For the EuRoC 2026 competition, Redshift Aerospace initiated Project NOCTURNA, a student-developed experimental launch vehicle designed to carry a 6.5 kg, 5U CubeSat-inspired payload to an altitude of approximately 9,000 meters. The rocket is powered by our custom-developed SRAD solid motor, ALAN-7, developed following an extensive propulsion and structural testing campaign involving multiple aerodynamic and systems-integration iterations. Beyond propulsion performance, the project focuses on avionics reliability, recovery-system autonomy, telemetry infrastructure, and high-speed flight stability throughout subsonic, transonic, and supersonic flight regimes. NOCTURNA also represents an important step in the evolution of Redshift Aerospace into a multidisciplinary aerospace engineering organization bringing together students from multiple universities and technical fields across Transylvania.

For the EuRoC 2026 competition, Redshift Aerospace initiated Project NOCTURNA, a student-developed experimental launch vehicle designed to carry a 6.5 kg, 5U CubeSat-inspired payload to an altitude of approximately 9,000 meters. The rocket is powered by our custom-developed SRAD solid motor, ALAN-7, developed following an extensive propulsion and structural testing campaign involving multiple aerodynamic and systems-integration iterations. Beyond propulsion performance, the project focuses on avionics reliability, recovery-system autonomy, telemetry infrastructure, and high-speed flight stability throughout subsonic, transonic, and supersonic flight regimes. NOCTURNA also represents an important step in the evolution of Redshift Aerospace into a multidisciplinary aerospace engineering organization bringing together students from multiple universities and technical fields across Transylvania.

In this discussion, I would describe the project as the structural and geometric design of a small-scale launch vehicle developed as a three-dimensional CAD model in SolidWorks. The project focuses on a cylindrical rocket body intended for educational or experimental aerospace applications. From the beginning, the design approach emphasizes dimensional accuracy, ease of manufacturing, and compatibility with standardized payload interfaces. From a geometric point of view, the project is based on an axially symmetric cylindrical structure, with a constant external diameter along most of its length. This choice is deliberate, as it supports aerodynamic stability during ascent and helps reduce drag by avoiding sudden changes in cross-section. All dimensions are defined in centimeters, following engineering drawing conventions, and are selected to ensure compatibility with small-scale launch systems and typical competition constraints. Internally, the rocket body is sized to house a modular payload assembly while preserving enough wall thickness to guarantee structural rigidity. The relationship between internal volume and external diameter represents a balance between payload capacity and mechanical strength, allowing the structure to withstand axial loads, vibrations, and short-duration stresses encountered during launch. The SolidWorks model includes multiple orthographic views and a sectional view that clearly show key features such as wall thickness, internal clearances, and interface regions. A detailed, enlarged view is used to highlight areas of mechanical importance, particularly payload retention zones and internal shoulders, where dimensional precision is critical. All dimensions are annotated using consistent tolerancing conventions, making the design suitable for reproducible manufacturing with standard fabrication techniques. The use of explicit decimal tolerances ensures that any deviations introduced during machining or additive manufacturing remain within acceptable limits, maintaining proper alignment between the rocket body and the internal subsystems. Although no specific material is assigned in the project, the geometry is compatible with commonly used aerospace and prototyping materials, including aluminum alloys, composite tubes, and high-strength polymers. The constant cross-section and the absence of complex features make the design appropriate for both subtractive manufacturing and additive processes. Surface finish requirements are intentionally left flexible, allowing post-processing to be adapted to aerodynamic or structural needs, and the overall simplicity supports rapid design iterations in experimental environments. From a systems integration perspective, the rocket body acts as the main structural backbone of the launch vehicle. Its internal dimensions allow payload modules, avionics, and deployment mechanisms to be integrated without extensive secondary structures. The cylindrical form supports concentric stacking of components, which helps distribute loads uniformly along the longitudinal axis. In addition, the lack of external protrusions minimizes aerodynamic disturbances and reduces the risk of asymmetric loading during ascent, an important consideration for small-scale rockets. The project follows standard engineering documentation practices within SolidWorks, including clear use of scales, projection views, and complete dimensional definition. These choices ensure that the design can be interpreted unambiguously by manufacturing personnel or collaborators. Clear guidance on scale usage and the avoidance of manual scaling further reduce the risk of dimensional errors when the drawings are shared or reproduced. Functionally, the rocket structure serves both as a protective enclosure and as a load-bearing element. During ascent, it must resist axial compression from propulsion and bending moments generated by aerodynamic forces. The uniform geometry and centralized mass distribution contribute to predictable structural behavior. At the same time, the internal layout supports reliable payload deployment, ensuring separation without interference from the surrounding structure during critical mission phases. Official blueprint metrics can be referenced within our attached design layouts. Overall, the project defines a structurally efficient and geometrically coherent rocket body suitable for small-scale aerospace missions. Through careful control of dimensions, tolerances, and overall form, the design achieves a balance between simplicity, functionality, and adaptability, providing a solid foundation for experimental launch activities and reliable payload integration.

In this discussion, I would describe the project as the structural and geometric design of a small-scale launch vehicle developed as a three-dimensional CAD model in SolidWorks. The project focuses on a cylindrical rocket body intended for educational or experimental aerospace applications. From the beginning, the design approach emphasizes dimensional accuracy, ease of manufacturing, and compatibility with standardized payload interfaces. From a geometric point of view, the project is based on an axially symmetric cylindrical structure, with a constant external diameter along most of its length. This choice is deliberate, as it supports aerodynamic stability during ascent and helps reduce drag by avoiding sudden changes in cross-section. All dimensions are defined in centimeters, following engineering drawing conventions, and are selected to ensure compatibility with small-scale launch systems and typical competition constraints. Internally, the rocket body is sized to house a modular payload assembly while preserving enough wall thickness to guarantee structural rigidity. The relationship between internal volume and external diameter represents a balance between payload capacity and mechanical strength, allowing the structure to withstand axial loads, vibrations, and short-duration stresses encountered during launch. The SolidWorks model includes multiple orthographic views and a sectional view that clearly show key features such as wall thickness, internal clearances, and interface regions. A detailed, enlarged view is used to highlight areas of mechanical importance, particularly payload retention zones and internal shoulders, where dimensional precision is critical. All dimensions are annotated using consistent tolerancing conventions, making the design suitable for reproducible manufacturing with standard fabrication techniques. The use of explicit decimal tolerances ensures that any deviations introduced during machining or additive manufacturing remain within acceptable limits, maintaining proper alignment between the rocket body and the internal subsystems. Although no specific material is assigned in the project, the geometry is compatible with commonly used aerospace and prototyping materials, including aluminum alloys, composite tubes, and high-strength polymers. The constant cross-section and the absence of complex features make the design appropriate for both subtractive manufacturing and additive processes. Surface finish requirements are intentionally left flexible, allowing post-processing to be adapted to aerodynamic or structural needs, and the overall simplicity supports rapid design iterations in experimental environments. From a systems integration perspective, the rocket body acts as the main structural backbone of the launch vehicle. Its internal dimensions allow payload modules, avionics, and deployment mechanisms to be integrated without extensive secondary structures. The cylindrical form supports concentric stacking of components, which helps distribute loads uniformly along the longitudinal axis. In addition, the lack of external protrusions minimizes aerodynamic disturbances and reduces the risk of asymmetric loading during ascent, an important consideration for small-scale rockets. The project follows standard engineering documentation practices within SolidWorks, including clear use of scales, projection views, and complete dimensional definition. These choices ensure that the design can be interpreted unambiguously by manufacturing personnel or collaborators. Clear guidance on scale usage and the avoidance of manual scaling further reduce the risk of dimensional errors when the drawings are shared or reproduced. Functionally, the rocket structure serves both as a protective enclosure and as a load-bearing element. During ascent, it must resist axial compression from propulsion and bending moments generated by aerodynamic forces. The uniform geometry and centralized mass distribution contribute to predictable structural behavior. At the same time, the internal layout supports reliable payload deployment, ensuring separation without interference from the surrounding structure during critical mission phases. Official blueprint metrics can be referenced within our attached design layouts. Overall, the project defines a structurally efficient and geometrically coherent rocket body suitable for small-scale aerospace missions. Through careful control of dimensions, tolerances, and overall form, the design achieves a balance between simplicity, functionality, and adaptability, providing a solid foundation for experimental launch activities and reliable payload integration.