Annotation: The problem is defined of designing the space rocket low-pressure air thermostating systems joints. The basic requirements imposed to the joints from the side of space rocket and ground complex are determined and stated. For this purpose, the analysis of operating conditions and possible situations during rocket launches is made. Besides, the methodological principles based on problematic, systematic, and structuralfunctional approach were applied using the theoretical and empirical capabilities, attraction of general scientific and special investigation methods, as well as historical and logical methods. The list of topical issues is reflected for implementation in joint’s design. The ways are proposed to create the joints meeting the requirements imposed. As a result, it was ascertained that the joints can be made of simpler and at the same time failure-free design in the form of combined triune rubber hose fitted with a metal fixation/release unit installed on a sealing flange in a special groove. Of special note is the versatility of the proposed technical solution for use in any of the space launch systems known in the world’s practice. The article is concluded with following: the basic requirements have been formulated for ground complexes thermostating systems joints to ensure space rockets prelaunch processing and launch, in doing so, the topical problems were defined; the scientific principles were proposed to design the thermostating systems joints for comprehensive solution of the topical problems , including potential critical situations; the thermostating systems joints have been developed, manufactured and have successfully passed the ground development tests with simulation of the conditions maximally close to operating ones at static operating air pressures and in off-nominal situations.

Annotation: The conceptual engineering solution was examined to increase the unification and interchangeability of components in a vehicle that can regularly transport cargo and be operationally adapted to solving various problems on the surface of different planets. The difference between this engineering solution and the existing designs of planetary roving vehicles was described. The objective is achieved by assembling a selfpropelled modular platform from generic modules that are rigidly joined with each other to create a unified control system and a unified power supply system for the platform. The number of modules is chosen depending on the objective and equipment installed on the platform. Self-propelled modular platform can function as a unified remote-controlled unit with capability to adapt operationally to solving new problems on the surface of various planets. Novelty of the modular vehicle concept lies in creation of the generic vehicle that is capable of being rebuilt depending on the functional task and can be delivered by parts to the site of its direct operation.