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  • BSI Flex 1903 v2:2024-06 community preview

    This is an interactive version 2 of BSI Flex 1903. The aim of the standard is to create a lexicon of standard terms and acronyms used in this sector. Please note, content is still undergoing internal review and there may be minor changes at full publication.

    We welcome your engagement and comments on this version to help inform the development of the standard. We would also welcome general feedback including what terms could be considered for future versions and these can be made through our dedicated feedback page .

Terms and definitions

3.1 Terms and definitions
D

  1. decentralized remote crew  

    remote crew members separated from each other to the extent that communications between them rely entirely on electronic means   NOTE An example of decentralized remote crew is  airspace observer beyond visual line of sight (AO-BVLOS) operations (3.1.10), where the remote pilot communicates with the  airspace observer(s) (3.1.9) via private mobile radio, mobile phone or voice over internet protocol (VoIP) (3.1.146).   Previous version: 1.0 Release date: September 2023 fl
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  2. deconfliction  

    arrangement, negotiation, coordination, and prioritization of intended operational volumes, routes, or trajectories to minimize the likelihood of airborne conflicts between operations   NOTE “Strategic deconfliction” are actions taken prior to take-off while “tactical deconfliction” are actions taken once an aircraft is airborne. “Collision avoidance” (3.1.40)  refers to last resort actions or manoeuvres   [SOURCE: ICAO Unmanned Aircraft Systems Traffic Management (UTM) – A C
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  3. depth of discharge (DOD)  

    percentage of a battery’s capacity that has been discharged relative to its maximum capacity NOTE DOD is typically expressed as a percentage value (0%–100%).  
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  4. design verification  

    evaluation of an implementation of design requirements to determine that the requirements have been met NOTE 1 In other words, "Did we design the aircraft/system/function/item in accordance with the requirements?” NOTE 2 The requirements include any applicable regulatory and safety requirements.  NOTE 3 The design verification process is utilized by European Union Aviation Safety Agency (EASA) as a means of demonstrating compliance with “uncrewed aircraft system (UAS)” (3.1.137
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  5. detect and avoid (DAA)  

    capability to see, sense or detect conflicting traffic or other hazards and take the appropriate action   NOTE 1 UK CAA, CAP 722, Unmanned aircraft system operations in UK airspace – Policy and guidance [13] describes the following as necessary DAA functions: detect and avoid traffic (aircraft in the air and on the ground) in accordance with the Rules of the Air; detect and avoid all airborne objects, including gliders, hang-gliders, paragliders, microlights, balloons,
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  6. deterministic  

    characteristic of a system or algorithm such that, when functioning as designed and given identical inputs, it is capable of producing different outputs
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  7. direct command and control (C2) link  

    data link architecture established between an uncrewed aircraft (UA) (3.1.134) and its command unit, which is self-contained, does not require any third-party services, and enables real-time command and control NOTE Typically relies on a wireless communication system such as radio frequency (RF) (3.1.114) communication with devices located within radio line of sight (3.1.115) of one another.   Previous Version: 1.0 Release date: September 2023  direct command and control link

  8. distributed operations  

    operation where the remote pilot (3.1.118) is not physically in the same local operating area as the uncrewed aircraft take-off and landing zone (TOLZ) (3.1.130) and is reliant on inputs from other flight crew, sensors or instrumentation to assess relevant operating conditions prior to and during flight   NOTE Local operating conditions would include items such as current local weather or the status of the take-off and landing zone (TOLZ) (3.1.130).  
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E

  1. electric/hybrid propulsion system (EHPS)  

    combination of technologies that involve the use of electric motors or a combination of electric motors and combustion engines to form a system which produces lift, thrust or power for flight   NOTE 1 An EHPS might include but is not limited to: a) electric motors; b) turbine engines; c) piston engines; d) generators; e) electrical power generation; f) distribution; g) wirings; h) propulsion batteries; i) integrated fans; j) cooling systems; k) controllers; l)
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  2. EHPS control system  

    system or device that controls, limits, monitors, or protects the operation of the electric/hybrid propulsion system (EHPS) (3.1.59) or a sub-system of the EHPS [Source: EASA Special Condition, SC E-19, Electric / Hybrid Propulsion System Issue 1, April 2021] [21]
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  3. electric motor controller  

    device or devices that serves to govern the operation of an electric motor   NOTE It could include a manual or automatic means for powering on or stopping the motor, selecting direction of rotation, selecting, and regulating motor speeds, regulating, or limiting the torque, and protecting against overloads and faults. The inverter function is often a part of the motor controller.   [SOURCE: ASTM, F3338-18: Standard specification for design of electric propulsion units for gen
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  4. electric motor  

    machine that converts electrical power into rotational mechanical power NOTE This definition is provided in the context of electric motor use for aircraft propulsion. [SOURCE: ASTM F3338 – 18: Standard Specification for Design of Electric Propulsion Units for General Aviation Aircraft, October 2021] ) [15]  

  5. electric propulsion unit (EPU)  

    unit comprising at a minimum an electric motor, and the associated electronic controllers, disconnects, wiring, and sensors [SOURCE: ASTM, F3338-18: Standard specification for design of electric propulsion units for general aviation aircraft] [22]
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  6. electromagnetic compatibility (EMC)  

    ability of equipment or a system to function satisfactorily in its electromagnetic environment without introducing intolerable electromagnetic disturbances to anything in that environment [SOURCE: International Electrotechnical Commission (IEC) 60050 - International Electrotechnical Vocabulary] ) [16]  
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  7. electromagnetic interference (EMI)  

    degradation in the performance of equipment or transmission channel or a system caused by an electromagnetic disturbance   NOTE 1 EMI sources can be either manmade (intentional or unintentional) or naturally occurring phenomena such as lightning or solar flares. NOTE 2 The three main types of EMI are radiated EMI, conducted EMI and coupled EMI. NOTE 3 On an uncrewed aircraft (UA) (3.1.134), undesirable EMI effects include, but are not limited to, collision avoidance (3.1.40).
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  8. electronic conspicuity (EC)  

    technologies that support the function of cooperative surveillance systems   Previous Version: 1.0 Release date: September 2023 range of technologies that support the function of cooperative surveillance systems
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  9. energy margin  

    margin available between the available energy and the energy that is estimated to be required to complete a flight
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  10. energy storage device (ESD)  

    device that stores some form of energy that can be drawn upon at a later time to perform some useful operation   NOTE Energy storage devices include, but are not limited to, batteries, fuel cells and capacitors.   [SOURCE: ASTM, F2840-14: Standard practice for design and manufacture of electric propulsion units for light sport aircraft] [24]
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  11. energy storage system (ESS)  

    onboard system whose main function is to provide an aircraft with accessible energy for safe flight and landing   NOTE 1 ESS components include, but are not limited to, battery modules, the associated battery management system (BMS) (3.1.29), and all the associated wires, cabling and connections/terminals. NOTE 2 The ESS includes a means by which limits are placed on accessible energy, e.g. due to cell temperature or state of charge, it also provides predictions of battery states
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  12. eVTOL  

    type of VTOL-capable aircraft (VCA) (3.1.143) which utilizes electric/hybrid propulsion systems and is generally regarded as an aircraft intended for the carriage of passengers and/or cargo within the context of advanced air mobility   Previous Version: 1.0 Release date: September 2023 vertical take-off and landing (VTOL) (3.1.87) aircraft which utilizes electric/hybrid propulsion systems NOTE An eVTOL is generally considered to be an aircraft intended for the carriage of pa
    • Updated
F

  1. final-approach and take-off area (FATO)  

    defined area over which the final phase of the approach manoeuvre to hover or landing is completed and from which the take-off manoeuvre is commenced   NOTE 1 A vertiport (VPT) (3.1.144) is expected to include at least one FATO. NOTE 2 The FATO should provide an area free of obstacles (except for essential objects which because of their function are located on it), and of sufficient size and shape to ensure containment of every part of the design VTOL-capable aircraft (VCA) (3.1.1
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  2. flight volume  

    volume of airspace that encompasses the entire operation, with sufficient buffer for any operational movement around the flight path, due to navigational errors, expected weather conditions and any other reason for deviating from the flight path   NOTE 1 Refers to normal operations and is surrounded by the contingency volume (3.1.44) that provides a buffer within which contingency procedures are activated. NOTE 2 Similar in concept to the EASA term “flight geography”, which refers
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  3. flightworthy  

    uncrewed aircraft system (UAS) (3.1.137) status when the aircraft and all its associated elements are designed, manufactured and maintained to a standard and/or means of conformance deemed acceptable by the national aviation authority, but does not necessarily meet the International Civil Aviation Organization (ICAO) definition of being airworthy (3.1.13)
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  4. fly-by-light  

    flight control system with signalling by optical fibres   NOTE 1 In a fly-by-light system, the electrical wiring used in fly-by-wire (3.1.75) systems is replaced with optical fibres, offering advantages such as increased data transmission speed, electromagnetic interference (EMI) (3.1.65) immunity, and potentially reduced weight. NOTE 2 On fly-by-light aircraft, flight controls are typically implemented according to complex control laws and logics.   [SOURCE: CUP, The Ca
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  5. fly-by-wire  

    flight control system with electronic signalling   NOTE 1 In a fly-by-wire system, traditional mechanical linkages are replaced with electrical wiring, offering advantages such as enhanced control precision, flexibility in aircraft design, and the ability to incorporate advanced control features. NOTE 2 On fly-by-wire aircraft, flight controls are typically implemented according to complex control laws and logics.   [SOURCE: CUP, The Cambridge aerospace dictionary] [27]
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