Spacecraft Antenna Asymmetry Reduces Parasitic Reflections
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Solution Overview
Problem
Conventional spacecraft designs in geostationary orbit suffer from parasitic reflection phenomena that degrade the quality of radiofrequency wave transmission and reception, limiting their field of view and increasing manufacturing complexity and cooling challenges.
Innovation Solution
A spacecraft design featuring a support structure with angled side walls and a movable arm that positions radiating elements perpendicularly to the side walls, forming an offset angle of 25° to 65°, along with an L-shaped heat transfer device for efficient cooling, reduces parasitic reflections and enhances the field of view while simplifying manufacturing and cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If radiating elements are mounted on side walls with central axes parallel to the Earth-directed axis, then the spacecraft structure is simple, but parasitic reflection phenomena occur that deteriorate signal quality
Solution Approach 1:
The patent applies asymmetry by orienting the central axes of radiating elements perpendicular to the side walls rather than parallel to the Earth-directed axis. This asymmetric configuration prevents parasitic reflections from side walls while maintaining manufacturing simplicity through standardized mounting procedures.
Solution Approach 2:
The patent implements preliminary anti-action by pre-configuring the radiating elements at perpendicular angles to side walls during manufacturing, thereby preventing parasitic reflection phenomena before the spacecraft operates. This proactive design eliminates signal degradation issues rather than attempting to correct them during operation.
2Adaptability or versatility
If side walls are oriented parallel to the Earth-directed axis, then the spacecraft structure is conventional, but the field of view is limited
Solution Approach 1:
The patent employs asymmetry by angling side walls relative to the Earth-directed axis and orienting radiating elements perpendicular to these angled surfaces. This asymmetric geometry expands the field of view for communication antennas while maintaining a relatively simple support structure through modular construction.
3Temperature
If radiating elements are cooled with heat pipes having multiple bends, then thermal contact is achieved, but the cooling device complexity increases
Solution Approach 1:
The patent applies dimensionality change by transitioning from multi-bend heat pipes to planar heat dissipation structures that spread thermal energy across two-dimensional surfaces. This approach maintains effective cooling while eliminating the complexity of multiple bends and connections in traditional heat pipe designs.
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 improves radiofrequency wave transmission and reception quality, increases the field of view, simplifies manufacturing, and provides efficient cooling, reducing parasitic reflections and enhancing operational efficiency.
Implementation Method 1
at least one radiating element having a central axis of radiation, said at least one radiating element being able to emit or receive radiofrequency waves
Implementation Method 2
a reflector carried by the movable arm, said reflector being suitable for reflecting or receiving radiofrequency waves in a direction of emission
Implementation Method 3
an L-shaped heat transfer device for efficient cooling
Data Source
AI summary
A spacecraft is disclosed having at least three flat side walls, at least one main communication antenna, including a radiating element having a central axis of radiation (AC-AC), a movable arm configured to move between a deployed position and a folded position, a reflector suitable for reflecting or receiving radiofrequency waves in a direction of emission (DE). The radiating element is fixed to a side wall so that the central axis of radiation (AC-AC) is arranged perpendicularly to the side wall, and the movable arm is shaped so that an offset angle (β) of between 25° and 65° is formed between the side wall and the direction of emission (DE), when the movable arm is in a deployed position.