Knowledge (XXG)

Triad method

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reference vectors are usually known directions (e.g. stars, Earth magnetic field, gravity vector, etc.). Body fixed vectors are the measured directions as observed by an on-board sensor (e.g. star tracker, magnetometer, etc.). With advances in micro-electronics, attitude determination algorithms such as TRIAD have found their place in a variety of devices (e.g. smart phones, cars, tablets, UAVs, etc.) with a broad impact on modern society.
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is the earliest published algorithm for determining spacecraft attitude, which was first introduced by Harold Black in 1964. Given the knowledge of two vectors in the reference and body coordinates of a satellite, the TRIAD algorithm obtains the direction cosine matrix relating to both frames. Harold
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TRIAD was used as an attitude determination technique to process the telemetry data from the Transit satellite system (used by the U.S. Navy for navigation). The principles of the Transit system gave rise to the global positioning system satellite constellation. In an application problem, the
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Black played a key role in the development of the guidance, navigation, and control of the U.S. Navy's Transit satellite system at Johns Hopkins Applied Physics Laboratories. TRIAD represented the state of practice in spacecraft attitude determination before the advent of
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are also left-handed because of the one-one correspondence between the vectors. This is because of the simple fact that, in Euclidean geometry, the angle between any two vectors remains invariant to coordinate transformations. Therefore, the determinant
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are noisy and the orthogonality condition of the attitude matrix (or the direction cosine matrix) is not preserved by the above procedure. TRIAD incorporates the following elegant procedure to redress this problem. To this end, one defines unit vectors,
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It is of consequence to note that the TRIAD method always produces a proper orthogonal matrix irrespective of the handedness of the reference and body vectors employed in the estimation process. This can be shown as follows: In a matrix form given
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Note that computational efficiency has been achieved in this procedure by replacing the matrix inverse with a transpose. This is possible because the matrices involved in computing attitude are each composed of a TRIAD of
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transforms vectors in the body fixed frame into the frame of the reference vectors. Among other properties, rotational matrices preserve the length of the vector they operate on. Note that the direction cosine matrix
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This is quite useful in practical applications since the analyst is always guaranteed a proper orthogonal matrix irrespective of the nature of the reference and measured vector quantities.
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be the corresponding measured directions of the reference unit vectors as resolved in a body fixed frame of reference. Following that, they are then related by the equations,
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Black, Harold (July–August 1990). "Early Developments of Transit, the Navy Navigation Satellite System".
2606: 309: 1969: 2533: 2498: 527:{\displaystyle {\vec {R}}_{1}\times {\vec {R}}_{2}=A\left({\vec {r}}_{1}\times {\vec {r}}_{2}\right)} 2117: 2015: 75: 39: 2343: 1510: 580: 2469: 25: 303: 2242: 2222: 854: 2587: 2541: 2506: 1723:). Thus an estimate of the spacecraft attitude is given by the proper orthogonal matrix as 2489:
Black, Harold (July 1964). "A Passive System for Determining the Attitude of a Satellite".
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Wahba, Grace (July 1966). "A Least Squares Estimate of Satellite Attitude, Problem 65.1".
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depending on whether its columns are right-handed or left-handed respectively (similarly,
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The solution presented above works well in the noise-free case. However, in practice,
2639: 2607:"Attitude Determination Using Vector Observations: A Fast Optimal Matrix Algorithm" 1144:{\displaystyle {\hat {s}}={\frac {{\vec {r}}_{1}}{||{\vec {r}}_{1}||}}} 1028:{\displaystyle {\hat {S}}={\frac {{\vec {R}}_{1}}{||{\vec {R}}_{1}||}}} 2591: 2545: 2510: 36:
Firstly, one considers the linearly independent reference vectors
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basis vectors. "TRIAD" derives its name from this observation.
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to be used in place of the first two columns of equation (
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TRIAD proposes an estimate of the direction cosine matrix
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Solution to the spacecraft attitude determination problem
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is a rotation matrix (sometimes also known as a proper
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as a solution to the linear system equations given by
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also transforms the cross product vector, written as,
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have been used to separate different column vectors.
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TRIAD Attitude Matrix and Handedness of Measurements
2416: 2361: 2332: 2309: 2289: 2251: 2231: 2211: 2106: 1987: 1921: 1680: 1470: 1308: 1143: 1027: 924: 863: 826: 563: 526: 405: 384: 364: 294: 274: 225: 158: 100: 64: 2239:form a left-handed TRIAD, then the columns of 226:{\displaystyle {\vec {R}}_{i}=A{\vec {r}}_{i}} 925:{\displaystyle {\vec {r}}_{1},{\vec {r}}_{2}} 159:{\displaystyle {\vec {r}}_{1},{\vec {r}}_{2}} 8: 1922:{\displaystyle {\hat {A}}=\left.\left^{T}} 2526:Journal of Guidance, Control and Dynamics 2386: 2345: 2322: 2302: 2265: 2244: 2224: 2190: 2189: 2175: 2174: 2154: 2153: 2133: 2132: 2119: 2088: 2087: 2073: 2072: 2052: 2051: 2031: 2030: 2017: 1971: 1913: 1897: 1896: 1882: 1881: 1861: 1860: 1840: 1839: 1814: 1813: 1799: 1798: 1778: 1777: 1757: 1756: 1737: 1736: 1734: 1662: 1661: 1647: 1646: 1626: 1625: 1605: 1604: 1577: 1576: 1562: 1561: 1541: 1540: 1520: 1519: 1512: 1460: 1455: 1449: 1438: 1437: 1427: 1416: 1415: 1409: 1404: 1396: 1385: 1384: 1374: 1363: 1362: 1358: 1344: 1343: 1341: 1298: 1293: 1287: 1276: 1275: 1265: 1254: 1253: 1247: 1242: 1234: 1223: 1222: 1212: 1201: 1200: 1196: 1182: 1181: 1179: 1133: 1128: 1122: 1111: 1110: 1104: 1099: 1092: 1081: 1080: 1077: 1063: 1062: 1060: 1017: 1012: 1006: 995: 994: 988: 983: 976: 965: 964: 961: 947: 946: 944: 916: 905: 904: 894: 883: 882: 879: 856: 808: 797: 796: 786: 775: 774: 753: 742: 741: 725: 714: 713: 685: 674: 673: 663: 652: 651: 630: 619: 618: 602: 591: 590: 582: 556: 513: 502: 501: 491: 480: 479: 461: 450: 449: 439: 428: 427: 424: 398: 377: 317: 311: 287: 255: 217: 206: 205: 192: 181: 180: 177: 150: 139: 138: 128: 117: 116: 113: 92: 81: 80: 77: 56: 45: 44: 41: 2481: 2290:{\displaystyle det\left(\Gamma \right)} 1705:While the normalizations of equations ( 2614:The Journal of Astronautical Sciences 7: 2417:{\displaystyle det\left(A\right)=1.} 2377: 1962: 1725: 1503: 1332: 1170: 1051: 935: 573: 415: 168: 2605:Markley, Landis (April–June 1993). 2347: 2280: 2246: 2226: 2121: 2019: 1982: 1973: 365:{\displaystyle A^{T}A=I,det(A)=+1} 14: 1988:{\displaystyle \Gamma =A\Delta } 2565:1999 Flight Mechanics Symposium 2212:{\displaystyle \Delta =\left.} 2195: 2180: 2159: 2138: 2107:{\displaystyle \Gamma :=\left} 2093: 2078: 2057: 2036: 1902: 1887: 1866: 1845: 1819: 1804: 1783: 1762: 1742: 1667: 1652: 1631: 1610: 1582: 1567: 1546: 1525: 1461: 1456: 1443: 1421: 1410: 1405: 1390: 1368: 1349: 1299: 1294: 1281: 1259: 1248: 1243: 1228: 1206: 1187: 1134: 1129: 1116: 1105: 1100: 1086: 1068: 1018: 1013: 1000: 989: 984: 970: 952: 910: 888: 802: 780: 747: 719: 679: 657: 624: 596: 507: 485: 455: 433: 350: 344: 211: 186: 144: 122: 101:{\displaystyle {\vec {R}}_{2}} 86: 65:{\displaystyle {\vec {R}}_{1}} 50: 1: 2567:: 2 – via ResearchGate. 2460:Attitude Dynamics and Control 2362:{\displaystyle \Delta =\pm 1} 2651:Rotation in three dimensions 2371: 2219:Note that if the columns of 1681:{\displaystyle \left=A\left} 827:{\displaystyle \left=A\left} 2646:Spacecraft attitude control 2559:Markley, F. Landis (1999). 1719: 1713: 1707: 1497: 2667: 2375:), one concludes that 2252:{\displaystyle \Delta } 2232:{\displaystyle \Gamma } 864:{\displaystyle \vdots } 2465:Orientation (Geometry) 2418: 2363: 2334: 2311: 2291: 2253: 2233: 2213: 2108: 1989: 1923: 1682: 1472: 1310: 1145: 1029: 926: 865: 828: 565: 528: 407: 386: 366: 296: 276: 227: 160: 102: 66: 2419: 2364: 2335: 2312: 2292: 2254: 2234: 2214: 2109: 1990: 1924: 1683: 1473: 1311: 1146: 1030: 927: 866: 829: 566: 529: 408: 387: 367: 297: 277: 275:{\displaystyle i=1,2} 228: 161: 103: 67: 2385: 2344: 2321: 2301: 2264: 2243: 2223: 2118: 2016: 1970: 1733: 1511: 1340: 1178: 1059: 943: 878: 855: 581: 555: 423: 397: 376: 310: 286: 254: 176: 112: 76: 40: 2538:1990JGCD...13..577B 2503:1964AIAAJ...2.1350. 2414: 2359: 2333:{\displaystyle -1} 2330: 2307: 2287: 2249: 2229: 2209: 2104: 1985: 1919: 1678: 1468: 1306: 1141: 1025: 922: 861: 824: 561: 524: 403: 382: 362: 292: 272: 223: 156: 98: 62: 2439: 2438: 2310:{\displaystyle 1} 2198: 2183: 2173: 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Retrieved 2620:(2): 261–280 2617: 2613: 2600: 2583: 2579: 2573: 2564: 2554: 2529: 2525: 2519: 2494: 2491:AIAA Journal 2490: 2484: 2448: 2445:Applications 2440: 2429: 2381: 2370: 2011: 2000: 1966: 1958: 1945: 1934: 1729: 1718: 1712: 1706: 1704: 1693: 1507: 1496: 1494: 1483: 1336: 1321: 1174: 1167: 1156: 1055: 1040: 939: 873: 850: 839: 577: 550: 539: 419: 249: 238: 172: 35: 21:TRIAD method 20: 18: 2586:: 385–386. 2580:SIAM Review 1949:orthonormal 2640:Categories 2476:References 2624:April 18, 2354:± 2348:Δ 2325:− 2281:Γ 2247:Δ 2227:Γ 2196:^ 2187:× 2181:^ 2169:⋮ 2160:^ 2148:⋮ 2139:^ 2122:Δ 2094:^ 2085:× 2079:^ 2067:⋮ 2058:^ 2046:⋮ 2037:^ 2020:Γ 1983:Δ 1974:Γ 1903:^ 1894:× 1888:^ 1876:⋮ 1867:^ 1855:⋮ 1846:^ 1820:^ 1811:× 1805:^ 1793:⋮ 1784:^ 1772:⋮ 1763:^ 1743:^ 1668:^ 1659:× 1653:^ 1641:⋮ 1632:^ 1620:⋮ 1611:^ 1583:^ 1574:× 1568:^ 1556:⋮ 1547:^ 1535:⋮ 1526:^ 1444:→ 1434:× 1422:→ 1391:→ 1381:× 1369:→ 1350:^ 1282:→ 1272:× 1260:→ 1229:→ 1219:× 1207:→ 1188:^ 1117:→ 1087:→ 1069:^ 1001:→ 971:→ 953:^ 911:→ 889:→ 859:⋮ 803:→ 793:× 781:→ 763:⋮ 748:→ 735:⋮ 720:→ 680:→ 670:× 658:→ 640:⋮ 625:→ 612:⋮ 597:→ 508:→ 498:× 486:→ 456:→ 446:× 434:→ 212:→ 187:→ 145:→ 123:→ 87:→ 51:→ 2454:See also 306:, i.e., 282:, where 2534:Bibcode 2499:Bibcode 2012:where 32:Summary 2172:  2166:  2151:  2145:  2070:  2064:  2049:  2043:  1879:  1873:  1858:  1852:  1796:  1790:  1775:  1769:  1644:  1638:  1623:  1617:  1559:  1553:  1538:  1532:  851:where 766:  760:  738:  732:  643:  637:  615:  609:  108:. Let 2610:(PDF) 2114:and 1711:) - ( 2626:2012 1168:and 250:for 72:and 19:The 2588:doi 2542:doi 2507:doi 2317:or 2297:is 372:). 2642:: 2618:41 2616:. 2612:. 2582:. 2563:. 2540:. 2530:13 2528:. 2505:. 2493:. 2432:11 2412:1. 2372:10 2023::= 2003:10 2628:. 2594:. 2590:: 2584:8 2548:. 2544:: 2536:: 2513:. 2509:: 2501:: 2495:2 2434:) 2430:( 2409:= 2405:) 2402:A 2399:( 2395:t 2392:e 2389:d 2357:1 2351:= 2328:1 2305:1 2284:) 2278:( 2274:t 2271:e 2268:d 2207:. 2203:] 2193:m 2178:s 2157:m 2136:s 2129:[ 2125:= 2101:] 2091:M 2076:S 2055:M 2034:S 2027:[ 2005:) 2001:( 1980:A 1977:= 1939:) 1937:9 1935:( 1915:T 1910:] 1900:m 1885:s 1864:m 1843:s 1836:[ 1831:. 1827:] 1817:M 1802:S 1781:M 1760:S 1753:[ 1749:= 1740:A 1720:8 1714:7 1708:4 1698:) 1696:8 1694:( 1675:] 1665:m 1650:s 1629:m 1608:s 1601:[ 1597:A 1594:= 1590:] 1580:M 1565:S 1544:M 1523:S 1516:[ 1498:3 1488:) 1486:7 1484:( 1462:| 1457:| 1451:2 1441:r 1429:1 1419:r 1411:| 1406:| 1398:2 1388:r 1376:1 1366:r 1356:= 1347:m 1326:) 1324:6 1322:( 1300:| 1295:| 1289:2 1279:R 1267:1 1257:R 1249:| 1244:| 1236:2 1226:R 1214:1 1204:R 1194:= 1185:M 1161:) 1159:5 1157:( 1135:| 1130:| 1124:1 1114:r 1106:| 1101:| 1094:1 1084:r 1075:= 1066:s 1045:) 1043:4 1041:( 1019:| 1014:| 1008:1 998:R 990:| 985:| 978:1 968:R 959:= 950:S 918:2 908:r 901:, 896:1 886:r 844:) 842:3 840:( 821:] 816:) 810:2 800:r 788:1 778:r 770:( 755:2 745:r 727:1 717:r 709:[ 705:A 702:= 698:] 693:) 687:2 677:R 665:1 655:R 647:( 632:2 622:R 604:1 594:R 586:[ 559:A 544:) 542:2 540:( 521:) 515:2 505:r 493:1 483:r 475:( 471:A 468:= 463:2 453:R 441:1 431:R 401:A 380:A 360:1 357:+ 354:= 351:) 348:A 345:( 342:t 339:e 336:d 333:, 330:I 327:= 324:A 319:T 315:A 290:A 270:2 267:, 264:1 261:= 258:i 243:) 241:1 239:( 219:i 209:r 202:A 199:= 194:i 184:R 152:2 142:r 135:, 130:1 120:r 94:2 84:R 58:1 48:R

Index

Wahba's problem
orthogonal matrix
3
4
7
8
orthonormal
10
Attitude Dynamics and Control
Orientation (Geometry)
Wahba's problem
Bibcode
1964AIAAJ...2.1350.
doi
10.2514/3.2555
Bibcode
1990JGCD...13..577B
doi
10.2514/3.25373
"Attitude Determination Using Two Vector Measurements"
doi
10.1137/1008080
"Attitude Determination Using Vector Observations: A Fast Optimal Matrix Algorithm"
Categories
Spacecraft attitude control
Rotation in three dimensions

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