During liftoff of a launch vehicle, the acoustic pressure fluctuations caused by the engine exhaust gases produce high noise levels inside the fairing cavity and can damage the payload. Work presented in this paper investigates the nature of the external acoustic pressure distribution, in the frequency range from 50 to 400 Hz, on the fairing of a launch vehicle during liftoff. The acoustic pressure acting on a representative small launch vehicle fairing was estimated from the complex acoustic field generated by the rocket exhaust during liftoff. The estimation procedure involved the use of a unique source allocation technique which considered acoustic sources along the rocket engine exhaust flow. Numerical and analytical results for the acoustic loads on the fairing agree well. Nomenclatureof sound in the exhaust flow, m=s D e = nozzle exit diameter, m d = projected distance, m E = total number of surface elements E i = element shape function F = thrust of rocket engine, N f = frequency, Hz f b = frequency bandwidth, Hz G = Green's function H = coefficient matrix H m z = Hankel function or Bessel function of the third kind of mth order and argument, z I N = identity matrix J m z = Bessel function of the first kind of mth order and argument, z k = wave number L P;b; = sound pressure level on the circumference of the vehicle, dB L P;OA; = overall sound pressure level, dB L w = overall acoustic power level, dB L w;b = sound power level for each frequency band, dB M = total number of terms M e = Mach number m = term number n = number of nozzles, and particle outward velocity direction P = field point or observation point p, p = acoustic pressure, Pa p i = incident sound pressure, Pa p i = constant nodal pressure on ith element, Pa p o = incident sound pressure amplitude, Pa p s = scattered sound pressure, Pa p t a = total sound pressure at the surface of a cylinder, dB p 0 = spatially dependent factor Q = projection point, and integration point on the boundary Q s = source strength, m 3 =s R = distance between the integration point and observation point, and resultant oblique distance, m r = radial distance, and distance of the source from the nozzle exit, m r P = distance of observation point, m r Q = distance of integration point, m S = cylinder surface area, m 2 U e = exhaust velocity, m=s u n = outward normal particle velocity, m=s V = volume of a problem geometry, m 3 V e = exterior volume, m 3 V i = interior volume, m 3 W b = acoustic power for each frequency band, Watt Wf = sound power per Hz, Watt W OA = overall acoustic power, Watt X = X component of the cylindrical coordinate axes x 1 = axial distance of the observation point on the vehicle from the nozzle exit, m x 2 = vertical distance from the nozzle exit of the sources along the flow axis, m x 3 = distance of the source from the vehicle axis along the flow axis, m Y = Y component of the cylindrical coordinate axes Z = Z component of the cylindrical coordinate axes z = elevation height, m = incline angle between the line joining the observation point to ...
Severe acoustics loading, which occurs during the flight mission of launch vehicles, is often responsible for damage to the payload inside the fairing compartment. The prediction of the acoustic loads on the payload fairing generated by large propulsion devices requires the use of analytical and numerical methods to identify the acoustic sources and the spectrum of the acoustic loads. The work presented in this paper investigates the nature of the external acoustic pressure excitations on the fairing in the low-frequency range of 50 to 400 Hz during the liftoff of a launch vehicle. The acoustic pressure excitation acting on a representative small launch vehicle fairing was estimated from the complex acoustic field generated by the rocket engine exhaust gases. The estimation procedure involved the use of a nonunique source allocation technique, which considered acoustic sources along the rocket engine exhaust flow. Numerical and analytical results for the acoustic loads on the fairing agree well. Nomenclatureradius, m a e = speed of sound in the exhaust flow, m∕s a o = speed of sound in air, m∕s b = frequency band number C = diagonal matrix CP = solid angle, rad D e = nozzle exit diameter, m DI = directivity index, dB f = frequency, Hz H = coefficient matrix H m z = Hankel function or Bessel function of the third kind of mth order and argument z I N = identity matrix J m z = Bessel function of the first kind of mth order and argument z k = wave number, rad∕m L p;OA;seg;b;ϕ = overall sound pressure level, dB L w = overall acoustic power level, dB L w;seg = sound power level for each segment, dB L w;seg;b = sound pressure level for each segment in each frequency band, dB L w;seg;b;ϕ = sound pressure level on the circumference of the vehicle, dB M = total number of terms m = term number N = total number of point sources n = source number and number of nozzles P = field point or observation point P 0 = spatially dependent factor p, p = acoustic pressure, Pa p t a = total sound pressure at the surface of a cylinder, Pa p i , p i = incident sound pressure, Pa p s = scattered sound pressure, Pa Q = projection point and integration point on the boundary Q s = source strength, m 3 ∕s R = distance between the integration point and observation point, and resultant oblique distance, m r = radial distance and distance of the source from the nozzle to the center of each segment, m U e = exhaust velocity, m∕s Wf = sound power per Hz, W Wr = sound power as a function of distance between the nozzle exit and the source, W W OA = overall acoustic power, W W seg;b = acoustic power of each source for each frequency band, W X = X component of the cylindrical coordinate axes x t = core length, m x 1 = axial distance of the observation point on the vehicle from the nozzle exit, m x 2 = vertical distance from the nozzle exit of the sources along the flow axis, m x 3 = distance of the source from the vehicle axis along the flow axis, m Y = Y component of the cylindrical coordinate axes Z = Z component of the cylindrical coordinate axes z =...
During the launch of space vehicles, there is a large external excitation generated by acoustic and structural vibration. This is due to acoustic pressure fluctuations on the vehicle fairing caused by the engine exhaust gases. This external excitation drives the fairing structure and produces large acoustic pressure fluctuations inside the fairing cavity. The acoustic pressure fluctuations not only produce high noise levels inside the cavity but also cause damage such as structural fatigue, and damage to, or destruction of, the payload inside the fairing. This is an important problem because one trend of the aerospace industry is to use composite materials for the construction of launch vehicle fairings, resulted in large-scale weight reductions of launch vehicles, but increased the noise transmission inside the fairing. This work investigates the nature of the external acoustic pressure distribution on a representative small launch vehicle fairing during liftoff. The acoustic pressure acting on a representative small launch vehicle fairing was estimated from the complex acoustic field generated by the rocket exhaust during liftoff using a non-unique source allocation technique which considered acoustic sources along the rocket engine exhaust flow. Numerical and analytical results for the acoustic loads on the fairing agree well.
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