Spacecraft Membrane Coupling Device with Adjustable Angle
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing spacecraft membrane coupling devices face challenges in efficiently transmitting forces for unpacking and orienting spacecraft membranes, particularly in terms of strength, force transmission, and compact packing, which can lead to mechanical stress and damage during deployment.
Innovation Solution
A spacecraft membrane coupling device featuring a flat coupling element and a flat, band-shaped tension element with adjustable angles and a film hinge, allowing for improved force transmission and orientation, reducing mechanical stress by forming large-area contact surfaces and enabling flexible deployment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional bearing eyes and pull cables are used to attach spacecraft membrane, then the coupling device structure is simple, but the force transmission strength and reliability are insufficient
Solution Approach 1:
The coupling element is constructed as a composite structure integrating a flat material piece with a tension element, where the tension element (made of high-strength material such as spectral or dyneema) is attached to the flat material piece. This composite design achieves superior force transmission strength while maintaining structural simplicity, resolving the contradiction between strength and complexity.
2Volume of moving object
If compact packing of spacecraft membrane is implemented, then space saving is achieved, but mechanical stress and damage risk increase during deployment
Solution Approach 1:
The flat material piece of the coupling element serves as a cushioning interface between the spacecraft membrane and the tension element. During compact packing and subsequent deployment, this flat material piece distributes and absorbs mechanical stresses, preventing stress concentration and potential damage to the membrane, thus resolving the contradiction between compact packing and mechanical stress reduction.
3Adaptability or versatility
If fixed orientation coupling device is used, then manufacturing is simplified, but adaptability to different membrane orientations in space is reduced
Solution Approach 1:
The coupling element is designed with flexible material and can assume different spatial orientations through controlled deformation. The tension element can be attached at various angles to the flat material piece, allowing the coupling device to adapt to different membrane orientations in space while maintaining manufacturing simplicity through standardized components and attachment methods.
4Stress or pressure
If small contact surface is used in coupling element, then device size is reduced, but force distribution and stress reduction capability deteriorate
Solution Approach 1:
The coupling element transitions from a traditional point or small-area contact (bearing eye) to a planar flat material piece with larger surface area. This dimensional expansion from zero-dimensional point contact to two-dimensional surface contact improves force distribution and stress reduction capability while the overall device size remains compact through the thin profile of the flat material piece.
Data Source
Figure 1
Figure 2
Figure 3
AI summary
The invention relates to a spacecraft membrane coupling device (8) for tensioning a spacecraft membrane (1). The spacecraft membrane coupling device (8) has a coupling element (9) which is attached to the spacecraft membrane (1). Furthermore, the spacecraft membrane coupling device (8) has a tension element (10) which is held to a support structure, in particular a coil (7). In a connection area of the coupling element (9) with the tension element (10), these form a cross-section in which the coupling element (9) and the tension element (10) form two legs (39, 40). In one operating state, the legs (39, 40) form an angle of 90°, while in another operating state the legs (39, 40) can form a different angle, in particular an angle of 0°, which is advantageous for winding the spacecraft membrane coupling device (8).