CN212501033U - Light-duty sport aircraft of firefly - Google Patents
Light-duty sport aircraft of firefly Download PDFInfo
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- CN212501033U CN212501033U CN202020878441.2U CN202020878441U CN212501033U CN 212501033 U CN212501033 U CN 212501033U CN 202020878441 U CN202020878441 U CN 202020878441U CN 212501033 U CN212501033 U CN 212501033U
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Abstract
The utility model discloses a light-duty motion aircraft of firefly belongs to motion aircraft technical field, include the fuselage and be located the truss-like undercarriage of fuselage lower part, the front portion of fuselage is the no-load cabin, the middle part of fuselage is the cockpit, the rear portion of fuselage is the propulsion equipment cabin, the afterbody in propulsion equipment cabin is provided with the screw, be provided with the engine in the propulsion equipment cabin, the engine with the screw links to each other, the well rear portion bilateral symmetry in no-load cabin is provided with duck wing, the upper portion bilateral symmetry is provided with the wing in the propulsion equipment cabin. The maximum stall speed of the airplane can be reduced to 75km/h through the duck-type layout, so that the airplane has good maneuvering performance.
Description
Technical Field
The utility model belongs to the technical field of the motion aircraft, concretely relates to light-duty motion aircraft of firefly.
Background
The Light Sport Aircraft (LSA-Light Sport Aircraft) is a new Aircraft type which is newly promoted in 2004 by the Federal Aviation Administration (FAA-Federal Aviation Administration) according to the requirements of civil Aviation proposals, and is a novel general Aircraft which fills the gap between an ultra-Light Aircraft and a high-grade two-engine single piston Aircraft.
Such aircraft are commonly used for flight training, personal entertainment, aerial photography, emergency rescue, forest patrol, geographic reconnaissance, and services in special industries such as power, sea prison, traffic, news, environmental protection, and the like. According to the trend prediction of the current general aviation development, China has wide market prospects and demands for general aviation sports airplanes, particularly multipurpose light sports airplanes in the next 10 years. The airplane has the characteristics of portability, safety, low use requirement, easiness in operation, low price and the like.
The maneuverability of an airplane, which is an important tactical and technical index of the airplane, refers to the capability of the airplane to change the flying speed, flying altitude and flying direction within a certain time, and is correspondingly called speed maneuverability, altitude maneuverability and direction maneuverability. It is clear that the shorter the time required for the aircraft to change speed, altitude or direction, the better the maneuverability of the aircraft. In air combat, the excellent maneuverability is beneficial to obtaining the advantages of air combat.
The conventional layout of a horizontal tail wing behind a wing is mainly adopted in the existing light sports aircraft, the design scheme cannot effectively utilize the vortex lift force, so that the maneuverability at a large elevation angle is poor, and for the sports aircraft participating in special-effect flight, the difficulty of completing the action is reduced, thereby losing the ornamental value.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a: provides a firefly light sport aircraft, which solves the problems of poor maneuverability and low flight performance ornamental value of the prior light sport aircraft.
The utility model adopts the technical scheme as follows:
the utility model provides a light-duty motion aircraft of firefly, includes the fuselage and is located the truss-like undercarriage of fuselage lower part, the front portion of fuselage is the no-load cabin, the middle part of fuselage is the cockpit, and the cockpit lid (be located the cockpit top) can be upturned, makes things convenient for the driver to get into the cockpit. The aircraft is characterized in that a propelling equipment cabin is arranged at the rear part of the aircraft body, propellers are arranged at the tail part of the propelling equipment cabin, an engine is arranged in the propelling equipment cabin and connected with the propellers, canard wings are symmetrically arranged on two sides of the middle rear part of the no-load cabin, and wings are symmetrically arranged on two sides of the middle upper part of the propelling equipment cabin.
According to the technical scheme, the maximum takeoff weight of the light sport aircraft cannot exceed 600 kg (land takeoff and landing type)/650 kg (water takeoff and landing type), the single-engine double-seat (parallel form) and middle single-wing duck type layout are achieved, the aircraft height is 2.290m, the aircraft length is 6.742m, the maximum takeoff total weight is 584kg, and the passenger number (including a driver)/the carrying capacity is 2 persons/160 kg. The maximum horizontal flight speed of the airplane is as follows: v60.78 m/s, cruise speed: v49.77 m/s, minimum fly speed (stall speed): v40.45 m/s, maximum rate of climb: vy is 3.465 m/s. The engine is a Leconming O-235-H engine, which is arranged behind the machine head and adopts a propulsion propeller. The maximum stall speed of the airplane can be reduced to 75km/h through the duck-type layout, so that the airplane has good maneuvering performance.
The engine is a Leconming O-235-H engine.
Furthermore, the duck wing is connected with the body of the no-load cabin through a large interference bolt. The upper part of the machine body at 0.93m is fixedly connected with a duck wing. The connection mode not only meets the requirement of structural strength, but also reduces the cost.
Still further, the duck wing includes follows first roof beam and the second roof beam that duck wing length direction level and symmetry set up are located first roof beam with between the second roof beam and follow a plurality of first ribs and cladding that duck wing width direction set up first roof beam second roof beam and a plurality of the covering of first rib surface, the rear portion of duck wing is provided with by the first aileron of covering cladding, is provided with a plurality of second ribs in the first aileron, the second rib is fixed on the second roof beam, first roof beam with between the second roof beam be provided with a plurality of head rods between the first rib, head rod integrated into one piece in duck wing length direction. The duck wing is a straight duck wing and has a double-beam structure, the distance from the duck wing to the cabin is short, and the force transmission path is short.
Furthermore, the front part of the duck wing and one end far away from the fuselage are first rounded wingtips.
Further, the wing (wing is connected with the fuselage through big excessive bolt) includes the edge third roof beam and the fourth roof beam that wing length direction and interval shrink in proper order are located between third roof beam and the fourth roof beam and follow a plurality of third ribs and cladding that wing width direction set up the third roof beam the fourth roof beam and a plurality of the skin of surface between the third rib, the rear portion of wing is provided with by skin coated flap and second aileron, and is a plurality of the third rib extends to the flap with the second aileron is kept away from the edge of fourth roof beam, the flap is close to the fuselage, the second aileron is located the flap is kept away from one side of fuselage. The wing is a straight wing, the sweep angle is 19.2 degrees, the area of the wing is 10.32m by adopting an NACA2415 airfoil section2The span 8.165m, the tip ratio 0.6, and the aspect ratio 6.7. The wing is a double-beam type wing with a fillet wingtip. The ailerons, of length 1.293m, are arranged outboard of the wing and simple flaps, of length 2.147m, are arranged inboard. The wing area of the fixed connection wing at the position of 2.797m of the fuselageIs 3.74m2. The wings are slightly inclined backwards (tail), and the widths of the wings from the fuselage to the end parts (far away from the fuselage) are reduced in sequence.
Furthermore, a structural oil tank is arranged in the middle of the bottom of each wing and used for loading fuel oil.
Furthermore, a plurality of second connecting rods are arranged between the third ribs between the third beam and the fourth beam, and each second connecting rod is integrally formed in the wing length direction. The wing adopts a cantilever type wing and adopts a high and large vertical tail which is arranged on the wing tip of the wing. The spoiler is arranged to facilitate deceleration, so that the requirement of the airplane on the length of the runway during landing is reduced.
Furthermore, one end of the front part of the wing, which is far away from the fuselage, is a second rounded wingtip.
Furthermore, a vertical tail wing is fixed at the end part of the wing, the vertical tail wing is connected with the wing through a large interference bolt, and a rudder is arranged on the vertical tail wing. The vertical tail wing is a symmetrical wing type, and the area of the vertical tail wing is as follows: 3.80m2The vertical tail wing is provided with a rudder with the length of 1.24m and the width of 0.468 m.
Further, the landing gear comprises a nose landing gear positioned at the bottom of the body at the rear part of the empty cabin and main landing gears positioned at two sides of the bottom of the body at the middle rear part of the propulsion equipment cabin. The undercarriage is the fixed undercarriage of three point type in the front, and its undercarriage is apart from the aircraft nose 1.47m, and main undercarriage is apart from the aircraft nose 3.74m, and two wheels of main undercarriage interval 1.8m adopt cantilever type carbon beam leading wheel bearing structure, and the front and back wheel is great, and the undercarriage is equipped with hydraulic buffer (being favorable to coarse place take-off and land) simultaneously, makes the aircraft can take off and land on simple and easy runway such as rubble, sand and meadow, takes the radome fairing outward, does benefit to and reduces aerodynamic drag.
Furthermore, a display and control console is arranged in front of the upper portion of the cockpit, two seats are horizontally arranged in the cockpit, and a firewall is arranged on one side, far away from the propeller, of the propulsion equipment cabin.
Further, vertical fin includes the edge fifth roof beam and the sixth roof beam that vertical fin length direction and interval shrink in proper order are located the fifth roof beam with just follow between the sixth roof beam a plurality of fourth ribs that vertical fin width direction set up are located a plurality of third connecting rods between the fourth rib, the cladding are in the covering of fifth roof beam, sixth roof beam, a plurality of fourth rib and third connecting rod surface follows vertical fin length direction third connecting rod integrated into one piece, be provided with a plurality of fifth ribs on the rudder.
To sum up, owing to adopted above-mentioned technical scheme, the beneficial effects of the utility model are that:
1. in the utility model, the maximum stall speed of the airplane can be reduced to 75km/h through the duck-type layout, so that the airplane has good maneuvering performance;
2. the duck wing is a straight duck wing and has a double-beam structure, the distance from the duck wing to the cabin is short, and the force transmission path is short;
3. the undercarriage is a front three-point fixed undercarriage, the distance between the front undercarriage and the nose is 1.47m, the distance between the main undercarriage and the nose is 3.74m, the interval between two wheels of the main undercarriage is 1.8m, a cantilever type carbon beam main wheel supporting structure is adopted, the front wheel and the rear wheel are larger, and meanwhile, the front undercarriage is provided with a hydraulic buffer (beneficial to taking off and landing in a rough field), so that the airplane can take off and land on simple runways such as gravels, sandy soil, grasslands and the like, and a fairing is arranged outside the airplane, so that the aerodynamic resistance is;
4. low cost and high price advantage.
Drawings
FIG. 1 is a schematic structural view of a light-weight sport firefly aircraft according to the present invention;
FIG. 2 is a schematic structural view of the duck wing of the present invention;
FIG. 3 is a schematic view of the wing of the present invention;
fig. 4 is a schematic structural view of the body of the present invention;
FIG. 5 is a schematic view of the vertical rear wing of the present invention;
figure 6 is a side view of the aircraft of the present invention.
The labels in the figure are: 1-fuselage, 2-empty cabin, 3-cockpit, 4-propulsion equipment cabin, 5-canard wing, 6-wing, 7-flap, 8-second aileron, 9-propeller, 10-vertical tail, 11-first aileron, 12-first beam, 13-second beam, 14-first rib, 15-second rib, 16-first connecting rod, 17-third beam, 18-fourth beam, 19-third rib, 20-second connecting rod, 21-firewall, 22-seat, 23-display console, 24-fifth beam, 25-sixth beam, 26-rudder, 27-fourth rib, 28-fifth rib, 29-third connecting rod, 30-front landing gear, 31-main landing gear.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.
Example 1
As shown in fig. 1 and 4, a light-duty sport aircraft of firefly, include fuselage 1 and be located the truss-like undercarriage of fuselage 1 lower part, the front portion of fuselage 1 is unloaded cabin 2, the middle part of fuselage 1 is cockpit 3, the rear portion of fuselage 1 is propulsion unit cabin 4, the afterbody of propulsion unit cabin 4 is provided with screw 9, be provided with the engine in the propulsion unit cabin 4, the engine with screw 9 links to each other, the well rear portion bilateral symmetry of unloaded cabin 2 is provided with duck wing 5, the upper portion bilateral symmetry is provided with wing 6 in the propulsion unit cabin 4.
According to the technical scheme, the maximum takeoff weight of the light sport aircraft cannot exceed 600 kg (land takeoff and landing type)/650 kg (water takeoff and landing type), the single-engine double-seat (parallel form) and middle single-wing duck type layout are achieved, the aircraft height is 2.290m, the aircraft length is 6.742m, the maximum takeoff total weight is 584kg, and the passenger number (including a driver)/the carrying capacity is 2 persons/160 kg. The maximum horizontal flight speed of the airplane is as follows: v60.78 m/s, cruise speed: v49.77 m/s, minimum fly speed (stall speed): v40.45 m/s, maximum rate of climb: vy is 3.465 m/s. The Lekang Ming O-235-H engine is arranged behind the machine head and adopts a propulsion propeller 9. The maximum stall speed of the airplane can be reduced to 75km/h through the duck-type layout, so that the airplane has good maneuvering performance.
The engine is a Leconming O-235-H engine. The specific parameters are shown in Table 1.
TABLE 1 basic Engine parameters
Example 2
As shown in fig. 1, on the basis of embodiment 1, the canard wing 5 is connected with the fuselage 1 of the empty cabin 2 through a large interference bolt. The upper part of the fuselage 10.93m is fixedly connected with a duck wing 5. Not only meets the structural strength requirement, but also reduces the cost.
Example 3
As shown in the title 1-2, on the basis of embodiment 2, the duck wing 5 includes a first beam 12 and a second beam 13 horizontally and symmetrically arranged along the length direction of the duck wing 5, a plurality of first ribs 14 arranged between the first beam 12 and the second beam 13 and along the width direction of the duck wing 5, and a skin covering the outer surfaces of the first beam 12, the second beam 13, and the first ribs 14, a first secondary wing 11 covered by the skin is arranged at the rear portion of the duck wing 5, a plurality of second ribs 15 are arranged in the first secondary wing 11, the second ribs 15 are fixed on the second beam 13, a plurality of first connecting rods 16 are arranged between the first ribs 14 between the first beam 12 and the second beam 13, and the first connecting rods 16 are integrally formed in the length direction of the duck wing 5. The duck wing 5 is a straight duck wing 5, has a double-beam structure, is close to the cabin, and has a short force transmission path.
Example 4
As shown in fig. 1, on the basis of embodiment 3, the front part of the canard 5 and the end far away from the fuselage 1 are first rounded wingtips.
Example 5
As shown in fig. 1 and 3, in example 1, the wing 6 (the wing 6 is connected with the fuselage 1 by large-interference bolts) includes a third beam 17 and a fourth beam 18 horizontally and symmetrically arranged along the length direction of the wing 6, a plurality of third ribs 19 arranged between the third beam 17 and the fourth beam 18 and along the width direction of the wing 6, and a skin covering the outer surface between the third beam 17, the fourth beam 18, and the third ribs 19, a flap 7 and a second aileron 8 covered by the skin are arranged at the rear part of the wing 6, the third ribs 19 extend to the edge of the flap 7 and the second aileron 8 far from the fourth beam 18, the flap 7 is close to the fuselage 1, and the second aileron 8 is arranged at the side of the flap 7 far from the fuselage 1. The wing 6 is a straight wing 6, the sweep angle is 19.2 degrees, the area of the wing 6 is 10.32m2, the span is 8.165m, the tip ratio is 0.6, and the aspect ratio is 6.7 by adopting an NACA2415 airfoil section. The wing 6 is a double-beam wing 6 with a rounded wingtip. The wing 6 is provided outboard with an aileron of length 1.293m and inboard with a simple flap 7 of length 2.147 m. The wing 6 is fixedly connected with the fuselage 12.797m, and the area of the wing 6 is 3.74m 2.
Example 6
As shown in fig. 3, in embodiment 5, a plurality of second link bars 20 are provided between the third ribs 19 between the third beam 17 and the fourth beam 18, and each of the second link bars 20 is integrally formed in the longitudinal direction of the wing 6. The wing 6 adopts a cantilever type wing 6 and adopts a high and large vertical tail which is arranged on the wingtip of the wing 6. The spoilers facilitate deceleration, thereby reducing runway length requirements for the aircraft on descent.
Example 7
As shown in fig. 1, on the basis of embodiment 5, the front part of the wing 6 and the end far away from the fuselage 1 are second rounded wingtips.
Example 8
Referring to fig. 1 and 5, in embodiment 5, a vertical tail 10 is fixed to an end of the wing 6, and a rudder 26 is provided on the vertical tail 10. The vertical tail 10 is a symmetrical wing, the vertical tail area: 3.80m2, the vertical tail 10 is provided with a rudder 26 of length 1.24m and width 0.468 m.
Example 9
As shown in fig. 6, based on embodiment 1, the landing gear includes a nose landing gear 30 located at the bottom of the body 1 at the rear of the empty cabin 2 and main landing gears 31 located at both sides of the bottom of the body 1 at the rear in the propulsion device compartment 4. The undercarriage is the fixed undercarriage of three point type in the front, its nose undercarriage 30 is apart from the aircraft nose 1.47m, main undercarriage 31 is apart from the aircraft nose 3.74m, two driving wheels interval 1.8m of main undercarriage 31, adopt cantilever type carbon beam main wheel bearing structure, the front and back wheel is great, nose undercarriage 30 is equipped with hydraulic buffer simultaneously (being favorable to the coarse place to take off and land), make the aircraft can take off and land on simple and easy runway such as rubble, sand and meadow, the outer fairing that takes does benefit to reduces aerodynamic drag.
Example 10
As shown in fig. 4, in addition to embodiment 1, a display console 23 is provided in front of the upper portion of the cabin 3, two seats 22 are horizontally provided in the cabin 3, and a firewall 21 is provided on a side of the propulsion plant cabin 4 away from the propeller 9.
Example 11
As shown in fig. 5, in embodiment 1, the vertical stabilizer 10 includes fifth and sixth beams 24 and 25 whose pitches are sequentially reduced in the longitudinal direction of the vertical stabilizer 10, a plurality of fourth ribs 27 disposed between the fifth and sixth beams 24 and 25 and in the width direction of the vertical stabilizer 10, a plurality of third connecting rods 29 disposed between the fourth ribs 27, a skin covering the outer surfaces of the fifth beam 24, the sixth beam 25, the fourth ribs 27 and the third connecting rods 29, the third connecting rods 29 formed integrally in the longitudinal direction of the vertical stabilizer 10, and a plurality of fifth ribs 28 provided on the rudder 26.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. The utility model provides a light-duty sport aircraft of firefly, includes fuselage (1) and is located fuselage (1) lower part's truss-like undercarriage, its characterized in that: the front portion of fuselage (1) is unloaded cabin (2), the middle part of fuselage (1) is cockpit (3), the rear portion of fuselage (1) is propulsion unit cabin (4), the afterbody of propulsion unit cabin (4) is provided with screw (9), be provided with the engine in propulsion unit cabin (4), the engine with screw (9) link to each other, the well rear portion bilateral symmetry of unloaded cabin (2) is provided with duck wing (5), upper portion bilateral symmetry is provided with wing (6) in propulsion unit cabin (4).
2. A firefly light sport aircraft as set forth in claim 1, wherein: the duck wing (5) is connected with the body (1) of the no-load cabin (2) through a large interference bolt.
3. A firefly light sport aircraft as set forth in claim 2, wherein: duck wing (5) include along duck wing (5) length direction level and first roof beam (12) and second roof beam (13) that the symmetry set up are located first roof beam (12) with between second roof beam (13) and follow a plurality of first rib (14) that duck wing (5) width direction set up and cladding are in first roof beam (12), second roof beam (13) and a plurality of the covering of first rib (14) surface, the rear portion of duck wing (5) is provided with by covering clad first aileron (11), is provided with a plurality of second ribs (15) in first aileron (11), second rib (15) are fixed on second roof beam (13), first roof beam (12) with between second roof beam (13) be provided with a plurality of first connecting rods (16) between first rib (14).
4. A firefly light sport aircraft as set forth in claim 3, wherein: the front part of the duck wing (5) is far away from one end of the machine body (1) and is a first fillet wingtip.
5. A firefly light sport aircraft as set forth in claim 1, wherein: the wing (6) comprises a third beam (17) and a fourth beam (18) which are sequentially reduced along the length direction and the distance of the wing (6), the third beam (17) and the fourth beam (18) are located between the third beam (17) and the fourth beam (18) and along a plurality of third ribs (19) arranged in the width direction of the wing (6) and cover the third beam (17), the fourth beam (18) and the third ribs (19) to form a skin, a flap (7) and a second aileron (8) covered by the skin are arranged at the rear part of the wing (6), the third ribs (19) extend to the flap (7) and the second aileron (8) to be far away from the edge of the fourth beam (18), the flap (7) is close to the fuselage (1), and the second aileron (8) is located on one side of the flap (7) far away from the fuselage (1).
6. A firefly light sport aircraft according to claim 5, characterized in that: a plurality of second connecting rods (20) are arranged between the third ribs (19) between the third beam (17) and the fourth beam (18).
7. A firefly light sport aircraft according to claim 5, characterized in that: and one end of the front part of the wing (6) far away from the fuselage (1) is a second rounded wingtip.
8. A firefly light sport aircraft according to claim 5, characterized in that: the end part of the wing (6) is fixed with a vertical tail wing (10), and the vertical tail wing (10) is provided with a rudder (26).
9. A firefly light sport aircraft as set forth in claim 1, wherein: the truss type undercarriage comprises a nose undercarriage (30) positioned at the bottom of the airframe (1) at the rear part of the no-load cabin (2) and main undercarriages (31) positioned at two sides of the bottom of the airframe (1) at the middle rear part of the propulsion equipment cabin (4).
10. A firefly light sport aircraft as set forth in claim 1, wherein: the front of the upper part of the cockpit (3) is provided with a display and control console (23), two seats (22) are horizontally arranged in the cockpit (3), and one side of the propulsion equipment cabin (4) far away from the propeller (9) is provided with a firewall (21).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020878441.2U CN212501033U (en) | 2020-05-22 | 2020-05-22 | Light-duty sport aircraft of firefly |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020878441.2U CN212501033U (en) | 2020-05-22 | 2020-05-22 | Light-duty sport aircraft of firefly |
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| CN212501033U true CN212501033U (en) | 2021-02-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112849397A (en) * | 2021-03-09 | 2021-05-28 | 中国民用航空飞行学院 | Structure, wing and aircraft for enhancing vortex surfing |
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2020
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112849397A (en) * | 2021-03-09 | 2021-05-28 | 中国民用航空飞行学院 | Structure, wing and aircraft for enhancing vortex surfing |
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