CN210503184U

CN210503184U - Double-seat light airplane with complete machine parachute

Info

Publication number: CN210503184U
Application number: CN201821561444.2U
Authority: CN
Inventors: 徐强; 欧阳星; 田云; 曾晓康; 万勇波
Original assignee: Zhuoer Aircraft Manufacturing Wuhan Co ltd
Current assignee: Zhuoer Aircraft Manufacturing Wuhan Co ltd
Priority date: 2018-09-25
Filing date: 2018-09-25
Publication date: 2020-05-12
Anticipated expiration: 2028-09-25

Abstract

The utility model discloses a take light-duty aircraft of double seat of complete machine parachute, the reciprocating impact tunnel drilling machine comprises a machine body, fuselage front portion and cockpit rear portion riveting, the front portion riveting of cockpit has the engine compartment, and fuselage rear portion and fin riveting, cockpit rear portion fixed mounting have the parachute cabin, and the complete machine parachute places in the parachute cabin, and the wing contains central wing box and trapezoidal outer wing to and the wing winglet of upwarping slightly. The utility model discloses a complete machine parachute, very big improvement the aircraft security, guarantee member's life safety to alleviate the aircraft to a certain extent when turning to, lead to the accident that the aircraft unstability produced because of the lift distribution is uneven.

Description

Double-seat light airplane with complete machine parachute

Technical Field

The utility model relates to an airborne vehicle field specifically is a take light-duty aircraft of double seat of complete machine parachute.

Background

In recent years, the nation changes the advanced industry of the general aviation industry positioning strategy to boost economy, continuously issues support policies from the aspects of low-altitude airspace management, general airport construction, general airplane research and development and manufacture, flight approval, operation, maintenance and the like, and comprehensively promotes the rapid development of general aviation.

Because the double-seat light airplane has the advantages of low purchase and operation cost and simple and convenient maintenance, the double-seat light airplane is widely applied to aspects of license training, private flight, sightseeing and touring, aviation mapping and the like, and plays a significant role in the general aviation market.

The double-seat light aircraft on the market at present has large flight cruising resistance, does not have the functions of heat insulation and fire prevention, has insufficient structural strength and poor lift increasing effect.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a take light-duty aircraft of double seat of complete machine parachute, its technical scheme as follows:

a double-seat light airplane with a complete machine parachute comprises a fuselage 1, a cockpit 2, an engine cabin 3, a rudder 5, a nose landing gear 6, a main landing gear 7, a canopy 8, wings 9, ailerons 10, flaps 11, a parachute cabin 12, a horizontal stabilizer 13, a vertical stabilizer 14, small wing wings 15, a central wing box 16, a trapezoidal outer wing 17, a lifting rudder 18 and a firewall 19, and is characterized in that the front part of the fuselage 1 is riveted with the rear part of the cockpit 2, the front part of the cockpit 2 is riveted with the engine cabin 3, the rear part of the fuselage 1 is riveted with a tail wing, the parachute cabin 12 is fixedly installed at the rear part of the cockpit 2, the complete machine parachute is placed in the parachute cabin 12, the wings 9 comprise the central wing box 16, the trapezoidal outer wing 17 and the upturned wing winglets 15, the outer wing sections of the wings 9 are riveted with a central wing box 16 penetrating through three connecting lugs and bolts on double beams, the central wing box 16 is riveted with one side of the trapezoidal outer wing 17, the other side of the trapezoidal outer wing 17 is riveted with a wing tip winglet 15, the inner back edge of the trapezoidal outer wing 17 is fixedly provided with a fuller flap 11 and the outer back edge is fixedly provided with an aileron 10, the nose landing gear 6 is fixedly arranged at the bottom of a firewall 19, the main landing gear 7 is fixedly arranged on the central wing box 16 of the belly, the vertical stabilizer 14 and the rudder 5 form a vertical tail, the vertical stabilizer 14 is directly riveted with the rear part of the fuselage 1, the rudder 5 is riveted with the vertical stabilizer 14 through a hinged support, the horizontal stabilizer 13 and the elevator 18 form a horizontal tail, the horizontal stabilizer 13 is fixed with the rear part of the fuselage 1 through bolts, and the elevator 18 is riveted with the horizontal stabilizer 13 through a hinged support.

The nose landing gear 6 and the main landing gear 7 are damped by rubber blocks.

The cockpit 2 adopts integral transparent canopy, and two seats side by side are arranged in the cockpit 2.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model discloses very big improvement the aircraft security, guarantee passenger's life safety. The airplane with the fullerene flap has good lift-increasing effect.

Drawings

Fig. 1 is a left side view of a double-seat light aircraft with a complete set parachute.

Fig. 2 is a top view of a double-seater light aircraft with complete machine parachute.

Fig. 3 is a front view of a double-seat light aircraft with complete machine parachute.

As shown in the figure: the airplane comprises a fuselage 1, a cockpit 2, an engine compartment 3, a rudder 5, a nose gear 6, a main gear 7, a canopy 8, wings 9, ailerons 10, flaps 11, a parachute bay 12, a horizontal stabilizer 13, a vertical stabilizer 14, a wing tip wing 15, a central wing box 16, a trapezoidal outer wing 17, an elevator 18 and a firewall 19.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1 to 3, in an embodiment of the present invention, a double-seat light aircraft with a complete machine parachute includes a fuselage 1, a cockpit 2, an engine compartment 3, a rudder 5, a nose gear 6, a main gear 7, a canopy 8, wings 9, ailerons 10, flaps 11, a parachute bay 12, a horizontal stabilizer 13, a vertical stabilizer 14, a wing minor wing 15, a central wing box 16, a trapezoidal outer wing 17, a lift rudder 18, and a firewall 19;

the front part of the fuselage 1 is riveted with the rear part of the cockpit 2, the front part of the cockpit 2 is riveted with an engine compartment 3, the rear part of the fuselage 1 is riveted with a tail wing, and the engine compartment 3 and the cockpit 2 are separated by a firewall 19. The fireproof wall 19 is provided with a stainless steel plate and fireproof cotton, has the functions of heat insulation and fire prevention, and also has the function of reinforcing the structure, and the whole structure is mainly made of metal materials;

a parachute cabin 12 is fixedly installed at the rear portion of the cockpit 2, and the complete parachute is placed in the parachute cabin 12, and in case of emergency, the complete parachute is popped up by pulling a starting handle on an instrument board in the cockpit 2. After the parachute is unfolded, the whole machine and passengers land at a safe descending speed, and the cockpit 2 (namely the cockpit) adopts an integral transparent cockpit cover, so that the visual field of the passengers is good. Two seats side by side are arranged in the cockpit, a bent square steel pipe is designed at the top of the center of the cockpit 2 to serve as a guide rail, and the cockpit cover slides backwards along the guide rail to be opened. The guide rail has a handrail supporting function when a driver gets in and out of the cab 2 and sits down and gets up, and provides convenience for passengers.

The wing 9 comprises a central wing box 16, a trapezoidal outer wing 17 and an upturned wing tip 15. The wing 9 adopts a double-beam structure, and the outer wing section is connected with a central wing box 16 penetrating through the bottom of the fuselage 1 through three connecting lugs and bolts on the double beams; the two lugs on the main beam are mainly used for transmitting vertical shear force on the wing 9 and bending moment around the longitudinal axis of the fuselage 1, and the single lug on the rear beam and the two lugs on the main beam bear the wing span-wise torque and the bending moment around the vertical axis of the fuselage on the wing. The three-point connecting lug has the advantages of simple butt joint and high positioning precision. The slightly smaller upturned wing 15 effectively reduces flight cruise drag and improves cruise efficiency. The inner rear edge of the trapezoidal outer wing 17 section is fixedly provided with a fuller flap 11 and the outer rear edge is fixedly provided with an aileron 10. The driving rod and the transmission gear rotate through the flap motor, and the driving flap 11 is unfolded backwards and downwards along the wing rib guide groove, so that the camber of the wing 9 is increased, the effective area of the wing 9 is increased, and a larger lift force is provided.

The nose landing gear 6 and the main landing gear 7 jointly form a landing gear system, and the landing gear system adopts a three-point nose layout. The nose landing gear 6 is fixedly arranged at the bottom of the firewall 19, has a ground steering function, and adopts a rubber block for damping, and the main landing gear 7 is fixedly arranged on a central wing box 16 of the belly and also adopts a rubber block for damping;

the vertical stabilizer 14 and the rudder 5 form a vertical tail, the vertical stabilizer 14 is directly riveted with the rear part of the machine body 1, and the rudder 5 is riveted with the vertical stabilizer 14 through a hinged support. The horizontal stabilizing surface 13 and the elevator 18 form a horizontal tail, the horizontal stabilizing surface 13 is fixed on the rear part of the machine body 1 through bolts, and the elevator 18 is riveted with the horizontal stabilizing surface 13 through a hinged support;

although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention.

Claims

1. The utility model provides a take light-duty aircraft of double seat of complete machine parachute, includes fuselage (1), cockpit (2), engine compartment (3), rudder (5), nose gear (6), main undercarriage (7), canopy (8), wing (9), aileron (10), flap (11), parachute cabin (12), horizontal stabilizer (13), perpendicular stabilizer (14), wing tip winglet (15), central wing box (16), trapezoidal outer wing (17), elevator (18) and prevent hot wall (19), its characterized in that, fuselage (1) front portion and cockpit (2) rear portion riveting, the front portion riveting of cockpit (2) has engine compartment (3), fuselage (1) rear portion and fin riveting, cockpit (2) rear portion fixed mounting has parachute cabin (12), and the parachute is placed in parachute cabin (12), wing (9) contain central wing box (16), The wing tip winglet comprises a trapezoidal outer wing (17) and an upturned wing tip winglet (15), wherein the outer wing section of a wing (9) is riveted with a central wing box (16) penetrating through the bottom of a fuselage (1) through three connecting lugs and bolts on two beams, one side of the central wing box (16) is riveted with the trapezoidal outer wing (17), the other side of the trapezoidal outer wing (17) is riveted with the wing tip winglet (15), the rear edge of the inner side of the trapezoidal outer wing (17) section is fixedly provided with a flap (11) and a secondary wing (10) of a fullerene, a front undercarriage (6) is fixedly arranged at the bottom of a firewall (19), a main undercarriage (7) is fixedly arranged on the central wing box (16) of the belly, a vertical stabilizer (14) and a rudder (5) form a vertical tail, the vertical stabilizer (14) is directly riveted with the rear part of the fuselage (1), and the rudder (5) is riveted with the vertical stabilizer (14) through a hinged support, the horizontal stabilizer (13) and the elevator (18) form a horizontal tail, the horizontal stabilizer (13) is fixed on the rear part of the machine body (1) through bolts, and the elevator (18) is riveted with the horizontal stabilizer (13) through a hinged support.

2. A light aircraft with double seats and complete set parachute as claimed in claim 1, wherein the nose landing gear (6) and the main landing gear (7) are damped by rubber blocks.

3. The double-seat light aircraft with complete machine parachute as claimed in claim 1, wherein the cockpit (2) is an integral transparent canopy, and two seats are arranged side by side in the cockpit (2).