Bound-Mass Orbital Drive for Trajectory Change in Gravity
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Solution Overview
Problem
Existing orbital propulsion systems lack an efficient method to modify the trajectory of a spacecraft or payload assembly within gravitational fields, particularly for gaining altitude, changing orbital planes, or manipulating orbital periods.
Innovation Solution
The use of a pair of propellable masses constrained by a binding mechanism, which are cyclically movable in diverging and converging directions, to exert mechanical energy within gravitational fields, thereby altering the trajectory of the spacecraft or payload assembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional orbital propulsion systems are used to modify trajectory, then orbital maneuvers can be achieved, but the systems lack efficiency in gaining altitude, changing orbital planes, or manipulating orbital periods
Solution Approach 1:
The patent applies dynamics by making the mass distribution of the spacecraft dynamic rather than static. The propellable masses are moved to different positions within the spacecraft structure to alter the gravitational deviation of the trajectory. This dynamic reconfiguration allows the same physical structure to perform multiple orbital maneuvers by changing its mass distribution pattern, thereby improving trajectory modification efficiency without additional energy expenditure.
Solution Approach 2:
The patent changes the parameter of spatial mass distribution to achieve trajectory modification. By altering the positions of propellable masses within the spacecraft, the gravitational interaction parameters change, which in turn modifies the orbital trajectory. This parameter change approach enables efficient altitude gain, orbital plane changes, and orbital period manipulation without conventional propulsion energy costs.
2Speed
If masses are separated to gain altitude, then kinetic energy is added to the apparatus, but the gravitational vectors diverge requiring energy investment
Solution Approach 1:
The patent applies self-service by using the spacecraft's own mass distribution to achieve altitude gain without external energy input. The propellable masses are repositioned within the spacecraft structure to create gravitational deviation that naturally propels the spacecraft to higher altitudes. The system serves itself by utilizing its own gravitational interaction with Earth rather than requiring separate propulsion energy.
Solution Approach 2:
The patent employs periodic action through cyclic movement of propellable masses between different positions. The masses are moved to create gravitational deviation for altitude gain, then returned to their original positions to restore the initial state. This periodic reconfiguration allows repeated orbital maneuvers using the same mass elements, achieving sustained altitude adjustments without continuous energy investment.
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 allows for precise control of the spacecraft's trajectory, enabling altitude gain, orbital plane manipulation, and adjustment of orbital periods by altering the spatial distribution of the propellable masses and utilizing gravitational forces effectively.
Implementation Method 1
The use of a pair of propellable masses constrained by a binding mechanism, which are cyclically movable in diverging and converging directions, to exert mechanical energy within gravitational fields, thereby altering the trajectory of the spacecraft or payload assembly.
Data Source
AI summary
An apparatus comprised of positionally directable masses attached to a binding component that includes a coupling device for payload to reduce gravitational deviation of the apparatus' trajectory by alternatingly accelerating and retracting physically bound component masses in equal and opposite directions to the extents of their bindings, initially and optimally perpendicular to the gravitational field and perpendicular to the apparatus trajectory by using in built transduction componentry located within the masses or the binding componentry or both that utilises electromagnetic forces, forces generated by chemical reactions, or other applied or responsive motive force to positionally direct the bound directable masses.