CUBESAT PLATFORMS

 Dimensions:

• Size: 10 cm x 10 cm x 10 cm
• Volume: 1 unit (1U) CubeSat
• Mass: Approximately 1.33 kilograms

Structure:

• Material: Aluminum alloy 6061 or similar lightweight, aerospace-grade material
• Wall Thickness: 1.5 mm for structural integrity
• External Finish: Anodized coating for protection against space environment

Power System:

• Solar Panels: Deployable solar panels with high-efficiency solar cells
• Solar Cell Type: Triple-junction gallium arsenide (GaAs) or similar for high power generation in space
• Battery: Lithium-ion (Li-ion) battery with a capacity of at least 4.5 Ah for power storage
• Power Management: Efficient power management system for voltage regulation and distribution

Communication:

• Transceiver: Software-defined radio (SDR) transceiver for reliable communication
• Frequency Bands: UHF/VHF for uplink and S-band/X-band for downlink
• Antenna: Quarter-wave monopole or patch antenna for omnidirectional coverage
• Data Rate: Up to 9.6 kbps for telemetry and 1 Mbps for payload data

Onboard Computer:

• Processor: ARM Cortex-M7 or similar low-power processor
• Clock Speed: 72 MHz or higher for data processing
• Memory: 256 MB of flash memory and 32 MB of RAM for data storage and processing
• Operating System: FreeRTOS or similar real-time operating system for satellite operations

Sensors:

• Attitude Determination and Control System (ADCS): Magnetorquers, sun sensors, and gyros for attitude determination and control
• Imaging: CMOS or CCD camera with at least 1 MP for Earth observation
• Payload: Customizable payload interface for various mission payloads

Deployment Mechanism:

• Launch: Compatible with standard CubeSat deployment systems (P-POD, ISS deployment, etc.)
• Deployment: Spring-loaded or electromagnetic deployment mechanism for successful satellite deployment

Mission Capabilities:

• Earth Observation: Imaging capabilities for Earth observation missions
• Technology Demonstration: Platform for demonstrating new technologies in space
• Education: Educational tool for universities and research institutions

Compatibility:

• Launch Vehicles: Compatible with a wide range of launch vehicles (e.g., Falcon 9, PSLV, etc.)
• Deployment: Compatible with standard CubeSat deployment systems

Development and Support:

• Customization: Customization options available based on mission requirements
• Technical Support: Dedicated technical support for mission planning and operations

Dimensions:

• Size: 10 cm x 10 cm x 20 cm
• Volume: 2 units (2U) CubeSat
• Mass: Approximately 2.66 kilograms

Structure:

• Material: Aluminum alloy 6061 or similar lightweight, aerospace-grade material
• Wall Thickness: 1.5 mm for structural integrity
• External Finish: Anodized coating for protection against space environment

Power System:

• Solar Panels: Deployable solar panels with high-efficiency solar cells
• Solar Cell Type: Triple-junction gallium arsenide (GaAs) or similar for high power generation in space
• Battery: Lithium-ion (Li-ion) battery with a capacity of at least 7 Ah for power storage
• Power Management: Efficient power management system for voltage regulation and distribution

Communication:

• Transceiver: Software-defined radio (SDR) transceiver for reliable communication
• Frequency Bands: UHF/VHF for uplink and S-band/X-band for downlink
• Antenna: Quarter-wave monopole or patch antenna for omnidirectional coverage
• Data Rate: Up to 9.6 kbps for telemetry and 1 Mbps for payload data

Onboard Computer:

• Processor: ARM Cortex-M7 or similar low-power processor
• Clock Speed: 72 MHz or higher for data processing
• Memory: 512 MB of flash memory and 64 MB of RAM for data storage and processing
• Operating System: FreeRTOS or similar real-time operating system for satellite operations

Sensors:

• Attitude Determination and Control System (ADCS): Magnetorquers, sun sensors, and gyros for attitude determination and control
• Imaging: CMOS or CCD camera with at least 2 MP for Earth observation
• Payload: Customizable payload interface for various mission payloads

Deployment Mechanism:

• Launch: Compatible with standard CubeSat deployment systems (P-POD, ISS deployment, etc.)
• Deployment: Spring-loaded or electromagnetic deployment mechanism for successful satellite deployment

Mission Capabilities:

• Earth Observation: Imaging capabilities for Earth observation missions
• Technology Demonstration: Platform for demonstrating new technologies in space
• Education: Educational tool for universities and research institutions

Compatibility:

• Launch Vehicles: Compatible with a wide range of launch vehicles (e.g., Falcon 9, PSLV, etc.)
• Deployment: Compatible with standard CubeSat deployment systems

Development and Support:

• Customization: Customization options available based on mission requirements
• Technical Support: Dedicated technical support for mission planning and operations

Dimensions:

• Size: 10 cm x 10 cm x 30 cm
• Volume: 3 units (3U) CubeSat
• Mass: Approximately 4 kilograms

Structure:

• Material: Aluminum alloy 6061 or similar lightweight, aerospace-grade material
• Wall Thickness: 1.5 mm for structural integrity
• External Finish: Anodized coating for protection against space environment

Power System:

• Solar Panels: Deployable solar panels with high-efficiency solar cells
• Solar Cell Type: Triple-junction gallium arsenide (GaAs) or similar for high power generation in space
• Battery: Lithium-ion (Li-ion) battery with a capacity of at least 10 Ah for power storage
• Power Management: Efficient power management system for voltage regulation and distribution

Communication:

• Transceiver: Software-defined radio (SDR) transceiver for reliable communication
• Frequency Bands: UHF/VHF for uplink and S-band/X-band for downlink
• Antenna: Quarter-wave monopole or patch antenna for omnidirectional coverage
• Data Rate: Up to 9.6 kbps for telemetry and 1 Mbps for payload data

Onboard Computer:

• Processor: ARM Cortex-M7 or similar low-power processor
• Clock Speed: 72 MHz or higher for data processing
• Memory: 1 GB of flash memory and 128 MB of RAM for data storage and processing
• Operating System: FreeRTOS or similar real-time operating system for satellite operations

Sensors:

• Attitude Determination and Control System (ADCS): Magnetorquers, sun sensors, and gyros for attitude determination and control
• Imaging: CMOS or CCD camera with at least 3 MP for Earth observation
• Payload: Customizable payload interface for various mission payloads

Deployment Mechanism:

• Launch: Compatible with standard CubeSat deployment systems (P-POD, ISS deployment, etc.)
• Deployment: Spring-loaded or electromagnetic deployment mechanism for successful satellite deployment

Mission Capabilities:

• Earth Observation: Imaging capabilities for Earth observation missions
• Technology Demonstration: Platform for demonstrating new technologies in space
• Education: Educational tool for universities and research institutions

Compatibility:

• Launch Vehicles: Compatible with a wide range of launch vehicles (e.g., Falcon 9, PSLV, etc.)
• Deployment: Compatible with standard CubeSat deployment systems

Development and Support:

• Customization: Customization options available based on mission requirements
• Technical Support: Dedicated technical support for mission planning and operations