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Structural engineering requirements for space vehicle primary and secondary structures The primary structure of a spacecraft typically represents 18–25% of the total launch mass. Every kilogram of structure saved translates directly into increased payload mass or reduced propellant requirements for…
Design, tribology, actuation and reliability of space mechanisms Space mechanisms are the most failure-prone subsystem on spacecraft, accounting for approximately 20–25% of all in-orbit anomalies. A single stuck mechanism can render a multi-billion dollar mission completely useless. 1. Mechanism Classification…
Selection, qualification, procurement and management of electrical electronic and electromechanical parts for spacecraft EEE Parts (Electrical, Electronic and Electromechanical components) account for 60–80% of all spacecraft anomalies. A single counterfeit part or latent manufacturing defect can compromise a mission costing…
ISO Standard — Space systems — Thermal control — Engineering Technical Article 1. Overview of ISO 29764 ISO 29764 defines thermal control requirements for space systems, covering passive and active thermal management, material thermophysical properties, analysis verification, and acceptance testing.…
ISO Standard — Space systems — Propellant systems — Engineering Technical Article 1. Overview of ISO 29765 ISO 29765 specifies safety and performance requirements for propellant systems in space applications, including liquid and solid propellant handling, storage, transfer, and compatibility…
Engineering design principles for passive and active thermal control subsystems Thermal control is the single largest mass contributor to spacecraft after the primary structure. A 1 kg saving in thermal hardware can reduce launch cost by approximately USD 10,000–20,000 depending…
Design, qualification, and performance characterisation of space solar array systems Solar arrays are the most cost-effective power source for the vast majority of space missions. Modern triple-junction (3J) InGaP/InGaAs/Ge cells achieve beginning-of-life (BOL) efficiencies exceeding 32% under AM0 illumination —…
ISO Standard — Space systems — Safety materials — Engineering Technical Article 1. Overview of ISO 29661 ISO 29661 establishes requirements for safety materials used in space systems, covering material selection, flammability control, offgassing constraints, and contamination prevention. The standard…
ISO Standard — Space systems — Cleanliness — Engineering Technical Article 1. Overview of ISO 29664 ISO 29664 defines cleanliness requirements for space systems hardware, including acceptable levels of particulate and molecular contamination on critical surfaces. It establishes classification levels,…
ISO Standard — Space systems — EMC — Engineering Technical Article 1. Overview of ISO 29681 ISO 29681 establishes electromagnetic compatibility (EMC) requirements for space systems, covering both conducted and radiated emissions and susceptibility. The standard ensures that spacecraft subsystems…