CN205059988U - Electronic microlight -type sport plane of combined material two -seater - Google Patents

Abstract

The two-seat electric ultra-light sports aircraft of composite materials mainly solves the problems of high cost, environmental pollution and high noise of existing light aircraft. The fuselage, wing, empennage and landing gear of the utility model adopt the composite material structure mainly based on carbon fiber and glass fiber. Its power system is powered by a rare earth permanent magnet synchronous motor, the power source is a lithium battery pack, the lithium battery pack is installed in the battery compartment, the propeller is connected to the motor, and the motor and motor controller are placed in the electric propulsion device compartment. It has a reasonable structure, fewer running and transmission parts, high reliability, fully enclosed structure, high protection level, high efficiency up to 94%, strong power and simple operation. Due to the low operating cost of the new clean energy lithium battery, it solves the problems of greenhouse effect and noise pollution caused by the emission of a large amount of exhaust gas from the existing fuel light aircraft flying in the sky. Its integral cockpit has good structural strength and comfortable ride, and the cockpit has a wide field of vision, which can be widely used in passenger transportation, agriculture, geological exploration, and strong disaster relief.

Description

Composite two-seater electric ultralight sport aircraft

technical field

The utility model relates to an electric manned ultra-light sports aircraft, in particular to a composite material two-seat electric aircraft, which belongs to the technical field of aerospace.

Background technique

From the United States, where the general aviation industry is the most developed, 70% of general-purpose aircraft are small and medium-sized private aircraft. Nowadays, spending 10,000 yuan for a four-hour two-seater light aircraft experience flight is not new in China. Therefore, the development of light aircraft with 4 seats and below is the first choice. Unlike the vast low-altitude airspace in Europe and the United States, my country's low-altitude airspace mostly exists independently in a small area. At the same time, due to the influence of high-speed rail, expressways and regional aviation, the living space of general aviation transportation is small. Private jets in my country are mainly used for local small-range, multi-sortie coaching, recreational flights and short-distance transition flights. The demand for long endurance is not urgent, so electric light aircraft can basically meet the above requirements.

my country has listed the general aviation industry as a national strategic emerging industry. The State Council deepened the reform of low-altitude airspace management, and the low-altitude airspace was gradually liberalized. Civil Aviation of China revised CCAR61, and newly proposed sports driver's license, which was included in the Northeast Old Industrial Base Revitalization Plan as a key development industry. These opportunities strongly stimulated the market's demand for general-purpose aircraft.

With the development of my country's general aviation industry, the demand for pilots will be large and urgent, and flying driving schools will emerge rapidly. Light electric aircraft are very suitable for large-scale purchases by driving schools because of their low purchase cost, low operating cost and convenient maintenance. Training on sports photos and private photos.

Contents of the invention

The purpose of the utility model is to solve the above problems, mainly to solve the problems of high manufacturing cost, environmental pollution and high noise in the prior art, and to provide a composite material two-seater electric manned ultra-light sports car with reasonable structure and good applicability. Aircraft to meet people's needs.

In order to achieve the above object, the technical solution adopted by the utility model is: composite material two-seater electric ultra-light sports aircraft, the aircraft structure adopts a composite material structure mainly based on carbon fiber and glass fiber, and it includes a fuselage, wing, empennage and starting off the shelf. It also includes the aircraft power system. The aircraft power system is powered by a rare earth permanent magnet synchronous motor. The power source is a lithium battery pack. The lithium battery pack is located in the battery compartment. Inside the electric propulsion unit compartment. The wing adopts a double-segment wing shape with a large aspect ratio, and the structure is composed of three parts: the main wing, the aileron and the spoiler.

The fuselage includes a battery compartment, an electric propulsion unit compartment, a firewall, a windshield, a window, a cockpit, a fuselage skin, a bulkhead, a vertical stabilizer, and the like. The above-mentioned firewall is installed between the electric propulsion device cabin and the cockpit, which plays the role of fire prevention and heat insulation, so as to effectively protect the safety of the pilots; The structural strength of the rear section; the above-mentioned windshield is installed on the fuselage directly in front of the cockpit and fixed by rivets; the above-mentioned window is installed on the fuselage above the rear and upper part of the cockpit provided with pedals and driving rods and fixed by rivets; the above-mentioned fuselage The skin and vertical stabilizer are integrally formed.

The battery compartment is installed at the rear and lower part of the cockpit.

The wing adopts a large-aspect-ratio upper monoplane, a T-shaped tail, a front three-point fixed landing gear, a front propeller, and a layout structure of two seats with doors on both sides. The above-mentioned main wing structure includes wing skin, spar, rear wall, root rib, ordinary rib, etc.; the above-mentioned root rib is glued and installed on the outermost side; the above-mentioned spoiler is installed between the spar and the rear wall, Among them, it plays the role of deceleration; the above-mentioned ordinary ribs are distributed and installed inside the wing skin through glue joints, and effectively support the wing skin; the above-mentioned rear wall is connected with the aileron through hinges; the above-mentioned tail structure includes a flat tail stabilizer, an elevator and rudder.

The rudder is connected to the vertical stabilizer through a hinge.

The elevator is connected with the stabilizer of the flat tail through a hinge.

The flat tail stabilizer is installed on the upper side of the vertical stabilizer through a connecting piece.

Described undercarriage is made up of two parts of front undercarriage and main undercarriage. The front landing gear adopts the form of spring shock absorption, which has the function of ground taxiing and steering, and is linked with the rudder; the main landing gear adopts the form of leaf spring shock absorption, and has the function of braking when taxiing on the ground. The above-mentioned front landing gear is installed on the fuselage front, and the main landing gear is installed on the bottom of the fuselage below the rear side of the cockpit through connecting pieces.

The aircraft power system mainly includes a motor, a motor controller, a lithium battery pack and a propeller. Both the motor and the motor controller are placed in the electric propulsion device compartment; the lithium battery pack is placed in the battery compartment; the propeller is connected with the motor.

Beneficial effects and characteristics of the utility model:

1. Rare earth permanent magnet synchronous motor is used as the power. The motor has simple structure, fewer running and transmission parts, high reliability and a fully enclosed structure, high protection level, and its efficiency can be as high as 94%. It has large specific power, strong power and simple operation. .

2. The use of a new type of clean energy lithium battery has a low operating cost, which solves the greenhouse effect caused by the emission of a large amount of exhaust gas from the existing fuel light aircraft flying in the sky, while the utility model has no pollution gas emission during flight and has little impact on the environment In addition, my country is densely populated, and fuel-fueled aircraft will cause relatively large noise pollution, but the utility model solves the problem of high noise of existing light aircraft.

3. 90% of the body structure of the utility model is made of full-composite materials mainly composed of carbon fiber and glass fiber. It has a reasonable structure, streamlined appearance, smooth surface, long life and easy maintenance.

4. Integral cockpit structure with good structural strength and beautiful appearance. The seat design conforms to ergonomics. The backrest angle of the seat is 26°. Disaster relief and other fields.

Description of drawings

Figure 1 is a front view of the aircraft (omitting the right wing).

Fig. 2 is a left side view of Fig. 1 .

Figure 3 is a structural diagram of the fuselage.

Figure 4 is a structural layout diagram of the wing.

The symbols in the figure represent: 1. Electric motor; 2. Motor controller; 3. Pedals; 4. Steering rod; 5. Battery compartment; 6. Aileron; 7. Spoiler; ; 10, electric propulsion cabin; 11, firewall; 12, windshield; 13, window; 14, cockpit and hatch; 15, fuselage skin; 16, bulkhead; 17, vertical tail stabilizer; 18, spar ; 19, root rib; 20, common rib; 21, wing skin; 22, rear wall; 23, rudder; 24, front landing gear; 25, main landing gear; 26, propeller.

detailed description

Example

Referring to Fig. 1-Fig. 4, the two-seater electric ultra-light sports aircraft made of composite materials, the aircraft structure adopts a full composite material structure mainly composed of carbon fiber and glass fiber, which mainly includes the fuselage, wing, empennage and landing gear. It also includes an aircraft power system, which is powered by a rare earth permanent magnet synchronous motor, and the power source is a lithium battery pack, which is located in the battery compartment 5 .

The fuselage includes a battery compartment 5, an electric propulsion unit compartment 10, a firewall 11, a windshield 12, a window 13, a cockpit 14, a fuselage skin 15, a bulkhead 16, a vertical stabilizer 17, and the like.

The above-mentioned firewall 11 is installed between the electric propulsion device cabin 10 and the cockpit 14, and plays the role of fire prevention and heat insulation, thereby effectively protecting the safety of the pilots;

The above-mentioned bulkhead 16 is installed inside the rear section of the fuselage through glue bonding, effectively enhancing the structural strength of the rear section of the fuselage;

Above-mentioned windshield 12 is installed on the fuselage directly in front of cockpit 14, fixed by rivets; above-mentioned window

Door 13 is installed on the fuselage above the cockpit 14 that is provided with pedal 3 and driving bar 4, is fixed by rivets;

The fuselage skin 15 and the vertical stabilizer 17 are integrally formed.

Described battery compartment is installed in the rear bottom of cockpit 14.

The wing adopts the shape of a double-section wing with a large aspect ratio, and the structure is composed of three parts: the main wing, the aileron 6 and the spoiler 7 .

The main wing structure includes wing skin 21, spar 18, rear wall 22, root rib 19, common rib 20, etc.; the root rib 19 is glued and installed on the outermost side;

The above-mentioned spoiler 7 is installed between the spar 18 and the rear wall 22, and plays the role of deceleration during the landing process of the aircraft;

The above-mentioned ordinary ribs 20 are distributed and installed inside the wing skin 21 through glue bonding, so as to effectively support the wing skin 21;

Above-mentioned aileron 6 is connected with rear wall 22 by hinge. Above-mentioned empennage structure comprises flat tail stabilizer 8, elevator 9 and rudder 23. The rudder 23 is connected to the vertical stabilizer 17 through a hinge; the elevator 9 is connected to the horizontal stabilizer 8 through a hinge; the horizontal stabilizer 8 is installed on the upper side of the vertical stabilizer 17 through a connecting piece.

Above-mentioned landing gear is made up of front landing gear 24 and main landing gear 25 two parts. The front landing gear 24 adopts a spring damping form, has a ground taxiing steering function, and is linked with the rudder; the main landing gear 25 adopts a leaf spring damping form, and has a braking function when taxiing on the ground. The above-mentioned front landing gear 24 is installed on the fuselage front, and the main landing gear 25 is installed on the fuselage bottom below the cockpit 14 rear side by connecting pieces.

The aircraft power system mainly includes a motor 1 , a motor controller 2 , a lithium battery pack 5 and a propeller 26 . Both the motor 1 and the motor controller 2 are placed in the electric propulsion device cabin 10 ; the lithium battery pack is placed in the battery compartment 5 ; the propeller 26 is connected with the motor 1 .

The utility model has an efficient aerodynamic shape, high aerodynamic efficiency, low resistance, measured lift-to-drag ratio up to 22, good gliding performance, low stall speed, good maneuverability, and safe flight. The aerodynamic layout and performance parameters of the aircraft are shown in Table 1 and Table 1. 2 and Table 3:

Table 1 General parameters of the aircraft

Table 2 Aerodynamic layout parameters

Table 3 aircraft performance parameters

The operating system of the utility model adopts a manual operation scheme and is divided into a main operating system and an auxiliary operating system. The main control system is parallel double control sticks, with two sets of linked control sticks and pedals. The control stick controls the elevator and aileron deflection, and the pedals control the rudder deflection and front wheel turning. All rudder surfaces are controlled by push-pull cables. , the auxiliary control system manipulates the resistance plate by pushing and pulling the steel cable.

Claims (5)

1. the electronic microlight-type sport plane of composite material two-seater, comprise fuselage, wing, empennage and alighting gear, also comprise aircraft power system, it is characterized in that: described aircaft configuration, that is: fuselage, wing, empennage and alighting gear adopt the composite structure based on carbon fiber and glass fibre; Described aircraft power system take rare-earth permanent-magnet synchronous motor as power, and propulsion source is lithium cell group, and lithium cell group is located in battery flat, and screw propeller is connected with electrical motor, and electrical motor and electric machine controller are all placed in electric propulsion device cabin; Described wing adopts the two section wing-like of high aspect ratio, structure by main wing, aileron and spoiler three part form.

2. the electronic microlight-type sport plane of composite material two-seater as claimed in claim 1, it is characterized in that: described fuselage comprises battery flat, electric propulsion device cabin, fireproof brickwork, windscreen, window, passenger cabin, fuselage skin, bulkhead and fixed fin, and above-mentioned fireproof brickwork is arranged between electric propulsion device cabin and passenger cabin; Above-mentioned bulkhead, by glueing joint, is arranged on aft body inside, and actv. strengthens the structural strength of aft body; Above-mentioned windscreen is arranged on the fuselage in passenger cabin dead ahead, is fixed by rivet; Above-mentioned window is arranged on the fuselage of the passenger cabin back upper place being provided with pedal and jociey stick, is fixed by rivet; Above-mentioned fuselage skin and fixed fin adopt one-body molded; Described battery flat is arranged on the back lower place of passenger cabin.

3. the electronic microlight-type sport plane of composite material two-seater as claimed in claim 1, is characterized in that: it adopts high aspect ratio high mounted wing, T-tail, front three-point fixed landing gear, preposition screw propeller, and the layout structure form opened the door in two-seater both sides.

4. the electronic microlight-type sport plane of composite material two-seater as claimed in claim 1, is characterized in that: described main wing structure comprises wing cover, spar, Hou Qiang, root, common rib etc.; Above-mentioned root splicing is arranged on outermost; Above-mentioned spoiler is arranged between spar and rear wall; Above-mentioned common rib is inner at wing cover by glueing joint distributing installation, and actv. supports wing cover; Above-mentioned aileron is connected with rear wall by hinge, and above-mentioned tail structure comprises horizontal tail stabilator, elevating rudder and yaw rudder, and described yaw rudder is connected with fixed fin by hinge; Described elevating rudder is connected with horizontal tail stabilator by hinge; Described horizontal tail stabilator is arranged on the upside of fixed fin by attaching parts.

5. the electronic microlight-type sport plane of composite material two-seater as claimed in claim 1, it is characterized in that: described alighting gear is made up of nose-gear and main landing gear two parts, nose-gear adopts spring shock absorption form, has ground taxi turning function, links with yaw rudder; Main landing gear adopts leaf spring damping form, and have brake function during ground taxi, above-mentioned nose-gear is arranged on forebody, and main landing gear is arranged on the fuselage bottom of below on rear side of passenger cabin by attaching parts.