Guidance system

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

Miss distance analysis for command guided missiles

Abstract: A concise theoretical technique is presented for estimating the minimum miss distance capability of command guided missile systems using synthetic proportional navigation. The effect of the parameter values on the system capability is shown to be a function of range-to-intercept; the technique enables the system designer and analyst to quantify system performance and to develop a systematic understanding of the performance limitations of command guidance systems at each intercept range. New analytical equations based upon adjoint theory are developed for statistical miss distance caused by target maneuver, range-dependent, servo, glint and atmosphere noises for command guided systems. An optimal total system time constant is derived which yields the minimum statistical miss distance. Realistic constraints on the minimum achievable system time constant are considered. The equations derived for the optimal total system time constant are valuable to the system designer for minimizing miss distance over the ranges of system parameters and limitations, and intercept conditions.

Target Maneuver Adaptive Guidance Law for a Bounded Acceleration Missile

Abstract: A new estimator-guidance law is presented, for a bounded acceleration interceptor pursuing a target performing a sudden step maneuver. The linearized end-game scenario is investigated. The missile’s acceleration saturation is represented by the equivalent random input describing function. The estimator proposed for this problem features a mechanism constructed to e‐ciently identify a sudden target maneuver. Due to the bound on the missile acceleration, the certainty equivalence property is not valid, and so, the resulting controller (guidance law) depends on the measurement noise level, statistics of the target maneuver, and the saturation limit. The derivation of this guidance law proceeds in two stages. In the flrst simplifled stage, it is assumed that the instance that the target issues a step command in its acceleration is known. However, the size of the target maneuver jump must still be estimated. Simulation results show signiflcant improvement over the deterministic optimal guidance law when the jump times vary from 10 to 3 missile time constants prior to the intercept time. If the jump occurs earlier or later than this duration no improvement is gained. In the second stage, a suboptimal guidance law is derived using the multiple model adaptive control formulation for a target performing a single step maneuver near the intercept time. Note that this sub-optimal guidance law does not require a-priory knowledge of the time of the jump in the target acceleration command. Performance improvement of the same order of magnitude as was observed for the known jump time scheme (that also serves as a performance bound) is achieved, verifying the validity of this approach. Sensitivity analysis to various noise levels and expected target maneuvers was carried out emphasizing the robustness and advantages of this scheme.

Reinforcement Metalearning for Interception of Maneuvering Exoatmospheric Targets with Parasitic Attitude Loop

Abstract: This Paper uses Reinforcement Meta-Learning to optimize an adaptive integrated guidance, navigation, and control system suitable for exoatmospheric interception of a maneuvering target. The system ...

Community parking space management and guidance system and method based on unmanned aerial vehicle and cloud computing technology

Abstract: The invention discloses a community parking space management and guidance system and method based on an unmanned aerial vehicle and cloud computing technology. The system manages parking spaces in a community by adopting an automatic sensing and intelligent guiding mode. Compared with a convention method, the method has the following three advantages: 1) automatic search and simple operation: the parking place worker judgment process is avoided; 2) comprehensive functions, and being more human-friendly: a cloud server can intelligently arrange detection regions of the unmanned aerial vehicle according to visit regions to screen out an optimum parking place for a destination and generate an optimum parking path, and a visitor is guided by the unmanned aerial vehicle to park a vehicle; and 3) time saving and power consumption reducing: through the guidance for the vehicle, the parking time of the visitor can be greatly reduced, especially for the new visitors, and reduction of the parking time helps to save fuel oil and reduce power consumption.

Four-dimensional optimal route guidance system for aircraft

Abstract: PROBLEM TO BE SOLVED: To provide a four-dimensional optimum route guidance system of an aircraft for calculating four-dimensional optimum routes for all aircrafts, for all the periods, from entering a flight control air area, until leaving therefrom, under conditions by which a plurality of aircrafts will not generate conflict with one another. SOLUTION: A four-dimensional optimum route guidance system 1 for aircrafts comprises an optimum route calculating device 31 that obtains pieces of aircraft information of a plurality of aircrafts 2, respectively, and calculates each four-dimensional optimum route for each aircraft 2 so that each route cost for the entire period, from the entering of each aircraft 2 into the flight control air area Areal, until leaving therefrom, in a state where the aircraft 2 do not conflict with one another, respectively, for the plurality of aircrafts 2 present in the flight control air area Areal; and a transmitting and receiving device 34 receiving each piece of the aircraft information from the plurality of aircrafts 2, to transmit the aircraft information to the calculation device 31 and transmitting each four-dimensional optimum route calculated by the calculation device 31 to each aircraft 2. COPYRIGHT: (C)2010,JPO&INPIT