Features and Modernization Methods of Thrust Measurement Devices for Liquid Rocket Engine Test Stands

Begishev, A. M.; Zhuravlev, V. Y.; Торгашин, А С

doi:10.31772/2587-6066-2020-21-1-62-69

Cited by 2 publications

(1 citation statement)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This article aims to develop an approach to predicting the spacecraft dynamic loads launched into orbits by launch vehicles (of different layout schematics) under oscillations in the rocket engine's thrust in the LV flight's active leg. Thrust oscillations and operational vibration accelerations of the LRE structure, recorded during the LV flight and fire tests of its propulsion system [11][12], are studied during the design and development of the propulsion system in the framework of the tasks of determining the operability of the LRE systems and the vibration strength of the LRE design, taking into account the action of a combination of internal and external factors affecting the engine operation. Vibration loads acting on the engine structure (during their fire tests) at the points of attachment of the liquid-propellant rocket engine to the LV structure, during launch and in the flight of the launch vehicle, are divided into loads caused by low-frequency processes, as well as high-frequency oscillations in the rocket engine systems [13][14].…”

Section: Introductionmentioning

confidence: 99%

Forecasting of the Spacecraft Dynamic Loading Under the Rocket Engine Thrust Oscillations of the Launch Vehicle

Nikolayev

2024

Advances in Transdisciplinary Engineering

View full text Add to dashboard Cite

During the rocket launch into working orbits, the rocket structure and its spacecraft are subjected to extreme dynamic impacts. During this period, the rocket structure and the spacecraft may be subjected to vibroacoustic loads, which can lead to malfunctions of the devices and the strength of the light, thin-walled spacecraft. Testing the spacecraft’s self-oscillations and predicting the spacecraft’s reaction to dynamic loads from the launch vehicle (LV) is a complex task, the relevance of which is manifested in the significant saving of material and technical resources invested in spacecraft development. An approach has been developed to predict the dynamic loads of spacecraft launched into working orbits using LVs (of various layout schemes). The approach makes it possible to estimate the values of dynamic loads (spectral densities of vibration accelerations) of the spacecraft under the propulsion system thrust oscillations acting on the LV structure in the active part of the liquid LV flight. The approach includes mathematical modeling of spatial oscillations of the launch vehicle structure by its structural and layout scheme and preliminary experimental determination of the power spectral density of the rocket engine structure.

show abstract

Section: Introductionmentioning

confidence: 99%

Forecasting of the Spacecraft Dynamic Loading Under the Rocket Engine Thrust Oscillations of the Launch Vehicle

Nikolayev

2024

Advances in Transdisciplinary Engineering

View full text Add to dashboard Cite

show abstract

Prediction of dynamic loads on spacecraft in the active light of the launch vehicle using the results of liquid-propellant rocket engine fire tests

Nikolayev,

Khoroshylov

2024

Teh. Meh.

View full text Add to dashboard Cite

In orbital injection, the launch vehicle (LV) structure and the spacecraft are subjected to extreme dynamic loads, in particular to vibroacoustic loads (from rocket engine thrust oscillations and aerodynamic loads), which may cause spacecraft instrumentation malfunction and damage spacecraft light-weight thin-walled structures. This paper is dedicated to the development of an approach to predicting dynamic loads on spacecraft in orbital injection by LVs of various layouts under propulsion system thrust oscillations in active flight. The paper presents an approach to predicting dynamic loads on spacecraft in orbital injection by LVs of various layouts. The approach makes it possible to evaluate dynamic loads (spectral densities of vibration accelerations) on spacecraft under propulsion system thrust oscillations acting on the liquid-propellant LV structure in active flight. The approach includes a mathematical simulation of the spatial oscillations of the LV structure according to its structural layout scheme and the experimental pre-determination of the spectral density of the rocket engine power. The workability of the proposed approach in predicting the spacecraft dynamic loads is demonstrated by the example of a computational analysis of the spectral densities of spacecraft oscillations in orbital injection by LVs of various structural layouts. It is shown that the approach allows one to predict, as early as at the initial LV design stage, the spacecraft vibratory load parameters at different times of the LV first-stage liquid-propellant rocket engine operation accounting for the rocket layout (with the spacecraft) and design features and using the vibroacoustic characteristics of the liquid-propellant rocket engine (known from the results of its fire tests).

show abstract

Features and Modernization Methods of Thrust Measurement Devices for Liquid Rocket Engine Test Stands

Cited by 2 publications

References 1 publication

Forecasting of the Spacecraft Dynamic Loading Under the Rocket Engine Thrust Oscillations of the Launch Vehicle

Forecasting of the Spacecraft Dynamic Loading Under the Rocket Engine Thrust Oscillations of the Launch Vehicle

Prediction of dynamic loads on spacecraft in the active light of the launch vehicle using the results of liquid-propellant rocket engine fire tests

Contact Info

Product

Resources

About