Spacecraft Continuous Propulsion Payload Ejection
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Solution Overview
Problem
Existing spacecraft propulsion methods by intermittence lead to increased propellant consumption, complexity in trajectory prediction, and higher system activation/deactivation cycles, posing challenges in preventing payload collisions and optimizing orbital maneuvers.
Innovation Solution
A method employing continuous propulsion force to eject payloads, where the spacecraft is driven by a continuous propulsion force relative to the celestial body, reducing the need for frequent engine ignition and maintaining propellant at the bottom of the tank, thus minimizing consumption and collision risks.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If propulsion by intermittence is used to eject payloads, then collision prevention between payloads and spacecraft is achieved, but propellant consumption increases
Solution Approach 1:
The patent applies continuous propulsion instead of intermittent propulsion to maintain the spacecraft's orbit during payload ejection. The propulsion system operates continuously to provide constant orbital maintenance, eliminating the need to reignite engines after ballistic phases, thereby reducing propellant consumption while still preventing collisions through continuous trajectory control
2Reliability
If propulsion by intermittence is used to eject payloads, then collision prevention is achieved, but trajectory complexity increases
Solution Approach 1:
By maintaining continuous propulsion, the spacecraft follows a more predictable and simpler trajectory compared to intermittent propulsion with ballistic phases. The continuous thrust provides steady orbital maintenance, eliminating complex trajectory calculations required for reignition and ballistic coasting phases
3Reliability
If propulsion by intermittence is used to eject payloads, then collision prevention is achieved, but system activation and deactivation cycles increase
Solution Approach 1:
The continuous propulsion system eliminates repeated activation and deactivation cycles of the propulsion system. The engine operates continuously throughout the payload ejection process, removing the need for multiple ignition and shutdown sequences required by intermittent propulsion methods
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 propellant consumption, simplifies trajectory management, and prevents payload collisions by maintaining continuous propulsion during ejection, ensuring efficient and safe orbital deployment of satellites.
Implementation Method 1
The spacecraft (1) is driven by a continuous propulsion force with respect to the celestial body around which it is in orbit, in addition to the force of gravity
Data Source
AI summary
An ejection method (100) for ejecting at least one payload such as a satellite. The ejection method includes a step (108) of ejecting the payload from a spacecraft that is driven by a continuous propulsion force when the satellite is ejected.