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Slosh Observer Design for Aeroelastic Launch Vehicles. / Mooij, Erwin.

AIAA Scitech 2020 Forum: 6-10 January 2020, Orlando, FL. AIAA, 2020. AIAA 2020-1606.

Research output: Chapter in Book/Report/Conference proceedingConference contributionScientificpeer-review

Harvard

Mooij, E 2020, Slosh Observer Design for Aeroelastic Launch Vehicles. in AIAA Scitech 2020 Forum: 6-10 January 2020, Orlando, FL., AIAA 2020-1606, AIAA, AIAA Scitech 2020 Forum, Orlando, United States, 6/01/20. https://doi.org/10.2514/6.2020-1606

APA

Mooij, E. (2020). Slosh Observer Design for Aeroelastic Launch Vehicles. In AIAA Scitech 2020 Forum: 6-10 January 2020, Orlando, FL [AIAA 2020-1606] AIAA. https://doi.org/10.2514/6.2020-1606

Vancouver

Mooij E. Slosh Observer Design for Aeroelastic Launch Vehicles. In AIAA Scitech 2020 Forum: 6-10 January 2020, Orlando, FL. AIAA. 2020. AIAA 2020-1606 https://doi.org/10.2514/6.2020-1606

Author

Mooij, Erwin. / Slosh Observer Design for Aeroelastic Launch Vehicles. AIAA Scitech 2020 Forum: 6-10 January 2020, Orlando, FL. AIAA, 2020.

BibTeX

@inproceedings{a248e844560342fa82205bdcb2653c8e,
title = "Slosh Observer Design for Aeroelastic Launch Vehicles",
abstract = "Long and slender bodies, such as (small) conventional launch systems, may suffer from an unwanted coupling between the rigid body and its flexible modes. The current research treats the launch vehicle as a flexible beam with lumped masses to account for the subsystems and fuel, using a three-dimensional assumed-modes method with longitudinal and lateral effects. Given the response of a simple proportional-derivative controller as benchmark, the performance of an Incremental Non-linear Dynamic Inversion (INDI) controller and a system based on Simple Adaptive Control is studied for a number of distinct manoeuvres. Of the three, the INDI controller has a superior performance and is not affected much by the inclusion of engine dynamics and flexible modes. Properly designed filters in the feedback loops show that the rigid-body response can be decoupled from the flexible-body motion, although controller gains need to be adapted to this new configuration. A second advantage is that structural vibration is reduced. Finally, the inclusion of gyroscopes, placed far away from the launcher's centre of mass and which suffer from the effects of aeroelasticity, does not lead to a large performance degradation if both the pitch-rate and pitch-angle feedback signals are properly filtered. To just counter the effects of flexibility, band-pass filters are best suited. However, the effect of flexibility on the gyroscope output is best compensated by notch filters.",
author = "Erwin Mooij",
year = "2020",
doi = "10.2514/6.2020-1606",
language = "English",
booktitle = "AIAA Scitech 2020 Forum",
publisher = "AIAA",

}

RIS

TY - GEN

T1 - Slosh Observer Design for Aeroelastic Launch Vehicles

AU - Mooij, Erwin

PY - 2020

Y1 - 2020

N2 - Long and slender bodies, such as (small) conventional launch systems, may suffer from an unwanted coupling between the rigid body and its flexible modes. The current research treats the launch vehicle as a flexible beam with lumped masses to account for the subsystems and fuel, using a three-dimensional assumed-modes method with longitudinal and lateral effects. Given the response of a simple proportional-derivative controller as benchmark, the performance of an Incremental Non-linear Dynamic Inversion (INDI) controller and a system based on Simple Adaptive Control is studied for a number of distinct manoeuvres. Of the three, the INDI controller has a superior performance and is not affected much by the inclusion of engine dynamics and flexible modes. Properly designed filters in the feedback loops show that the rigid-body response can be decoupled from the flexible-body motion, although controller gains need to be adapted to this new configuration. A second advantage is that structural vibration is reduced. Finally, the inclusion of gyroscopes, placed far away from the launcher's centre of mass and which suffer from the effects of aeroelasticity, does not lead to a large performance degradation if both the pitch-rate and pitch-angle feedback signals are properly filtered. To just counter the effects of flexibility, band-pass filters are best suited. However, the effect of flexibility on the gyroscope output is best compensated by notch filters.

AB - Long and slender bodies, such as (small) conventional launch systems, may suffer from an unwanted coupling between the rigid body and its flexible modes. The current research treats the launch vehicle as a flexible beam with lumped masses to account for the subsystems and fuel, using a three-dimensional assumed-modes method with longitudinal and lateral effects. Given the response of a simple proportional-derivative controller as benchmark, the performance of an Incremental Non-linear Dynamic Inversion (INDI) controller and a system based on Simple Adaptive Control is studied for a number of distinct manoeuvres. Of the three, the INDI controller has a superior performance and is not affected much by the inclusion of engine dynamics and flexible modes. Properly designed filters in the feedback loops show that the rigid-body response can be decoupled from the flexible-body motion, although controller gains need to be adapted to this new configuration. A second advantage is that structural vibration is reduced. Finally, the inclusion of gyroscopes, placed far away from the launcher's centre of mass and which suffer from the effects of aeroelasticity, does not lead to a large performance degradation if both the pitch-rate and pitch-angle feedback signals are properly filtered. To just counter the effects of flexibility, band-pass filters are best suited. However, the effect of flexibility on the gyroscope output is best compensated by notch filters.

U2 - 10.2514/6.2020-1606

DO - 10.2514/6.2020-1606

M3 - Conference contribution

BT - AIAA Scitech 2020 Forum

PB - AIAA

ER -

ID: 68406032