Moving-mass actuator system options for entry vehicles with deployable decelerators

Kevin G. Lohan, Zachary R Putnam

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This study assesses internal moving-mass actuator configuration options for trajectory control in the hypersonic regime of planetary entry. Trajectory control is achieved by shifting the location of the center of gravity relative to the center of pressure to modify aerodynamic trim conditions. The vehicle is modeled as a cylinder with a deployable forebody and a moving-mass actuator that can translate along a linear track. Placing the track in the rear of the vehicle can reduce the required actuator mass fraction for a specific trim lift-to-drag ratio by up to 5%. Increasing the length of the track similarly reduces required mass fraction. Vehicle packaging density and size do not significantly influence the required actuator mass; geometric properties such as length-to-diameter ratio and the diameter of the deployable impact the required actuator mass. Using these design guidelines, and actuator mass fraction of approximately 13% is required to achieve a maximum lift-to-drag ration similar to the Mars Science Laboratory.

Original languageEnglish (US)
Title of host publicationSpaceflight Mechanics 2016
EditorsMartin T. Ozimek, Renato Zanetti, Angela L. Bowes, Ryan P. Russell, Martin T. Ozimek
PublisherUnivelt Inc.
Pages1875-1886
Number of pages12
ISBN (Print)9780877036333
StatePublished - Jan 1 2016
Event26th AAS/AIAA Space Flight Mechanics Meeting, 2016 - Napa, United States
Duration: Feb 14 2016Feb 18 2016

Publication series

NameAdvances in the Astronautical Sciences
Volume158
ISSN (Print)0065-3438

Other

Other26th AAS/AIAA Space Flight Mechanics Meeting, 2016
CountryUnited States
CityNapa
Period2/14/162/18/16

Fingerprint

brakes (for arresting motion)
entry
vehicles
Actuators
actuators
trajectory control
Drag
drag
Trajectories
aerodynamic balance
center of pressure
trajectory
forebodies
atmospheric entry
Hypersonic aerodynamics
rations
center of gravity
hypersonics
vehicle
aerodynamics

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

Lohan, K. G., & Putnam, Z. R. (2016). Moving-mass actuator system options for entry vehicles with deployable decelerators. In M. T. Ozimek, R. Zanetti, A. L. Bowes, R. P. Russell, & M. T. Ozimek (Eds.), Spaceflight Mechanics 2016 (pp. 1875-1886). (Advances in the Astronautical Sciences; Vol. 158). Univelt Inc..

Moving-mass actuator system options for entry vehicles with deployable decelerators. / Lohan, Kevin G.; Putnam, Zachary R.

Spaceflight Mechanics 2016. ed. / Martin T. Ozimek; Renato Zanetti; Angela L. Bowes; Ryan P. Russell; Martin T. Ozimek. Univelt Inc., 2016. p. 1875-1886 (Advances in the Astronautical Sciences; Vol. 158).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Lohan, KG & Putnam, ZR 2016, Moving-mass actuator system options for entry vehicles with deployable decelerators. in MT Ozimek, R Zanetti, AL Bowes, RP Russell & MT Ozimek (eds), Spaceflight Mechanics 2016. Advances in the Astronautical Sciences, vol. 158, Univelt Inc., pp. 1875-1886, 26th AAS/AIAA Space Flight Mechanics Meeting, 2016, Napa, United States, 2/14/16.
Lohan KG, Putnam ZR. Moving-mass actuator system options for entry vehicles with deployable decelerators. In Ozimek MT, Zanetti R, Bowes AL, Russell RP, Ozimek MT, editors, Spaceflight Mechanics 2016. Univelt Inc. 2016. p. 1875-1886. (Advances in the Astronautical Sciences).
Lohan, Kevin G. ; Putnam, Zachary R. / Moving-mass actuator system options for entry vehicles with deployable decelerators. Spaceflight Mechanics 2016. editor / Martin T. Ozimek ; Renato Zanetti ; Angela L. Bowes ; Ryan P. Russell ; Martin T. Ozimek. Univelt Inc., 2016. pp. 1875-1886 (Advances in the Astronautical Sciences).
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