Simplified Estimating Method for Shock Response Spectrum Envelope of V-Band Clamp Separation Shock

Iwasa, Takashi; Shi, Qinzhong

doi:10.1299/spacee.1.46

Cited by 5 publications

(4 citation statements)

References 2 publications

(2 reference statements)

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“…In the simplified analysis method proposed in our previous paper (3) , the SRS due to V-band clamp separation shock was calculated from the response of the single D.O.F model, which represents the dominating pyroshock response of the spacecraft interface. Then, the major vibration mode of the spacecraft interface after the separation of the V-band clamp separation devices was assumed to be in the circular form so that the single D.O.F model can be applied.…”

Section: Outline Of the Simplified Analysis Methods Proposed In Our Prmentioning

confidence: 99%

“…Therefore, estimation of such severe pyroshock loadings on a spacecraft interface in the early design stages is essential to provide a necessary input for the determination of the pyroshock environment applied to sensitive electromechanical equipments and to establish the associated shock design requirements which are necessary to ensure the overall spacecraft reliability. In our previous paper (3) , a simplified analysis method for predicting the Shock…”

Section: Introductionmentioning

confidence: 99%

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Calculation Method for Flight Limit Load of V-band Clamp Separation Shock

Iwasa

Shi

2010

JSE

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A simplified calculation method for estimating a flight limit load of the V-band clamp separation shock was established. With this method, the flight limit load is estimated through addition of an appropriate envelope margin to the results acquired with the simplified analysis method proposed in our previous paper. The envelope margin used in the method was calculated based on the reviews on the differences observed between the results of a pyroshock test and the analysis. Using the derived envelope margin, a calculating formula of the flight limit load, which envelopes the actual pyroshock responses with a certain probability, was developed. Based on the formula, flight limit loads for several actual satellites were estimated and compared to the test results. The comparative results showed that the estimated flight limit loads appropriately envelope the test results, which confirmed the effectiveness of the proposed method.

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Section: Outline Of the Simplified Analysis Methods Proposed In Our Prmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Calculation Method for Flight Limit Load of V-band Clamp Separation Shock

Iwasa

Shi

2010

JSE

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“…The frequency of the major bending mode of the base plate determines the knee frequency of the SRS. 6) Figure 3(a) compares the SRS and frequency response at a hammering impact on the structure shown in Fig. 3(b).…”

Section: Srs and Major Vibration Modesmentioning

confidence: 99%

Study on the Tuning Method of Shock Test Condition for Spacecraft Instruments

Yanagase

Fukuda

Iwasa

et al. 2020

AEROSPACE TECHNOLOGY JAPAN

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Satellites are exposed to various shock environments during launch. Large shock responses can be generated on rocket separation or deployment of solar arrays and antennas when the strain energy of retained parts is released. Therefore, a test to verify the shock resistance of spacecraft components is necessary. Specially designed separation mechanisms or explosive devices are used to facilitate separation but such methods are expensive to test. To reduce this cost, alternative methods (such as the falling weight shock method) are used but the shock excitation source and structural propagation paths of the test apparatus are different from the operational configurations. This poses problems in making adjustments to match the specified Shock Response Spectrum (SRS) and often causes over-and under-testing, decreasing confidence in the test. This paper reports the results of our study to improve the accuracy of the SRSs of satellite components in shock testing. In the mechanical impact method implemented by the drop weight shock test, the SRS is usually adjusted by changing the material at the impact point, but this method is often inadequate. Rather than changing the hardness of the impact point we modified the SRS adjustment by altering the structure in the path of shock propagation.

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“…Iwasa et al. 17–19 proposed a simplified model to predict the pyroshock environment near the V-band clamp separation device and applied this method for estimating the flight limit load. Chang 20 discussed the pyroshock characteristics and environments based on various test measurements conducted on several JPL spacecraft programs.…”

Section: Introductionmentioning

confidence: 99%

Dynamic analysis of satellite separation considering the flexibility of interface rings

Cui

Yan

et al. 2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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Dynamic characteristics of satellite separation are synthetical results of various influencing factors. The improvement of research methods for designing and analyzing the separation system is of great importance for optimizing the dynamic performance of satellite separation. However, there is lack of an integrated approach for studying the satellite separation dynamics with full consideration of the attitude dynamics of satellites, the dynamic envelope of clamp band and the separation shock responses. This paper proposes a modeling and simulation method for comprehensively predicting the dynamic characteristics of satellite separation with the consideration of the flexibility of interface rings. A contrastive analysis of separation dynamics is carried out to determine the effects of the flexible interface rings on satellite separation dynamic characteristics. Subsequently, parametric studies on dynamics of satellite separation are performed, and research emphasis is placed on investigating the effects of position relative to the separation plane, the preload of clamp band, the friction coefficient and the pyroshock of explosive bolts on separation shock responses. The research method proposed in this paper provides a reference for the initial engineering design of the clamp band joint of satellite separation system.

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Simplified Estimating Method for Shock Response Spectrum Envelope of V-Band Clamp Separation Shock

Cited by 5 publications

References 2 publications

Calculation Method for Flight Limit Load of V-band Clamp Separation Shock

Calculation Method for Flight Limit Load of V-band Clamp Separation Shock

Study on the Tuning Method of Shock Test Condition for Spacecraft Instruments

Dynamic analysis of satellite separation considering the flexibility of interface rings

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