A tandem two-seat general purpose aircraft

Abstract

The invention discloses a tandem two-seat general-purpose aircraft, comprising a teardrop-shaped fuselage, a pair of V-shaped vertical tails arranged at the rear of the fuselage, a turboprop engine and a thrust propeller, and an upper wing arranged at the upper part of the fuselage; two front and rear seats are arranged in the fuselage, wherein the front seat and the rear seat correspond to the front glass cabin cover opened upward and the side cabin door opened to the side, respectively. The fuselage of the invention adopts a teardrop-shaped profile, which can better achieve the aerodynamic drag reduction of the fuselage, and at the same time, the engine is rear-placed to reduce the influence of the propeller slipstream on the aerodynamic performance of the aircraft. The upper wing design is adopted to improve the downward field of vision of the passengers, which is more suitable for tourists to sightsee. The V-shaped vertical tail design is adopted to combine the functions of the horizontal tail and the vertical tail, thereby reducing the weight of the structure. A float is provided at the lower part of the fuselage, and the landing gear can be retracted and extended, so that water landing can be achieved in an emergency, thereby improving the safety of the passengers. At the same time, a whole-machine parachute is provided on the back of the fuselage to further ensure the safety of the aircraft and the passengers in an emergency.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft manufacturing, in particular to a tandem two-seat general-purpose aircraft. Background Art

[0002] At present, the existing tandem two-seat general-purpose aircraft mainly include China's CJ-6, Czech Shark aircraft, Austrian DART-450 and other three aircraft. Their common characteristics are that they all adopt the conventional lower single wing and low horizontal tail layout, lack a good downward field of view, and all use a pulling propeller. The engine is arranged at the nose. The propeller slipstream affects the overall aerodynamic performance of the aircraft and increases the aircraft induced drag. Chinese patent CN205418063U discloses "a flying car with a tandem two-seat layout", which has the following problems: 1. The double vertical tail + high horizontal tail layout leads to a large structural weight and poor aircraft maneuverability; 2. The vertical tail and the horizontal tail are in the propeller slipstream area, the aerodynamic surface efficiency is low, and it is easy to cause the tail structure acoustic fatigue problem, and the product life is short; 3. The car tires cannot be retracted into the fuselage compartment, causing large aerodynamic resistance, affecting the aircraft's fuel economy and further reducing the aircraft's range. Summary of the invention

[0003] The purpose of the present invention is to provide a tandem two-seat general purpose aircraft in view of the problems existing in the above-mentioned prior art.

[0004] The technical solution to achieve the purpose of the present invention is: a tandem two-seat general-purpose aircraft, which includes a teardrop-shaped fuselage, a pair of V-shaped vertical tails, a turboprop engine and a thrust propeller arranged at the rear of the fuselage, and an upper wing arranged at the upper part of the fuselage; two front and rear seats are arranged in the teardrop-shaped fuselage, wherein the front seat and the rear seat correspond to the front glass cabin cover that opens upward and the side cabin door that opens to the side, respectively.

[0005] Furthermore, an S-shaped air inlet is provided at the back of the rear fuselage for combustion bleed air of the turboprop engine; an exhaust port is provided at the lower part of the fuselage for discharging engine combustion gas.

[0006] Furthermore, the thrust propeller is mounted on a propeller hub at the tail of the fuselage, the propeller hub is connected to the engine torque output shaft, and is rectified by a propeller cap, and the propeller cap is covered and fixed on the propeller hub, and there is a gap between the propeller cap and the fuselage.

[0007] Furthermore, the upper monoplane is a double-beam wing structure with a swept leading edge and an unswept trailing edge; a winglet is provided at the end of the wing to improve aerodynamic performance and reduce resistance; an aileron is provided at the rear of the wing and on the side away from the fuselage to control the roll attitude of the aircraft; an outer flap and an inner flap are provided in sequence at the rear of the wing and along the aileron toward the fuselage to improve the take-off and landing performance of the aircraft and increase the lift of the aircraft.

[0008] Furthermore, the V-shaped vertical tail is provided with control surfaces for controlling the pitch and yaw attitude of the aircraft.

[0009] Furthermore, the aircraft includes a whole-machine landing system, which includes: a parachute compartment arranged in the rear part of the fuselage, in which a parachute bag and a propulsion device are arranged, a parachute compartment door arranged on the back of the rear fuselage of the fuselage and located in front of the S-shaped air inlet, the parachute compartment door is opened and closed under the control of the parachute compartment door retraction and extension struts, and the parachute compartment door will block the S-shaped air inlet when opened; it also includes a front end parachute tether arranged in the first skin mounting groove of the fuselage, and a pair of rear end parachute tethers arranged in the second skin mounting groove and the third skin mounting groove, the three tethers are fixed on the fuselage load-bearing frame, the first skin mounting groove extends from the parachute compartment to the front end of the fuselage, the second skin mounting groove and the third skin mounting groove extend from the parachute compartment to the rear end of the fuselage, and are symmetrically arranged with respect to the fuselage; when a dangerous situation occurs, the parachute compartment door retraction and extension struts are controlled to open the parachute compartment door, blocking the S-shaped air inlet, and the propulsion device brings the parachute bag out of the parachute compartment door, and drags the tether in the skin mounting groove to break out of the fuselage surface.

[0010] Furthermore, floats are symmetrically provided at the front end and both sides of the middle of the lower fuselage for respectively storing the front landing gear located at the front end of the lower fuselage and a pair of main landing gears symmetrically located on both sides of the middle of the lower fuselage after the aircraft takes off.

[0011] Compared with the prior art, the present invention has the following significant advantages: 1) The fuselage of the aircraft adopts a teardrop-shaped cross-section, which can better achieve aerodynamic drag reduction of the fuselage, and at the same time, the engine is placed at the rear to reduce the influence of propeller slipstream on the aerodynamic performance of the aircraft; 2) The upper wing design is adopted to improve the downward field of vision of the occupants, which is more suitable for sightseeing by passengers; 3) The V-shaped vertical tail design is adopted to combine the functions of the horizontal tail and the vertical tail to reduce the structural weight; 4) Floats are provided at the lower part of the fuselage, and the landing gear can be retracted and extended, so that water landing can be achieved in emergency situations, etc., thereby improving the safety of the occupants; 5) A whole-machine parachute is provided on the back of the fuselage to further ensure the safety of the aircraft and the occupants in emergency situations.

[0012] The present invention is further described in detail below in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a side view of a tandem two-seat universal aircraft when the cabin door is not opened in one embodiment.

[0014] Figure 2 It is a side view of a tandem two-seat universal aircraft with its cabin door open in one embodiment.

[0015] Figure 3 It is a side view of a tandem two-seat general-purpose aircraft with its landing gear and boarding steps retracted in one embodiment.

[0016] Figure 4 A top view of a tandem two-seat general purpose aircraft in one embodiment.

[0017] Figure 5 The figure is a front view of a tandem two-seat general purpose aircraft in one embodiment.

[0018] Figure 6 The figure is a layout diagram of a tandem two-seat general-purpose aircraft landing system in one embodiment.

[0019] Figure 7 It is a schematic diagram of the installation of a parachute strap in one embodiment.

[0020] Figure 8 This is a schematic diagram of the opening of the whole aircraft parachute in one embodiment. DETAILED DESCRIPTION

[0021] In order to facilitate the understanding of the present invention, the present invention will be described more fully below with reference to the relevant drawings. The preferred embodiments of the present invention are shown in the drawings. However, the present invention can be implemented in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of the present invention more thorough and comprehensive.

[0022] It should be noted that if the embodiments of the present invention involve directional indications such as up, down, left, right, front, back, etc., then the directional indications are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture as shown in the accompanying drawings. If the specific posture changes, the directional indication will also change accordingly.

[0023] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or suggesting their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0024] In one embodiment, in combination Figure 1 and Figure 2, provides a tandem two-seat general-purpose aircraft, the aircraft includes a teardrop-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, and an upper wing 3 arranged at the upper part of the fuselage; two front and rear seats are arranged in the teardrop-shaped fuselage 1, wherein the front seat 9 and the rear seat 10 correspond to the front glass cabin cover 11 opened upward and the side cabin door 14 opened to the side, respectively.

[0025] Preferably, the front glass cabin cover 11 and the side cabin door 14 are both connected to the fuselage via hinges 12 .

[0026] Here further, the side door 14 is provided with a glass window to facilitate sightseeing for passengers.

[0027] Here further, a small oval window 16 is provided on the rear fuselage of the rear seat 10 to increase the overall aesthetics of the aircraft.

[0028] Furthermore, in one of the embodiments, a retractable support rod 13 is provided between the opening and closing surfaces of the front glass cabin cover 11 and the side cabin door 14 for opening and fixing the cabin cover or the cabin door.

[0029] Furthermore, in one of the embodiments, a retractable footrest 15 is provided on the outside of the fuselage on the side of the front seat 9 for passengers to use when getting on and off the aircraft. When the aircraft is parked, the retractable footrest 15 is opened and lowered, and is retracted in the flight state.

[0030] Furthermore, in one of the embodiments, a luggage compartment 17 is provided in the rear fuselage of the rear seat 10 for storing luggage items.

[0031] Furthermore, in one of the embodiments, an S-shaped air inlet 18 is provided at the back of the rear fuselage of the fuselage 1 for combustion bleed air of the turboprop engine 4; an exhaust port 19 is provided at the lower part of the fuselage 1 for discharging engine combustion gas.

[0032] Here preferably, the air inlet lip is elliptical, such as Figure 5 shown.

[0033] Furthermore, in one of the embodiments, the thrust propeller 6 is mounted on a propeller hub 20 at the tail of the fuselage, the propeller hub 20 is connected to the engine torque output shaft 21, and is rectified by a propeller cap 22, the propeller cap 22 covers and is fixed on the propeller hub 20, and there is a gap between the propeller hub 20 and the fuselage to prevent collision and friction.

[0034] Preferably, the thrust propeller 6 has three blades.

[0035] Further, in one embodiment, in combination Figure 4The upper wing 3 is a double-beam wing structure, with a swept leading edge and an unswept trailing edge; a winglet 23 is provided at the end of the wing to improve aerodynamic performance and reduce resistance, while improving the overall appearance of the aircraft; an aileron 24 is provided at the rear of the wing and on the side away from the fuselage to control the rolling attitude of the aircraft; an outer flap 25 and an inner flap 26 are provided in sequence at the rear of the wing and along the aileron 24 close to the fuselage to improve the take-off and landing performance of the aircraft and increase the lift of the aircraft.

[0036] Here preferably, the wing leading edge sweep angle is 5° and the wing installation angle is 3°.

[0037] Further, in one embodiment, in combination Figure 4 The V-shaped vertical tail 2 is provided with a control rudder 27 for controlling the pitch and yaw attitude of the aircraft.

[0038] Further, in one embodiment, in combination Figures 6 to 8 The aircraft includes a whole-machine landing system, which includes: a parachute compartment 32 arranged in the rear part of the fuselage, in which a parachute bag 30 and a propulsion device 31 are arranged, a parachute compartment door 28 arranged on the back of the rear fuselage of the fuselage 1 and located in front of the S-shaped air inlet 18, the parachute compartment door 28 is opened and closed under the control of the parachute compartment door retracting strut 33, and the parachute compartment door 28 will cover the S-shaped air inlet 18 when opened; and also includes a parachute front end tether 34 arranged in the first skin mounting groove of the fuselage, and a parachute front end tether 34 arranged in the second skin mounting groove, the first skin mounting groove, the second ... A pair of parachute rear end straps 34 are in the three skin mounting grooves, and the three straps are fixed on the fuselage load-bearing frame. The first skin mounting groove extends from the parachute compartment 32 to the front end of the fuselage, and the second skin mounting groove and the third skin mounting groove extend from the parachute compartment 32 to the rear end of the fuselage, and are symmetrically arranged with respect to the fuselage. When a dangerous situation occurs, the parachute compartment door retraction strut 33 is controlled to open the parachute compartment door 28, blocking the S-shaped air inlet 18, and the pushing device 31 brings the parachute bag 30 out of the parachute compartment door 28, and drags the straps in the skin mounting groove to break out of the fuselage surface.

[0039] Here, the mounting groove is located between the aircraft skin paint layer 37 and the fuselage skin 39.

[0040] Here, preferably, the propulsion device 31 is a small rocket.

[0041] Here preferably, the skin mounting groove is a trapezoidal structure 38, such as Figure 7 Further, the base angle of the trapezoid is 80°.

[0042] Further, in one embodiment, in combination Figure 3Floats 5 are symmetrically provided at the front end and both sides of the middle of the lower part of the fuselage 1, which are used to respectively accommodate the front landing gear 7 located at the front end of the lower part of the fuselage 1 and a pair of main landing gears 8 symmetrically located on both sides of the middle of the lower part of the fuselage 1 after the aircraft takes off.

[0043] In summary, the fuselage of the aircraft of the present invention adopts a teardrop-shaped profile, which can better achieve aerodynamic drag reduction of the fuselage. At the same time, the engine is placed at the rear to reduce the influence of propeller slipstream on the aerodynamic performance of the aircraft. The upper wing design improves the downward field of vision of the occupants and is more suitable for sightseeing. The V-shaped vertical tail design combines the functions of the horizontal tail and the vertical tail to reduce the weight of the structure. The lower part of the fuselage is provided with a float, and the landing gear can be retracted and extended, which can achieve water landing in an emergency and improve the safety of the occupants. At the same time, a whole-machine parachute is designed on the back of the fuselage to further ensure the safety of the aircraft and the occupants in an emergency.

[0044] The above shows and describes the basic principles, main features and advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A tandem two-seat general purpose aircraft, characterized in that: The aircraft comprises a teardrop-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), and an upper wing (3) arranged at the upper part of the fuselage; two front and rear seats are arranged in the teardrop-shaped fuselage (1), wherein the front seat (9) and the rear seat (10) correspond to a front glass cabin cover (11) that opens upwards and a side cabin door (14) that opens to the side, respectively; The upper wing (3) is a double-beam wing structure, the leading edge of the wing is swept back, and the trailing edge of the wing is not swept back; a winglet (23) is provided at the end of the wing to improve aerodynamic performance and reduce resistance; an aileron (24) is provided at the rear of the wing and on a side away from the fuselage to control the rolling attitude of the aircraft; an outer flap (25) and an inner flap (26) are provided in sequence at the rear of the wing and along the aileron (24) close to the fuselage to improve the take-off and landing performance of the aircraft and increase the lift of the aircraft; The aircraft comprises a whole-machine landing system, which comprises: a parachute compartment (32) arranged in the rear part of the fuselage, in which a parachute bag (30) and a propulsion device (31) are arranged; a parachute compartment door (28) arranged on the back of the rear fuselage of the fuselage (1) and located in front of the S-shaped air inlet (18), the parachute compartment door (28) is opened and closed under the control of a parachute compartment door retracting and extending strut (33), and the parachute compartment door (28) will cover the S-shaped air inlet (18) when opened; and also comprises a parachute front end strap (34) arranged in the first skin mounting groove of the fuselage, and a parachute front end strap (34) arranged in the second skin mounting groove, A pair of parachute rear end straps (34) are in the third skin mounting groove, and the three straps are fixed on the fuselage load-bearing frame. The first skin mounting groove extends from the parachute compartment (32) to the front end of the fuselage, and the second skin mounting groove and the third skin mounting groove extend from the parachute compartment (32) to the rear end of the fuselage, and are symmetrically arranged with respect to the fuselage. When a dangerous situation occurs, the parachute compartment door retraction strut (33) is controlled to open the parachute compartment door (28), block the S-shaped air inlet (18), and the pushing device (31) brings the parachute bag (30) out of the parachute compartment door (28), and drags the straps in the skin mounting groove to break out of the fuselage surface.

2. The tandem two-seat general purpose aircraft according to claim 1, characterized in that: The back of the rear fuselage of the fuselage (1) is provided with an S-shaped air inlet (18) for combustion bleed air of the turboprop engine (4); and the lower part of the fuselage (1) is provided with an exhaust port (19) for discharging engine combustion gas.

3. The tandem two-seat general purpose aircraft according to claim 1, characterized in that: The thrust propeller (6) is mounted on a propeller hub (20) at the rear of the fuselage. The propeller hub (20) is connected to the engine torque output shaft (21) and is rectified by a propeller cap (22). The propeller cap (22) covers and is fixed on the propeller hub (20) and has a gap with the fuselage.

4. The tandem two-seat general purpose aircraft according to claim 1, characterized in that: The V-shaped vertical tail (2) is provided with a control rudder (27) for controlling the pitch and yaw attitude of the aircraft.

5. The tandem two-seat general purpose aircraft according to claim 1, characterized in that: The skin mounting groove is a trapezoidal structure.

6. The tandem two-seat general purpose aircraft according to claim 1, characterized in that: The front end and both sides of the middle of the lower part of the fuselage (1) are symmetrically provided with floats (5), which are used to respectively accommodate the front landing gear (7) located at the front end of the lower part of the fuselage (1) and a pair of main landing gears (8) located at both sides of the middle of the lower part of the fuselage (1) symmetrically after the aircraft takes off.

7. The tandem two-seat general purpose aircraft according to claim 1, characterized in that: The front glass cabin cover (11) and the side cabin door (14) are both connected to the fuselage via hinges (12).

8. The tandem two-seat general purpose aircraft according to claim 1, characterized in that: A retractable support rod (13) is provided between the opening and closing surfaces of the front glass cabin cover (11) and the side cabin door (14) for opening and fixing the cabin cover or the cabin door.

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