Key Takeaways
- This case study presents the development of a sub-meter high-resolution optical payload that redefines the balance between optical precision and mass efficiency. Leveraging space-proven technical heritage, the project successfully integrated a coaxial reflective optical system with a correction lens group to achieve diffraction-limited imaging performance.
- The resulting lightweight remote sensing camera achieves a significant reduction in mass—down to 2.6 kg—while maintaining exceptional structural stability and a wavefront error of sub-0.03λ.
- By optimizing the optical design and utilizing zero-expansion materials, this payload offers a high-performance, low-distortion solution (< 0.05%) for next-generation satellite missions where strict mass constraints and high-resolution requirements coexist.
Technological Heritage & Safeguard Measures
Our development process is rooted in a mature industrial chain and extensive flight heritage. We utilize a “design-for-success” methodology that integrates past mission data with rigorous safeguard measures.
Table 1: Technological Inheritance and Safeguard Measures
Order | Technical Project | Technical Basis and Experience | Measure of Safeguard |
1 | Coaxial Reflective System Design | Multi-model Camera Application | Specialized optical re-optimization |
2 | Mirror Machining and Inspection | Legacy of high-precision processing | Multi-set fabrication & metrology equipment |
3 | Space Camera Optical Alignment | 20+ internal system integrations | Dedicated detection and installation facilities |
4 | Ultra-lightweight Support Structure | In-house manufacturing excellence | Gravity deformation & aero-thermal investigation |
5 | Thermal Focusing | Space-proven camera heritage | Vacuum thermal test verification post-calibration |
6 | Satellite Platform Interface | Multi-model Camera Application | Collaborative engineering with bus structures |
7 | Opto-mechanical Materials | Multi-model Camera Application | Mature design inheritance |
Technical Specifications
The project was defined by strict requirements for resolution, spectral range, and physical envelope. Table 2: Overall Indicators Requirements
Name |
Technical Requirement |
Effective Focal Length |
580 mm |
Spectral Band (PAN) |
450 nm – 900 nm |
MTF @ 156 lp/mm (PAN) |
> 20% |
Image Circle |
37.5mm |
Aperture |
150 mm |
Total Length |
< φ190 × 550 mm (Inc. BFD) |
Mass |
< 3.0 kg |
Max Transmission / Throughput |
> 76% |
Distortion (Dist.) |
< 2% |
Optical System Architecture & Performance
Avantier implemented a coaxial two-mirror reflective system integrated with a corrective lens group to eliminate aberrations and maximize image clarity.- Focal Length: 600 mm (Design baseline)
- Field of View (FOV): 3.6°
- Relative Aperture: f/4
- Optical Dimensions: 150 mm × 150 mm × 200 mm
Performance Analysis
The system achieves near-diffraction-limited performance across the entire field of view:- Wavefront Error: Sub-0.03λ @ 632.8nm RMS.
- Achromatic Performance: Effective convergence from 450nm to 900nm without secondary spectrum residuals.
- Image Quality: All field diffraction spots reach or approach the Airy disk size. Maximum distortion is contained below 0.1%, far exceeding the 2% requirement. MTF exceeds 0.22 at 156 lp/mm.
Structural Design & Mechanical Integrity
The camera structure is engineered for extreme stability during launch and orbital operations, enduring vibration, microgravity, and vacuum thermal stresses.- Box-Type Architecture: A primary load-bearing frame ensures high rigidity and avoids mutual interference between optical components.
- Material Selection: Mirrors are crafted from zero-expansion microcrystalline glass, ensuring exceptional environmental adaptability and long-term focal stability.
- Truss-Optimized Structure: High rigidity achieved through lightweight optimization.
Table 3: Camera Mass Budget Distribution
Order | Component Name | Design Mass (kg) |
1 | Primary Mirror Assembly | 0.60 |
2 | Secondary Mirror Assembly | 0.05 |
3 | Correction Mirror Assembly | 0.30 |
4 | Main Support Structure | 1.20 |
5 | Prism Assembly | 0.01 |
6 | Light-shielding / Baffle | 0.20 |
7 | Thermal Control Subsystem | 0.20 |
8 | Fasteners (Bolts/Nuts) | 0.04 |
Total | 2.60 kg |
Conclusion: Compliance & Success
The development resulted in a payload that not only met but surpassed all technical specifications, providing a significant performance margin for mission success.
Table 4: Indicator Compliance Matrix
Name | Technical Requirement | Design Value | Status |
Effective Focal Length | 580 mm | 580 mm | Verified |
Spectral Band (PAN) | 450 nm – 900 nm | 450 nm – 900 nm | Verified |
MTF @ 156 lp/mm | > 20% | 22% | Verified |
Image Circle | 37.5mm | 37.7 mm (GMAX3265 Ready) | Verified |
Aperture | 150 mm | 150 mm | Verified |
Total Envelope | < φ190 × 550 mm | φ185 × 300 mm | Verified |
Total Mass | < 3.0 kg | 2.6 kg | Verified |
Max Throughput | > 76% | 76.54% | Verified |
Distortion | < 2% | 0.05% | Verified |
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