• 소음진동
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• 제8권1호
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• pp.180-186
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• 1998

Vibration test fixture is used in random vibration control testing. The specified reference spectrum should be transmitted equally to the specimen attachment points on the fixture. In most practical cases, however, spectrum at each of specimen attachment points may be quite different from the specified reference spectrum because of the dynamic characteristics of vibration test fixture. This paper proposes the method of experimental dynamic modification of fixture system for vibration test so that the reference spectrum can be transmitted to the specimen attachment points without distortion. The stiffness of mounts of specimen and the thickness of fixture are considered as design variables. The frequency response functions of specimen used for input data are obtained from vibration testing, and the frequency response functions of fixture are obtained from finite element modeling. The sensitivities of frequency response functions at specimen attachment points to the mount stiffness are derived from synthesis method of transfer function. And the sensitivities to the thickness of fixture are also derived from finite element modeling. The presented method is verified by computer simulation and vibration testing.

• 한국융합학회논문지
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• 제12권1호
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• pp.205-210
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• 2021

본 연구에서는 대상 시스템의 목표 값과 동일한 응답 특성을 얻기 위한 가진 입력 데이터의 생성 방법에 대해 연구하였다. 입력-출력 사이의 전달함수인 주파수 응답함수를 사용하여 가진 입력을 재구성하는 방법에 대해 논하였다. 이를 위하여 수치모델로 세 점에서 부싱으로 연결된 엔진 마운트 모델을 사용하였다. 3 방향의 입력에 대한 응답을 시험값과 비교하고, 목표 값과 동일한 응답을 얻을 수 있도록 가진 입력을 보정하였다. 오차함수를 계산한 다음 이 값이 수렴하는지 판단하여 반복 시뮬레이션을 수행하였다. 반복과정을 통해 시험과 동일한 응답을 가질 수 있도록 조정된 가진 입력 값을 얻을 수 있었다.

• Advances in aircraft and spacecraft science
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• 제5권2호
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• pp.187-204
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• 2018

The sine sweep base excitation test campaign is a major milestone in the process of mechanical qualification of space structures. The objectives of these vibration tests are to qualify the specimen with respect to the dynamic environment induced by the launcher and to demonstrate that the spacecraft FE model is sufficiently well correlated with the test specimen. Dynamic qualification constraints lead to performing base excitation sine tests using a sine sweep over a prescribed frequency range such that at each frequency the response levels at all accelerometers, load cells and strain gages is the same as the steady state response. However, in practice steady state conditions are not always satisfied. If the sweep rate is too high the response levels will be affected by the presence of transients which in turn will have a direct effect on the estimation of modal parameters. A study funded by ESA and AIRBUS D&S was recently carried out in order to investigate the influence of sine sweep rates in actual test conditions. This paper presents the results of this study along with recommendations concerning the choice of methods.

• 항공우주시스템공학회지
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• 제16권4호
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• pp.88-94
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• 2022

진동모드 측정시험은 대상 시험체의 고유진동 특성을 측정하는 시험으로써, 측정된 고유모드 특성은 수치해석 결과와의 비교를 통해 수치해석의 신뢰성을 검증하고, 필요시 동특성 해석에 사용하는 시험체의 수치해석 모델을 보완하는데 활용된다. 본 연구에서는 진동모드 측정시험과 유한요소 모델을 이용한 수치해석을 통해서 외부연료탱크의 고유주파수와 고유모드를 각각 구하고, 그 결과를 비교하여 항공기 전기체 모델에 적용하고자 하는 외부연료탱크의 수치해석 모델에 대한 신뢰성을 검증하고자 한다. 시험체의 진동모드 측정을 위해 번지코드를 이용하여 시험체에 대한 자유경계 조건을 모사하였다. 그리고, 시험체에 3축 가속도계를 설치하고 임팩트 해머로 가진하여 시험체의 응답특성을 측정하였다. 시험결과로, 응답 가속도에 대한 주파수 응답해석을 수행한 후, 시험체의 고유주파수와 해당 진동모드를 확인하였다. 그리고, 시험과 수치해석을 통해 구해진 고유주파수와 진동모드를 비교하여 수치해석 모델에 대한 신뢰성을 검증하였다.

• Journal of Biosystems Engineering
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• 제36권6호
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• pp.476-483
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• 2011

The aerial application using an unmanned helicopter has been already utilized and an attitude controller would be developed to enhance the operational convenience and safety of the operator. For a preliminary study of designing flight controller, a state space model for an RC helicopter would be identified. Frequency sweep flight tests were performed and time history data were acquired in the previous study. In this study, frequency response of the flight test data of a small unmanned helicopter was analyzed by using the CIFER software. The time history flight data consisted of three replications each for collective pitch, aileron, elevator and rudder sweep inputs. A total of 36 frequency responses were obtained for the four control stick inputs and nine outputs including linear velocities and accelerations and angular velocities in 3-axis. The results showed coherence values higher than 0.6 for every primary control inputs and corresponding on-axis outputs for the frequency range from 0.07 to 4 Hz. Also the analysis of conditioned frequency response showed its effectiveness in evaluating cross coupling effects. Based on the results, the dynamic characteristics of the model helicopter can further be analyzed in terms of transfer functions and the undamped natural frequency and damping ratio of each critical mode.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 추계학술대회논문초록집
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• pp.363.2-363
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• 2002

The spectrum of impulse response signal from an impulse hammer testing is widely used to obtain frequency response function(FRF) of the structure. However the FRFs obtained from impact hammer testing have not only leakage errors but also finite record length errors when the record length for the signal processing is not sufficiently long. The errors cannot be removed with the conventional signal analyzer which treats the signals as if they are always steady and periodic. (omitted)

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 춘계학술대회논문집
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• pp.71-77
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• 2002

The spectrum of impulse response signal which is obtained from an impulse hammer testing is used for frequency response function, nevertheless it has serious faults when the record length for the signal processing is not very long. The faults cannot be avoided with the conventional signal analyzer that is processing all the signals as if they are always periodic. The signals generated by the impact hammer are undoubtedly non-periodic because of the damping, and are acquired for limited recording time due to the memory as well as the computation performance of the signal analyzer. This paper will make clear the relation between the faults and the length of recording time, and propose the way for solving the faults.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 추계학술대회논문집
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• pp.623-629
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• 2002

The spectrum of impulse response signal from an impulse hammer testing is widely used to obtain frequency response function(FRF) of the structure. However the FRFs obtained from impact hammer testing have not only leakage errors but also finite record length errors when the record length for the signal processing is not sufficiently long. The errors cannot be removed with the conventional signal analyzer which treats the signals as if they are always steady and periodic. Since the response signals generated by the impact hammer are transient and have damping, they are undoubtedly non-periodic. It is inevitable that the signals be acquired for limited recording time, which causes the finite record length error and the leakage error. In this paper, the errors in the frequency response function of multi degree of freedom system are formulated theoretically. And the method to remove these errors is also suggested. This method is based on the optimization technique. A numerical example of 3-dof model shows the validity of the proposed method.

• 한국추진공학회지
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• 제2권2호
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• pp.88-98
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• 1998

충격반응 스펙트럼 시험을 수행하기 위한 가진기의 파형이 웨이브레트들을 이온하여 시험규격에서 규정한 충격반응 스펙트럼을 만족하도록 합성된다. 웨이브레트의 매개변수는 중간주파수, 진폭, 반파의 개수, 지연시간 그리고 극성이다. 시험규격에서 규정한 충격반응 스펙트럼과 정합이 되도록 각 웨이브레트의 진폭은 반복하여 조절된다. 이렇게 합성된 파형은 가진기를 이용한 충격반응 스펙트럼 시험의 참조 가속도 파형으로 간주된다. 본 연구에서는 충격 지속시간을 길게 하여 첨두치가 작은 파형을 제안한다. 몇 가지 사례를 통하여 이 방법의 유용성이 확인되었다.