CN105253288A - Double-seater power-driven ultra-light sport aircraft made of composite materials - 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 present invention 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 invention 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 present invention is to solve the above-mentioned problems, and mainly solve the problems of high manufacturing cost, environmental pollution and high noise in the prior art, and provide a composite material two-seater electric manned ultra-light sports aircraft with reasonable structure and good applicability to meet people's needs.

In order to achieve the above object, the technical solution adopted in the present invention is: composite material two-seater electric ultra-light sports aircraft, the aircraft structure adopts a composite material structure based on carbon fiber and glass fiber, which includes fuselage, wing, empennage and landing gear . 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 present invention:

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 new type of clean energy lithium battery has low operating cost, which solves the greenhouse effect caused by the emission of a large amount of exhaust gas when the existing fuel light aircraft flies in the sky, while the present invention has no pollution gas emission during flight and has little impact on the environment; In addition, my country's population is dense, and fuel-fueled aircraft will cause relatively large noise pollution, but the invention solves the problem of high noise in existing light aircraft.

3. 90% of the body structure of the present invention is made of full-composite materials mainly composed of carbon fiber and glass fiber. It has 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 unit 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 13 is installed on the fuselage above the cockpit 14 that is provided with pedal 3 and driving rod 4, 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 invention 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 2 respectively. and table 3:

Table 1 General parameters of the aircraft

Table 2 Aerodynamic layout parameters

Table 3 aircraft performance parameters

The control system of the present invention adopts a manual operation scheme and is divided into a main control system and an auxiliary control 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. a composite material two-seater electric ultra-light sports aircraft, comprising fuselage, wing, empennage and landing gear, also comprises aircraft power system, is characterized in that: described aircraft structure, namely: fuselage, wing, The empennage and landing gear adopt a composite material structure mainly composed of carbon fiber and glass fiber; the aircraft power system 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. The motors are connected, and the motors and motor controllers are placed in the electric propulsion device cabin; 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 and the spoiler. 2. The two-seat electric ultra-light sports aircraft of composite material as claimed in claim 1, wherein the fuselage comprises a battery cabin, an electric propulsion cabin, a firewall, a windshield, a window, a cockpit, a fuselage skin, a partition Frame and vertical stabilizer, the above-mentioned firewall is installed between the electric propulsion device compartment and the cockpit; the above-mentioned bulkhead is installed inside the rear section of the fuselage through glue bonding, which effectively enhances the structural strength of the rear section of the fuselage; the above-mentioned windshield is installed in the cockpit The fuselage directly in front is fixed by rivets; the above-mentioned windows are installed on the fuselage above the cockpit with pedals and driving rods and fixed by rivets; the skin of the fuselage and the vertical stabilizer are integrally formed; The battery compartment is installed under the rear of the cockpit. 3. The two-seater electric ultra-light sports aircraft of composite material as claimed in claim 1, is characterized in that: it adopts a single wing with a large aspect ratio, a T-shaped tail, a front three-point fixed landing gear, a front propeller, and The layout and structure of double seats with doors on both sides. 4. The composite two-seat electric ultra-light sports aircraft according to claim 1, wherein the main wing structure includes wing skin, spar, rear wall, root ribs, common ribs, etc.; the root rib glue The above-mentioned spoiler is installed between the spar and the rear wall; the above-mentioned ordinary ribs are distributed and installed inside the wing skin through glue joints to effectively support the wing skin; the above-mentioned aileron is connected to the rear wall through hinges. The above-mentioned empennage structure includes a horizontal stabilizer, an elevator and a rudder, the rudder is connected to the vertical stabilizer through a hinge; the elevator is connected to the horizontal stabilizer through a hinge; the horizontal stabilizer is installed on the vertical stabilizer through a connecting piece on the upper side. 5. The composite material two-seat electric ultra-light sports aircraft according to claim 1, wherein the landing gear is composed of two parts, the front landing gear and the main landing gear, and the front landing gear adopts a spring shock absorbing form, with Ground taxi steering function, linked with the rudder; the main landing gear adopts the form of leaf spring shock absorption, and has a braking function when taxiing on the ground. The bottom of the fuselage.