The problem of guiding a hypersonic gliding vehicle in the terminal phase to a target location is considered. In addition to the constraints on its final position coordinates, the vehicle must also impact the target from a specified direction with very high precision.The proposed 3-dimensional guidance laws take simple proportional forms. The analysis establishes that with appropriately selected guidance parameters the 3-dimensional guided trajectory will satisfy these impact requirements. We provide the conditions for the initial online selection of the guidance law parameters for the given impact direction requirement. The vehicle dynamics are explicitly taken into account in the realization of guidance commands. To ensure high accuracy in the impact angle conditions in an operational environment, we develop closed-loop nonlinear adaptation laws for the guidance parameters. We present the complete guidance logic and associated analysis. Simulation results are provided to demonstrate the effectiveness and accuracy of the proposed terminal guidance approach.
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SPONSORING/MONITORING AGENCY REPORT NUMBER(S)
AFRL-RQ-WP-TR-2016-0001
DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution unlimited.
SUPPLEMENTARY NOTESThis is a Small Business Innovation Research (SBIR) Phase III report. Barron Associates, Inc. has waived its SBIR data rights, and the report has been approved for public release (PA Case Number: 88ABW-2016-1452; Clearance Date: 11 March 2016).
ABSTRACTThis report was developed under a SBIR contract. This report describes the technical progress made by Barron Associates, Inc. and its partners in runtime assurance (RTA) systems, which hold the promise of protecting advanced systems that cannot be fully certified at design time due to their inherent complexity. A number of technical hurdles remain in the implementation of RTA systems for highly complex safety-critical systems, and the main objective of this effort was to further address these issues. One main focus of this project was to investigate the necessary structure of RTA frameworks for multi-level interacting feedback systems. As such, a challenge problem was constructed for a fleet of unmanned aircraft systems (UASs) performing a surveillance mission. The demonstration platform consisted of RTA systems for the inner-loop control, outer-loop guidance, ownship flight management, and fleet mission planning elements. The framework design and certification requirements for such a system were explored in this program. For the inner-loop, the concept of employing multiple transition controllers in the reversionary control system was studied. For all feedback levels, the required RTA checks were developed and the critical reversionary switching conditions defined. The interactions between the RTA protected systems and certified collision avoidance systems were also investigated. A safety case argument for design-time certification of the RTA protected systems was constructed using subsystem requirements contracts that were developed from a compositional reasoning approach explored over the course of the project.
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