Ablative Thrust Deflector for Passive Satellite Deorbit Vectoring
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Solution Overview
Problem
Small satellites face challenges in deorbiting due to alignment issues with ammonium perchlorate composite propellant motors, buildup of alumina slag in nozzles, and lack of active thrust vector control systems, leading to inefficient and costly thrust deflection solutions.
Innovation Solution
The use of ablative or fugacious thrust deflectors that ablate or melt away, allowing passive control of thrust direction through materials like ceramics, polymers, and metals, attached to nozzles or spacecraft structures, providing a passive thrust vector control mechanism.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If traditional thrust deflectors are used to control thrust direction, then thrust vector control is achieved, but device complexity and mass increase
Solution Approach 1:
The patent employs ablative materials that are consumed during operation to create the thrust deflection effect. These materials are intentionally designed to be temporary and sacrificial, eliminating the need for complex mechanical adjustment systems. The deflection is achieved through the controlled ablation of material rather than through complex mechanical structures.
Solution Approach 2:
The patent replaces active mechanical thrust vector control systems with a passive chemical/thermal process. Instead of using mechanical deflectors that require actuators and control systems, the invention uses ablative materials that chemically or thermally decompose to create the desired thrust direction changes automatically.
2Ease of operation
If traditional thrust deflectors are used to direct exhaust, then thrust direction control is achieved, but mass increases
Solution Approach 1:
The thrust deflection is achieved through sacrificial ablative materials that are consumed during the burn. These materials are lightweight and intentionally designed to be temporary, eliminating the need for heavy mechanical deflection structures that would permanently increase satellite mass.
Solution Approach 2:
The patent changes the physical state and properties of materials during operation. By using materials that undergo phase changes or chemical decomposition at high temperatures, the system achieves thrust direction control without requiring permanent heavy structural components.
3Ease of operation
If thrust deflectors obstruct gas flow, then thrust direction control is achieved, but overall thrust is reduced
Solution Approach 1:
The patent employs a dynamic approach where the deflection surface is not fixed but evolves during operation. The ablative material is consumed over time, allowing the thrust vector to dynamically adjust its deflection characteristics. This dynamic behavior enables the system to maintain thrust direction control while minimizing obstruction to gas flow throughout the burn.
Solution Approach 2:
The thrust deflection occurs in periodic intervals as the ablative material is consumed. The material ablates away in controlled portions, creating the deflection effect only when needed and allowing full thrust to be achieved when the material is consumed or repositioned.
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
Enables efficient and cost-effective deorbiting maneuvers by minimizing obstruction and maintaining thrust direction stability without active systems, reducing the risk of satellite damage from rapid spinning.
Implementation Method 1
The ablative surface is configured to ablate-away, leaving un-deflected thrust for a majority of the burn
Implementation Method 2
The meltable deflector is composed of a ceramic material or a metal, and is composed of polymers, elastomers, metals, or alloys
Data Source
AI summary
An ablative thruster includes a nozzle configured to control a flow of thrust from the satellite. The ablative thruster also includes an ablative surface inside of the nozzle, configured to deflect the thrust at a predefined angle. The ablative surface is configured to ablate-away, leaving un-deflected thrust for a majority of the burn.