Aerodynamics and flow characterisation of multistage rockets

Srinivas, G; Prakash, Mano

doi:10.1088/1757-899x/197/1/012077

Cited by 5 publications

(3 citation statements)

References 2 publications

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“…During ascent phase, when the first stage of an aerospace vehicle is ignited, heavy ionized plumes from the nozzle of the solid rocket motor exist around the nozzle of the vehicle [8][9][10][11][12] . The ionised exhaust plumes continue till the propellant is completed in all stages.…”

Section: Plume Attenuationmentioning

confidence: 99%

A Novel Loss Tolerant Data Transmission Schemes for Airborne Telemetry System of a Long Range Aerospace Vehicle

2022

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The on-board telemetry system of an aerospace vehicle sends the vehicle performance parameters to the ground receiving station at all instances of its trajectory. During the course of its trajectory, the communication channel of a long range vehicle, experiences various phenomena such as plume attenuation, stage separation, manoeuvring of a vehicle and RF blackout, causing loss of valuable telemetry data. The loss of communication link is inevitable due to these harsh conditions even when using the space diversity of ground receiving systems. Conventional telemetry systems do not provide redundant data for long range aerospace vehicles. This research work proposes an innovative delay data transmission, frame switchover and multiple frames data transmission schemes to improve the availability of telemetry data at ground receiving stations. The proposed innovative schemes are modelled using VHDL and extensive simulations have been performed to validate the results. The functionally simulated net list has been synthesised with 130 nm ACTEL flash based FPGA and verified on telemetry hardware.

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Section: Plume Attenuationmentioning

confidence: 99%

A Novel Loss Tolerant Data Transmission Schemes for Airborne Telemetry System of a Long Range Aerospace Vehicle

2022

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“…Compared to experimental investigations, computational design and analysis provide economic benefits. The computational model will be used for the preliminary analysis [5]. The design can be changed computationally according to the findings.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic and External Ballistic modelling of a Rocket Target with Two Motors in a Parallel Configuration

MANIMARAN

FEDARAVICIUS

2023

mech

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Rocket targets are essential for live-fire military training. RT-400 is a short-range rocket target. This rocket must be improvised for a longer range. So, two motors are used to upgrade the range of the rocket. as the dimensions of the rocket change, it is required to analyse the nose cone shape for the prediction of forces and coefficients. With obtained values, ballistic analysis is carried out to determine the theoretical maximum range and altitudes are obtained.

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“…The double-section 3D beam model can also be utilized to model a high-speed double-stage rocket motion. The most concerns on the multi-stage rocket motion are the stage separation dynamic control [18] or the high speed flows over the joint of the space rocket stages [19].…”

Section: Introductionmentioning

confidence: 99%

The Study of Primary and Internal Resonance on 3D Free-Free Double-Section Beam

Wang

Chang

2020

Adv. technol. innov.

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This work investigates the primary resonance and internal resonance of a double-section beam with cubic nonlinearities. This model can be applied in a wide range of engineering problems, such as rocket and missile structures. Even space technology has been developed for decades; several nonlinear properties deserve further study, especially, for the internal resonance. The method of multiple scales (a perturbation technique) is employed to analyze this nonlinear problem. This study focuses on finding the forcing conditions of this 3D double-section beam to trigger the often-ignored internal resonance or prime resonance in rocket structures. A primary resonance is found on a uniform free-free beam at certain flight speed. The three-to-one internal resonance of the double-section beam occurs within the first and the second modes in the diameter ratio of 1/0.75 with the length ratio of 0.33 or 0.51. The semi-analytical results are verified by the time marching numerical method.

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Aerodynamics and flow characterisation of multistage rockets

Cited by 5 publications

References 2 publications

A Novel Loss Tolerant Data Transmission Schemes for Airborne Telemetry System of a Long Range Aerospace Vehicle

A Novel Loss Tolerant Data Transmission Schemes for Airborne Telemetry System of a Long Range Aerospace Vehicle

Aerodynamic and External Ballistic modelling of a Rocket Target with Two Motors in a Parallel Configuration

The Study of Primary and Internal Resonance on 3D Free-Free Double-Section Beam

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