In modern launch vehicles, combined composite structures in the form of thin-walled spherical shells are used as pressure accumulators and tanks. Such balloons consist of an inner metal body (liner), which ensures tightness, and an outer reinforcing composite shell, which ensures the operability of the structure.The paper presents a methodology for the design calculation of a combined composite balloon by using zonal winding on a liner. An analysis of publications on this topic showed that the requirements for the strength and continuity of the tape covering the entire surface of the balloon depend on the tape geometry, its width, thickness, the ultimate strength of the bundle along the fibers, the number of zones and the angular coordinates of the beginning of the zones. The even distribution of the location of the beginning of each zone, accepted by the authors in publications, leads to the need to use an excess number of winding turns to fulfill the strength conditions than is necessary for a continuous coverage of the zone surface.A rational design of the reinforcing composite shell will be in the case when the strength conditions and the conditions of the coating continuity are met in each zone with the same number of required tape turns. The algorithm is based on a sequential calculation of zone parameters. According to the known coordinate of the beginning of the first zone, the required number of turns of the tape is determined, which is necessary to fulfill the condition of the continuity of the coverage of the zone. The strength conditions in the first zone determine the angular coordinate of the beginning of the second zone. The calculation of the parameters of each zone is made taking into account the influence of the value of the width and thickness of the wound tape. Each subsequent zone is determined in the same way, taking into account all the previous zones.The paper compares the results obtained by the proposed method with the results known in the press. The performed numerical experiments showed that the proposed engineering technique allows to reduce the weight of the composite tape by 30%, and the designed spherical shell in this case will be thinner and has a more uniform distribution of the shell thickness along the meridian.
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