Reusable Launcher Module with Airfoils for Autonomous Recovery
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Solution Overview
Problem
Current launchers have high operating costs and development times due to the consumable nature of their first stages, which are difficult to recover and require significant modifications for reusability, leading to increased mass and cost.
Innovation Solution
A reusable launcher design with a separable stage consisting of a recoverable module equipped with an airfoil and aircraft engine for landing, and a non-recoverable tank section, allowing the module to detach and land autonomously, reducing the need for complex recovery systems and increasing density for easier recovery.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the first stage is designed to be completely reusable with airfoils and landing gear, then the launcher can be recovered and reused, but the average density of the first stage becomes very low due to large empty tank volumes, making recovery difficult
Solution Approach 1:
The first stage is divided into two separable parts: a recoverable module containing the propulsion system and avionics, and non-recoverable tank sections. This segmentation allows the dense recoverable module to be separated from the low-density empty tanks, solving the density problem while maintaining reusability of the valuable components.
Solution Approach 2:
The tank sections are extracted and designated as non-recoverable, while the valuable propulsion system and avionics are extracted into a separate recoverable module. This extraction allows the recoverable portion to have high density and be easily recovered, while the empty tanks are discarded.
2Reliability
If airfoils are attached to the launcher body to enable return flight, then the first stage can be recovered, but additional mass must be added which increases tank size and launcher cost
Solution Approach 1:
The airfoil-equipped recoverable module is segmented as a separate entity from the consumable tanks. This allows the aerodynamic recovery system to be concentrated in a small, dense module rather than distributed across the entire first stage, minimizing the additional mass penalty.
Solution Approach 2:
The tanks are discarded after use, while the recoverable module with airfoils is recovered and reused. This allows the expensive recovery system to be applied only to the valuable components that justify the additional mass, rather than the entire first stage.
3Reliability
If the launcher design is modified to enable first stage recovery, then reusability is achieved, but the design becomes very different from known launchers, increasing development complexity
Solution Approach 1:
The launcher is segmented into modular components: a standardized recoverable module with propulsion and avionics, and interchangeable consumable tank sections. This modularity allows reusability to be implemented in a systematic way that reduces overall design complexity compared to completely reconfigurable systems.
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 significantly reduces operating costs and development time by enabling the reuse of high-cost components, achieving a high volume density for easier recovery and stability during ascent, while maintaining robustness and reliability.
Implementation Method 1
each stabilizer comprising at least one pair intrados and extrados flaps mounted articulated on said stabilizer so as to be able to move apart from each other in order to position themselves part and other of a mean plane of the stabilizer
Implementation Method 2
airfoils for subsonic flight and a stabilizer mounted articulated in rotation on a downstream end of each wing
Implementation Method 3
the recoverable module being able to land in a controlled manner after a cruise flight
Data Source
AI summary
Recoverable module for propulsion module intended to launch a craft into space, said recoverable module of longitudinal axis (X1), said recoverable module (14) comprising a central body, a propulsive system (8) intended for launching the craft, systems for control and command of the propulsive system, at least one propulsion motor (20) for subsonic flight, lifting surfaces for subsonic flight and a landing gear (30), the lifting surface comprising two substantially plane wings (19a1, 19b1) fixed with respect to the central body, and arranged on either side of the central body of the module and a stabilizer (19a2, 19b2) mounted articulated in rotation on a downstream end of each wing (19a1, 9b1), each stabilizer comprising at least one pair of intrados flaps and extrados flaps mounted articulated on said stabilizer (19a2, 19b2) or any other flap affording a dynamic function.