The instrument shall be designed and tested to demonstrate that it conforms to the general requirements laid down for equipment to be flown on board EXPRESS Pallet defined in AD 1.
The instrument shall perform as intended on-orbit for three years.
The engineering model shall permit tbd hours ground operation. This lifetime is to be achieved with a minimum of refurbishment and maintenance.
Instrument reliability and maintainability requirements are defined in GPQ-010-PSA-107 (AD 4). The user shall demonstrate that his instrument is designed such that no potential malfunction can propagate over its interfaces with the CPD (if applicable), the Express Pallet Adapter, the EXPRESS Pallet, the International Space Station or the NSTS Shuttle Orbiter.
The maximum storage time of the instrument is five years without refurbishment.
Safety and materials requirements for the instrument, together with the corresponding safety certification process, are defined in AD 3. The user shall deliver the necessary inputs to the Safety Data Packages for Safety Reviews. These packages shall be submitted for review and integration into the overall safety data package.
The instrument shall be designed so as to minimise the impact, during its operation in orbit, of any disturbance to the microgravity environment of the ISS and the EXPRESS Pallet in particular. In this respect, the ISS Microgravity Control Plan shall be taken as the leading reference (RD 2) unless and until final requirements definitions are available.
Surfaces of the instrument shall be designed for easy cieaning on the ground. Appropriate workmanship standards shall be applied as laid down in the applicable quality assurance documents.
The instrument shall be designed for easy operation both on the ground and in flight. Operation, servicing and maintenance activities shall be defined such as to minimise the required flight and ground crew training and skills. Operations manuals, maintenance procedures and check-out procedures shall be established and provided.
The design environments below encompass all conditions to which the instrument and its GSE may be subjected over their lifetime.
The instrument shall be designed to withstand all the relevant environmental conditions to which it shall be exposed on the ground, during ground transportation, ground handling, launch, ascent, on-orbit, descent and landing (nominal and emergency) as specified in AD 1.
The instrument shall be tested and operated under normal clean laboratory conditions on the ground.
The initial strength of any purpose built equipment shall be based on the load factors specified in AD 1, multiplied by suitable design safety factors defined in AD 3.
The strength of all instrument structures and associated equipment shall be based on the flight loads multiplied by suitable design safety factors, taking into account applicable cases (such as whether metallic/non-metallic materials, non-pressurised etc.) and the related flight and ground safety load definitions.
These and related requirements for stress analysis, stiffness, material compatibility, fracture control etc. shall be considered in line with what is required in the applicable documentation.
The ground handling environment shall typically be maintained at
temperature -10°C to +50°C (TBC) RH 40 to 80% Cleanliness class 100,000
The storage and transport environment (air, road) shall be compatible with the demands of the instrument and its GSE, mounted within their storage/transport containers.
The relevant documentation given in Section User Interfaces with the Space Station Programme shall provide the mandatory baseline for all applicable requirement specifications including those not explicitly addressed in the above context (eg; on-orbit accelerations, induced vibrations, acoustics, atmosphere, illumination, radiation, contamination). The flight environment shall be assumed at:
temperatures of -20°C to +60°C operational (tbc)
temperatures of -60°C to +80°C non-operational (tbc).
The instrument requirements for the selection of materials and processes are given in AD 3. The user shall submit for approval a data package consisting of parts, materials and processes lists in compliance with the requirements.
The instrument requirements for the selection of EEE parts are given in AD 2.
The instrument structures shall comply with the requirements
of PSS-01-401, ESA
Fracture control requirements.
In addition, the following requirements apply:
Non-destructive inspections shall be performed in accordance with NASA-MSFC-STD-1249 Standard NDE Guidelines and Requirements for Fracture Control Programs (AD6). The etching requirement before penetrant inspection is not applicable to rolled threads
Acceptance of the hardware and/or software will be based on the accompanying Acceptance Data Package(s) (ADPs).
SP1201