Rocket Landing Leg Damping Geometry for Controlled Deployment
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Solution Overview
Problem
Existing rocket landing systems face challenges in controlling unfolding speed, adaptability, mechanical component replacement, and structural stress management during flight and landing, particularly in telescoping and parallel linkage systems.
Innovation Solution
A propulsive landing leg system with a body, revolute joints, shock absorbers, damping units, and a locking mechanism, allowing controlled rotation and unfolding, and utilizing power sources like solenoids for precise deployment, along with aerodynamic and stress management geometry to manage high structural stress.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If telescoping or parallel linkage systems are used for rocket landing, then the landing system can support the rocket structure, but the unfolding speed control becomes difficult and mechanical component replacement is complicated
Solution Approach 1:
The patent employs a dynamically adjustable landing leg system where the legs can transition between folded and unfolded states through controlled rotation joints. The system uses adjustable linkages that allow dynamic modification of the landing leg configuration during deployment, enabling precise control over unfolding speed and position while maintaining structural integrity.
Solution Approach 2:
The landing leg is divided into multiple segmented components including separate thigh, shin, and foot sections connected by rotation joints. This segmentation allows each component to be independently controlled and replaced, simplifying maintenance while enabling precise control over the deployment sequence and speed of each segment.
2Reliability
If traditional landing leg systems are used, then basic landing support is provided, but adaptability and ease of mechanical component replacement are limited
Solution Approach 1:
The patent designs universal mounting interfaces and standardized connection points across all landing leg components, allowing different leg configurations to be interchangeably mounted on the same rocket platform. The rotation joints and linkage mechanisms are designed with universal compatibility, enabling easy replacement and reconfiguration of mechanical components for different mission requirements.
Solution Approach 2:
The system incorporates dynamically adjustable parameters including variable leg lengths, adjustable damping characteristics, and reconfigurable linkage geometries. These dynamic features allow the landing system to adapt to different rocket masses, landing sites, and mission profiles while maintaining reliable support functionality.
3Ease of manufacture
If simple landing leg design is used, then manufacturing is easier, but ability to withstand high structural stress during flight and landing is reduced
Solution Approach 1:
The patent specifies the use of composite materials for landing leg construction, combining high-strength alloys with advanced composite structures. The thigh and shin sections utilize composite laminates that provide high strength-to-weight ratios, while critical connection points employ high-strength forged components. This composite approach maintains manufacturing feasibility through standardized fabrication processes while dramatically improving stress tolerance.
Solution Approach 2:
The landing leg components incorporate curved and optimized structural geometries that distribute stress more effectively throughout the structure. The rotation joints use spherical or cylindrical contact surfaces that reduce stress concentrations, and the overall leg geometry is optimized to channel landing forces through efficient load paths, achieving high strength without excessive manufacturing complexity.
4Stability of the object's composition
If landing legs allow free movement, then stabilization is reduced, but guidance system strain increases
Solution Approach 1:
The patent incorporates damping mechanisms and shock-absorbing elements within the landing leg structure that activate during deployment and landing. These passive energy dissipation systems provide stabilization throughout the unfolding process and impact absorption, reducing the burden on active guidance systems while ensuring stable landing configuration.
Solution Approach 2:
The system includes sensors and control mechanisms that monitor landing leg deployment status and provide feedback to the guidance system. This feedback enables the guidance system to make minimal adjustments based on actual leg position and rocket attitude, reducing energy consumption while maintaining stability through coordinated control of the landing leg deployment sequence.
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 system provides controlled unfolding speed, increased stabilization, reduced strain on guidance systems, and improved stress tolerance, enabling successful landings across various stress and flow regimes, suitable for planetary exploration missions.
Implementation Method 1
the shock absorber including a central shaft associated with a shock absorbing spring configured to allow for limited pivotal movement of the landing leg relative to the rocket
Implementation Method 2
a damping unit configured to cushion the landing of the rocket upon contact with the landing surface
Data Source
AI summary
The embodiments described herein provide a propulsive landing rocket landing leg system that provides for a high probability of a successful landing across wide stress and flow regimes due to the mechanism's ability to be implemented across a variety of compact and aerodynamic landing leg geometries. It provides for the ability to control unfolding speed for increased stabilization and removes unfolding dependence on the assistance of the gravitational force or separate “forced” actuating deployment sub-systems. The utilization of both rotational and linear damping units provides higher flexibility in the sourcing of lower cost components promoting higher cost-efficient construction and ease of parameter adaptation for the respective dynamics of the mechanism. The structural arrangement of the components allows for favorable distribution of stress, and in turn high stress tolerance due to the collaborative efforts of the parallel linear rod shafts and the landing leg structure, thus effective management of bending and other stress modes. Corresponding landing legs and methods are disclosed.