Dynamics of nose cone jettisoning from spinning rockets

Babu, K. Kamal; Lochan, Rajeev

doi:10.1243/0954410001531926

Cited by 3 publications

(2 citation statements)

References 9 publications

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“…A method for limiting cross-range dispersion of spinning missiles was introduced in [11] and the effect of lift non-averaging on the dispersion of a spinning missile was discussed in [12]. The dynamic analysis of a nose cone, jettisoned from a spinning rocket, was investigated in [13]. An analytical approach to quantify the dynamic effects of a lateral square impulse, disturbing a projectile during free flight, was presented in [14].…”

Section: Introductionmentioning

confidence: 99%

Multiple-input describing function technique applied to design a single channel ON-OFF controller for a spinning flight vehicle

Nobahari

Mohammadkarimi

2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this study, the guidance and control problem of a single-channel spinning missile is investigated. The missile utilizes a single ON-OFF actuator to drive a pair of control surfaces (e.g. elevators) and consequently to perform all required lateral maneouvers. An approximated linear response of the so-called non-rotating frame to ON-OFF input, applied to the rotating frame, is derived using the multiple-input describing function technique. It is shown that there is a relationship between the response of the non-rotating frame and that of the equivalent non-rotating body. It is also shown that the two-channel flight controller, designed for the equivalent non-rotating body, can be reduced to a single-channel controller, the output of which is applied to the rotating body. A necessary condition is introduced for this purpose. A proportional navigation guidance law for such a spinning missile is also introduced that generates an angular rate command instead of the acceleration command. Finally, the performance of the proposed controller in the presence of noise and uncertainties is validated through flight simulations.

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Section: Introductionmentioning

confidence: 99%

Multiple-input describing function technique applied to design a single channel ON-OFF controller for a spinning flight vehicle

Nobahari

Mohammadkarimi

2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Using the experimental data for dynamic forces, the separation dynamics of strapon boosters from the core rocket was investigated by Lochan and other researchers. [3][4][5][6] Jeyakumar and Biswas 7 and Keyakumar et al 8 provided stage separation system design and dynamic analysis of ISRO launch vehicles. The elastic response due to separation impulse of the payload fairing made of carbon fiber reinforced plastic composite materials was numerically investigated by Ramamurti et al 9 Hu et al 10 evaluated the design of separation mechanism by considering the effect of spring constant on the dynamics of fairing jettison.…”

Section: Introductionmentioning

confidence: 99%

Separation dynamics of large-scale fairing section: a fluid–structure interaction study

Liu

Qin

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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The separation dynamics of a large-scale fairing section in ground test is investigated numerically using a fluid-structure interaction method. The commercial finite element software MSC/Dytran is adopted to establish the dynamic fluidstructure coupling model of the fairing. Two coupling surfaces are constructed for the inner and outer surfaces of the fairing section. The coupling equations are solved using the sequenced-coupling method, in which the fluid and structural problems are examined by the finite volume method and the finite element method, respectively. A comparison between fluid-structure interaction and dynamical response analysis is performed under the conditions with and without atmosphere effect. Results shown that the consideration of atmosphere effect will attenuate the vibration frequency and slow down the center of mass velocity. The effect of aerodynamic interference on the displacement response indicates that a maximum of 13.3% relative displacement can be induced, which may cause collision between the lower trailing portion of fairing section and the core vehicle. Therefore, it can be concluded that the fluid-structure interaction analysis is essential for evaluating and validating the reliability of separation mechanisms in ground tests.

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Separation investigation of endo-atmospheric multi-stage space probe

Samani¹,

Ghapanvary

2015

Aeronaut.j.

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This paper deals with selection and analysis of two-stage endo-atmospheric separation of supersonic parachute of a test projectile. Flight scenario reads that after the motor burns out, it is separated from the projectile, a few moments after which the parachute is ejected out of the payload and set in the open mode. It is important to study the modes of the stages involved and set a safe distance between them. As this process involves some random variables and needs more time, a shortcut statistical method has been employed in uncertainty variables functions to carry out the analysis. It is meant to take appropriate measures in order for the separation to be collision-free and safe. To do so, relative position of the two stages are modelled and simulated. A statistical method is employed to analyse the relative distance between the two stages in critical points. The results reflect that a safe distance is maintained in the stage of parachute deployment and after supersonic parachute is employed. In addition the said analysis is also carried out via Monte Carlo method. Comparison of the results of these two methods is indicative of a small error. The statistical method is validated and sufficient knowledge on relative attitudes of the stages is obtained.

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Dynamics of nose cone jettisoning from spinning rockets

Cited by 3 publications

References 9 publications

Multiple-input describing function technique applied to design a single channel ON-OFF controller for a spinning flight vehicle

Multiple-input describing function technique applied to design a single channel ON-OFF controller for a spinning flight vehicle

Separation dynamics of large-scale fairing section: a fluid–structure interaction study

Separation investigation of endo-atmospheric multi-stage space probe

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