Guidance system

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

The Analysis of a Generic Air-to-Air Missile Simulation Model

Abstract: A generic missile model was developed to evaluate the benefits of using a dynamic missile fly-out simulation system versus a static missile launch envelope system for air-to-air combat simulation. This paper examines the performance of a launch envelope model and a missile fly-out model. The launch envelope model bases its probability of killing the target aircraft on the target aircraft9s position at the launch time of the weapon. The benefits gained from a launch envelope model are the simplicity of implementation and the minimal computational overhead required. A missile fly-out model takes into account the physical characteristics of the missile as it simulates the guidance, propulsion, and movement of the missile. The missile9s probability of kill is based on the missile miss distance (or the minimum distance between the missile and the target aircraft). The problems associated with this method of modeling are a larger computational overhead, the additional complexity required to determine the missile miss distance, and the additional complexity of determining the reason(s) the missile missed the target. This paper evaluates the two methods and compares the results of running each method on a comprehensive set of test conditions.

Flight Testing of a Low-Cost Precision Aerial Delivery System

Abstract: The Affordable Guided Airdrop System is essentially an enhancement for a Container Delivery System (CDS) payload that allows the payload to be deployed over a drop zone from high altitude (10,000'+ MSL), while maintaining or even dramatically improving upon the accuracy achievable with low-altitude deployments. The ability of an aircraft to deliver payloads from these high altitudes greatly enhances the survivability of the aircraft when re- supplying units in hostile areas of operation. To achieve accurate payload delivery with the round parachutes used with CDS payloads, we have developed an autonomously guided actuator system that uses knowledge of the wind intensity and direction over the drop zone to guide these low-performance round parachutes to an accurate landing. The effectiveness of this method of aerial re-supply was demonstrated at the Precision Airdrop Technology Conference and Demonstration (PATCAD) 2003 using early prototype Airborne Guidance Units (AGUs). After demonstrating with proof-of-concept prototype AGAS units that riser slips can be used to effectively control the descent of a round parachute system, we set out to design an actuator system that would provide effective control while reducing the weight and complexity of the control unit. We also needed to answer questions about the best method of parachute rigging, what actuation stroke length would provide the best drive performance, expected system response times, what the upper and lower practical payload limits for the system would be, and what factors would have the greatest impact on system accuracy. Instrumented drop tests of the AGAS prototype systems provided data about loads in the parachute risers during actuations, the performance of the parachutes using various actuation stroke lengths, and electrical current-draw requirements of the actuators during operation. The data were analyzed and used to identify the ideal operating characteristics of an AGAS-equipped payload. In a joint effort between Capewell Components and Vertigo Inc., these characteristics were used to refine the design of the guidance system and to develop the design into a mature product. The result of this effort was a lighter, more compact, and more reliable actuator system, and better integration of the subsystems that support AGAS deployments. Five redesigned Airborne Guidance Units (AGUs), two windpacks, and a mission computer were then fabricated. Six separate test missions have been conducted with the new systems, with multiple payloads being deployed on each mission. The payloads were all of similar weight and configuration, were programmed for the same target coordinates, and were deployed on the same pass. This near simultaneous deployment of multiple systems with the same rate of descent and the same target resulted in close formation flying of the systems, and frequent collisions between the systems, but the overall accuracy results were excellent. System development and testing is ongoing, with the

Quasi-optimum proportional navigation

Abstract: The problem of deriving feedback guidance laws for interceptor type aerodynamically controlled missiles which seek to engage moving targets is considered. These missiles contain target trackers which provide angular information about the relative interceptor-to-target geometry. The performance criterion for this problem is quadratic, but the system equations are nonlinear. Suitable guidance mechanizations are obtained by applying the technique of quasi-optimum control. The efficiency of the resulting guidance system, relative to a linear optimum guidance system and a proportional navigation system, is demonstrated by simulations of attack situations in which the interceptor missile launch conditions depart from the nominal attack geometry.

Aircraft autopilot with control wheel steering

Abstract: 1,218,472. Automatic control of aircraft. SPERRY RAND CORP. Jan. 18, 1968 [Feb. 6, 1967], No. 19731/70. Divided out of 1, 218, 471. Heading G3R. The subject matter of this Specification is identical with that of Specification 1,218,471 but the claims are directed to a radio guidance system for an aircraft in which signals dependent on displacement and rate of change of displacement from course combine to correct the course by controlling the datum of a system responding to and controlling aircraft attitude by adjusting a control surface through a follow-up servo-system, control of the datum being capable of being overriden by a signal proportional to the force on a manual controller only when the radio guidance signals are above a predetermined value.