A Refined and Less Conservative Day-of-Launch Atmospheric Flight Loads Analysis Approach

Kabe, A. M.; Spiekermann, Charles E.; Kim, M. C.; Lee, S. S.

doi:10.21236/ada381335

Cited by 3 publications

(4 citation statements)

References 4 publications

(4 reference statements)

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“…The vibration levels of a spacecraft during its launch into a working orbit [20,39,46] are mainly determined in several frequency ranges (Fig. 3): a) vibrations of the launch vehicle structure during transient processes (with frequencies less than 80 Hz) due to changes in the parameters of the working processes in the rocket engine, b) random vibrations and acoustic loads -with frequencies from 20 to 2000 Hz, c) shock loads -vibrations with frequencies from 100 to 10000 Hz due to the pyrotechnic effects of shock waves.…”

Section: Flight Dynamic Loads From the Side Of The Modern Launch Vehi...mentioning

confidence: 99%

“…The basis for calculating the structure of the spacecraft [3,20,39] is the determination of the static and dynamic loads acting on the spacecraft during the flight of the launch vehicle, the design verification, and the experimental testing of strength. At the same time, optimizing the spacecraft should also reduce its size and cost.…”

Section: Flight Dynamic Loads From the Side Of The Modern Launch Vehi...mentioning

confidence: 99%

“…Maintaining the operability and operational characteristics of various spacecraft systems [15,20,30,39,48] during their launch into a working orbit and during their operation in orbit is no less difficult design task in comparison with the task of ensuring the integrity and strength of the spacecraft.…”

Section: Introductionmentioning

confidence: 99%

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Development of Vibration Protection Systems of Spacecraft — State of the Art and Perspectives

PYLYPENKO,

KHOROSHYLOV,

NIKOLAYEV

2023

Kosm. nauka tehnol.

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Vibration loads on the launch vehicle and spacecraft can reach a high level, leading to abnormal and emergency situations. Therefore, the spacecraft structure must not only support the payload and subsystems of the spacecraft but also have sufficient strength and rigid- ity to exclude any emergencies (damage, destruction, unwanted deformations of the structure, failure and failure of instruments and equipment) that may interfere with the success of the mission. The article aims to analyze the state of research on the design of vibration protection systems for spacecraft launched into working orbits by modern launch vehicles. The results of this analysis will contribute to the development of fundamental schemes of vibration protection systems and methods for effectively suppressing spacecraft spatial vibrations. It is shown that the development of new promising vibration protection systems will take place in the following directions: increasing the frequency range and damping parameters of the dynamic coupled system of “spacecraft and vibration isolation system”; changing approach to vibration suppression of the entire spacecraft (as a whole unit) to setting up the system for damping individual (the most re- sponsible and vibration-sensitive) spacecraft; the use the spacecraft active vibration suppression system in combination with a passive vibration protection system; use of schematic diagrams of spacecraft vibration protection systems with the introduction of hydraulic, electromagnetic and mechanical functional elements in order to increase the efficiency of vibration isolation systems; active suppres- sion of random vibrations in outer space during the operation of various spacecraft systems (due to disturbances from engines of orbit correction systems, etc.); using the adapter structure to perform the functions of a passive vibration protection system of the spacecraft.

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Section: Flight Dynamic Loads From the Side Of The Modern Launch Vehi...mentioning

confidence: 99%

Section: Flight Dynamic Loads From the Side Of The Modern Launch Vehi...mentioning

confidence: 99%

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Development of Vibration Protection Systems of Spacecraft — State of the Art and Perspectives

PYLYPENKO,

KHOROSHYLOV,

NIKOLAYEV

2023

Kosm. nauka tehnol.

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“…The rocket structure and its spacecraft (SC) are subjected to extreme dynamic impacts [1][2][3] during the period of launching into working orbits. The rocket structure and the spacecraft can be affected by vibroacoustic loads (from propulsion system thrust oscillations and aerodynamic influences), which can lead to malfunctions of the instruments and the strength of the light, thin-walled spacecraft structures.…”

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

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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.

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Dynamic Ascent Loads Estimation of Winged Reusable Launch Vehicle: Formulation, Analysis and Post Flight Studies

Jayan,

Pavanasam,

Daniel

2024

SAE Technical Paper Series

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<div class="section abstract"><div class="htmlview paragraph">A structural load estimation methodology was developed for RLV-TD HEX-01 hypersonic experimental mission, the maiden winged body technology demonstrator vehicle of ISRO. Primarily the method evaluates time history of station loads considering effects of vehicle dynamics and structural flexibility. Station loads of critical structures are determined by superposition of quasi-static aerodynamic loads, dynamic inertia loads, control surface loads and propulsion loads based on actual physics of the system, improving upon statistical load combination approaches. The technique characterizes atmospheric regime of flight from vehicle loads perspective and ensures adequate structural margin considering atmospheric variations and system level perturbations. Features to estimate change in loads due to wind variability and atmospheric turbulence are incorporated into the load estimation methodology. Augmentation in loads due to structural flexibility is assessed along the trajectory using vehicle states calculated by a flexible vehicle response solver integrated to 6-DOF trajectory solver. This methodology was used to authorize the successful maiden launch of RLV-TD HEX-01 flight on May 23, 2016. The paper describes basic formulation of elastic load estimation technique, pertinent mission design simulation studies and comparison of estimated load with flight measured data. A close agreement between computed structural load and flight measured load throughout the atmospheric regime of flight demonstrates technological maturity of the methodology.</div></div>

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A Refined and Less Conservative Day-of-Launch Atmospheric Flight Loads Analysis Approach

Cited by 3 publications

References 4 publications

Development of Vibration Protection Systems of Spacecraft — State of the Art and Perspectives

Development of Vibration Protection Systems of Spacecraft — State of the Art and Perspectives

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

Dynamic Ascent Loads Estimation of Winged Reusable Launch Vehicle: Formulation, Analysis and Post Flight Studies

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