Two-Orbiter Fuel Segmentation for Interplanetary Missions
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Solution Overview
Problem
The significant weight of fuel required for interplanetary missions leads to exponential fuel consumption and increased costs due to the 'snowball' effect, and existing aero-thermo-dynamic passive re-entry capsules pose risks to the terrestrial environment during return journeys.
Innovation Solution
A method involving two orbiter spacecraft on separate trajectories, with one spacecraft launching to a rendezvous spot and the other taking over to complete the mission, utilizing gravitational assistance to minimize fuel weight, and allowing for fuel transfer and docking to reduce overall fuel load.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single orbiter spacecraft carries all fuel for the complete interplanetary mission, then the mission can be accomplished, but the fuel weight becomes extremely large due to the snowball effect
Solution Approach 1:
The mission is divided into two separate orbiter spacecraft, each carrying fuel for only a portion of the journey. The first orbiter carries fuel from Earth to the target planet, while the second orbiter carries fuel from the target planet back to Earth. This segmentation eliminates the need to carry all fuel for the complete round trip in a single vehicle, dramatically reducing the fuel weight required for each spacecraft.
2Use of energy by moving object
If a passive re-entry capsule is used for return to Earth, then the last braking phase can be circumvented, but risks to the terrestrial environment are created
Solution Approach 1:
The invention introduces an active orbiter spacecraft as an intermediary vehicle for the return journey, replacing the passive re-entry capsule. This active orbiter uses controlled propulsion to perform braking maneuvers, allowing for precise and safe return of samples to Earth without the uncontrolled risks associated with passive atmospheric re-entry.
3Quantity of substance
If larger rockets are used to carry more fuel, then the fuel weight requirement can be met, but the cost and size of the launcher increase
Solution Approach 1:
The total fuel requirement is segmented between two separate launch missions. Each rocket only needs to carry fuel for a one-way journey rather than the complete round trip, allowing the use of smaller, more cost-effective launch vehicles. This segmentation makes the mission economically viable by avoiding the need for extremely large and expensive heavy-lift rockets.
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 reduces the total fuel weight carried, decreases mission costs, and avoids risks to the terrestrial environment by optimizing fuel distribution and using smaller, less expensive rockets, while ensuring efficient return trajectories.
Implementation Method 1
the method furthermore consists in using at least one gravitational assistance of a planet or of a moon situated on the second interplanetary trajectory to further decrease the weight of fuel necessary for the accomplishment of the mission
Data Source
AI summary
The method for lightening the weight of fuel stowed onboard during an interplanetary mission is characterized in that it consists:in launching (10a) a first orbiter spacecraft (1) from the Earth on a first interplanetary trajectory (31, 33) towards a target planet to be explored,in launching (10b) a second orbiter spacecraft (2) from the Earth on a second interplanetary trajectory (32, 34) towards a rendezvous spot (38), the second interplanetary trajectory not comprising any phase of placing in orbit around the target planet,in recovering a load to be transported and in loading it onto the first orbiter spacecraft (1),in returning the first orbiter spacecraft (1) and the load from the target planet to the rendezvous spot (38),in effecting a docking (14) of the two orbiter spacecraft (1, 2),in returning at least the second orbiter spacecraft (2) and the load, from the rendezvous spot (38) to a terrestrial orbit (41).