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b2864355b0
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| b2864355b0 | |||
| ce8ef142b4 |
@ -33,6 +33,6 @@
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"useInternalPlugins": false
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},
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"InterestingStuffs": "LiCoffee",
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"力学书籍": "📚",
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"补课": "🧑🏫"
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"补课": "🧑🏫",
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"书籍/力学书籍": "📚"
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}
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BIN
书籍/其他/engineering design optimization.pdf
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@ -20,21 +20,21 @@ $$
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where $\left[\varSigma\right]$ is a diagonal matrix containing the singular values of $[A]$ , which are $\sqrt{e i g e n\nu a l u e s\;o f\left[A\right]\left[A\right]^{T}}\;=\sqrt{e i g e n\nu a l u e s\;o f\left[A\right]^{T}\left[A\right]}\;.$
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This was derived symbolically by J. Jonkman by computing $\left[U\right]\!\!\left[V\right]^{T}$ by hand with verification in Mathematica.
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Tower Base / Platform Coordinate System
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Tower Element-Fixed Coordinate System
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Tower-Top / Base Plate Coordinate System
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Nacelle / Yaw Coordinate System${\pmb d}_{t}$ cos (qYaw) 0 −sin (qYaw) b${\pmb d}_{2}$ 0 1 0 b${\pmb d}_{3}$ sin (qYaw) 0 cos (qYaw) b
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@ -74,7 +74,7 @@ The equation for $i^{B2}$ is similar.
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Blade / Pitched Coordinate System
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The equation for $j^{B2}$ is similar.
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@ -94,26 +94,26 @@ $$
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where,
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The equation for ${\pmb n}^{B2}(r)$ is similar.
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Blade Element-Fixed Coordinate System Used for Calculating and Returning Aerodynamic Loads This coordinate system is coincident with $i^{B I}$ when the blade is undeflected.
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The equation for $m^{B2}(r)$ is similar.
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Blade Element-Fixed Coordinate System Aligned with Local Aerodynamic Axes (i.e., chordline) / Trailing Edge Coordinate System
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The equation for $t e^{B2}(r)$ is similar.
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Tail-Furl Coordinate System
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Tail Fin Coordinate System
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@ -1,12 +1,12 @@
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There are several points on a 2-bladed turbine: Z (platform reference), Y (platform mass center), T (tower node), O (tower-top / base-plate / yaw bearing mass center), U (nacelle mass center), V (arbitrary point on rotor-furl axis), W (arbitrary point on tail-furl axis), D (center of mass of structure that furls with the rotor [not including rotor]), IMU (nacelle inertial measurement unit), P (teeter pin), SG [shaft strain gage location: i.e., a point on the shaft a distance ShftGagL towards the nacelle from point P (or point Q for a 3-blader since point P does not exist)], Q (apex of coning angle), C (hub mass center), S1 (blade node for blade 1), S2 (blade node for blade 2), I (tail boom mass center), J (tail fin mass center), and K (tail fin center-of-pressure). There are also several reference frames: E (earth / inertial), X (platform / tower base), F (tower element body), B (tower-top / base plate), N (nacelle), R (structure that furls with the rotor—generator housing, etc…), L (low speed shaft on rotor end of LSS-compliance), H (hub / rotor), M1 (blade 1 element body), M2 (blade 2 element body), G (fixed in the high speed shaft / generator), and A (tail). The following are derivations of the position vectors, angular velocities, linear velocities, partial angular velocities, partial linear velocities, angular accelerations, and linear accelerations of all these points on the 2-bladed turbine (point SG’s velocities and accelerations are not derived since they wont be used in the ensuing analysis). The velocities and accelerations of points on a 3-bladed turbine are very similar.
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ZO =[qTFA1+qTFA2]a1 + Ptfm Re f+TowerHt 21S1T1F+A(S1TT1SwSr(FTlwerxFLl) eqxT2LFA) 1qT+2SSS12T2F+AS(2TT2SSw(rTFlwerxFLl) exqT2LF) A2qT2+SS 22S+1T2F2AS(1T2TSSw(rTFwlerxFLle) xqLTF) A1qTqSTSF1Aq2TSS 2 u +[qTSS1+qTSS 2]a3
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OU =NacCMxnd1+NacCMznd2−NacCMynd3 rVD=(RFrlCMxn−RFrlPntxn)rf1+(RFrlCMzn−RFrlPntzn)rf2−(RFrlCMyn−RFrlPntyn)rf3 rVIMU= $\big(N c I M U x n-R F r l P n t x n\big)r f_{I}+\big(N c I M U z n-R F r l P n t z n\big)r f_{J}-\big(N c I M U y n-R F r l P n t y n+R F r l P n t z n\big)$ )rf3 rVP= −RFrlPntxnrf1+(Twr2Shft−RFrlPntzn)rf2−(Yaw2Shft−RFrlPntyn)rf3+OverHangc1
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PSG = ShftGagLc
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