Reusable Payload Module With Deployable Wings for Controlled Reentry
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing space transport vehicles face limitations in size, controllability, and reusability due to their cylindrical or asymmetrical designs, leading to side loads during launch, limited re-entry control, and complex heat shield requirements.
Innovation Solution
A reusable payload module with a rotationally symmetrical fairing that can pivot outward to form wings, allowing it to transform into a lift-generating glider for controlled re-entry and landing, while maintaining a cylindrical shape for launch compatibility and reducing thermal loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If a winged space transporter is used to increase size and improve controllability, then payload volume and flight control are improved, but side loads on the launch vehicle increase due to asymmetrical shape
Solution Approach 1:
The payload module employs dynamically deployable wings that are stowed during launch and deployed during re-entry. This allows the vehicle to transition from a symmetric configuration during ascent (minimizing side loads) to a winged configuration during atmospheric re-entry (providing lift and control), effectively resolving the contradiction between launch performance and re-entry controllability
Solution Approach 2:
The wings are divided into multiple segments that can be independently controlled and deployed. This segmentation allows for precise control of the wing configuration, enabling the vehicle to optimize its aerodynamic properties for different flight phases while maintaining symmetry during launch to avoid side loads
2Adaptability or versatility
If a winged space transporter is used to improve re-entry control, then flight envelope is expanded, but heat shield geometry becomes significantly more complex and expensive
Solution Approach 1:
The heat shield is designed to work in conjunction with dynamically deployable wings, allowing the heat shield itself to maintain a simpler, more manageable geometry while the wings provide the necessary aerodynamic control during re-entry. The wings can be adjusted to control the re-entry trajectory, reducing the complexity requirements for the heat shield geometry
3Ease of manufacture
If a capsule is used for return transport, then integration into cylindrical rocket is easy and no side loads occur, but size and volume are limited by rocket diameter
Solution Approach 1:
The payload module uses a cylindrical capsule configuration during launch that integrates easily into the rocket, then transforms by deploying wings during re-entry. This dynamic transformation allows the vehicle to achieve both easy integration during ascent and expanded volume/c controllability during re-entry, overcoming the volume limitations of traditional capsules
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 design minimizes lateral forces during ascent, enhances re-entry control, and simplifies heat shield construction, enabling efficient reuse and extended landing site selection.
Implementation Method 1
the outwardly pivotable surface sections extend laterally away from the fuselage in a pivoted state and each form a wing and/or a control surface of the payload module
Data Source
Figure 1
Figure 2~7
AI summary
A reusable payload module (2; 2') as part of an upper stage (12) of a space rocket (1) is provided with a fairing (20A) which, when the payload module (2) is closed, surrounds a payload receiving space (21) and forms an outer shell (20; 20') of a fuselage (29) of the payload module (2; 2'), which is rotationally symmetrical to a payload module longitudinal axis (XN) which runs coaxially with or parallel to a longitudinal axis (XR) of the space rocket (1), and is characterized in that the fairing (20A) forming the outer shell (20; 20') has at least two surface sections (23, 24) which can each be pivoted outwards about a pivot axis (X23, X24).