Utilizing air-turborocket and rocket propulsion for a single-stage-to-orbit vehicle

Dry weights for single-stage launch vehicles that incorporate nontangent, developed contour bulkheads are estimated and compared to a baseline vehicle with 1.414 aspect ratio ellipsoidal bulkheads. Weights, volumes, and heights of optimized bulkhead designs are computed using a preliminary design bulkhead analysis code. The dry weights of vehicles that incorporate the optimized bulkheads are predicted using a vehicle weights and sizing code. Two optimization approaches are employed. A structural-level method, where the vehicle's three major bulkhead regions are optimized separately and then incorporated into a model for computation of the vehicle dry weight, predicts a reduction of 4365 Ib (2.2%) from the 200,679-1b baseline vehicle dry weight. In the second, vehicle-level, approach, the vehicle dry weight is the objective function for the optimization. For the vehicle-level analysis, modified bulkhead designs are analyzed and incorporated into the weights model for computation of a dry weight. The optimizer simultaneously manipulates design variables for all three bulkheads to reduce the dry weight. The vehiclelevel analysis predicts a dry weight reduction of 5129 Ib, a 2.6% reduction from the baseline weight. Based on these results, nontangent, developed contour bulkheads may provide substantial weight savings for single stage vehicles. RIIR2 r Nomenclature= ratio of the local circumferential and meridional radii of curvature = normalized radius

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Utilizing air-turborocket and rocket propulsion for a single-stage-to-orbit vehicle

Cited by 10 publications

References 1 publication

Operation matching model and analysis between an air inlet and a compressor in an Air Turbo Rocket

Operation matching model and analysis between an air inlet and a compressor in an Air Turbo Rocket

Design Optimization on Cost Basis Using Orthogonal Arrays

Nontangent, Developed Contour Bulkheads for a Single-Stage Launch Vehicle

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