Guidance system

About: Guidance system is a research topic. Over the lifetime, 4282 publications have been published within this topic receiving 45964 citations.

Sharing Control with Elderly Drivers: Haptic Guidance during Curve Negotiation

Abstract: Elderly drivers suffer from deterioration of sight and hearing. This makes visual and auditory information for driver support during curve negotiation not very suitable. We present the design and experimental evaluation of a haptic guidance system for curve negotiation. Twelve elderly (>50 years) subjects participated in a fixed-base driving experiment. Based on previous experience with haptic guidance systems, we hypothesized that the benefits of the haptic guidance would be a small increase of curve negotiation performance with less control activity. Results of the experiment show that this was indeed achieved. However, the haptic guidance system resulted in a relatively large increase in steering forces, which could also be a disadvantage for elderly drivers. This needs to be investigated in the future.

Device for interactive dialogue between an aircraft operator and a system for guiding said aircraft

Abstract: The device (1) has a control unit including a display screen on which graphic representations (11A-11C) are displayed. Each representation is carried out in form of a graphic unit (12A). The unit comprises a set of portions (13) that is associated with a guidance mode of associated control axis to represent all guidance modes of a guidance system. One of the portions related to one of the modes engaged on the guidance system is highlighted on the corresponding representation, where the representation highlights a fact that the guidance modes are active exclusively on a given guidance axis.

Guidance system with varying error correction gain

Abstract: A guided missile or projectile and associated guidance control are provided to control a path to a point of intersection with a potentially moving target. A new path is repetitively recomputed and acceleration orthogonal to the path is applied to minimize heading error and thereby to converge on the target. The gain of the control function is partly proportional to heading error, but the gain is reduced approaching the point of convergence. In this way, the guidance control is more responsive to actual variance of the true heading error and is less responsive to random error in sensing the target heading, which random error would otherwise increase in its contribution to corrective guidance movements approaching the point of intersection.

Analytical Evaluation of a Method of Midcourse Guidance for Rendezvous with Earth Satellites

Abstract: A digital-computer simulation was made of the midcourse or ascent phase of a rendezvous between a ferry vehicle and a space station. The simulation involved a closed-loop guidance system in which both the relative position and relative velocity between ferry and station are measured (by simulated radar) and the relative-velocity corrections required to null the miss distance are computed and applied. The results are used to study the effectiveness of a particular set of guidance equations and to study the effects of errors in the launch conditions and errors in the navigation data. A number of trajectories were investigated over a variety of initial conditions for cases in which the space station was in a circular orbit and also in an elliptic orbit. Trajectories are described in terms of a rotating coordinate system fixed in the station. As a result of this study the following conclusions are drawn. Successful rendezvous can be achieved even with launch conditions which are substantially less accurate than those obtained with present-day techniques. The average total-velocity correction required during the midcourse phase is directly proportional to the radar accuracy but the miss distance is not. Errors in the time of booster burnout or in the position of the ferry at booster burnout are less important than errors in the ferry velocity at booster burnout. The use of dead bands to account for errors in the navigational (radar) equipment appears to depend upon a compromise between the magnitude of the velocity corrections to be made and the allowable miss distance at the termination of the midcourse phase of the rendezvous. When approximate guidance equations are used, there are limits on their accuracy which are dependent on the angular distance about the earth to the expected point of rendezvous.