[논문]우주발사체 발사 시 음향하중 저감을 위한 발사대 설계

Tsutsumi, Seiji

doi:10.7776/ask.2020.39.4.331

우주발사체 발사 시 음향하중 저감을 위한 발사대 설계
Design of launch pad for mitigating acoustic loads on launch vehicle at liftoff 원문보기

한국음향학회지= The journal of the acoustical society of Korea, v.39 no.4, 2020년, pp.331 - 341

Tsutsumi, Seiji (Japan Aerospace Exploration Agency)

초록
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우주발사체는 발사 시 추진장치에서 발생하는 고강도 소음에 의한 음향하중의 영향을 받는다. 로켓소음은 발사체와 페이로드 내 전자 및 기계 부품의 손상 및 오작동을 유발할 수 있기 때문에 음향하중의 예측 및 저감은 설계에 있어 중요한 고려사항이다. 본 논문에서는 로켓 소음의 생성 및 발사대의 음향설계 기법에 대한 최신 연구동향을 논하였다. 특히, 새로운 발사대 설계 방법론의 예로서 일본 Epsilon 로켓 발사대의 개발과정을 기술하였다. 전산유체역학 모사 및 1/42 축소모형 실험을 통하여 설계된 발사대의 음향하중 저감 효과를 Epsilon 로켓의 실제 비행 데이터 분석을 통하여 검증하였다.

Abstract ▼ AI-Helper

At liftoff, launch vehicles are subject to harmful acoustic loads due to the intense acoustic waves generated by propulsion systems. Because these waves can cause electronic and mechanical components of launch vehicles and payloads to fail, predicting and mitigating acoustic loads is an important design issue. This article presents the latest information about the generation of acoustic waves and the acoustic design methods applicable to the launch pad. The development of the Japanese Epsilon solid launcher is given as an example of the new methodology for launch pad design. Computational fluid dynamics together with 1/42 scale model testing were performed for this development. Effectiveness of the launch pad design to reduce acoustic loads was confirmed by the post-flight analysis.

주제어

표/그림 (11)

그림 Fig. 1. Typical time history of vibration measured on launch vehicle.^[1]
그림 Fig. 2. Schematic of typical launch pad.
그림 Fig. 3. (Color available online) Acoustic wave generated above ML.^[6]
그림 Fig. 4. (Color available online) Acoustic wave generated due to jet impingement on deflector.^[8]
그림 Fig. 5. Procedure of acoustic design.
표 Table 1. CFD methods used in development of Epsilon solid launcher.
그림 Fig. 6. Schematic of test stand used in detailed design for Epsilon solid launcher.
그림 Fig. 7. Baseline configuration of launch pad for Epsilon solid launcher.
그림 Fig. 8. (Color available online) CFD result of baseline shape for detailed design.
그림 Fig. 9. (Color available online) Launch pad for Epsilon solid launcher.
그림 Fig. 10. Microphone measurements of Epsilon's first flight.

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문제 정의

On the other hand, vibroacoustics is concerned with the transmission of acoustic waves through the fairing structure and the effects on the satellite inside. This article focuses on aeroacoustics and introduces the latest studies on the mechanism of acoustic generation and design methodologies of the launch pad. Then, the example of launch pad design for the Epsilon solid launcher, developed by the Japan Aerospace Exploration Agency (JAXA), is introduced with post-flight analysis.
This article has presented the latest information of the mechanism of acoustic waves generated by launch vehicles at liftoff, as well as introducing acoustic design methods for the launch pad. Then, as an example, development of the launch pad for the Japanese Epsilon solid launcher is outlined.
The aerodynamic vibration is generated by oscillating shock waves, a turbulent boundary layer, and separated flow behind protuberances. This study focuses on the acoustic loads that appear at liftoff.

제안 방법

1, the effect of the Mach wave radiation from the free jet can be reduced by raising the launch mount. Based on the CFD results and structural design, the shape of the launch pad in the detailed design was determined by considering the installation on the existing launch pad. Finally, the configuration shown in Fig 7(b) was obtained as the baseline for detailed design.
The turbulent boundary layer on the deflector was computed by RANS, and off-wall region were computed by LES. Convective terms were evaluated by a high-resolution method with 6^th order accuracy, and the cut-off frequency reached 800 Hz using 2048 cores of the JSS (20 TFlops) for 2 to 5 months. Validation of CFD2 was performed using the results of the subscale model test.
By increasing the curvature of the deflector and gradually changing the flow direction, the tail shock waves are weakened, and eventually the acoustic level can be reduced.^[8,35] In the preliminary design, the effect on the acoustic level was evaluated by CFD for three explanatory variables: (1) the height of the launch mount, (2) the initial inclination angle of the deflector, and (3) the curvature of the deflector. About twenty deflector shapes were evaluated.
A triangular roof was attached to the ground flame duct to reduce the reflection of the Mach waves radiated from the free jet.The deflector inside the ground flame duct was designed based on the CFD results obtained in the preliminary design. The launch pad of the Epsilon does not have a large underground flame duct or water injection system, resulting in a compact launch pad compared to others in the world.
The application range of the empirical method was known to be limited, so CFD methods listed in Table 1 were used heavily in both the preliminary and detailed designs. The detailed design also used subscale model testing. Considering the similarity of acoustic spectra, a 1/42-scale solid motor was employed in that test.
Conventionally, the preliminary stage of design uses the empirical method, a simplified model test, and past flight data if available. The detailed design mainly involves a subscale model test.
Convective terms were evaluated by a high-resolution method with 6^th order accuracy, and the cut-off frequency reached 800 Hz using 2048 cores of the JSS (20 TFlops) for 2 to 5 months. Validation of CFD2 was performed using the results of the subscale model test. Prediction accuracy of approximately 4 dB in OASPL was confirmed.

대상 데이터

^[8,35] In the preliminary design, the effect on the acoustic level was evaluated by CFD for three explanatory variables: (1) the height of the launch mount, (2) the initial inclination angle of the deflector, and (3) the curvature of the deflector. About twenty deflector shapes were evaluated.

이론/모형

The empirical method described in NASA SP-8072^[4] is used in the preliminary design. This method was based on results obtained from static-firing tests and flights.
CFD2 used in the detailed design requires fidelity rather than throughput. The zonal hybrid LES / Reynolds-averaged Navier-Stokes (RANS) method was employed. The turbulent boundary layer on the deflector was computed by RANS, and off-wall region were computed by LES.

성능/효과

In addition, the results were significantly lower than that of the M-V. OASPL measured outside the payload fairing of the Epsilon was at most 144.4 dB, which means that the acoustic environment was reduced by about 13 dB compared with the M-V. Although the difference of the acoustic level due to the motor size was 3 dB as mentioned earlier, the acoustic level could be reduced by 10 dB through the improvement of the launch pad.

후속연구

While the former is thought to be generated by the interaction between the vortex structure of the jet shear layer and a plate shock wave appeared at the jet impingement region, the interaction of the vortex structure with tail shock waves generated inside the wall jet also contributes to the former acoustic wave.^[9-12] However, the cause of the waves due to jet impingement has not been clarified, and further research is necessary. At the launch pad shown in Fig.
In addition, there is a possibility for engineers to achieve further reduction of the acoustic loads by modifying the shape of the launch pad. I hope this article will help to promote cooperation between Korea and Japan in the research and development of liftoff acoustics.
The author wishes to thank Dr. Kyoichi Ui (JAXA) and Dr. Tatsuya Ishii (JAXA) for their help to the research and development of the launch pad for the Epsilon solid launcher.

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