Deformable lift and buoyancy integrated aircraft aerodynamic configuration

Abstract

Belonging to the technical field of aircraft design, the invention discloses a deformable lift and buoyancy integrated aircraft aerodynamic configuration. The aerodynamic configuration has a single-fuselage, tandem wing and horizontal tail-free layout, double vertical tails tilt outward certain angle, wings are located at the upper part of the fuselage, front wings and back wings have the same design. The fuselage can produce radial deformation, the fuselage is divided into a front section, a middle section and a back section, and the three sections of the fuselage deform respectively. Because of the introduction of dynamic lift, the aircraft has higher flight height than an airship, greater flight speed, and stronger wind resistant performance and maneuverability; and due to the introduction of static lift, the aircraft has loading capacity far higher than that of conventional high-altitude unmanned aerial vehicles, and has higher structural height and strength. In the process of vertical rising and fall, the fuselage can produce corresponding deformation to change the fuselage volume so as to guarantee the fuselage lift and the aircraft weight balance. With no need for ballonet and ancillary equipment in conventional airships and lift and buoyancy integrated aircrafts, the deformable lift and buoyancy integrated aircraft aerodynamic configuration provided by the invention can reduce the aircraft weight and decrease the ground parking volume of the aircraft.

Description

technical field [0001] The invention belongs to the technical field of aircraft design, and relates to a deformable aerodynamic shape of a lift-floating integrated aircraft, in particular to an aerodynamic shape of an aircraft which comprehensively utilizes dynamic lift and static lift and whose fuselage can be adaptively deformed. Background technique [0002] Near-space flight platforms have broad application prospects. For this kind of high-altitude and long-endurance aircraft platform, high-altitude airships, solar-powered aircraft, and lift-and-float integrated aircraft are currently the most researched directions. But these kinds of aircraft also have their obvious disadvantages: high-altitude airships are too bulky, low flying speed, poor maneuverability, poor wind resistance, and high transportation, storage and maintenance costs. Due to the limitation of solar power, the weight of solar aircraft must be very light, which greatly limits its ability to carry loads, an...

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Problems solved by technology

However, these types of aircraft also have their obvious disadvantages: the high-altitude airship is too large, the flight speed is low, the maneuverability is poor, the wind resistance is poor, and the transportation, storage and maintenance costs are very high

Due to the limitation of solar power, the weight of the solar aircraft must be very light, which greatly limits its ability to carry loads, and the body structure has to sacrifice strength and rigidity due to the pursuit of light weight. In order to pursue high aerodynamic efficiency, the wings often use large The chord ratio configuration results in greater flexibility of the wing, serious deformation of the wing during flight, and prone to flight safety problems

At present, most of the static lift components of the lift-floating integrated aircraft are semi-rigid airship structures, and their shape cannot be changed. There must be a huge auxiliary airbag inside to store air to adjust the weight of the aircraft. The ground parking volume is huge, and there must be equipment such as intake and exhaust pumps to adjust The auxiliary airbag has a complex structure and a large additional weight

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