Ion Blocker Tethered to Spacecraft for Thrust Enhancement
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Solution Overview
Problem
Current spacecraft propulsion systems face challenges in achieving high specific impulse with low mass and low electric power, particularly in Low Earth Orbit (LEO), where chemical rockets require large propellant masses and ion engines have high power requirements and ion self-impingement issues.
Innovation Solution
The implementation of an ion propulsion system with an ion blocker and electrically insulated tethers, where the ion blocker is positioned to capture additional momentum from the ion stream, reducing ion self-impingement and increasing thrust efficiency by deflecting or blocking ions, thereby reducing the mass and power requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If chemical rockets are used for orbit-raising maneuvers in LEO, then large propellant mass is required, but this results in high launch costs
Solution Approach 1:
The invention changes the fundamental parameter of propellant ejection velocity. Instead of using chemical rockets with low exhaust velocity, the system uses an ion propulsion system that accelerates ions to very high velocities (thousands of meters per second). This parameter change in exhaust velocity dramatically increases specific impulse, reducing the required propellant mass by a factor of 10 or more compared to chemical rockets, thereby reducing launch costs.
Solution Approach 2:
The invention replaces the chemical combustion mechanism with an electromagnetic acceleration mechanism. Instead of using chemical energy conversion to propel exhaust, the system uses electric fields and magnetic fields to accelerate ions to high velocities. This substitution of the propulsion mechanism achieves much higher exhaust velocities with significantly reduced propellant mass requirements.
2Quantity of substance
If ion engines are used to achieve high specific impulse, then propellant mass is reduced, but electric power requirements increase
Solution Approach 1:
The invention extracts and utilizes the planet's magnetic field as an external resource to curve the ion beam trajectory. Instead of requiring all energy for both ion acceleration and trajectory control, the system uses the planet's magnetic field to naturally curve the ion path, reducing the energy burden on the onboard power system. The magnetic field acts as a free external resource that assists in achieving the desired ion trajectory.
Solution Approach 2:
The invention introduces an ion blocker as an intermediary component that captures momentum from the ion beam. The ion blocker intercepts ions that have been curved by the magnetic field and transfers their momentum to the spacecraft. This intermediary mechanism allows the system to achieve enhanced thrust efficiency by utilizing the kinetic energy already present in the ion beam, rather than requiring additional power for direct thrust generation.
3Quantity of substance
If ion engines operate in LEO, then high specific impulse is achieved, but ion self-impingement occurs reducing efficiency
Solution Approach 1:
The invention changes the trajectory dimension of the ion beam by utilizing the planet's magnetic field to curve the ion path in three-dimensional space. Instead of ions traveling in a straight line and potentially re-impinging on the spacecraft, the magnetic field curves their trajectory, and the ion blocker is positioned to intercept them at a different spatial location. This dimensional change in ion trajectory prevents self-impingement and improves system reliability.
Solution Approach 2:
The invention extracts ions from the continuous ion beam stream using the ion blocker, which intercepts and removes ions that have been curved by the magnetic field. By taking these ions out of the beam at a controlled location away from the spacecraft, the system prevents them from potentially re-impinging on the spacecraft body, thereby eliminating the self-impingement problem and associated reliability issues.
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 configuration enhances specific impulse, reduces propellant mass, and minimizes ion self-impingement damage, achieving higher thrust efficiency with lower power consumption compared to traditional systems.
Implementation Method 1
a magnetic field to curve the ion beam and transfer momentum to the blocker
Implementation Method 2
The ion blocker may block ions within the ion stream by contacting the ions or deflecting the ions to generate the second propulsive force on the ion blocker
Implementation Method 3
The ion propulsion system may be configured to generate a first propulsive force by emitting a charged ion beam in a direction with an ion velocity vector comprising an ion vector component that is perpendicular to a magnetic field of a planet
Implementation Method 4
A gravitational force of the planet may produce a restoring force on the ion blocker that stabilizes the ion blocker from propulsive forces caused by ions contacting the ion blocker or deflected by the ion blocker
Data Source
AI summary
Provided are various spacecraft propulsion systems, and associated methods of operation. A spacecraft comprises an ion propulsion system and an ion blocker suspended from the spacecraft via one or more electrically insulated tethers. The ion propulsion system is configured to generate a first propulsive force by emitting a charged ion beam in a direction with an ion velocity vector comprising an ion vector component that is perpendicular to a magnetic field of a planet, such as Earth. The magnetic field causes the ion beam to curve toward the ion blocker at a trajectory such that ions within the ion beam are blocked by the ion blocker to generate a second propulsive force on the ion blocker. The ion blocker blocks the ions by contacting or deflecting the ions. The ion blocker is positioned approximately twice the gyroradius of the ion beam trajectory.