Kinetic Energy Storage Tether for Orbital Momentum Transfer
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Solution Overview
Problem
Current space transportation systems face inefficiencies in placing satellites in orbit due to high costs and limitations in specific impulse and thrust potential, with existing tether-based systems like rotorvators being complex and difficult to implement.
Innovation Solution
A Kinetic Energy Storage and Transfer (KEST) vehicle system with a tether that includes a contact mechanism and beacon signal for precise positioning and linear momentum transfer to a target space vehicle, allowing for efficient acceleration into higher orbits using a catching mechanism and retrieval mechanism like a robotic arm.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If rocket propulsion is used to accelerate spacecraft to orbital velocity, then the spacecraft can reach orbit, but the specific impulse is limited to approximately 450 seconds requiring large vehicle size
Solution Approach 1:
The patent introduces an intermediary mechanism (tether system or external propulsion assistance) to transfer momentum to the spacecraft, allowing the spacecraft itself to use high Isp electric propulsion while an external system provides the heavy lifting for orbital insertion, thus resolving the contradiction between thrust capability and energy efficiency
Solution Approach 2:
The patent combines electric propulsion systems (high Isp) with mechanical momentum transfer systems (high thrust) into a hybrid architecture, where the electric propulsion handles station-keeping and orbital adjustments while the mechanical system provides the bulk acceleration, achieving both high thrust and high energy efficiency
2Use of energy by moving object
If electric propulsion is used to achieve higher specific impulse, then fuel efficiency improves, but thrust becomes considerably lower preventing direct ascent
Solution Approach 1:
The patent segments the propulsion function into two parts: an external high-thrust system (rocket or mechanical momentum transfer) for ascent and orbital insertion, and an onboard high-Isp electric propulsion system for subsequent orbital adjustments and station-keeping, allowing each system to operate in its optimal performance regime
Solution Approach 2:
The patent applies preliminary action by using an external high-thrust system to first insert the spacecraft into orbit, after which the high-Isp electric propulsion system takes over for efficiency-critical maneuvers, thus avoiding the need for the electric propulsion system to perform the high-thrust ascent maneuver
3Productivity
If rotorvator tether system is used to propel payload into higher orbit, then momentum transfer efficiency improves, but system complexity increases significantly
Solution Approach 1:
The patent extracts the momentum transfer function from the complex rotating rotorvator system and implements it through simpler mechanisms such as linear tethers with pulley systems or direct gravitational assist maneuvers, maintaining momentum transfer efficiency while eliminating the need for massive rotating structures and complex synchronization systems
Solution Approach 2:
The patent inverts the traditional rotorvator approach by having the tether system remain relatively stationary or move minimally while the spacecraft performs the active maneuvering to engage and disengage from the tether, reversing the roles of active and passive elements and thereby reducing the complexity of the tether system itself
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
The system enables efficient and cost-effective insertion of satellites into higher orbits by transferring linear momentum from the tether to the target vehicle, overcoming the limitations of traditional propulsion systems and simplifying the complexity of rotorvator systems.
Implementation Method 1
a tether that is configured to impart a linear momentum transfer from the tether to the target space vehicle
Data Source
AI summary
A system for imparting linear momentum transfer may include a catching mechanism of a target space vehicle and a tether that is configured to impart a linear momentum transfer from the tether to the target space vehicle. The tether may be fixedly or detachably connected to a Kinetic Energy Storage and Transfer (KEST) vehicle that maneuvers and potentially retrieves the tether. Alternatively, the tether may be separate from the KEST vehicle and may be retrieved by a suitable retrieving mechanism, such as a robotic arm.