Optimal Design of Deviation-Correction Trajectory Considering Inter-Well Interference
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Abstract In the process of shale gas mining, if the actual well deviates from the planned trajectory, significant inter-well interference will occur. Therefore, in order to reduce production loss, operators want to get back on the planned trajectory economically. To obtain the best deviation-correction trajectory, an optimization model considering inter-well interference was established. Firstly, the function relation between production envelope and deviation distance is constructed to calculate the production loss. Then, based on the deviation-correction trajectory design, the deviation distance under different curvature trajectory is obtained. Finally, the production loss of different trajectory is obtained, and a new multi-objective optimization model for deviation-correction trajectory is established. Based on the field data of Fuling shale gas area in China, the established model is verified. The results show that the smaller the curvature value is, the greater the production loss occurs. When the curvature value exceeds 10.8°/30m, the production loss value remains minimal. With the same production loss, the longer the production time leads to the greater well profile energy. When the optimization objectives are considered comprehensively, a trajectory with lower well profile energy and higher production can be obtained. It is concluded that the established model can not only reduce the probability of drilling accidents but also achieve better shale gas production. This study fully considers various factors affecting horizontal well in shale gas area, which can provide theoretical guidance for the design of deviation-correction trajectory.Keywords:
Trajectory Optimization
As the number of small Unmanned Aircraft Systems (sUAS) in the national airspace increases, it is becoming increasingly important to develop and implement a system for their air traffic management. Such an envisioned system will be capable of trajectory prediction, trajectory validation and trajectory optimization while accounting for uncertainty due to wind gusts, and in aircraft and flight control system parameters. This paper illustrates the use of covariance propagation based on linearized models for fast sUAS trajectory prediction and for trajectory optimization subject to chance constraints. The approach is demonstrated to be sufficiently accurate and much faster than Monte Carlo simulation techniques.
Trajectory Optimization
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The purpose of this communication is to investigate the interest of using a spatial reference for performing first aircraft trajectory generation and then trajectory tracking while overfly or arrival time constraints are imposed. The adoption of a space reference leads us to rewrite the aircraft flight dynamics. Then an aircraft trajectory optimization problem, including time constraints, is formulated and discussed. Then a new nonlinear control structure for trajectory tracking based on spatial reference is developed and simulation results are displayed.
Trajectory Optimization
Tracking (education)
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The factors affecting the drill trajectory were analyzed to improve the trajectory accuracy in horizontal directional drilling.The engineering equations were simplified and optimized to show how to reduce the trajectory error caused by measurement errors.Simulations with real environmental parameters showed that the errors were reduced by the optimization.Thus,the results give guidance on how to improve the trajectory accuracy.
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Trajectory Optimization
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A method was proposed for the trajectory optimization of prompt reentry strike vehicle.In this method,the model of prompt reentry strike vehicle was established with earth-rotating considered,based on standard atmosphere model and numerical aerodynamic model.The trajectory was divided into boost phase and glide phase,which were optimized respectively and the optimal trajectory was obtained.An example shows that the optimal trajectory has about 7% improvement in range over the maximum lift-to-drag ratio trajectory.Therefore this method is feasible and effective for the optimization of prompt reentry trajectory.
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Trajectory Optimization
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Optimization problem is solved for the trajectory of a typical medium range aircraft flying between two airdromes. The optimization is considered with respect to the fuel consumption and is performed for the entire trajectory, without decomposition into separate stages. The optimal trajectory is calculated on the basis of the complete model of the trajectory motion of an aircraft in a vertical plane. To account for all constraints imposed by both the engineering features of the aircraft, as well as other requirements, including passenger safety and comfort, Bellman's dynamic programming method is used.
Trajectory Optimization
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In order to obtain the optimal glide project trajectory,the extend-range trajectory optimal model was established based on the partile trajectory model of guided projectile,the flight state constraint conditions and the objective function of maximum range.Accurate optimal trajectory can't be obtained by traditional uniform parameterization method.Aiming at this problem,the control horizon was divided into several time stages of varying lengths and the length of each time period was defined as optimization parameters.The glide project trajectory was optimized by time-scaling non-uniform parametric method combined with sequadratic programming.The simulation results show that,compared with traditional methods,the project trajectory designed by this approach has a farther range,a higher terminal speed and more advantages of ballistic performance.
Trajectory Optimization
Time horizon
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Longer range and larger impact angle are the requirements of modern anti-armor missiles being studied. In order to achieve this goal, a method for trajectory optimization is introduced by transferring the design of trajectory optimization to solving nonlinear programming problems, and the gliding trajectory as well as the terminal guidance trajectory is optimized. The improved flight model of the unpowered gliding submissile is simulated, and results show that the optimized trajectory is much better with larger range and almost perfect impact angle by 85deg. What's more, shorter miss distance and smaller overload of the hit point are achieved at the same time.
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Trajectory Optimization
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Compared with launching new satellites, it is an economic scheme to use on-orbit satellites to maneuver to meet users' particular needs for Earth observation. This article studies the mission design method of on-orbit satellite maneuver for observing large-scale ground targets within a given duration. This article divides the original large-scale sequence optimization problem into two small-scale subproblems that are easy to optimize: short-sequence trajectory generation and multitrajectory combination optimization. The multitrajectory combination framework, including database generation, multitrajectory combination selection, trajectory patching, and trajectory keeping, is adopted to optimize the observation sequence and design the satellite's trajectory. In two specific scenarios, the fuel-optimal scenario and accurate revisit observation scenario, the proposed framework shows competitive optimization performance compared with the existing tree search algorithms. In addition, this article provides a known optimal result for the 11th China Trajectory Optimization Competition problem.
Trajectory Optimization
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Orbit (dynamics)
Ground track
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