Separable Propellant Tank Layout for Upper-Stage Satellite Missions
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Solution Overview
Problem
Existing satellite launch systems face inefficiencies due to the mass of propellant tanks, which cannot be optimized, leading to high structural mass and increased development costs, and lack a structure that integrates the satellite with the upper stage for higher trajectories.
Innovation Solution
A combined launch vehicle and satellite system with in-built tank separation technology that allows the satellite to shed used propellant tanks, utilizing high-accuracy and low-shock mechanisms to reduce mass and enable higher orbits.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If propellant tanks are included in the launch vehicle upper stage, then the propellant capacity is sufficient for deep space missions, but the structural mass increases drastically
Solution Approach 1:
The propellant tanks are divided into multiple separable units that can be jettisoned independently as propellant is consumed. This allows the tank mass to be segmented and discarded in portions, reducing the structural mass carried during different phases of the mission while maintaining sufficient propellant capacity for deep space trajectories.
Solution Approach 2:
The system implements discarding of empty propellant tanks after their propellant is consumed. The tanks are designed to be separated and jettisoned from the upper stage, eliminating the dead weight of empty tanks and reducing the structural mass that would otherwise be carried throughout the entire mission.
2Productivity
If conventional separation systems are used, then the satellite can be deployed from the upper stage, but the development cycle and cost increase
Solution Approach 1:
The satellite deployment function and upper stage propellant tank jettisoning function are merged into a single integrated separation system. This combined approach eliminates the need for separate deployment mechanisms, reducing development complexity and time while maintaining efficient satellite launch capability.
3Device complexity
If tanks are not separated after propellant depletion, then the system structure is simpler, but the mass cannot be optimized for higher trajectories
Solution Approach 1:
The system transitions from a static tank configuration to a dynamic one where tanks are separated based on mission phase and propellant consumption. The separation capability allows the vehicle mass to be dynamically optimized during the mission, enabling higher trajectories by shedding dead weight when and where it is most beneficial.
Data Source
AI summary
A combined launch vehicle and satellite system relates to the satellite combined with the launch vehicle's upper stage to provide a more efficient system that includes tank separation technology which allows the satellite system to shed tanks that have used up all the propellants stored therein. The method separation of the tank set is enabled by using a merman band or pneumatic type of separation system; wherein the three bottom tanks are emptied first during the process, followed by the separation of the emptied tanks herein the fuel is completely filled in the second set of tanks. The first pair of tanks is then separated after the fuel is emptied. Similarly, the plumbing lines are also separated. The separation of the used components is achieved herein and the satellite is ready for orbit insertion.