This design proposes a cost-effective, reusable satellite launch system that combines a high-altitude balloon lift (rockoon) with a novel oblique-wing first stage and skip re-entry procedure to overcome the prohibitive costs, slow turnaround times, and infrastructure demands of traditional rockets. The system lifts a 36–40 metric ton vehicle via ten balloons to 36 km, avoiding dense atmospheric drag, which reduces propellant mass and enables lighter, more efficient designs. The first-stage solid boosters use an APHP and magnesium diboride propellant blend, proven to increase energy release by 78%,and after separation, they perform skip re-entry and pivot their oblique wings from a hypersonic narrow profile to a subsonic high-lift configuration, enabling precise runway landings like conventional aircraft. The core tow-vehicle then ignites its hydrolox or tripropellant engine to deliver a 150–250 kg satellite to low Earth orbit, after which it too executes skip re-entry and is recovered via parachute and mid-air retrieval. Navigation and attitude control rely on a redundant "4-stack" system comprising GPS, laser gyroscopes, star trackers, magnetorquers, a ferrofluid system, and a reaction sphere, while thermal protection uses flight-proven AVCOAT/PICA coatings augmented by regenerative cooling through propellant channels.

The system achieves a per-kilogram launch cost of $1,500–$2,000,undercutting SpaceX's small-satellite rideshare price by 45–75%,with a remarkable four-day refurbishment turnaround and major components rated for up to 50 reuse cycles, far surpassing current industry benchmarks. Environmentally, stratospheric ignition eliminates ground-level noise and tropospheric emissions, while the solid boosters burn more completely and the hydrolox option produces only water vapor. Technologically, every subsystem rests on proven or near-term advancements with novel applications only where necessary: rockoon concepts have flown since the 1950s, China's Honghu balloons already lift 3.6 tons to 36 km, the MgB₂ additive is experimentally validated, and standard De Laval nozzles ensure manufacturing simplicity.

The oblique wing has undergone extensive wind-tunnel and CFD validation, and mid-air retrieval is demonstrated by existing military and NASA operations. By removing the need for large launch pads, blast zones, drone ships, and saltwater-prone sea recovery, this modular, scalable architecture dramatically lowers financial barriers for small-to-medium enterprises and research groups, enabling dedicated small-satellite launches with unprecedented operational agility, minimal environmental impact, and a credible five-to-seven-year development timeline.

Provided illustrations represent basic conceptual CAD models, of the Core Adapter assembly, the first stage and finally the complete pre-launch assembly. The core adapter connects to the high altitude balloons and to the first stages as well as the main tow vehicle. The first stage is represented with the main oblique wing in blue, whilst the final complete assembly functions as follows: Complete assembly is lifted to 36 Kilometers after which all first stages ignite and reach higher altitude and gain velocity. At near-depletion fuel levels, all first stages jettison from the core tow vehicle and pursue Independent re-entry trajectories. The core tow vehicle ignites its engines and reaches orbital velocity, depositing its payload to orbit. The core vehicle now begins the re-entry procedure and is recovered.