Variable Thrust Catapult Valve for Weight-Adaptive Ejection
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Solution Overview
Problem
Existing ejection systems for aircraft struggle to provide a consistent and safe propulsion force for occupants of varying weights, as a single thrust amount may not be suitable for both lightweight and heavyweight individuals.
Innovation Solution
A rocket catapult assembly with a motor assembly, outlet tube, and a valve system that adjusts operating pressure based on occupant weight using a solenoid, modulated bleed, or relief valve, controlled by a load cell and controller to ensure appropriate ejection force.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a single fixed thrust amount is used in the ejection system, then the system structure is simple, but it cannot provide appropriate propulsion force for occupants of varying weights
Solution Approach 1:
The patent applies dynamics by making the thrust output variable rather than fixed. The rocket motor incorporates a valve system that dynamically adjusts the propellant flow rate based on detected occupant weight, transforming a static thrust system into a dynamic one that adapts to different conditions.
Solution Approach 2:
The patent changes the thrust parameter dynamically by modifying the propellant flow rate through a valve system. By adjusting the flow rate parameter in response to weight detection, the system achieves variable thrust output suitable for different occupant weights without requiring multiple separate motor systems.
2Reliability
If a single fixed thrust amount is used in the ejection system, then the device complexity is low, but the ejection force is not appropriate for all occupant weights
Solution Approach 1:
The patent implements feedback by using a weight detection system that continuously monitors occupant weight and automatically adjusts the propellant flow rate through the valve system. This closed-loop feedback ensures the thrust is appropriately matched to the occupant weight, improving safety while managing system complexity through automation.
Solution Approach 2:
The system performs self-service by automatically detecting occupant weight and adjusting its own thrust output without requiring manual intervention. The integrated weight detection and flow control system enables the rocket motor to self-regulate its performance based on the actual load conditions.
3Force
If the propellant flow rate is increased for heavier occupants, then sufficient thrust is achieved for heavy weights, but excessive force is applied to lighter occupants
Solution Approach 1:
The patent applies dynamics by enabling the propulsion force to vary dynamically rather than remaining fixed. The valve system allows real-time adjustment of propellant flow rate, creating a dynamic force output that adapts to the specific weight of each occupant within the designed range.
Solution Approach 2:
The patent changes the force parameter by modifying the propellant flow rate through controlled valve operation. This parameter change enables the system to deliver appropriate force magnitudes across different occupant weights, expanding the adaptability range of the ejection system.
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 ensures safe and effective ejection of occupants by varying the propulsion force according to the occupant's weight, providing a lower ejection force for lighter individuals and maintaining safety for heavier ones.
Implementation Method 1
The valve comprises a solenoid valve. The solenoid valve may be in communication with a controller.
Implementation Method 2
The solenoid valve may be configured to be in a closed position in response to a command by the controller when a load of a load cell exceeds a threshold load.
Implementation Method 3
a rocket catapult assembly with a motor assembly, outlet tube, and a valve system that adjusts operating pressure
Implementation Method 4
A rocket catapult assembly for use in an ejection seat system of an aircraft
Data Source
AI summary
A rocket catapult assembly for an ejection seat may comprise a motor assembly including a proximal end and a distal end, an outlet tube coupled to the distal end, and a valve coupled to the outlet tube. The valve may be configured to vary an operating pressure based on an occupant's weight. The valve may be in a closed configuration, on open configuration, or a partially open configuration during ejection of the ejection seat.