Spacecraft Transfer Orbit via Multi-Body Dynamics
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Solution Overview
Problem
Traditional orbital transfer methods, such as the Hohmann transfer, require significant fuel expenditure and do not effectively leverage multi-body dynamics, particularly the gravitational interactions between celestial bodies like the Earth and the Sun, to optimize transfer efficiency.
Innovation Solution
The method generates transfer orbits by utilizing multi-body dynamics, specifically the gravitational influences of the Earth and the Sun, to create a transfer trajectory that traverses beyond the final orbit, allowing for efficient inclination changes and reduced fuel requirements by leveraging the Sun's gravitational attraction, using a processor to generate a transfer orbit that defines a continuous trajectory with specific maneuvers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If traditional Hohmann transfer is used, then the transfer orbit remains within the final orbit radius, but the fuel consumption is high and transfer efficiency is low
Solution Approach 1:
The patent extends the transfer orbit beyond the final orbit radius into the third dimension of radial space, allowing the spacecraft to traverse to a radius greater than the final orbit before returning. This dimensional extension enables utilization of solar gravitational influence at larger radii where the Earth's gravitational pull is weaker, thereby reducing the delta-v required for inclination changes and improving transfer efficiency.
Solution Approach 2:
The patent introduces the Sun as an intermediary gravitational body in the transfer process. By leveraging the Sun's gravitational attraction at larger radial distances, the spacecraft can perform inclination changes more efficiently. The Sun acts as a mediator that provides additional gravitational assistance, reducing the fuel consumption compared to traditional Earth-centric transfer methods.
2Use of energy by moving object
If transfer orbit stays within final orbit radius, then the maneuver control is simpler, but the fuel efficiency is reduced
Solution Approach 1:
The patent employs dynamic trajectory adjustment by allowing the transfer orbit to extend beyond the final orbit radius and then return. The spacecraft performs a series of maneuvers including departing the initial orbit, traversing to a larger radius, performing inclination changes, and returning to the final orbit. This dynamic approach optimizes fuel efficiency by leveraging varying gravitational fields at different radial distances.
3Adaptability or versatility
If conventional transfer methods are used, then the trajectory remains simple and contained, but the ability to leverage multi-body dynamics is lost
Solution Approach 1:
The patent changes the orbital parameters by extending the transfer trajectory to radii greater than the final orbit. This parameter change enables the spacecraft to operate in a regime where solar gravitational influence is more significant relative to Earth's gravity, allowing effective utilization of multi-body dynamics. The trajectory complexity increases but is justified by the improved fuel efficiency and ability to perform inclination changes more efficiently.
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 velocity change required for spacecraft transfers, minimizing fuel consumption and enhancing transfer efficiency, enabling the placement of larger or more massive payloads in geostationary orbits with reduced energy expenditure.
Implementation Method 1
leveraging the gravitational attraction of the Sun (or another planet) to reduce the total velocity change required by the satellite
Data Source
AI summary
A method of generating orbital transfers for spacecraft. The method provides an innovative technique for transferring spacecraft from one Earth orbit to another Earth orbit using significant solar gravitational influences. In one particular implementation, the multi-bodies in the transfer determination are the Earth (about which the spacecraft is to orbit) and the Sun (e.g., the Earth and the Sun are the first and second celestial bodies providing multi-body dynamics). The transfer orbit or trajectory is determined to make use of efficient tangential maneuvers by leveraging solar gravitational influences to improve transfer performance. Based on the generated transfer orbit, the spacecraft is controlled to perform one or more maneuvers to achieve a transfer orbit that traverses into a regime where the spacecraft's trajectory is significantly affected by gravity from both the Sun and the Earth. The spacecraft performs a near-tangential orbit insertion maneuver to enter the final orbit.