Browse Topic: Sound quality
Acoustic flight testing of rotorcraft often involves generating noise source hemispheres to gain an understanding about the aircraft's acoustic emissions. However, aerodynamically complex Urban Air Mobility and Future Vertical Lift vehicles may not maintain a steady aerodynamic state during flight, making source hemispheres measured using traditional linear arrays unreliable or difficult to interpret. To address this challenge, all emission angles need to be measured simultaneously. This has lead to the concept of the two dimensional 'snapshot' array layout. A mathematically defined microphone distribution was utilized to achieve uniform coverage on the source hemisphere. Within the chosen distribution, two lower microphone count distributions are embedded, allowing for a comparison of the effects of number of microphones. The array was deployed as part of a joint Army/NASA acoustic research flight test in July of 2024. Data were collected using an MD530F helicopter as the test vehicle, executing both steady and unsteady flight. Analysis of the array resolution is used to determine adequate channel count and spatially varying sensitivity to array density.
An extensive flight test campaign was recently completed, which aims to reduce the operational noise generated by helicopters in an effort to improve community acceptance. Using a ground-based microphone array, acoustic measurements were acquired on helicopters in the medium-sized vehicle weight class over a number of flight conditions including steady level flight, steady descents, and approaches. While data were collected across four helicopters, the Leonardo AW139 and Sikorsky S-76D will be the focus of this paper. Source noise hemispheres are computed for the steady test points, but the ground noise contours measured during approach conditions cover only a small portion of the area impacted by noise because of practical constraints on the size of the deployed array. Thus, the Noise Informed Community Environment Operations Planning System (NICEOPS) in conjunction with the flight test data was used to estimate how changes in the approach procedures impact noise exposure over a larger ground area. It was found that even small longitudinal accelerations can have a substantial influence on the noise generation processes during approach and must be modeled appropriately to develop new flight procedures which minimize the acoustic impact on the ground.
ABSTRACT This paper combines the synthesis and propagation of rotorcraft sounds, or auralizations, with their noise predictions and design optimization to incorporate human response into the process of creating low-noise rotorcraft. The NASA Auralization Framework is described and used to auralize the sounds of an AS350 helicopter main rotor at a ground observer from predicted acoustic pressure time histories. This paper uses spherical phase interpolation as part of the sound synthesis. This interpolation is an improvement over the linear phase interpolation described in previous work, which can introduce artifacts in the auralized sound. The effects of noise prediction source resolution are discussed. Two AS350 helicopter main rotor planform optimizations using certification noise metrics as the objective function are performed. One objective function is the Effective Perceived Noise Level metric and the other is the A-weighted Sound Exposure Level metric. The planform optimization includes determining trim state, predicting and propagating source noise, and changing design variables to affect the noise metric. Auralizations of the rotor sounds are computed, and due to their time domain nature, enable a more thorough exploration of sound quality metrics applied to the rotor sounds than traditional 1/3-octave predictions. These other metrics can be used to assess community annoyance and help develop human perception metrics that can potentially be incorporated into the helicopter design cycle.
The cabin and cockpit noise levels of a Royal Canadian Air Force CH-147F Chinook medium to heavy lift utility helicopter were evaluated in this study. The sound pressure levels were measured at nine aircrew locations through 43 unique and representative flight and ground conditions in accordance with the ISO 5129:2001 standard. Additionally, the performance of a combination of currently in service helmets and headsets were evaluated in accordance with the ANSI Standard S12.42. The hearing protection performance results were used in combination with the measured sound pressure levels to evaluate the performance of the hearing protection in the context of the CH-147F noise environment. Results showed that the David Clark headsets equipped with active noise reduction provided the most superior hearing protection. The maximum exposure limit duration was calculated for each microphone location, hearing protector performance and flight condition combination. It was found that the David Clark headsets provided sufficient protection for an unlimited duration of exposure for an individual with a properly fitted headset. It was also found that improperly fitted hearing protection could result in an increased risk of hearing damage after merely 18 seconds.
Items per page:
50
1 – 50 of 243