function of throttle and yaw(!). |
386 | * Apply "dynamic stability" - that is: Limit pitch and roll terms to a growing function of throttle and yaw(!). |
397 | * The higher the dynamic stability parameter, the wider the bounds. 64 seems to be a kind of unity |
387 | * The higher the dynamic stability parameter, the wider the bounds. 64 seems to be a kind of unity |
398 | * (max. pitch or roll term is the throttle value). |
388 | * (max. pitch or roll term is the throttle value). |
399 | * TODO: Why a growing function of yaw? |
389 | * TODO: Why a growing function of yaw? |
400 | */ |
390 | */ |
401 | if (term[axis] < -tmp_int) { |
391 | if (term[axis] < -tmp_int) { |
402 | debugOut.digital[1] |= DEBUG_CLIP; |
392 | debugOut.digital[1] |= DEBUG_CLIP; |
403 | } else if (term[axis] > tmp_int) { |
393 | } else if (term[axis] > tmp_int) { |
404 | debugOut.digital[1] |= DEBUG_CLIP; |
394 | debugOut.digital[1] |= DEBUG_CLIP; |
405 | } |
395 | } |
406 | CHECK_MIN_MAX(term[axis], -tmp_int, tmp_int); |
396 | CHECK_MIN_MAX(term[axis], -tmp_int, tmp_int); |
407 | } |
397 | } |
408 | 398 | ||
409 | // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
399 | // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
410 | // Universal Mixer |
400 | // Universal Mixer |
411 | // Each (pitch, roll, throttle, yaw) term is in the range [0..255 * CONTROL_SCALING]. |
401 | // Each (pitch, roll, throttle, yaw) term is in the range [0..255 * CONTROL_SCALING]. |
412 | // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
402 | // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
413 | 403 | ||
414 | debugOut.analog[3] = rate_ATT[PITCH]; |
404 | debugOut.analog[3] = rate_ATT[PITCH]; |
415 | debugOut.analog[4] = rate_ATT[ROLL]; |
405 | debugOut.analog[4] = rate_ATT[ROLL]; |
416 | debugOut.analog[5] = yawRate; |
406 | debugOut.analog[5] = yawRate; |
417 | 407 | ||
418 | debugOut.analog[6] = filteredAcc[PITCH]; |
408 | debugOut.analog[6] = filteredAcc[PITCH]; |
419 | debugOut.analog[7] = filteredAcc[ROLL]; |
409 | debugOut.analog[7] = filteredAcc[ROLL]; |
420 | debugOut.analog[8] = filteredAcc[Z]; |
410 | debugOut.analog[8] = filteredAcc[Z]; |
421 | 411 | ||
422 | debugOut.analog[12] = term[PITCH]; |
412 | debugOut.analog[12] = term[PITCH]; |
423 | debugOut.analog[13] = term[ROLL]; |
413 | debugOut.analog[13] = term[ROLL]; |
424 | debugOut.analog[14] = yawTerm; |
414 | debugOut.analog[14] = yawTerm; |
425 | debugOut.analog[15] = throttleTerm; |
415 | debugOut.analog[15] = throttleTerm; |
426 | 416 | ||
427 | for (i = 0; i < MAX_MOTORS; i++) { |
417 | for (i = 0; i < MAX_MOTORS; i++) { |
428 | int32_t tmp; |
418 | int32_t tmp; |
429 | uint8_t throttle; |
419 | uint8_t throttle; |
430 | 420 | ||
431 | tmp = (int32_t)throttleTerm * mixerMatrix.motor[i][MIX_THROTTLE]; |
421 | tmp = (int32_t)throttleTerm * mixerMatrix.motor[i][MIX_THROTTLE]; |
432 | tmp += (int32_t)term[PITCH] * mixerMatrix.motor[i][MIX_PITCH]; |
422 | tmp += (int32_t)term[PITCH] * mixerMatrix.motor[i][MIX_PITCH]; |
433 | tmp += (int32_t)term[ROLL] * mixerMatrix.motor[i][MIX_ROLL]; |
423 | tmp += (int32_t)term[ROLL] * mixerMatrix.motor[i][MIX_ROLL]; |
434 | tmp += (int32_t)yawTerm * mixerMatrix.motor[i][MIX_YAW]; |
424 | tmp += (int32_t)yawTerm * mixerMatrix.motor[i][MIX_YAW]; |
435 | tmp = tmp >> 6; |
425 | tmp = tmp >> 6; |
436 | motorFilters[i] = motorFilter(tmp, motorFilters[i]); |
426 | motorFilters[i] = motorFilter(tmp, motorFilters[i]); |
437 | // Now we scale back down to a 0..255 range. |
427 | // Now we scale back down to a 0..255 range. |
438 | tmp = motorFilters[i] / MOTOR_SCALING; |
428 | tmp = motorFilters[i] / MOTOR_SCALING; |
439 | 429 | ||
440 | // So this was the THIRD time a throttle was limited. But should the limitation |
430 | // So this was the THIRD time a throttle was limited. But should the limitation |
441 | // apply to the common throttle signal (the one used for setting the "power" of |
431 | // apply to the common throttle signal (the one used for setting the "power" of |
442 | // all motors together) or should it limit the throttle set for each motor, |
432 | // all motors together) or should it limit the throttle set for each motor, |
443 | // including mix components of pitch, roll and yaw? I think only the common |
433 | // including mix components of pitch, roll and yaw? I think only the common |
444 | // throttle should be limited. |
434 | // throttle should be limited. |
445 | // --> WRONG. This caused motors to stall completely in tight maneuvers. |
435 | // --> WRONG. This caused motors to stall completely in tight maneuvers. |
446 | // Apply to individual signals instead. |
436 | // Apply to individual signals instead. |
447 | CHECK_MIN_MAX(tmp, 1, 255); |
437 | CHECK_MIN_MAX(tmp, 1, 255); |
448 | throttle = tmp; |
438 | throttle = tmp; |
449 | 439 | ||
450 | if (i < 4) debugOut.analog[22 + i] = throttle; |
440 | if (i < 4) debugOut.analog[22 + i] = throttle; |
451 | 441 | ||
452 | if ((MKFlags & MKFLAG_MOTOR_RUN) && mixerMatrix.motor[i][MIX_THROTTLE] > 0) { |
442 | if ((MKFlags & MKFLAG_MOTOR_RUN) && mixerMatrix.motor[i][MIX_THROTTLE] > 0) { |
453 | motor[i].SetPoint = throttle; |
443 | motor[i].SetPoint = throttle; |
454 | } else if (motorTestActive) { |
444 | } else if (motorTestActive) { |
455 | motor[i].SetPoint = motorTest[i]; |
445 | motor[i].SetPoint = motorTest[i]; |
456 | } else { |
446 | } else { |
457 | motor[i].SetPoint = 0; |
447 | motor[i].SetPoint = 0; |
458 | } |
448 | } |
459 | } |
449 | } |
460 | 450 | ||
461 | I2C_Start(TWI_STATE_MOTOR_TX); |
451 | I2C_Start(TWI_STATE_MOTOR_TX); |
462 | 452 | ||
463 | // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
453 | // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
464 | // Debugging |
454 | // Debugging |
465 | // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
455 | // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ |
466 | if (!(--debugDataTimer)) { |
456 | if (!(--debugDataTimer)) { |
467 | debugDataTimer = 24; // update debug outputs at 488 / 24 = 20.3 Hz. |
457 | debugDataTimer = 24; // update debug outputs at 488 / 24 = 20.3 Hz. |
468 | debugOut.analog[0] = (10 * angle[PITCH]) / GYRO_DEG_FACTOR_PITCHROLL; // in 0.1 deg |
458 | debugOut.analog[0] = (10 * angle[PITCH]) / GYRO_DEG_FACTOR_PITCHROLL; // in 0.1 deg |
469 | debugOut.analog[1] = (10 * angle[ROLL]) / GYRO_DEG_FACTOR_PITCHROLL; // in 0.1 deg |
459 | debugOut.analog[1] = (10 * angle[ROLL]) / GYRO_DEG_FACTOR_PITCHROLL; // in 0.1 deg |
470 | debugOut.analog[2] = yawGyroHeading / GYRO_DEG_FACTOR_YAW; |
460 | debugOut.analog[2] = yawGyroHeading / GYRO_DEG_FACTOR_YAW; |
471 | 461 | ||
472 | debugOut.analog[16] = gyroPFactor; |
462 | debugOut.analog[16] = gyroPFactor; |
473 | } |
463 | } |
474 | } |
464 | } |
475 | 465 |