Spacecraft Nozzle Pneumatic Deployment System
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Upper stage engine nozzles for space vehicles are structurally complex, leading to increased weight and reduced reliability, which complicates their deployment and engagement, thereby affecting the performance of the upper stage.
Innovation Solution
A pneumatic deployment system for a two-portion nozzle with a stationary and movable portion, utilizing a deployment actuator, high and low unlocking actuators, and an ejector, actuated by a pneumatic pressure feed system to sequentially deploy, unlock, and eject the deployment system, reducing complexity and weight while ensuring reliable operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a two-portion nozzle with movable and stationary portions is used, then the nozzle can be deployed and engaged to form the complete nozzle, but the deployment system becomes structurally complex, increasing total weight and reducing reliability
Solution Approach 1:
The deployment system is segmented into three independent pneumatic actuators (deployment actuator, high unlocking actuator, low unlocking actuator) that operate sequentially. Each actuator handles a specific function: deploying the movable portion, unlocking the high locking position, and unlocking the low locking position. This segmentation simplifies the overall system by dividing complex deployment tasks into manageable, independent stages, reducing structural complexity while maintaining deployment capability
Solution Approach 2:
The nozzle transitions from a static stored configuration to a dynamic deployed configuration through controlled movement of the movable portion. The system uses dynamic pneumatic actuation to achieve smooth transitions between locked and unlocked states, enabling the nozzle to adapt its shape from a compact form during launch to a fully expanded form during engine operation
2Adaptability or versatility
If known deployment systems are used, then the nozzle can be deployed, but the structure becomes complex, increasing total weight of the upper stage and penalizing performance
Solution Approach 1:
The deployment system uses pneumatic actuators instead of traditional mechanical or hydraulic systems. Compressed gas stored in accumulators provides the force needed for deployment, unlocking, and ejection operations. This pneumatic approach reduces weight by eliminating heavy mechanical linkages, motors, and hydraulic fluid systems while providing sufficient force for all deployment operations
Solution Approach 2:
The deployment system is designed as a temporary structure that is discarded after use. Once the nozzle is deployed and locked into position, the deployment system is ejected from the nozzle assembly. This allows the use of lighter-weight temporary deployment mechanisms without compromising the permanent structural integrity or weight of the operational nozzle system
3Adaptability or versatility
If structurally complex deployment systems are used, then the nozzle can be deployed, but reliability is reduced due to the complexity of the structure
Solution Approach 1:
The pneumatic actuators are designed to operate autonomously using stored compressed gas. Each actuator contains its own gas supply and control mechanism, eliminating the need for external control systems, sensors, or feedback mechanisms. This self-service approach reduces the number of potential failure points and simplifies the control architecture, thereby improving reliability
Solution Approach 2:
The deployment system components are designed as single-use, disposable elements that are ejected after completing their function. This allows the use of simpler, less redundant components that would be too complex if designed for multiple uses, improving reliability by reducing the number of moving parts and potential failure modes in the permanent nozzle structure
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 pneumatic deployment system simplifies the nozzle deployment process, reduces the overall weight and complexity of the upper stage, and enhances its reliability by minimizing obstructive components during engine operation, allowing for efficient and reliable nozzle extension and retraction.
Implementation Method 1
a pneumatic pressure feed system for actuating the deployment actuator, the high unlocking actuator, and the low unlocking actuator, and the ejector
Implementation Method 2
an ejector adapted to exert a thrust force tending to eject the deployment system from the nozzle
Data Source
AI summary
A nozzle (1) for a space vehicle engine (M), the nozzle comprising a stationary portion (2) and a movable portion (3), the nozzle (1) including a pneumatic deployment system (4) comprising: a deployment actuator (5) for deploying the movable portion (3) of the nozzle (1); a high unlocking actuator (6); a low unlocking actuator (7); and an ejector (41); the deployment system (4) including a feed system (8) configured so as to, sequentially: move the deployment actuator (5) from its support position towards its deployment position; move the high and low unlocking actuators (6, 7) into their high and low unlocking positions; and actuate the ejector so as to eject the deployment system (4) from the nozzle (1).