External Umbilical Fuel Supply for Rocket Ascent
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Solution Overview
Problem
Current rocket delivery systems face challenges in reducing cost per unit mass and require large, heavy rockets due to the need for extensive fuel and oxidant onboard, which limits payload capacity and increases energy expenditure during liftoff.
Innovation Solution
The method involves using external umbilical tubes connected to ground-based or airborne auxiliary tanks containing fuel and oxidant, which supply propellants to the rocket during liftoff and ascent, allowing for smaller internal tanks and increased payload capacity, with umbilicals automatically disconnecting at predetermined altitudes and speeds.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a rocket carries extensive fuel and oxidant onboard, then it can achieve sufficient thrust for liftoff and ascent, but the rocket becomes large and heavy, limiting payload capacity and increasing energy expenditure
Solution Approach 1:
The fuel and oxidant supply system is segmented into onboard internal tanks and external auxiliary tanks. The external tanks are positioned around the launch pad and connected to the rocket via umbilical tubes, allowing the rocket to receive propellants during ascent without carrying all fuel onboard from the start.
Solution Approach 2:
Umbilical tubes serve as intermediaries to transfer fuel and oxidant from external auxiliary tanks to the rocket's internal tanks during liftoff and ascent. This mediator system enables continuous propellant supply without requiring the rocket to carry all fuel onboard, reducing initial mass.
2Force
If a rocket carries extensive fuel and oxidant onboard, then it can achieve sufficient thrust for liftoff and ascent, but the payload capacity decreases due to increased mass
Solution Approach 1:
By segmenting the propellant supply between onboard and external sources, the rocket can maintain sufficient thrust for liftoff while reducing the mass of fuel and oxidant carried onboard, thereby increasing payload capacity.
Solution Approach 2:
Fuel and oxidant are pre-positioned in external auxiliary tanks at the launch pad. During ascent, these external tanks continuously supply propellants to the rocket, ensuring sufficient thrust is maintained without requiring the rocket to carry all fuel from the start, thus freeing up mass for payload.
3Use of energy by moving object
If ground-based or airborne systems are used to impart energy to the rocket at liftoff, then the delivery cost can be reduced, but excessive G-force is generated to personnel and equipment
Solution Approach 1:
The external auxiliary tanks are pre-positioned and begin supplying fuel and oxidant to the rocket at the start of ascent. This continuous propellant supply enables efficient combustion and thrust generation without requiring extreme acceleration forces, thereby reducing harmful G-force effects on personnel and equipment.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach enables a lighter, more efficient rocket design that uses less fuel, reducing the energy required for liftoff and allowing for a greater payload capacity while minimizing drag and G-force on personnel and equipment.
Implementation Method 1
rockets are primarily powered by chemical, nuclear, and/or ground-based projected energy sources, with chemical propellants being the most popular
Data Source
AI summary
A system for providing fuel and oxidant to a rocket in flight, including a rocket having at least one internal tank for storing propellant, at least one external tank for holding a liquid rocket propellant, and at least one umbilical hose in fluidic communication with the at least one internal tank and the at least one external tank. The at least one umbilical hose is configured to automatically disengage from the rocket when the rocket reaches a predetermined state such as a predetermined altitude, for example. The at least one internal tank remains in fluidic communication with the at least one external tank while the at least one umbilical hose is engaged.