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Since its inception, helping behavior has been viewed as a cooperative and affiliative behavior with prudent employee involvement. The paradox of employee involvement, however, implies that helping behavior can be intrusive and obstructive. The primary purpose of this article is to conceptualize helicopter helping as an intrusive and obstructive type of discretionary workplace behavior. In addition, the authors discuss possible antecedents and consequences of helicopter helping.

To conceptualize helicopter helping, the authors utilized the ABI/INFORM Global, Academic Search Complete, Business Source Complete, PsycARTICLES and JSTOR Archive Collection databases focusing on the helping behavior and helicopter parenting research. In particular, the authors applied the hovering nature of helicopter parenting to the conceptualization of helicopter helping exhibited by an employee in the organization. Additionally, the authors discuss antecedents and consequences of helicopter helping by integrating the bright and dark side of helping behavior research.

The authors conceptualize helicopter helping as an employee's excessive involvement in and interference with coworkers' task environment. Based upon the conceptualization of helicopter helping, the authors further propose that the need for achievement, Type-A personality, group rewards, high-performance group norms, a hierarchy organizational culture and strong social ties are possible antecedents of helicopter helping. Furthermore, the authors suggest that helicopter helping can result in reduced organization-based self-esteem, general self-efficacy, group creativity and innovation, quality of social-exchange relationships, learning and development and increased organizational vulnerability.

This article is one of the few studies exploring helping behavior from an intrusive and invasive perspective. Theoretically, the authors advance the dark side of helping behavior literature. Drawing upon the propositions, the authors offer some managerial recommendations that help managers mitigate the intrusive and obstructive type of helping in the organization.

This paper aims to examine the ethical foundations of Gen Z individuals by studying the impact of helicopter parenting on moral courage and moral disengagement. In addition, this study considers the implications for Millennial generation managers that are likely to be supervising this current generational cohort.

Hypotheses were tested using a two-wave online survey of 215 undergraduate students.

Helicopter parenting was associated with lower levels of moral courage and an elevated propensity to morally disengage in a sample of Gen Z individuals. The impact of helicopter parenting on these moral foundations was mediated by the children’s increased desire for continued parental involvement in their lives.

Similar to the Gen Z students surveyed in this study, many Millennials were raised by helicopter parents, thus, it is likely that they are also prone to moral disengagement and low moral courage. Furthermore, Millennial managers will be managing Gen Z workers. Thus, many companies will need to enhance their efforts in providing Millennial managers with business ethics training aimed at developing moral courage and reducing moral disengagement.

This study examines a previously unidentified antecedent of moral courage and moral disengagement

Increasingly, product managers and promotional strategists weigh the impacts of homogeneous products and uniform promotion coupled with the unique character of specific market segments. This is especially crucial in an era when many products are advertised in identical ways and consumed in analogous manners over diverse cultural areas. In order to explore the influence of cultural variations on marketing, discusses the conflicting ways in which an international advertising icon, “the Marlboro man”, is interpreted in three different cultural settings. The resulting analysis has both theoretical and practical value.

The implementation of interaction design concepts to facilitate communication between users and shopping websites has gained increasing attention in recent years. Mouse hover is a vital interaction method for users to access shopping sites and significantly impacts their decision-making experience. A well-designed mouse hover function can effectively enhance the user's search performance and improve the user experience. The purpose of this study is to investigate whether the dynamic prompt designs at the hover position and the degree of feedback transparency may affect the user's task performance and personal feelings when operating the hover function on the shopping website.

The study employed two independent variables in the experiments: dynamic prompt and background transparency of hover feedback. A between-subject design of 2 (single flicker and continuous flicker) × 3 (transparency at 0%, 25%, and 50%) was adopted in the experiment. A total of 60 participants were invited to participate in the experiment using the purposive sampling method. Participants were asked to complete four operation tasks, and the time of each was recorded. They were then asked to complete the system usability scale (SUS) questionnaire and conduct subjective evaluations before they were briefly interviewed.

The generated results revealed that: (1) In the interaction with a shopping website, the degree of background transparency of hover feedback affected the participants' task performance. (2) The effect of a single flicker had significantly higher subjective evaluation results regarding the degree of rationality compared with a continuous flicker. (3) The participants' perceptions of the information clarity were affected when the background transparency of hover feedback was 50%. (4) The effect of a continuous flicker was better than that of a single flicker when the background transparency of hover feedback was 25%. The participants' attraction to a continuous flicker was significantly higher than that of a single flicker. Nonetheless, when the degree of background transparency was at 0% or 50%, the results were the opposite.

The findings generated from the research can be a reference for the development of hover operation in the user interface design for shopping websites.

The purpose of this paper is to present and validate an efficient time‐marching free‐vortex method for rotor wake analysis and study the rotor wake dynamics in transient and maneuvering flight conditions.

The rotor wake is represented by vortex filament elements. The equations governing the convection, strain and viscous diffusion of the vortex elements are derived from incompressible Navier‐Stokes equations based on the viscous splitting algorithm. The initial core size of the blade tip vortices is directly computed by a vortex sheet roll‐up model. Then, a second‐order time‐marching algorithm is developed for solving the governing equations. The algorithm is formulated in explicit form to improve computing efficiency. To avoid the numerical instability, a high order variable artificial dissipative term is directly introduced into the algorithm. Finally, the developed method is applied to examine rotor wake geometries in steady‐state and maneuvering flight conditions. Comparisons between predictions and experimental results are made for rotor wake geometries, induced inflow distributions and rotor transient responses, to help validate the new method.

The algorithm is found to be numerically stable and efficient. The predicted rotor responses have good agreement with experimental data. The transient behavior of the wake dominates the rotor responses following rapid control inputs in hover. The wake curvature effect induced by rotor pitching or rolling rate significantly changes the rotor off‐axis response.

This method should be further validated using experimental measurements of full‐scale helicopter rotors.

The paper presents a new time‐marching free‐vortex wake method, which is suitable for application in helicopter flight simulation.

The purpose of this paper is to develop a real‐time simulation environment for the validation of controller for an autonomous small‐scale helicopter.

The real‐time simulation platform is developed based on the nonlinear model of a series of small‐scale helicopters. Dynamics of small‐scale helicopter is analyzed through simulation. The controller is designed based on the extracted linear model.

The model‐based linear controller can be effectively designed and tested using real‐time simulation platform. The hover controller is demonstrated to be robust against wind disturbance.

To use the real‐time simulation environment to test and validate controllers for small‐scale helicopters, basic helicopter parameters need to be measured, calculated or estimated.

The real‐time simulation environment can be used generically to test and validate controllers for small‐scale helicopters.

The paper presents the design and development of a low‐cost hardware in the loop simulation environment using xPC target critical for validating controllers for small‐scale helicopters.

The purpose of this paper is to propose a new algorithm for pendulum‐like oscillation control of an unmanned rotorcraft (UR) in a reconnaissance mission and improve the stabilizing performance of the UR's hover and stare.

The algorithm is based on linear‐quadratic regulator (LQR), of which the determinable parameters are optimized by the artificial bee colony (ABC) algorithm, a newly developed algorithm inspired by swarm intelligence and motivated by the intelligent behaviour of honey bees.

The proposed algorithm is tested in a UR simulation environment and achieves stabilization of the pendulum oscillation in less than 4s.

The presented algorithm and design strategy can be extended for other types of complex control missions where relative parameters must be optimized to get a better control performance.

The ABC optimized control system developed can be easily applied to practice and can safely stabilize the UR during hover and stare, which will considerably improve the stability of the UR and lead to better reconnaissance performance.

This research presents a new algorithm to control the pendulum‐like oscillation of URs, whose performance of hover and stare is a key issue when carrying out new challenging reconnaissance missions in urban warfare. Simulation results show that the presented algorithm performs better than traditional methods and the design process is simpler and easier.

This paper examines how a beginning teacher in Virginia and a beginning teacher in Florida make sense of the high-stakes tests in their state. By examining beginning teachers in two states where the tests are so very different, we gain important insight into whether there are similarities and differences across states and how the nature of the test affects the teaching and learning of history. We first offer insight into the context of accountability in Virginia and Florida and then discuss what ambitious teaching and learning look like in these states as informed by the literature. Then, we turn to our research methods, findings, and implications for the field of social studies.

Dual-thrust hybrid unmanned aerial vehicle (UAV) technology offers a highly robust and efficient system that incorporates the take-off and landing capabilities of rotary-wing aircraft with the endurance capacities of fixed-wing aircraft. The purpose of this study is to model and control a hybrid UAV in three distinct flight modes: rotary-wing, fixed-wing and over-actuated model.

Model predictive control (MPC) along with linear models are applied to design controllers for the rotary-wing or vertical take-off and transition to the fixed-wing flight. The MPC algorithm is implemented with two approaches, first in its usual form and then in a new form with the help of tracking error variables as state variables.

Because the tracking error variables are more compatible with the cost function used in MPC, the results improve significantly. This is especially important for a safe and stable transition from rotary-wing to fixed-wing flight, which should be done quickly. The authors also propose a control allocation strategy with MPC algorithm to exploit the thrust and control inputs of both rotary-wing and fixed-wing systems for the transition phase. As the control system is over-actuated, the proposed algorithm distributes the control signal among the actuators better than the MPC alone. The numerical results show that the flight trajectory is also improved.

The research background is reviewed in the introduction section. The other sections are originally developed in this paper to the best of the authors’ knowledge.