Satellite Optical Instrument Parallel Launcher Axis Design
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Solution Overview
Problem
Current satellite designs that incorporate optical instruments face limitations in performance due to the constraints of launchers, where shocks and vibrations can damage the instruments, and the need to increase the diameter and length of telescopes for better resolution is hindered by limited space within the launcher fairing.
Innovation Solution
A satellite design where the optical axis of the instrument is directed from the upper end towards the lower end of a cylindrical launcher interface system, with a connecting device that includes a side wall parallel to the axis of sight, allowing the optical instrument to be protected from shocks and vibrations while maximizing its diameter and focal length within the limited launcher space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the optical instrument is spaced away from the launcher interface ring by the support structure to limit shock and vibration transmission, then the protection of the optical instrument is improved, but the satellite occupies more space and the instrument diameter and focal length are constrained
Solution Approach 1:
The patent reorients the optical axis of the instrument to be substantially parallel to the launcher axis rather than perpendicular, fundamentally changing the spatial arrangement. This dimensional shift allows the instrument to be positioned closer to the interface ring while maintaining shock protection, as the optical path now extends along the launcher axis direction, maximizing the use of available longitudinal space within the fairing.
Solution Approach 2:
The patent inverts the conventional arrangement by directing the optical axis parallel to the launcher axis instead of perpendicular to it. This inversion allows the instrument opening to face toward the front of the satellite (in the direction of motion), enabling the optical path to extend forward along the launcher axis, thereby reducing the transverse space required while maintaining instrument protection.
2Measurement precision
If the diameter and length of the telescope are increased to improve resolution and radiometric sensitivity, then the performance of the optical instrument is improved, but the satellite dimensions and space requirements increase
Solution Approach 1:
By orienting the optical axis parallel to the launcher axis, the patent enables the telescope to utilize the longitudinal dimension of the fairing more effectively. This allows for increased focal length and aperture diameter without proportionally increasing the transverse footprint, as the optical components are arranged along the length of the satellite rather than requiring additional width or height.
Solution Approach 2:
The inverted configuration with the optical axis parallel to the launcher axis allows the telescope to be positioned with its aperture at the front, extending backward along the satellite body. This arrangement maximizes the use of available longitudinal space for the optical path, enabling larger aperture and focal length within the same fairing volume constraints.
3Ease of manufacture
If the optical axis is oriented perpendicular to the launcher interface ring to simplify mounting, then the ease of manufacture is improved, but the available space for large diameter instruments is reduced
Solution Approach 1:
The patent changes the mounting orientation from perpendicular to parallel with respect to the launcher axis. This dimensional change allows the instrument aperture to be positioned at the front of the satellite with the optical path extending backward, effectively utilizing the longitudinal space available in the fairing to accommodate larger aperture diameters without increasing the transverse envelope.
Data Source
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AI summary
The invention relates to a satellite (1) which comprises: at least one optical photography instrument (3) comprising a main lens having an optical axis (V) and the optical instrument (3) having a field of view; at least one launcher interface system (2), intended for being removably secured to a satellite interface system (2') of a launcher of the satellite; a linking device (7) between the launcher interface (2) and the optical instrument (3) extending substantially parallel to the optical axis (V) of the main lens between an upper end (9) and a lower end (10); the launcher interface system (2) is connected to the linking device (7) by the lower end (10) and the optical axis (V) of the optical instrument (3) is directed from the upper end (9) towards the lower end (10) of the linking device (7), the launcher interface system being outside the field of view of the instrument.