Conceptual design and performance analysis of an airborne-launched rocket system

Conceptual design of an air-launched rocket system deployed from a Boeing 747, capable of delivering 250 kg payloads to Low Earth Orbit through a two-stage launcher and a dedicated kick-stage for orbital insertion. The system features an aerodynamic maneuver exploiting initial static instability, thrust vector control for attitude convergence, and a recoverable first stage, enabling a flexible and cost-effective alternative to traditional ground-based launch systems.

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Mirko

Project Timeline

Sep 2024 - Dec-2024

HighlightS

Propulsion System Architecture: Led the engine selection and sizing for a two-stage LOX/RP-1 architecture to optimize the thrust-to-weight ratio specifically for an airborne launch profile
Propellant Tank Sizing & Mass Budgeting: Executed comprehensive geometric sizing of LOX and RP-1 tanks utilizing RPA, determining accurate ullage volumes and structural requirements to support a 22.5-ton total lift-off mass.
Aerodynamic & Stability Modeling: Conducted aerodynamic simulations using Simulink, ensuring positive static margin stability through the trans-sonic and supersonic flight envelopes
Nose Cone Design & Thermal Analysis: Designed a spherical-blunted tangent ogive nose cone to minimize hypersonic drag, and developed a 1D Finite Difference Method (FDM) thermal model to validate that the 0.03 m Thermal Protection System (TPS) successfully maintained the internal aluminum structure below its 660°C limit during peak aerodynamic heating
CAD Modeling & Mass Properties: Developed the 3D CAD model of the launch vehicle to accurately calculate the system's time-varying inertia and Center of Gravity (Cg) as propellant depletes

SKILLS

MATLAB

Simulink

3D CAD (SolidEdge)

RPA

OpenRocket

Hypersonic Aerodynamics

Rocket Static Stability Analysis

Engine Trade Studies

External Links

Project Report

Problem Statement

This study presents the conceptual design and performance analysis of an airborne-launched rocket system deployed from a civil Boeing 747, and able to carry 250 kg of payload to LEO. After release from the carrier aircraft, the launcher enters an unpowered aerodynamic maneuvering phase, exploiting a static unstable system. To converge to optimal attitude, the tail fins are deployed to ensure stability, while thrust vector control (TVC) is employed to dissipate the momentum. Then the vehicle is propelled by two stages to its target altitude, performing the payload orbital insertion through a dedicated kick-stage. The first stage is designed to be recovered using parachutes, highlighting simplicity and cost-effectiveness. This preliminary design offers a promising solution to improve satellite launch accessibility and flexibility, reducing dependence on traditional ground-based systems.

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