ISO/TC 20/SC 16/WG 5 - Testing and evaluation

This document specifies methods for recording the time history of instantaneous sound pressure in several positions around rotor powered unmanned aircraft systems (UAS) with a maximum take-off mass (MTOM) of less than 150 kg in accordance with ISO 21895[9]. The UAS can be either electrically powered or fuel-powered. It is not applicable to the tilt-rotor or tilt-wing UAS. It does not account for the UAS noise certification or regulation This document can also be applied to measure the sound pressure from a UAS with either multiple rotors or a single rotor. This document specifies: a) recommendations and requirements for three different test facilities for the noise measurements of various categories of multirotor-powered UAS: — requirements and recommendations of UAS noise tests in anechoic chambers (Clause 7); — requirements and recommendations of UAS noise tests in anechoic wind tunnels (Clause 8); — requirements and recommendations of UAS noise tests in outdoor environments (Clause 9); b) requirements and recommendations for the configuration of noise measurement for multirotor-powered UAS in hover, vertical take-off and landing, and horizontal cruise; c) recommendations for the test configuration and procedures to minimize the influence of meteorological effects.

This document specifies the test conditions and methods to be used for the vibration testing of unmanned aircraft system (UAS, including unmanned aircraft and ground station) which applies to level II through V according to ISO 21895.

This document specifies the test requirements and methods for verifying the specified flight performance items of civil fixed-wing unmanned aircraft systems (UAS). This document is applicable to the category of civil small and light fixed-wing UAS, which applies to maximum take-off mass (MTOM) level I through V according to ISO 21895.

This document specifies the evaluation and test method for sharp injury to human body caused by rotor blades of civil small and light unmanned aircraft (UA), including injury scale, requirements, content, tests, results, etc. This document is applicable to evaluating and testing the sharp injury to human body caused by rotor blades of civil small and light UA (with maximum take-off mass between 0,25 kg to 4 kg, which are between the levels II and III as categorized by ISO 21895), including multicopter UA, unmanned helicopters and other rotor UA.

This document specifies test method to determine the operation ability of unmanned aircraft systems (UAS) at low-air-pressure conditions. This document is applicable to the category of civil small and light UAS, which applies to maximum take-off mass (MTOM) level II through V according to ISO 21895.

This document specifies the procedures for testing flight stability of a multi-copter unmanned aircraft system (UAS) and is applicable to multi-copter type UAS that can take-off and land vertically. A commercial multi-copter UAS weighing over 250 g to less than 150 kg is discussed in this document. Further, this document is applicable to military and civilian multi-copter UAS. However, quantitatively specific stability criteria for the test are not specified in this document.

This document provides a method for evaluating the resonance vibration frequency of the multi-copter unmanned aircraft (UA). This document specifies a method of designing the UA so as to avoid the resonance generated by the coincidence of the natural frequency of the UA body and the rotational frequency of the rotor. This document is applicable to multi-copter UA weighing less than 150 kg.

This document specifies test methods for civil electric multi-copter unmanned aircraft systems (UAS). This document is intended to be a general standard for testing the overall UAS functionality with the support of subsystems. It is applicable to the category of civil electric multi-copter UAS with maximum take-off mass (MTOM) level I to level V according to ISO 21895. The configuration control and subsystem (e.g. energy system and flight control system tests) test methods are out of the scope of this document. In addition, test methods for operations in snow and icing conditions are not included either, manufacturers have procedures identified to cope with flight in those conditions.