Integrated navigation and guidance for precision landing at Mars
Explore the source record for details and available documents.
entry descent and landing navigation Kalman filter↗
Engineering topics
Bishop, R. H.
Publications and source records attributed to Bishop, R. H..
Integrated navigation and guidance for precision landing at Mars
The focus of this paper is the interaction of the aided-navigation system with the rest of the flight system. Results from simulated EDL scenarios will be presented.
entry descent and landing navigation Kalman filter↗
Robust entry navigation using hierarchical filter architectures regulated with gating networks
The application of a hierarchical mixture of experts architecture to Martian entry navigation during the highly dynamic hypersonic pre-parachute deploy phase is investigated.
(IMU) navigation dead reckoning↗
Adaptive control of Space Station during nominal operations with CMGs
An adaptive control approach is investigated for the Space Station. The main components of the adaptive controller are the parameter identification scheme, the control gain calculation, and the control law. The control law is the Space Station baseline control law. The control gain calculation is based on linear quadratic regulator theory with eigenvalue placement in a vertical strip. The parameter identification scheme is a real-time recursive extended Kalman filter which estimates the inertias and also provides an estimate of the unmodeled disturbances due to the aerodynamic torques and to the nonlinear effects. An analysis of the inertia estimation problem suggests that it is possible to compute accurate estimates of the Space Station inertias during nominal CMG (control moment gyro) operations. The closed-loop adaptive control law is shown to be capable of stabilizing the Space Station after large inertia changes. Results are presented for the pitch axis.
Bishop, R. H.↗
Proposed CMG momentum management scheme for space station
A discrete control moment gyro (CMG) momentum management scheme (MMS) applicable to spacecraft with principal axes misalignments, such as the proposed NASA dual keel space station, is presented in this paper. The objective of the MMS is to minmize CMG angular momentum storage requirements for maintaining the space station near local vertical in the presence of environmental disturbances. It utilizes available environmental disturbances, namely gravity gradient torques, to minimize CMG momentum storage. The MMS is executed once per orbit and generates a commanded torque equilibrium attitude (TEA) time history which consists of a yaw, pitch and roll angle command profile. Although the algorithm is called only once per orbit to compute the TEA profile, the space station will maneuver several discrete times each orbit.
Bishop, L. R.↗