scholarly journals Flight Strategy Optimization for High-Altitude Solar-Powered Aircraft Based on Gravity Energy Reserving and Mission Altitude

2020 ◽  
Vol 10 (7) ◽  
pp. 2243 ◽  
Author(s):  
Mou Sun ◽  
Xinzhe Ji ◽  
Kangwen Sun ◽  
Ming Zhu
Keyword(s):  
High Altitude ◽  
Trajectory Optimization ◽  
Optimization Problem ◽  
Kinematic Model ◽  
Three Dimensional ◽  
Energy System ◽  
Solar Irradiation ◽  
Gravity Potential ◽  
Energy Store ◽  
Solar Powered

High-altitude long-duration (HALE) flight capability is one of the ultimate goals pursued by human aviation technology, and the high-altitude solar-powered aircraft (SPA) is the most promising technical approach to achieve this target as well as wide application prospects. Due to the particularity of the energy system, the flight strategy optimization through the storage of gravity potential energy and other methods is a significant way to enhance the flight and application abilities for the SPA. In this study, a flight strategy optimization model has been proposed for the aim of HALE flight capability, which is based on the gravity energy reserving and mission altitude in practical engineering applications. This integrated model contains the five flight path phase model, the three-dimensional kinematic model, aerodynamic model, solar irradiation model and energy store and loss model. To solve the optimization problem of three-dimensional flight strategy, the Gauss pseudo-spectral Method (GPM) was employed to establish and calculate the optimal target as its advantages in treating process constraints and terminal constraints for the multiphase optimization problem. At last, the flight trajectory optimization with minimal battery mass for Zephyr 7 was studied by the GPOPS with some function files in MATLAB. The results indicate that the Zephyr 7 can reduce the battery mass from 16 kg to 12.61 kg for the day and night cycle flight and missions, which equals to increasing the battery specific energy by 23.1%. Meanwhile, the optimization results also show that the attitude angel may contribute to increasing the energy gained by photovoltaic cells. In addition, this optimized flight strategy brings the possibility of monthly or annual continuous flight for SPA as the simulation date is set to the autumnal day.

Three-Dimensional Kinematic Modelling of the Human Shoulder Complex—Part II: Mathematical Modelling and Solution Via Optimization

1989 ◽  
Vol 111 (2) ◽  
pp. 113-121 ◽  
Author(s):  
S. T. Tu¨mer ◽  
A. E. Engin
Keyword(s):  
Optimization Problem ◽  
Kinematic Model ◽  
Three Dimensional ◽  
Joint Motion ◽  
Upper Arm ◽  
Complex Part ◽  
Kinematic Modelling ◽  
Shoulder Complex ◽  
The Individual

In this paper, individual joint sinus cones associated with the sternoclavicular, claviscapular, and glenohumeral joints of the three-dimensional kinematic model introduced in Part I for the human shoulder complex are quantitatively determined. First, mathematical description of the humerus orientation with respect to torso is given in terms of eight joint variables. Since the system is a kinematically redundant one, solution for the joint variables satisfying a prescribed humerus orientation is possible only if additional requirements are imposed; and the “minimum joint motion” criterion is introduced for this purpose. Two methods, namely the Lagrange multipliers and flexible tolerance methods, are formulated and tested for the optimization problem. The statistical in-vivo data base for the circumductory motion of the upper arm is employed to determine a set of joint variables via optimization, which are then utilized to establish the sizes and orientations of the elliptical cones for the individual joint sinuses. The results are discussed and compared with those given on the basis of measurements made on cadaveric specimens.

scholarly journals Energy Acquisition of Solar-Powered Joint-Wing Aircraft Considering Mismatch Power Loss

Energies ◽  
2021 ◽  
Vol 15 (1) ◽  
pp. 157
Author(s):  
Xinzhe Ji ◽  
Kangwen Sun ◽  
Xiao Guo ◽  
Mou Sun
Keyword(s):  
Power Loss ◽  
Estimation Method ◽  
Energy System ◽  
Photovoltaic System ◽  
Solar Irradiation ◽  
Mismatch Loss ◽  
Energy Acquisition ◽  
Time Of Year ◽  
Solar Powered

Solar-powered aircraft can perform long-term flights with clean solar energy. However, the energy derived from solar irradiation is influenced by the time of year and latitude, which limits the energy acquisition ability of solar aircraft with a straight-wing configuration. Hence, unconventional configurations based on increasing wing dihedral to track the sun are proposed to improve energy acquisition at high-latitude regions in winter, which may involve power loss caused by mismatch in the photovoltaic system. However, mismatch loss is seldom considered and may cause energy to be overestimated. In this paper, the energy acquisition characteristics of a joint-wing configuration are presented based on the simulation of an energy system to investigate the mismatch power loss. The results indicate a 4~15% deviation from the frequently used estimation method and show that the mismatch loss is influenced by the curved upper surface, the severity of shading and the circuit configuration. Then, the configuration energy acquisition factor is proposed to represent the energy acquisition ability of the joint-wing configuration. Finally, the matching between the aircraft configuration and flight trajectory is analyzed, demonstrating that the solar-powered aircraft with an unconventional wing configuration is more sensitive to the coupling between configuration and trajectory.

Joint optimization of battery mass and flight trajectory for high-altitude solar-powered aircraft

2014 ◽  
Vol 228 (13) ◽  
pp. 2439-2451 ◽  
Author(s):  
Xian-Zhong Gao ◽  
Zhong-Xi Hou ◽  
Zheng Guo ◽  
Xiao-Qing Chen ◽  
Xiao-Qian Chen
Keyword(s):  
Particle Swarm Optimization ◽  
High Altitude ◽  
Optimization Problem ◽  
Optimization Method ◽  
Joint Optimization ◽  
Flight Trajectory ◽  
Swarm Optimization ◽  
Solar Powered ◽  
Pseudo Spectral Method ◽  
Pseudo Spectral

The design parameters of high-altitude solar-powered aircraft are highly correlative with its flight trajectory. However, it is not an easy work to jointly optimize them in the concept design stage. This paper considers the joint optimization problem of battery mass and flight trajectory for high-altitude solar-powered aircraft. The system model including the aircraft dynamic model, aerodynamic parameters, and thrust model is presented. Then the problem to be optimized is formulated and a new optimization method, which uses the particle swarm optimization and Gauss pseudo-spectral method, is proposed. The Gauss pseudo-spectral method is employed to generate the minimal power consumed by following the flight trajectory in the given configuration of high-altitude solar-powered aircraft, while the particle swarm optimization is used to calculate the optimal battery mass of aircraft. The simulation result shows that the proposed joint optimization method can reduce the battery mass of high-altitude solar-powered aircraft from 16 kg to 13.6 kg, which is equivalent to enhancing its energy density by 19.7%. It can be also seen that the proposed optimization method connects each parameter in a logically clear way and hence provide a perspective for understanding the optimization problem.

Real-time footstep planning including capture point trajectory optimization for stable biped navigation

2021 ◽  
pp. 014233122198951
Author(s):  
Young-Dae Hong
Keyword(s):  
Real Time ◽  
Trajectory Optimization ◽  
Optimization Problem ◽  
Particle Swarm Optimization Algorithm ◽  
Three Dimensional ◽  
Stability Control ◽  
Planning Problem ◽  
Swarm Optimization ◽  
Foot Placement ◽  
Capture Point

For stable and efficient biped navigation, a real-time footstep planner taking bipedal dynamics for walking stability control into consideration is proposed. A capture point (CP)-based walking controller is utilized, and footstep planning including reference CP trajectory generation is formulated as an optimization problem. The footstep planning problem is solved using a particle swarm optimization algorithm. The walking period at every footstep is also planned to achieve more effective footstep planning, along with foot placement. Consequently, footstep placement, walking period, and reference CP trajectory for each footstep are optimized by the proposed method. The footstep optimization is performed in real-time without any approximations or precomputations. The effectiveness of the proposed method is demonstrated through experiments in a three-dimensional environment.

The influence of wind shear to the performance of high-altitude solar-powered aircraft

2013 ◽  
Vol 228 (9) ◽  
pp. 1562-1573 ◽  
Author(s):  
Gao Xian Zhong ◽  
Hou Zhong Xi ◽  
Guo Zheng ◽  
Liu Jian Xia ◽  
Chen Xiao Qian
Keyword(s):  
High Altitude ◽  
Wind Shear ◽  
Solar Powered

Spatial path analysis for high-altitude solar-powered airship with maximum net energy

2021 ◽  
pp. 106922
Author(s):  
Weiyu Zhu ◽  
Lanchuan Zhang ◽  
Yuanming Xu ◽  
Bangchu Zhang ◽  
Kuijian Yang
Keyword(s):  
Path Analysis ◽  
High Altitude ◽  
Net Energy ◽  
Solar Powered

Trajectory Optimization Applied to Space Rendezvous

2013 ◽  
Vol 756-759 ◽  
pp. 3466-3470
Author(s):  
Xu Min Song ◽  
Qi Lin
Keyword(s):  
Simulated Annealing ◽  
Optimization Model ◽  
Trajectory Optimization ◽  
Optimization Problem ◽  
Optimization Method ◽  
Nonlinear Constraints ◽  
Design Variables ◽  
Adaptive Simulated Annealing ◽  
Simulation Results

The trajcetory plan problem of spece reandezvous mission was studied in this paper using nolinear optimization method. The optimization model was built based on the Hills equations. And by analysis property of the design variables, a transform was put forward , which eliminated the equation and nonlinear constraints as well as decreaseing the problem dimensions. The optimization problem was solved using Adaptive Simulated Annealing (ASA) method, and the rendezvous trajectory was designed.The method was validated by simulation results.

Optimization of the Robot Calibration Process

1992 ◽  
Author(s):  
G. Zak ◽  
R. G. Fenton ◽  
B. Benhabib
Keyword(s):  
Optimization Problem ◽  
Kinematic Model ◽  
Optimization Procedure ◽  
Calibration Procedure ◽  
Residual Error ◽  
Industrial Robots ◽  
Multiple Objective Optimization ◽  
Robot Calibration ◽  
Calibration Process ◽  
The Cost

Abstract Most industrial robots cannot be off-line programmed to carry out a task accurately, unless their kinematic model is suitably corrected through a calibration procedure. However, proper calibration is an expensive and time-consuming procedure due to the highly accurate measurement equipment required and due to the significant amount of data that must be collected. To improve the efficiency of robot calibration, an optimization procedure is proposed in this paper. The objective of minimizing the cost of the calibration is combined with the objective of minimizing the residual error after calibration in one multiple-objective optimization. Prediction of the residual error for a given calibration process presents the main difficulty for implementing the optimization. It is proposed that the residual error is expressed as a polynomial function. This function is obtained as a result of fitting a response surface to either experimental or simulated sample estimates of the residual error. The optimization problem is then solved by identifying a reduced set of possible solutions, thus greatly simplifying the decision maker’s choice of an effective calibration procedure. An application example of this method is also included.

Sign in / Sign up

Export Citation Format

Share Document