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CubeSat is a standardized platform for small satellites, initially proposed jointly by Stanford University and California Polytechnic State University in the United States. The aim was to provide a low-cost, easy-to-manufacture, and launch form of small satellite for space science research and engineering experiments. CubeSat components typically include the following major parts：
Structural Frame: The standard unit of a CubeSat is 10x10x10 centimeters, known as "1U". Multiple units can be combined, such as 2U (20x10x10 centimeters) or 3U (30x10x10 centimeters). These frames are typically made from lightweight metals like aluminum alloys to ensure stability and durability in space.
Thermal Control System: Includes heat sinks, coatings, heat pipes, etc., to help the satellite operate normally under extreme temperature conditions.
Solar Panels: CubeSats usually rely on solar cells for power, which can be directly mounted on the chassis or deployed to form larger solar capture areas after the satellite is in orbit.
Batteries: Typically use lithium-ion batteries for energy storage, providing power during shadow periods and high power consumption phases.
Power Management and Distribution Unit (PMAD): Manages the generation, storage, and distribution of power to ensure each component has sufficient electricity.
Magnetometer and Magnetorquers: Control satellite attitude through Earth's magnetic field. The magnetometer senses the Earth's magnetic field, while the magnetorquers generate the corresponding magnetic torque.
Gyroscopes and Accelerometers: Used for attitude sensing and orbital adjustments.
Reaction Wheels: Precisely adjust and maintain attitude, generally used for missions requiring high stability.
Antennas: Typically omnidirectional or more complex directional antennas used for communication with Earth.
Transceivers: Enable data communication with ground stations, with typical frequency bands including VHF (Very High Frequency), UHF (Ultra High Frequency), and S-band. Higher frequency bands like X-band are sometimes used for high-speed data transmission.
Communication Protocols: Common protocols include AX.25, BPSK, QPSK, etc., to ensure signal reliability and anti-jamming capabilities.
Processor: The OBC is the satellite's core control unit, responsible for directing various systems. Commonly used processors include low-power, high-reliability embedded processors (such as the ARM series) or radiation-hardened chips designed for space applications.
Memory and Storage: Temporarily stores data and executes code. Some satellites use non-volatile memory to preserve critical data for extended periods.
The payload of a CubeSat varies depending on the mission. For example, payloads for scientific investigation missions might include cameras and spectrometers, while communication missions might utilize signal transponders.
Flight Software: Manages the entire satellite's operations, such as attitude control, data acquisition, and communication management.
Ground Software: Supports data reception, analysis, and satellite status monitoring, primarily interfacing with the satellite's communication system.
Deorbit Systems: Some CubeSats are equipped with deorbit systems, such as drag sails and aerobrakes, to ensure safe reentry into the atmosphere and reduce space debris.
Unlock Systems: Some satellites require deployment (like solar panels or antennas) after launch or reaching orbit, and unlocking devices are needed to complete the deployment.
Due to their standardized structure, small size, and lightweight, CubeSats have been widely applied in commercial, scientific, and educational fields and can perform a series of tasks such as Earth observation, technology validation, and deep space exploration.