Non-Coplanar Landing Legs for Space Probe Impact Damping
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Solution Overview
Problem
The challenge is to design a landing system for space probes that balances high initial damping capacity with low total stiffness, while minimizing mass increase with the number of landing legs, to ensure stable support on celestial bodies without damaging the payload.
Innovation Solution
The system employs non-coplanar landing legs with varying lengths and angles, allowing for multiple planes of contact, where each leg is dimensioned to absorb energy as a single shock absorber or in groups of up to three, using viscoelastic or inelastic damping means, and can adapt to different stable positions post-landing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If the number of landing legs is increased to improve stability, then the stability of the space probe on the ground is improved, but the mass of the landing device increases significantly
Solution Approach 1:
The landing system is segmented into multiple independent landing legs (at least 4), each capable of functioning independently. This segmentation allows the system to achieve stability through distributed support while maintaining the ability of individual legs to handle impact loads separately, thus reducing the need for overly robust individual components that would increase overall mass.
Solution Approach 2:
The feet of the landing legs are positioned at non-coplanar points in space, creating a three-dimensional support structure. This spatial arrangement enhances stability by distributing the probe's weight across multiple dimensions and providing redundant support paths, allowing for stable landing with fewer legs than would be required with coplanar arrangements.
2Strength
If each landing leg is dimensioned to absorb total landing energy alone, then the initial damping capacity is improved, but the total stiffness of the landing system becomes too high for simultaneous contact landing
Solution Approach 1:
Each landing leg is equipped with localized damping means (such as viscoelastic or inelastic deformable elements) that provide energy absorption capacity. This local damping capability ensures that each leg can handle impact loads independently when necessary, while the overall system stiffness remains manageable through the distributed nature of these local damping elements.
Solution Approach 2:
The landing legs incorporate damping means designed to absorb impact energy before the full force of landing is transmitted to the probe body. This prior cushioning effect is achieved through deformable elements that progressively absorb energy during the landing sequence, preventing sudden high-stiffness responses that would damage the payload.
3Weight of moving object
If the mass of the landing device is reduced, then the payload capacity is improved, but the stability of the space probe on the ground is compromised
Solution Approach 1:
The landing legs incorporate adjustable or adaptable damping characteristics that can respond dynamically to landing conditions. The damping means can adjust their stiffness and energy absorption characteristics based on the impact forces experienced, providing optimal performance across a range of landing scenarios without requiring excessive mass for worst-case scenarios.
Solution Approach 2:
The landing legs may have asymmetric configurations or varying lengths to optimize their performance for different landing attitudes and surface conditions. This asymmetry allows the system to achieve stability with lighter individual components by strategically positioning and sizing legs based on expected landing scenarios rather than using uniform over-engineered legs.
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 approach ensures effective deceleration and stability with reduced mass, as each leg is optimized for maximum damping with simultaneous contact of up to three legs, limiting the overall mass increase and maintaining payload integrity.
Implementation Method 1
each of said landing legs comprises damping means for absorbing at least part of the energy of landing impact
Implementation Method 2
These damping means are, for example, viscoelastic or inelastic deformable elements, which absorb substantial amounts of energy via inelastic or viscoelastic deformations
Data Source
Figure 1~2
AI summary
The invention relates to a landing system of a body and a space probe provided with such a system for landing on a bearing ground. Said landing system includes landing legs (5), each with a footpad (6) at the end thereof, intended for braking the landing impact of said body when coming into contact with the ground and for supporting said body on the ground after landing. According to the invention, said footpads (6) are not coplanar.