Contributed to the development of the next generation Moon Lander mission for Moon Rover delivery:• Determined and validated key Lander and Rover design solutions according to the mission plan and payload requirements: spacecraft structural scheme, hardware and payload layout, thermal management, and power systems characteristics; • Implemented custom algorithms that significantly increased the efficiency of the General Design Department in feasibility analysis and expanded the range of spacecraft parameters examined;• Developed versatile MATLAB and Simulink programs for analyzing spacecraft power system working cycles and thermal management system, integrating them with the orbital mechanics model, and developed algorithms for spacecraft dynamics analysis;• Created complex NX 3D models of Moon Lander and Moon Rover as part of their early design phase completion (Phase A);• Through effective communication with other departments, supported the spacecraft requirements management, budgeting, and the development and maintenance of project documentation for the spacecraft systems and subsystems, including payload, guidance, navigation and control, communication, power, thermal management, propulsion systems, structure and mechanisms.Participated in the design of Deep Space Asteroid Monitoring Telescope:• Successfully adapted the complex telescope system (payload) to the existing spacecraft base platform (satellite bus) meeting stringent payload requirements;• Conducted stress calculations for various load cases and modal analyses of the designed adapter to evaluate its eigenfrequencies and ensure compliance with launch vehicle requirements.

• Developed the unique concept of Mars Landing System comprising the Lander and Return Capsule;• Researched existing models of Mars atmosphere and analyzed the atmospheric descent characteristics of landers with four different aerodynamics shapes;• Examined temperature distribution on the Lander’s body during descent, proposed the structure of the heatshield, and estimated its mass characteristics; • Evaluated the mass efficiency and economic outcome of utilizing composite structures in the Lander: carbon fiber adapters, engine frames, anisogrid lattice structures as interbays, and shell structures;• Conducted analytical and finite element structural analyses (static, buckling) of highly loaded elements in MSC Patran/Nastran as part of the preliminary design, verification, and adjustment process: thrust-loaded pressurized aluminum alloy tanks, various composite materials structures;• Created SOLIDWORKS 3D models and AutoCAD drawings of the System parts as a result of its comprehensive analysis and design.