CN212530039U - Tandem double-seat general airplane - Google Patents

Abstract

The utility model discloses a tandem double-seat universal plane, which comprises a drop-shaped plane body, a pair of V-shaped vertical tails, a turbine propeller engine and a thrust propeller which are arranged at the rear part of the plane body, and an upper single wing which is arranged at the upper part of the plane body; the inside of the machine body is provided with a front seat and a rear seat, wherein the front seat and the rear seat respectively correspond to the front glass cabin cover which is opened upwards and the side cabin door which is opened to the side surface. The utility model discloses the fuselage adopts the water droplet form section, and the pneumatic drag reduction of better realization fuselage simultaneously with the engine rearmounted, reduces the influence of screw slipstream to aircraft pneumatic performance. The upper single wing design is adopted, the downward visual field of passengers is improved, and the passenger sightseeing device is more suitable for tourist. The V-shaped vertical fin design is adopted to combine the functions of the horizontal fin and the vertical fin, so that the weight of the structure is reduced. The lower part of the machine body is provided with a buoy, and the landing gear can be retracted and extended, so that the landing on water can be realized under the emergency condition, and the safety of passengers is improved. Meanwhile, the back of the machine body is provided with a complete machine parachute, so that the safety of the airplane and passengers under the emergency condition is further ensured.

Description

Tandem double-seat general airplane

Technical Field

The utility model relates to an aircraft manufacturing technical field, in particular to tandem double seat general aircraft.

Background

The existing tandem double-seat universal aircraft mainly comprises three types of aircraft such as a Chinese junior education 6, a Czech shark aircraft and an Austrian DART-450, and has the common characteristics that the conventional lower single-wing and low horizontal tail layout is adopted, a better downward visual field is lacked, tension propellers are adopted, an engine is arranged at the head part, the overall aerodynamic performance of the aircraft is influenced by the slipstream of the propellers, and the induced resistance of the aircraft is increased. Chinese patent CN205418063U discloses a tandem two-seater flying car, which has the following problems: 1. the layout of double vertical tails and high horizontal tails is adopted, so that the structure weight is large, and the maneuvering performance of the airplane is low; 2. the vertical tails and the horizontal tails are positioned in a slipstream area of the propeller, the pneumatic surface efficiency is low, the sound fatigue problem of the tail wing structure is easily caused, and the service life of the product is short; 3. the automobile tires can not be collected in the cabin section of the airplane body, so that large aerodynamic resistance is caused, the fuel economy of the airplane is influenced, and the voyage of the airplane is further reduced.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a tandem two seat general aircraft to the problem that above-mentioned prior art exists.

Realize the utility model discloses the technical solution of purpose does: a tandem two-seater universal airplane comprises a water-drop-shaped airplane body, a pair of V-shaped vertical tails, a turbine propeller engine and a thrust propeller, wherein the V-shaped vertical tails, the turbine propeller engine and the thrust propeller are arranged at the rear part of the airplane body; the front seat and the rear seat are respectively corresponding to a front glass cabin cover which is opened upwards and a side cabin door which is opened to the side.

Furthermore, an S-shaped air inlet channel is arranged at the back of the rear machine body of the machine body and is used for combustion air entraining of a turbine propeller engine; the lower part of the machine body is provided with an exhaust port for exhausting combustion gas of the engine.

Furthermore, the thrust propeller is mounted on a propeller hub at the tail of the fuselage, the propeller hub is connected with the torque output shaft of the engine and is rectified by a propeller cap, and the propeller cap is covered and fixed on the propeller hub and has a gap with the fuselage.

Furthermore, the upper single wing is of a double-beam wing structure, the front edge of the wing is swept backward, and the rear edge of the wing is not swept backward; the end part of the wing is provided with a wingtip winglet which is used for improving the aerodynamic performance and reducing the resistance; an aileron is arranged at the rear part of the wing and at one side far away from the fuselage and is used for controlling the rolling attitude of the airplane; and the outer wing flap and the inner wing flap are sequentially arranged at the rear part of the wing and close to the fuselage along the aileron, and are used for improving the take-off and landing performance of the airplane and increasing the lift force of the airplane.

Furthermore, a control surface is arranged on the V-shaped vertical tail and used for controlling the pitching and yawing postures of the airplane.

Further, the aircraft includes a complete machine landing system, which includes: the parachute cabin door is arranged at the back of the machine body and positioned in front of the S-shaped air inlet channel, is opened and closed under the control of the parachute cabin door retracting and stretching support rod, and can shield the S-shaped air inlet channel opening after being opened; the parachute assembly device is characterized by further comprising a parachute front end tying belt arranged in a first skin mounting groove of the fuselage and a pair of parachute rear end tying belts arranged in a second skin mounting groove and a third skin mounting groove, the third tying belts are fixed on a fuselage force bearing frame, the first skin mounting groove extends to the front end of the fuselage from the parachute bay, and the second skin mounting groove and the third skin mounting groove extend to the rear end of the fuselage from the parachute bay and are symmetrically arranged relative to the fuselage; when a dangerous condition occurs, the parachute cabin door is controlled to open the parachute cabin door through the retractable support rod, the S-shaped air inlet channel is blocked, the parachute is taken out of the parachute cabin door through the pushing device, and the tying belt in the covering installation groove is dragged to break out of the surface of the machine body.

Furthermore, buoys are symmetrically arranged at the front end of the lower portion of the airplane body and on two sides of the middle of the lower portion of the airplane body and used for respectively containing a front undercarriage located at the front end of the lower portion of the airplane body after the airplane takes off and a pair of main undercarriages located on two sides of the middle of the lower portion of the airplane body.

Compared with the prior art, the utility model, it is showing the advantage and is: 1) the body of the airplane adopts a drop-shaped section, so that pneumatic resistance reduction of the body is better realized, and meanwhile, the engine is arranged at the rear part, so that the influence of the slipstream of the propeller on the pneumatic performance of the airplane is reduced; 2) the upper single wing design is adopted, so that the downward visual field of passengers is improved, and the passenger sightseeing device is more suitable for travelers; 3) the V-shaped vertical fin design is adopted to combine the functions of the horizontal fin and the vertical fin, so that the structural weight is reduced; 4) the lower part of the machine body is provided with a buoy, and the landing gear can be retracted, so that the water landing and the like can be realized under the emergency condition, and the safety of passengers is improved; 5) the back of the machine body is provided with a complete machine parachute, so that the safety of the airplane and passengers under the emergency condition is further ensured.

The present invention will be described in further detail with reference to the accompanying drawings.

Drawings

Figure 1 is a side view of a tandem aircraft door in one embodiment, shown unopened.

Figure 2 is a side view of a tandem aircraft door in one embodiment.

Fig. 3 is a side view of a tandem universal aircraft landing gear, boarding foot stowed in one embodiment.

FIG. 4 is a top view of a tandem aircraft.

FIG. 5 is an elevation view of a tandem aircraft in one embodiment.

FIG. 6 is a layout diagram of a tandem aircraft total landing system according to one embodiment.

Figure 7 is a schematic view of parachute harness installation in one embodiment.

Fig. 8 is a schematic view showing the opening of the parachute of the complete machine in one embodiment.

Detailed Description

In order to facilitate understanding of the present invention, the present invention will be described more fully hereinafter with reference to the accompanying drawings. Preferred embodiments of the present invention are shown in the drawings. The invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

It should be noted that, if directional indications such as up, down, left, right, front, and back … … are provided in the embodiment of the present invention, the directional indications are only used to explain the relative position relationship between the components, the motion situation, etc. in a specific posture as shown in the drawings, and if the specific posture is changed, the directional indications are changed accordingly.

In addition, if there is a description relating to "first", "second", etc. in the embodiments of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions in the embodiments may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should not be considered to exist, and is not within the protection scope of the present invention.

In one embodiment, with reference to fig. 1 and 2, there is provided a tandem two-seater universal aircraft, comprising a waterdrop-shaped fuselage 1, a pair of V-shaped vertical tails 2 arranged at the rear of the fuselage, a turboprop engine 4 and a thrust propeller 6, an upper single wing 3 arranged at the upper part of the fuselage; two seats, namely a front seat and a rear seat, are arranged in the drop-shaped fuselage 1, wherein the front seat 9 and the rear seat 10 correspond to a front glass cabin cover 11 which is opened upwards and a side cabin door 14 which is opened to the side respectively.

Here, the front glass hatch 11 and the side hatch 14 are preferably connected to the fuselage by means of hinges 12.

Here, further, the side hatch 14 is provided with a glass window to facilitate the passenger's sightseeing.

Here further, the rear fuselage of the rear seat 10 is provided with an oval window 16 to increase the overall aesthetic appeal of the aircraft.

Further, in one embodiment, a retractable support rod 13 is arranged between the opening and closing surfaces of the front glass cabin cover 11 and the side cabin door 14, and is used for opening and fixing the cabin cover or the cabin door.

Further, in one embodiment, a retractable pedal 15 is arranged outside the fuselage of the side of the front seat 9 and used for passengers to get on or off the airplane, and in the shutdown state, the retractable pedal 15 is opened and put down, and the flying state is retracted.

Further, in one embodiment, a luggage compartment 17 is provided in the rear body of the rear seat 10 for storing luggage.

Further, in one of the embodiments, the rear fuselage back of the fuselage 1 is provided with an S-shaped air inlet duct 18 for the turbine propeller engine 4 to burn bleed air; the lower part of the body 1 is provided with an exhaust port 19 for discharging engine combustion gas.

Here, the inlet lip is preferably oval-shaped, as shown in fig. 5.

Further, in one embodiment, the thrust propeller 6 is mounted on a hub 20 at the rear of the fuselage, the hub 20 is connected to an engine torque output shaft 21 and is faired by a propeller cap 22, and the propeller cap 22 is attached to and fixed to the hub 20 with a clearance from the fuselage to prevent abrasion.

Here, the thrust propeller 6 is preferably trefoil.

Further, in one embodiment, referring to fig. 4, the upper monowing 3 has a double-beam wing structure, the wing leading edge has backswept, and the wing trailing edge has no backswept; the end part of the wing is provided with a wingtip winglet (23) for improving the aerodynamic performance, reducing the resistance and simultaneously improving the overall appearance of the airplane; an aileron 24 is arranged at the rear part of the wing and at one side far away from the fuselage and is used for controlling the rolling attitude of the airplane; and an outer flap 25 and an inner flap 26 are sequentially arranged at the rear part of the wing and close to the fuselage along the aileron 24, and are used for improving the take-off and landing performance of the airplane and increasing the lift force of the airplane.

Preferably here, the wing leading edge sweep angle is 5 ° and the wing stagger angle is 3 °.

Further, in one embodiment, referring to fig. 4, the V-shaped vertical fin 2 is provided with a control surface 27 for controlling the pitch and yaw attitude of the aircraft.

Further, in one embodiment, with reference to fig. 6-8, the aircraft includes a complete machine landing system, which includes: the parachute cabin 32 is arranged in the rear part of the fuselage, a parachute pack 30 and a pushing device 31 are arranged in the parachute cabin, the parachute cabin door 28 is arranged at the back part of the rear fuselage of the fuselage 1 and is positioned in front of the S-shaped air inlet channel 18, the parachute cabin door 28 is opened and closed under the control of a parachute cabin door folding and unfolding support rod 33, and the opening of the S-shaped air inlet channel 18 is shielded by the parachute cabin door 28 after being opened; the parachute assembly structure is characterized by further comprising a parachute front end tying belt 34 arranged in a first skin installation groove of the fuselage, and a pair of parachute rear end tying belts 34 arranged in a second skin installation groove and a third skin installation groove, wherein the third tying belts are fixed on a fuselage force bearing frame, the first skin installation groove extends from the parachute bay 32 to the front end of the fuselage, and the second skin installation groove and the third skin installation groove extend from the parachute bay 32 to the rear end of the fuselage and are symmetrically arranged relative to the fuselage; when a dangerous condition occurs, the parachute cabin door folding and unfolding support rod 33 is controlled to open the parachute cabin door 28, the S-shaped air inlet channel 18 is blocked, the parachute pack 30 is taken out of the parachute cabin door 28 by the pushing device 31, and the bridles in the skin installation grooves are pulled to break the surface of the fuselage.

Here, the mounting slot is located between the aircraft skin paint layer 37 and the fuselage skin 39.

Here, the pushing means 31 is preferably a small rocket.

Preferably, the skin mounting slots are trapezoidal shaped structures 38, as shown in FIG. 7. Further, the trapezoidal base angle is 80 °.

Further, in one embodiment, referring to fig. 3, the lower part of the fuselage 1 is symmetrically provided with buoys 5 at the front end and at the middle two sides for respectively receiving a nose landing gear 7 at the front end of the lower part of the fuselage 1 and a pair of main landing gears 8 at the middle two sides of the lower part of the fuselage 1 after the aircraft takes off.

To sum up, the utility model discloses the fuselage of aircraft adopts the water droplet form section, and the pneumatic drag reduction of better realization fuselage simultaneously with the engine postposition, reduces the influence of screw slipstream to aircraft aerodynamic performance. The upper single wing design is adopted, the downward visual field of passengers is improved, and the passenger sightseeing device is more suitable for tourist. The V-shaped vertical fin design is adopted to combine the functions of the horizontal fin and the vertical fin, so that the weight of the structure is reduced. The lower part of the machine body is provided with a buoy, and the landing gear can be retracted and extended, so that the landing on water can be realized under the emergency condition, and the safety of passengers is improved. Meanwhile, the back of the airplane body is provided with a complete machine parachute, so that the safety of the airplane and passengers under the emergency condition is further ensured.

The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims (10)

1. A tandem two-seater universal airplane is characterized by comprising a water-drop-shaped airplane body (1), a pair of V-shaped vertical tails (2) arranged at the rear part of the airplane body, a turbine propeller engine (4) and a thrust propeller (6), and an upper single wing (3) arranged at the upper part of the airplane body; a front seat and a rear seat are arranged in the drop-shaped machine body (1), wherein the front seat (9) and the rear seat (10) correspond to a front glass cabin cover (11) which is opened upwards and a side cabin door (14) which is opened to the side surface respectively.

2. A tandem twin-seater universal aircraft according to claim 1, wherein the rear fuselage back of said fuselage (1) is provided with S-shaped air intakes (18) for combustion bleed air of turboprop engines (4); the lower part of the machine body (1) is provided with an exhaust port (19) for exhausting combustion gas of the engine.

3. A tandem twin seat general purpose aircraft according to claim 1, wherein said thrust propeller (6) is mounted on a hub (20) at the rear of the fuselage, the hub (20) being connected to the engine torque output shaft (21) and being faired by a propeller cap (22), said propeller cap (22) being housed and fixed on the hub (20) with clearance from the fuselage.

4. A tandem general purpose aircraft according to claim 1, wherein said upper monowing (3) is of a twin-beam wing structure, with sweepback at the wing leading edge and no sweepback at the wing trailing edge; the end part of the wing is provided with a wingtip winglet (23) for improving the aerodynamic performance and reducing the resistance; an aileron (24) is arranged at the rear part of the wing and at one side far away from the fuselage and is used for controlling the rolling attitude of the airplane; and an outer flap (25) and an inner flap (26) are sequentially arranged at the rear part of the wing and close to the fuselage along the aileron (24) and are used for improving the take-off and landing performance of the airplane and increasing the lift force of the airplane.

5. A tandem two-seater general purpose aircraft according to claim 1, wherein said V-shaped vertical fin (2) is provided with a steering surface (27) for controlling the pitch and yaw attitude of the aircraft.

6. A tandem twin seat general purpose aircraft according to claim 1 or claim 2, wherein the aircraft includes a complete machine landing system comprising: the parachute cabin door (32) is arranged in the rear part of the fuselage, a parachute pack (30) and a pushing device (31) are arranged in the parachute cabin door (28) which is arranged at the back of the rear fuselage of the fuselage (1) and is positioned in front of the S-shaped air inlet channel (18), the parachute cabin door (28) is opened and closed under the control of a parachute cabin door folding and unfolding support rod (33), and the opening of the S-shaped air inlet channel (18) can be shielded by the parachute cabin door (28) after the parachute cabin door is opened; the parachute assembly structure is characterized by further comprising a parachute front end tying belt (34) arranged in a first skin installation groove of the fuselage, and a pair of parachute rear end tying belts (35) arranged in a second skin installation groove and a third skin installation groove, wherein the third tying belts are fixed on a fuselage force bearing frame, the first skin installation groove extends to the front end of the fuselage from the parachute cabin (32), and the second skin installation groove and the third skin installation groove extend to the rear end of the fuselage from the parachute cabin (32) and are symmetrically arranged relative to the fuselage; when a dangerous condition occurs, the parachute cabin door folding and unfolding support rod (33) is controlled to open the parachute cabin door (28), the S-shaped air inlet channel (18) is blocked, the parachute pack (30) is taken out of the parachute cabin door (28) by the pushing device (31), and the bridle in the skin installation groove is pulled to break out of the surface of the fuselage.

7. The tandem aircraft in accordance with claim 6, wherein said skin mounting slot is of trapezoidal configuration.

8. A tandem twin seat general purpose aircraft according to claim 1, wherein said fuselage (1) is symmetrically provided with pontoons (5) at the front end and at the middle of the lower portion thereof for respectively receiving a nose landing gear (7) at the front end of the lower portion of the fuselage (1) and a pair of main landing gears (8) at the middle of the lower portion of the fuselage (1) after the aircraft takes off.

9. A tandem two-seater general purpose aircraft according to claim 1, wherein said front glass canopy (11) and said side doors (14) are each connected to the fuselage by means of a hinge (12).

10. A tandem two-seater general purpose aircraft according to claim 1, wherein a retractable stay (13) is provided between the opening and closing surfaces of said front glass canopy (11) and said lateral door (14) for opening and fixing said canopy or door.

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