Three-Point Propulsion System for Orbital Modules
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Solution Overview
Problem
Existing space propulsion systems for orbital deployment modules are bulky and costly, with four-point architectures being inefficient for precise directional control and requiring complex control logic.
Innovation Solution
A three-point propulsion system with a chassis having three housings for propulsion units and one for a fuel tank, using a control unit to manage the supply and power of each propulsion unit, and incorporating auxiliary thrusters for temperature stabilization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a four-point propulsion architecture is used, then control simplicity is improved, but directional precision and propulsion efficiency deteriorate
Solution Approach 1:
The propulsion system is segmented into three independent propulsion units distributed at vertices of an equilateral triangle, each capable of independent thrust generation. This segmentation allows precise control of the resultant thrust vector by independently modulating each unit's contribution, achieving both control simplicity and directional precision through modular architecture.
Solution Approach 2:
The patent transitions from a two-dimensional planar thruster distribution (four points on a square/rectangle) to a three-dimensional spatial arrangement (three points forming an equilateral triangle in a plane perpendicular to the main propulsion axis). This dimensional reconfiguration enables precise directional control along the main axis while maintaining control simplicity through symmetric geometry.
2Volume of moving object
If a three-point propulsion system is used, then bulk and cost are reduced, but control logic complexity increases
Solution Approach 1:
While the overall geometry is symmetric (equilateral triangle), the control logic employs asymmetric thrust distribution strategies where individual propulsion units can operate at different thrust levels. This controlled asymmetry in thrust allocation enables complex maneuvers and precise directional control despite the simplified three-point mechanical architecture, resolving the apparent contradiction between reduced bulk and increased control complexity.
Solution Approach 2:
Each of the three propulsion units is designed as a universal, multi-functional element capable of providing thrust in any required direction through vector control. This universality allows the same three units to handle all propulsion needs (main propulsion, attitude control, maneuvering) without requiring additional specialized components, thereby reducing bulk while managing control complexity through software-based thrust vectoring.
3Ease of manufacture
If four propulsion points are distributed across corners, then load distribution is simplified, but space utilization and capacity are reduced
Solution Approach 1:
The propulsion system is segmented into three compact units positioned at the vertices of an equilateral triangle, minimizing the footprint required for propulsion components. This segmentation allows optimal space utilization within the orbital module while maintaining effective load distribution through the symmetric triangular configuration, which naturally balances forces and moments.
Solution Approach 2:
The propulsion units are arranged in a plane perpendicular to the main propulsion axis (transverse plane), rather than distributing them along the longitudinal axis at four corners. This dimensional reconfiguration projects the propulsion system into a different spatial dimension, achieving excellent load distribution through the equilateral triangle's geometric properties while maximizing the available volume for satellite housing and other payloads along the main axis.
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 three-point propulsion system reduces bulk and cost while simplifying control logic, allowing for efficient directional control and increased capacity for satellite housing.
Implementation Method 1
each propulsion unit including at least one thruster
Implementation Method 2
a control unit configured to control the supply and the power developed by each of the propulsion units
Data Source
AI summary
A three-point propulsion system of an orbital deployment space module for at least one satellite including: chassis including exactly three first housings shaped to each receive a propulsion unit and at least one second housing shaped to receive a tank, at least one liquid fuel tank disposed in a second housing, and exactly three propulsion units, each propulsion unit being disposed in one of the first housings, and each propulsion unit including at least one thruster.