Wahba's problem was published in 1965, SIAM Review, Vol 7, No 3.
Wabha's problem in short is determining ones (the body's) attitude using a number or co-registered vectors in a reference frame and observation vectors in body coordinates.
Basically the problem is minimizing the following cost function to get R, the rotation matrix (or attitude quaternion):
L = 0.5 SUM a_i (b_i - R r_i)^2
a_i - is the weights (a in the code)
b_i - observations in body coordinates (rb in the code)
r_i - known database of co-registered datapoints in a reference coordinates (rr in the code)
the above is equivalent to solving in quaternion from:
L = lambda_0 - trace(RB) = lambda_0 - q' K q
q - is the attitude quaternion; and
K - is calculated as below
Please follow the code. You will see the Equations were simply implemented as in the article.
There is one change however, the author
preferred using Zipfel's order for the quaternion representation, thus:
q = [ q0 q1 q2 q3 ] = [ cos (the/2) e(1)sin(the/2) e(1)sin(the/2) e(1)sin(the/2) ]
Note that Body orientations can similarly be found with Gupta's 1998 method or
by simply co-registering a known star-database distance matrix based on observed
angular-distances. Note that Gupta's work seems to be based on Hyslop 1987 work.
The main source document used was "Humble Problems" by F. Landis Markley - 2006. It was freely downloadable at the time of writing from: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20060012294_2006013132.pdf
See also Julian Balfour's work in on three-point tracking (basically a
distance matrix traversing method).
Note that to turn points the Tensor R is transpose(dcm) if you are using an allowable coordinate system. See the 1st or 2nd Edition of "Modeling and Simulation of Aerospace Vehicle Dynamics" - Zipfel.