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ISO 5305:2024

Current Revision

Noise measurements for UAS (unmanned aircraft systems)

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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.


SDO ISO: International Organization for Standardization
Document Number ISO 5305
Publication Date Not Available
Language en - English
Page Count
Revision Level
Supercedes
Committee ISO/TC 20/SC 16
Publish Date Document Id Type View
Not Available ISO 5305:2024 Revision