Variation modes of avian wings offer large-scale morphing aircraft an effective approach for solving problems such as the mass center shift in longitudinal trim and control system design during the morphing process. In this paper, a numerical method is established for fully understanding the influence of combined morphing on roll efficiency of a biomimetic wing unmanned aerial vehicle (UAV) from the perspective of aerodynamic change, system convergence time and aerodynamic energy consumption. Analysis and simulation results show that the biomimetic wing provides effective measures to improve the mission execution efficiency of UAV. System oscillation can obviously be reduced with asymmetric sweep angle change as the supervisory control surface for pure roll maneuver, and actuators require higher output power than that with the single deflection of the flexible trailing edge (Flex-TE). In addition, for aircraft design, a larger mass ratio of the inner wing is beneficial to enhance system stability. Energy consumption of wing and Flex-TE show laws of first increasing and then decreasing along the spanwise direction during the morphing process. For actuators of the Flex-TE, the output power of units 1 to 15 should higher than other spanwise units. For the sweep angle generalized control surface, the maximum value of energy consumption per unit time is located near the 20-th spanwise unit.

In this study, a design scheme for a high-aspect-ratio bionic multi-section variable-sweep wing unmanned aerial vehicle (UAV) that utilizes the reverse coordinated change in the sweep angle of the inner and outer wing sections is proposed, which improves the aerodynamic performance and realizes the self-trim compensation of the wing’s centroid. According to the layout characteristics of this type of UAV, a reasonable distribution design of the wingspan ratio of the inner and outer sections is explored, to reduce the impact of aerodynamic center movement and moment of inertia change. The calculation and analysis results show that the coordinated variable-sweep scheme can significantly improve the influence of sweep angle change on the longitudinal static stability margin of UAVs with a high aspect ratio. The coordinated sweep angle change in the inner and outer wing sections can not only reduce the drag during high-speed flight, but also play a significant role in improving the performance of the aircraft at different stages in the mission profile. Appropriately increasing the wingspan proportion of the inner section can reduce the trim resistance of the V-tail, reduce the thrust of the engine, and increase the range and duration of the UAV. From the perspective of stability change, the multi-section variable-sweep wing UAV with a wingspan ratio of the inner and outer sections that is between 1.41 and 1.78 has better dynamic stability performance. Among them, the UAV with a wingspan ratio of the inner and outer sections that is equal to 1.41 has better longitudinal stability performance, while the UAV with a wingspan ratio of the inner and outer sections that is equal to 1.78 has better lateral/directional stability performance.

Concerning the difficulties of lots of independent variables, high dependency and high risk of losing key information during the modeling process of airliner price prediction, this paper makes use of the advantage of Hierarchical PLSR (Hi-PLSR) in handling small-sample multivariate data fitting to establish the price prediction model based on the design parameters during overall design. The selected design parameters were divided into several groups so as to analysis the influence of various variables on the price and screen out the price driving factors. Then price prediction model was established through the Hi-PLSR method and the model’s prediction precision was verified. At last, engineering value ratio was used to modify the model so as to build a price prediction model suitable for the jetliners made in different countries. The calculation and analysis process suggested that Hi-PLSR method overcoming the difficulties mentioned above can efficiently reflect the relationship between the design parameters and the price.

Based on the research on the sweep angle change of the elbow and hand wing sections during the flight of large birds, this paper proposes a multi-section variable-sweep wing structure suitable for large-scale UAVs. The characteristics of multi-section variable-sweep wing are explored from the perspective of morphing controller design. This research selects stable roll and pitching motion to investigate the feasibility and effectiveness of using the asymmetric change of sweep angle as the control input and using the reverse collaborative morphing of the inner and outer wing sections to achieve centroid self-trimming. The computational analysis results show: (1) The asymmetry morphing of the sweep angle can significantly improve the maneuvering control performance of the UAV with a large lift coefficient. (2) The overall control efficiency of the UAV can be effectively improved by increasing the deflection rate of the sweep angle and the system parameters of the master controller and supervisory controller. (3) Increasing the feedback value of the integral term of the PI compensator in the inner loop can reduce the oscillation degree of the inner loop system in tracking the target signal when the Mach number is large, and improve the tracking accuracy of the inner loop system. (4) Increasing the wingspan ratio of the inner wing section can reduce the elevator deflection angle required to track the target pitch signal during the morphing process. This research provides a reference for the practical application of multi-section variable-sweep wings.