Submit your rocket part or vehicle concept. Our design team reviews it, understands the requirements, and delivers a complete redesign.
Submit a design How rockets are designedHinson11 Aerospace is a team of rocket designers. We take existing concepts and part designs, analyze them, and produce professional redesigns on a defined timeline and price basis.
Submit a rocket component — engine, tank, nozzle, structure, or subsystem. We analyze performance, manufacturability, and integration, then deliver a revised design.
Submit a complete vehicle concept. We review staging, propulsion architecture, mass budgets, and systems, then produce a coherent full-stack redesign.
Typical redesign cycles run over a few months depending on scope. Pricing is determined after initial review of the submitted design and requirements.
A clear path from submission to delivered redesign.
Send your rocket part or vehicle concept through the form. Include drawings, descriptions, performance targets, and any constraints.
Our design team studies the submission, identifies issues and opportunities, and defines the redesign scope.
You receive a timeline and price based on complexity. Work begins after agreement.
Within the agreed period — typically a few months — you receive the redesigned part or vehicle with documentation.
A structured overview of the full design process used for launch vehicles.
Every rocket design begins with the mission. Payload mass, target orbit or trajectory, launch site constraints, and operational requirements define the performance envelope.
Key parameters established at this stage include required delta-v, maximum acceleration limits, fairing volume, and reliability targets. These drive all subsequent decisions on staging, propulsion, and structure.
With requirements fixed, the vehicle architecture is selected. Number of stages, propellant types, and engine configuration are chosen to meet the delta-v budget at an acceptable mass fraction.
Propulsion is the central driver. Liquid bipropellant engines, solid motors, or hybrids are selected based on specific impulse, thrust level, throttle needs, and operational constraints. Engine cycle and cooling method are defined early because they shape the rest of the vehicle.
Primary structures and propellant tanks are sized to carry flight loads while maximizing mass fraction. Tank architecture, material selection, and interstage design are developed together with propulsion interfaces.
Avionics, guidance, thrust vector control, and thermal management are integrated in parallel. Separation systems, fairings, and ground interfaces complete the vehicle definition. All interfaces are controlled so that subsystems remain compatible as the design matures.
The complete vehicle is assembled in a coherent 3D design. Loads analysis, thermal analysis, trajectory simulation, and mass tracking are run continuously. Discrepancies between performance predictions and requirements drive design changes.
Manufacturability, assembly sequence, and test approach are considered throughout. The goal is a vehicle that meets mission requirements, can be produced, and can be verified through analysis and ground testing before flight.
Send your rocket part or vehicle concept. The team will review it and respond with scope, timeline, and pricing.
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