Gravity-turn descent from low circular orbit conditions

C.R. McInnes

Research output: Contribution to journalArticle

21 Citations (Scopus)

Abstract

GRAVITY-TURN descent to the surface of a planetary or small solar system body has been investigated for many years and, indeed, has been used for both lunar and Mars descent vehicles. Such a descent proŽ le requires that the vehicle thrust vector is oriented opposite to the instantaneous velocity vector along the entire descent trajectory. This requirement can be achieved with knowledge of the vehicle velocity vector from an inertial measurement unit and an attitude control system that can maintain the thrust vector antiparallel to the instantaneous velocity vector.1 For pure gravity-turndescent, the steering law is, therefore, relatively easy to implement in practice, although the descent may be modiŽ ed at the terminal phase for surface hazard avoidance. An important beneŽfit of gravity-turn descent is that the landing is assured to be vertical, and the steering law is close to fuel optimum.
LanguageEnglish
Pages183-185
Number of pages2
JournalJournal of Guidance, Control and Dynamics
Volume26
Issue number1
Publication statusPublished - 2003

Fingerprint

circular orbits
descent
Descent
Gravity
Gravitation
Orbits
Orbit
gravity
gravitation
vehicles
thrust
descent trajectories
Instantaneous
Units of measurement
Attitude control
Landing
attitude control
planetary systems
avoidance
landing

Keywords

  • mars
  • space travel
  • guidance systems
  • orbitsl gravity
  • astronautical engineering

Cite this

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Gravity-turn descent from low circular orbit conditions. / McInnes, C.R.

In: Journal of Guidance, Control and Dynamics, Vol. 26, No. 1, 2003, p. 183-185.

Research output: Contribution to journalArticle

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AB - GRAVITY-TURN descent to the surface of a planetary or small solar system body has been investigated for many years and, indeed, has been used for both lunar and Mars descent vehicles. Such a descent proŽ le requires that the vehicle thrust vector is oriented opposite to the instantaneous velocity vector along the entire descent trajectory. This requirement can be achieved with knowledge of the vehicle velocity vector from an inertial measurement unit and an attitude control system that can maintain the thrust vector antiparallel to the instantaneous velocity vector.1 For pure gravity-turndescent, the steering law is, therefore, relatively easy to implement in practice, although the descent may be modiŽ ed at the terminal phase for surface hazard avoidance. An important beneŽfit of gravity-turn descent is that the landing is assured to be vertical, and the steering law is close to fuel optimum.

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KW - space travel

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