Spaceplane Retractable Flaps for Reentry Speed Control
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Solution Overview
Problem
Space planes face challenges in transitioning from space flight to aeronautical flight, particularly in managing loads and decelerations during reentry, as existing braking systems are not suitable for reducing structural and passenger loads effectively.
Innovation Solution
A spacecraft design featuring maneuverable flaps under the lift-generating surface that can be deployed as airbrakes or landing gear doors, controlled independently to manage speed and attitude during transition, using pitch-attitude control surfaces to navigate through high-incidence to low-incidence phases, thereby controlling speed and reducing loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the space plane brakes by pressing its underside down on the air to increase drag, then the speed is reduced during reentry, but significant heating occurs and high G-forces are experienced by the crew
Solution Approach 1:
The braking function is segmented from the main fuselage by using deployable flaps on the wings. Instead of pressing the entire underside against the air, only specific wing sections with flaps are used for aerodynamic braking, distributing the forces and reducing concentrated heating and G-forces on the crew compartment.
Solution Approach 2:
The flaps are designed to be maneuverable and deployable during flight, allowing dynamic adjustment of the braking surface area. The flaps can be positioned at different angles and extended to different degrees, enabling progressive speed reduction while maintaining controllable heating and load levels throughout the reentry sequence.
2Speed
If conventional airbrakes or landing gear doors are used for braking during reentry, then speed control is achieved, but the structural loads and passenger comfort are compromised
Solution Approach 1:
The flaps are designed with multi-functionality, serving both as aerodynamic airbrakes for speed control during reentry and as landing gear doors for the landing phase. This universal design allows the same structure to perform braking functions while being optimized for both purposes, reducing the need for separate specialized components and improving overall system efficiency.
3Device complexity
If the flaps are deployed at fixed positions, then the structure is simpler, but the ability to control descent and manage different flight phases is reduced
Solution Approach 1:
The flap system incorporates maneuverability and deployability features that allow dynamic positioning during flight. The flaps can be adjusted to different angles and extended or retracted as needed, providing adaptability for different flight phases while maintaining a relatively simple structural design when in the retracted position.
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 solution allows for controlled speed management and reduced loads during transition, ensuring passenger comfort and structural integrity by maximizing drag and lift control, while also serving as landing gear doors to minimize noise and aerodynamic drag.
Implementation Method 1
The space plane is braked in this way and loses altitude... the flaps... operating as airbrakes... maximizing drag
Implementation Method 2
a spacecraft suited to aeronautical flight and for that purpose comprising lift-generating surfaces
Data Source
AI summary
A spaceplane suitable for aeronautical flight comprising a body and a wing defining a lower airfoil surface in addition to attitude control means that comprise one or a plurality of shutters disposed under the lower airfoil surface of same and maneuverable between a stowed position and an inclined extended position for aerodynamic braking during the transition from a phase of space flight to a phase of aeronautical flight of the aircraft.