Throttleable Solid Propellant System with Embedded Actuator
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Solution Overview
Problem
Current solid rocket propellants lack the ability to actively control the burning rate, limiting their performance and adaptability in applications requiring precise thrust control, such as space flight and planetary landings.
Innovation Solution
A throttleable solid propellant system that includes a substantially solid propellant with an embedded shape-altering structure, actuated by an electrical source to change its position and increase the burning surface area, allowing for on-demand control of the burning behavior.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If solid rocket propellant is used, then ease of manufacture and long shelf life are improved, but the ability to actively control burning rate deteriorates
Solution Approach 1:
A shape-altering structure is embedded within the solid propellant grain, creating a nested configuration where the actuator is contained inside the propellant. This allows the propellant to maintain its solid form and manufacturing simplicity while incorporating an internal mechanism that can alter the burning surface area on demand, thus resolving the contradiction between ease of manufacture and adaptability.
Solution Approach 2:
The patent introduces a dynamic element (shape-altering structure) within the otherwise static solid propellant. This structure can change its configuration in response to control signals, dynamically adjusting the burning surface area and thus the thrust output, enabling active control while maintaining the benefits of solid propellant operation.
2Adaptability or versatility
If custom grain geometries are used, then burning rate control is improved, but the ability to modify performance on demand deteriorates
Solution Approach 1:
Instead of relying on fixed custom grain geometries, the patent employs a dynamic shape-altering structure that can modify the burning surface in real-time. This provides automated, on-demand performance modification capability while maintaining precise burning rate control through active adjustment of the propellant's effective geometry during operation.
3Adaptability or versatility
If nozzle throat area is altered, then thrust adjustment is improved, but device complexity and material restrictions deteriorate
Solution Approach 1:
The patent extracts the thrust control function from the nozzle system and relocates it to the propellant grain itself. By embedding a shape-altering structure within the propellant, thrust adjustment is achieved through modification of the burning surface area rather than through complex nozzle mechanisms, thereby reducing device complexity and avoiding material restrictions associated with high-temperature nozzle components.
4Adaptability or versatility
If electrically controlled solid propellants are used, then burning rate control is improved, but chemical composition limitations deteriorate
Solution Approach 1:
The patent separates the control function from the propellant's chemical composition. Instead of incorporating electrically controlled components within the propellant formula itself, the invention embeds a shape-altering structure that physically modifies the burning surface. This allows the use of conventional, easily manufactured solid propellant compositions while achieving controlled burning rate adjustment through geometric modification.
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 enhances the burning rate and thrust of the propellant by increasing the surface area, enabling more efficient and adaptable rocket performance without the need for complex external mechanisms or nozzle modifications.
Implementation Method 1
The shape-altering structure may be actuated to increase a burning surface area of the propellant
Implementation Method 2
The actuation source may be configured to actuate the shape-altering structure between a first position and a second position
Data Source
AI summary
The throttleable solid propellant system includes a substantially solid propellant, a shape-altering structure, and an actuation source. The shape-altering structure is at least partially disposed within the substantially solid propellant. The actuation source is to be coupled to the shape-altering structure. The actuation source is to be configured to actuate the shape-altering structure between a first position and a second position. Transitioning the shape-altering structure between the first position and the second position may crack and/or deform the substantially solid propellant. Cracking and/or deforming the substantially solid propellant may increase the burning surface area of the propellant, thereby altering the thrust produced from the throttleable solid propellant system.