Guidance system

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

Device for aiding the piloting of an aircraft during an approach phase for the purpose of landing

Abstract: Device for aiding the piloting of an aircraft during an approach phase for the purpose of landing. The device (1) comprises a guidance system (8) for aiding guidance of the aircraft, in the event of the actuation of a control means (11A, 11B, 11n), both during an initial phase in accordance with a first guidance mode and during a terminal phase in accordance with a second guidance mode, the transition between these first and second guidance modes being achieved automatically by the guidance system (8).

Destination guidance system, destination guidance server, user terminal, destination guidance method, computer readable memory that stores program for making computer generate information associated with guidance in building, destination guidance data acquisition system, destination guidance data acquisition server, destination guidance data acquisition terminal, destination guidance data acquisition method, and computer readable memory that stores program for making computer acquire data associated with guidance in building

Abstract: This invention is directed to a destination guidance system for providing presentation information that contains guidance pertaining to movement from a place of departure to a destination on the basis of structure information and guidance information on the premises of a building or construction. The presentation information contains both information of the entire three-dimensional structure, and detailed information, and a three-dimensional movement and normal two-dimensional movement in the presentation information are presented by different methods. Also, this invention is directed to a destination guidance data acquisition system for acquiring structure information and guidance information on the premises of a building, which are used by the destination guidance system. The destination guidance data acquisition system inputs and compiles information of a three-dimensional structure on the basis of a plan view of the building to support acquisition of the detailed information.

A Reconfigurable Guidance Approach for Reusable Launch Vehicles

Abstract: : A guidance system with reconfiguration capabilities has been developed for reusable launch vehicles (RLVs). The focus of the development is on reconfiguration after a catastrophic effector failure during final approach - a failure that would otherwise cause loss of the vehicle. We assume here that the vehicle employs a reconfigurable inner-loop control system that recovers some maneuvering capabilities and maintains attitude stability. However, for RLVs, it is often the case that nominal performance cannot be fully recovered, and the outer-loop guidance system must account for the degraded response characteristics. Two approaches are presented. The first approach augments the existing production guidance system with adaptation capabilities. A case study shows that stability is maintained following a primary pitch effector failure. However, it is shown that the trajectory commands to the guidance loops must also be re-targeted in order to achieve a safe landing. The second approach employs an on-line optimal trajectory re-targeting algorithm. A database of neighboring optimal trajectories is encoded in an efficient manner and interrogated on line at regular intervals. Given the current states and certain vehicle parameters, this procedure generates optimal guidance commands and integrates the optimal trajectory to the next update point. A proof-of-concept study of this approach was performed. Following a primary speed control failure, the study shows that this approach achieves acceptable landing conditions.

Interception of spiraling ballistic missiles

Abstract: During re-entry the rolling velocity of the non-separating tactical ballistic missile caused by configurational asymmetries will normally pass through the missile pitch frequency. This may result in a large amplitude circular yaw and a severe spiraling of the vehicles center of mass. The presence of a static aerodynamic induced rolling moment may cause the roll rate to lock-in at the critical frequency in which case the severity of this spiraling motion is greatly increased. Both the amplitude and frequency of spiraling generally increase as the missile descends in altitude. The frequency of the motion is in the range 0.5 to 1 Hz which is the range of target weave frequencies most critical for fast-response proportional navigation interceptors. These motions can cause significant miss distance in a conventional proportional navigation guidance system. This paper demonstrates the advantages of using a weave guidance law. The paper shows that an alternative approach to improving interceptor performance is by improving the guidance law used to steer the missile. If the target weave frequency can be estimated the paper shows that the compensated weave guidance law substantially improves system performance.