Wyniki wyszukiwania - Biblioteka Nauki

Nowa wersja platformy, zawierająca wyłącznie zasoby pełnotekstowe, jest już dostępna.
Przejdź na https://bibliotekanauki.pl

Ograniczanie wyników

2 Computer Assisted Mechanics and Engineering Sciences

Znaleziono wyników: 2

Liczba wyników na stronie

Wyniki wyszukiwania

Sortuj według:

Ogranicz wyniki do:

Rest-to-rest attitude maneuvers of a satelite with flexible solar panels by using input shapers

100%

Parman S. , Koguchi H.

Computer Assisted Mechanics and Engineering Sciences

1998

tom Vol. 5, nr 4

421-441

A hybrid system of coordinates and a relatively general Lagrangian formulation for studying the dynamics and control of spacecraft with flexible members is developed. Versatility of the formulation is illustrated trough a dynamical study of the satellite with two symmetrical flexible solar panels, where the finite element method is used to describe elastic deformations of solar panels modelled as flat plate structures in bending. The performance of the satellite undergoing roll maneuver is simulated. Results indicate that, under an unshaped input, the maneuvers induce undesirable roll motion of the satellite as well as vibration of the solar panels. A zero vibration input shaper is then applied to reduce the largest magnitude of residual oscillation of roll motion. Once the shaped roll torque input is applied to the satellite, the performance improves significantly. When the longest distance of impulsing time sequences in the input shaper is close enough to the period of large amplitude vibration of flexible members, its maximum deflection during attitude maneuver will also be close enough to the amplitude of vibration with this period under the bang-bang input.

Fuel-efficient attitude maneuvers of flexible spacecraft with residual vibration reduction into an expected level

100%

Parman S. , Koguchi H.

Computer Assisted Mechanics and Engineering Sciences

2000

tom Vol. 7, No. 1

11-21

A three-dimensional rest-to-rest attitude maneuver of a satellite with flexible solar panels equipped by on-off reaction jets is studied. Results indicate that, under an unshaped input, the maneuver induces an undesirable motion of the satellite as well as vibration of the solar panels. Fuel-efficient input shapers are then applied to reduce the residual oscillation of its attitude. By reducing vibrations at several large-amplitude natural frequencies, the expected pointing precision of the satellite can be satisfied.