Multidisciplinary design optimization of solid-fueled multistage space launch vehicles requires complex highdimensional simulation models. To improve on the ability to efficiently explore and approximate large subspaces of these models, this research develops a new set of experimental designs for metamodeling with support vector regression. We propose to Latinize and improve the orthogonality of Hammersley sequence sampling for creating nearly orthogonal and excellent space-filling designs. Multiple measures are used to assess the quality of designed experiments. The designs are used to create metamodels of trajectory simulation of space launch vehicles using support vector regression. A hybrid genetic algorithm uses metamodels to identify minimum-launch-weight space launch vehicles. This approach resulted in an overall rapid and efficient design optimization scheme. Nomenclature A e = nozzle exit area, m 2 A t = nozzle throat area, m 2 A = inlet area ratio of the nozzle, A inlet =A throat Al = percentage of aluminum powder in the grain C = rank correlation matrix of W, penalty parameter of the error term C f = coefficient of thrust C = characteristic velocity, m=s D = diameter of the rocket motor, m d = Euclidean distance d t = nozzle throat diameter, cm F i = thrust of the ith stage, N H = Hadamard matrix I sp = specific impulse I o1 sp = ground specific impulse I vac sp = vacuum specific impulse K = kernel function k = number of factors or variables k s = propellant-grain-shape coefficient L = stage length, m L gi = grain length, m M = dimension of samples (number of variables) ML 2 = modified L 2 discrepancy m api = attachment-part mass of the ith stage, kg m cabi = cable mass of the ith stage, kg m cyi = motor cylinder mass of the ith stage, kg m c1 , m c2 = motor dome-ends mass, kg m gni = propellant mass of the ith stage, kg _ m gni = grain-mass-consumption rate of the ith stage, kg=s m ig = ignitor mass, kg m in;cyi = cylindrical-section insulation-liner mass, kg m in;c1 , m in;c2 = fore and aft insulation-liner mass, kg m j2i = aft attachment mass of the ith stage, kg m noz;ec = nozzle expansion-cone mass, kg m noz;in = nozzle insulation mass, kg m noz;sh = nozzle spherical-head mass, kg m qi = fore and aft skirt mass of the ith stage, kg m stri = structure mass of the ith stage, kg m TVC = thrust-vector-control mass, kg m 01 = takeoff mass of the space launch vehicle, kg m 0i1 = takeoff mass of the upper-stage rocket, kg N = number of samples or number of points in the design matrix, number of stages n = number of runs, number of levels p = integer number p c = chamber pressure of the rocket motor, bar p e= nozzle-exit-plane pressure, bar p h = atmospheric pressure at height h p 0 = atmospheric pressure on the ground Q = lower triangular matrix of size k k R = radix notation R c = gas constant, J=kg mol K R sub = submerged ratio of the nozzle, l sub =l nozzle R u = curative radius of the nozzle, mm r = kernel parameter S ri = burning surface area of the ith stage, m 2 T c = temperature in the combustion...