CN110861766A

CN110861766A - Low-speed aircraft capable of taking off and landing vertically

Info

Publication number: CN110861766A
Application number: CN201911195687.8A
Authority: CN
Inventors: 夏开心; 郑于骐; 吴志远; 邓司琪; 赵昌盛; 杨小侨
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-11-28
Filing date: 2019-11-28
Publication date: 2020-03-06

Abstract

The invention discloses a slow vertical take-off and landing aircraft, which is a high-efficiency small aircraft capable of vertical take-off and landing based on a 2032cjc wing profile. The aircraft is structurally distributed with wings, ailerons, an engine mounting seat, a square carbon rod, a round carbon rod, a load cylinder, an undercarriage structure and an aircraft electronic control circuit. In structural design, the aircraft adopts rectangular large-airfoil aero-pneumatic layout, so that a large lift force source can be ensured in the process of cruising flight at ultra-low speed and heavy load, and the stability of heavy load flight is ensured. The main structure of fuselage is the load section of thick bamboo that wood system fuselage and carbon fiber board and carbon fiber tubular product combination formed, and control circuit integrated installation is on the carbon fiber board in the middle of the fuselage, and the big wing surface aviation aerodynamic layout design of this machine rectangle can strengthen the stability in the big load cruise stage of low-speed greatly, can effectively improve aircraft task efficiency, better mobility when possessing the low-speed flight simultaneously.

Description

Low-speed aircraft capable of taking off and landing vertically

Technical Field

The invention relates to the field of aviation aircrafts, in particular to the design of an aerodynamic profile and an integrated system of an aircraft.

Background

The so-called aviation aircraft is a flight machine which can realize complex aerial motion based on a flight principle and depending on aerodynamic configuration, and belongs to the field of aviation aircraft, such as civil aviation aircraft which are taken during travel at ordinary times, individual unmanned aerial vehicles in the military field, and the like. The invention is primarily in the category of small aircraft, and in many small aircraft today, one or more of the following disadvantages exist: most aircraft models need to take off by means of a runway and land by means of the runway; aircraft with slow speed do not have large load ratio capability; the aircraft is not suitable for low-speed and high-maneuver flight; the model aircraft has the advantages of low structural weight and general cruising performance. Therefore, the existing small aircraft technology is still required to be further improved and developed in the aspects of takeoff and landing design, material carrying capacity, large-load-ratio slow aircraft aerodynamic design and the like so as to meet the social requirements.

Disclosure of Invention

The invention mainly solves the technical problem of providing a slow vertical take-off and landing aircraft, which can solve the problems that 1, a small aircraft vertically and stably takes off and lands, 2, the small aircraft has weak material carrying capacity, 3, the small aircraft has too low endurance performance, and 4, the small vertical take-off and landing aircraft is difficult to operate at a slow speed.

In order to overcome the defects in the prior art and solve the problem, the technical scheme of the invention is as follows: the slow vertical take-off and landing aircraft is a small aircraft based on 2032cjc airfoil profile and capable of vertical take-off and landing with high efficiency. The aircraft is structurally distributed with wings, ailerons, steering engines, engine mounting seats, load cylinders and throwing devices thereof, engines and an aircraft electronic control circuit. The rib is selected from a library of airfoils. The left side and the right side of the airplane are respectively provided with five wing ribs in a symmetrical design, and the large wing span can efficiently improve the lift force in the rotating and flat flying process of the airplane so as to reduce the energy consumption, thereby greatly improving the flying and carrying efficiency. The various structures of the fuselage assembly are bonded by special glue and high-strength epoxy resin.

The invention has the beneficial effects that: a slow vertical take-off and landing aircraft is characterized in that the upper surfaces of wing ribs are provided with the same type of hollows to reduce the weight. The proportion of the selected wing profile of the aircraft to the size of the aircraft is high in fitting degree, and the high lift coefficient, the low drag coefficient, the high lift-drag ratio, the proper range factor and the lift moment are all relatively optimal, so that the take-off and landing, the maneuvering performance, the maximum speed, the endurance time and the cruising efficiency of the aircraft are all excellent. After the airplane carries out material loading, an operator can send an instruction to the flight control panel according to the remote controller so as to control the airplane to take off vertically, then the airplane quickly turns to flat flight, then the airplane carries out accurate hovering and launching on a specified place, and finally the airplane vertically lands in a specified area. Compared with the conventional aircraft carrying technology, the invention can obviously overcome the limit of difficult taking off and landing and provide larger load ratio under the condition of slow speed.

Drawings

FIG. 1 is an overall view of the present invention;

FIG. 2 is a side view of the present invention in its entirety;

FIG. 3 is a front view of the present invention in its entirety;

FIG. 4 is a top view of a carbon fiber plate of the load cartridge of the present invention;

the parts in the drawings are numbered as follows: a wing rib 1, an engine base 2; a load cylinder 3; the flap 4; a circular carbon rod 5; a square carbon rod 6; the landing gear carbon tube 7; a carbon fiber plate 8 (comprising a circuit board mounting position 8-1 and a load cylinder connecting pin 8-2); a reinforcing plate 9; a bottom seal 10; steering wheel installation position 11.

Detailed Description

The following detailed description of the preferred embodiments of the present invention, taken in conjunction with the accompanying drawings, will make the advantages and features of the invention easier to understand by those skilled in the art, and thus will clearly and clearly define the scope of the invention.

Referring to fig. 1-4, the whole model of the present invention is symmetrically distributed, and comprises a rib 1, an engine base 2; a load cylinder 3; the flap 4; a circular carbon rod 5; a square carbon rod 6; the landing gear carbon tube 7; a carbon fiber plate 8 (comprising a circuit board mounting position 8-1 and a load cylinder connecting pin 8-2); a reinforcing plate 9; a bottom seal 10; a steering engine mounting position 11, a control circuit (electronic devices and control circuit are not described in detail), and the like. The rib is selected from a library of airfoils. The airplane is symmetrically designed, the left side and the right side of the airplane are respectively provided with five wing ribs, and the whole structure of the airplane body is combined and bonded by special glue iron wires and high-strength epoxy resin.

The embodiment comprises the following steps:

referring to fig. 1, a vertical take-off and landing high-efficiency small aircraft based on a 2032cjc airfoil. The airplane is characterized in that the left side and the right side of the airplane are symmetrically designed, the shapes of the side surfaces of the wing ribs are the same (only one wing rib 1 is marked in figure 1), the integral layout of a rectangular large wing surface is adopted, the wingspan is 1.4 meters, and the integral structure is in an isosceles trapezoid isometric reduction (or expansion) relationship, so that better middle-high speed flight performance can be achieved.

In another embodiment, as shown in fig. 1 and fig. 2, the wing ribs 1 are inserted together through the square carbon rods 6, the middle part of the wing ribs is reinforced by the reinforcing plate 9 for the rigidity and the strength of the structure, the engine base 2 is adhered to one of the wing ribs, the middle part of the engine base is provided with the load cylinder 3, the load cylinder 3 is formed by inserting the round carbon rods 5 and the carbon fiber plate 8, the ailerons 4 are connected to the whole bottom, and the landing gear of the airplane is formed into a four-point landing gear system by the landing gear carbon tubes 7.

In another embodiment, as shown in fig. 3, the steering engine mounting position 11 is a place for mounting a digital steering engine, and the steering engine is used for controlling the swing angle of the aileron.

In another embodiment, as shown in FIG. 4, the carbon fiber plate 8 is provided with a circuit board mounting location 8-1 and a load cell connecting pin 8-2, the circuit board mounting location 8-1 can be used for mounting an aircraft control system, and the load cell connecting pin 8-2 is used for connecting with a wing in a way that a thin iron wire and a square carbon rod 6 are wound together.

The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all equivalent structures or equivalent processes performed by the present specification and the attached drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention, and the present invention does not describe the electric control portion in detail.

Claims

1. A slow vertical take-off and landing aircraft is characterized in that a 2032cjc wing type, a rectangular large-camber airfoil and ten fuselage wing ribs are symmetrically arranged,

the structure of the load carrier 3 that can carry the mission load and mount the electronic circuits,

the loading cylinder structure 3 consists of a carbon fiber plate 8 and a plurality of round carbon rods 5,

the load-carrying cylinder 8 capable of carrying the task load and mounting the electronic circuit comprises a load-carrying cylinder connecting pin 8-2 connected with the square carbon rod 6 through a wire hinge mode.