Deployable Deceleration Surfaces for Rocket Landing Stability
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Solution Overview
Problem
The reusability of rocket systems remains a significant challenge due to the lack of effective deceleration and stabilization mechanisms during descent and landing, which affects the safety and efficiency of rocket missions.
Innovation Solution
The implementation of deployable deceleration surfaces, such as flare surfaces, that can be stowed during ascent and deployed during descent to stabilize and slow down the vehicle, along with adjustable fins for control and steering, enhances the aerodynamic lift-to-drag ratio and reduces terminal velocity, allowing for controlled tail-down landings.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If deployable deceleration surfaces are added to the vehicle, then stability and control during descent are improved, but device complexity increases
Solution Approach 1:
The deceleration surfaces are designed to be deployable rather than fixed, allowing them to be stowed during ascent and deployed during descent. This dynamic configuration provides stability when needed while maintaining simplicity during other phases of flight.
Solution Approach 2:
The deceleration system is divided into multiple deployable surfaces that can be independently controlled. This segmentation allows for fine-tuned stability control while keeping each individual surface relatively simple in design.
2Speed
If deployable deceleration surfaces are deployed during descent, then terminal velocity is reduced, but device complexity increases
Solution Approach 1:
The deceleration surfaces transition from a stowed configuration during ascent to a deployed configuration during descent, dynamically adjusting the vehicle's aerodynamic properties to reduce terminal velocity only when needed.
Solution Approach 2:
The deployment of deceleration surfaces changes the aerodynamic parameters of the vehicle, specifically increasing drag area to reduce terminal velocity during the descent phase.
3Ease of operation
If adjustable fins are added for control and steering, then control precision during descent is improved, but device complexity increases
Solution Approach 1:
The fins are designed to be adjustable rather than fixed, allowing real-time control precision improvement during descent while maintaining a relatively simple structure that can be integrated into the existing vehicle design.
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
This solution improves the stability and control of the vehicle during descent, reduces the need for excessive fuel usage, and enables precise landing back to the launch site, thereby enhancing the reusability and efficiency of rocket systems.
Implementation Method 1
deployable deceleration surfaces, such as flare surfaces, that can be stowed during ascent and deployed during descent to stabilize and slow down the vehicle
Implementation Method 2
enhances the aerodynamic lift-to-drag ratio and reduces terminal velocity, allowing for controlled tail-down landings
Data Source
AI summary
Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a launch vehicle that has a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. The vehicle carries an exposed outwardly facing surface having a first region positioned or positionable to have a first cross-sectional area generally normal to the vehicle axis toward the first end of the vehicle, and a second region positioned or positionable to have a second cross-sectional area generally normal to the vehicle axis toward the second end of the vehicle. The first cross-sectional area is less than the second cross-sectional area. The system can further include a propulsion system carried by the launch vehicle and having at least one nozzle positioned toward the first end of the vehicle to launch the launch vehicle. In a further particular embodiment, the exposed surface can include a deployable flare surface that is positioned toward the forward section of the vehicle and is stowed during an ascent phase of the vehicle. During descent, the deployable flare surface can pivot outwardly to slow the vehicle down for a tail-down landing. Systems is accordance with other embodiments include launch vehicles with fuel tanks shaped to control the motion of the center of gravity of fuel in the tanks as the fuel level in the tank changes.