CN212797324U - Unmanned flying wing capable of achieving short-distance take-off and landing - Google Patents
Unmanned flying wing capable of achieving short-distance take-off and landing Download PDFInfo
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- CN212797324U CN212797324U CN201922351608.XU CN201922351608U CN212797324U CN 212797324 U CN212797324 U CN 212797324U CN 201922351608 U CN201922351608 U CN 201922351608U CN 212797324 U CN212797324 U CN 212797324U
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Abstract
The utility model belongs to aircraft layout design field relates to an unmanned all-wing aircraft of short distance take-off and landing can be realized. Can realize that unmanned all-wing aircraft of short distance take-off and landing includes: the wing body fusion body comprises a fuselage and wings, a trailing edge simple flap, a ducted fan and a main engine; wherein the ducted fan and the main engine are powered by the aircraft; the central line of the ducted fan is positioned in the longitudinal symmetrical plane of the machine body; the simple wing flap of the trailing edge is positioned at the inner side of the trailing edge of the wing close to the symmetrical plane; the main engine is located at the rear end of the fuselage.
Description
Technical Field
The utility model belongs to aircraft layout design field relates to an unmanned all-wing aircraft of short distance take-off and landing can be realized.
Background
The flying wing layout has high-efficiency aerodynamic efficiency, excellent stealth performance and better structural efficiency due to the inherent characteristics, and is a layout which is inclined by designers. Due to the lack of a conventional tail fin, the control surface is usually located at the rear edge of the control surface, so that the control arm is short and the control surface is inefficient to operate. The flap is used as a pneumatic high lift device, and the lift force and the resistance are increased by changing the wing section bending moment in the taking-off and landing stages, so that the flap is an effective measure for realizing short-distance taking-off and landing. Based on the characteristic of weak control capability of the flying wing layout, the conventional flying wing layout cannot adopt a pneumatic high lift device to realize short-distance take-off and landing, and compared with the conventional layout with the same magnitude, the take-off and landing performance of the airplane is poorer and is an inevitable part in the layout design.
In the existing layout design, the requirement on the take-off and landing performance of the flying wing layout is generally relaxed, and further excellent aerodynamic efficiency is pursued.
SUMMERY OF THE UTILITY MODEL
Utility model purpose: the unmanned flying wing capable of realizing short-distance take-off and landing solves the defects of low inherent operating efficiency and poor take-off and landing performance of a flying wing layout aircraft.
The utility model provides a can realize short distance take-off and land unmanned all-wing aircraft, include: the wing body fusion body comprises a fuselage and wings, a trailing edge simple flap, a ducted fan and a main engine;
wherein the ducted fan and the main engine are powered by the aircraft; the central line of the ducted fan is positioned in the longitudinal symmetrical plane of the machine body; the simple wing flap of the trailing edge is positioned at the inner side of the trailing edge of the wing close to the symmetrical plane; the main engine is located at the rear end of the fuselage.
Further, the method also comprises the following steps: a leading edge flap at the leading edge of the wing.
Further, the method also comprises the following steps: an aileron located outboard of the trailing edge of the wing from the plane of symmetry.
Further, the method also comprises the following steps: the vertical tails are positioned at two sides of the wingtip of the wing.
Furthermore, the central line of the ducted fan is also positioned between the machine head and the gravity center connecting line at the longitudinal position of the fan.
Furthermore, the main engine is located at the rear end of the machine body and is symmetrical along the longitudinal symmetry plane.
The scheme utilizes the characteristic that the power propeller is arranged in front of the gravity center, improves the lifting performance through two aspects of force and moment, effectively meets the requirements of a lifting stage on a field area, and has the advantages of simple technology, easy realization and remarkable lifting effect.
Drawings
Fig. 1 is a structural bottom view of the unmanned flying wing capable of realizing short take-off and landing;
fig. 2 is the utility model provides a pair of can realize unmanned all-wing aircraft's of short distance take-off and landing structure elevation.
Detailed Description
The utility model provides a can realize unmanned all-wing aircraft of short distance take-off and landing, as shown in fig. 1-2, include: the wing body fusion body 1, a trailing edge simple flap 2, a ducted fan 3, a main engine 4, a leading edge flap 5, an aileron 6 and a vertical tail.
The scheme adopts the layout of the wing body fusion body 1, the height of the fuselage and the height of the wings are integrated, and the aerodynamic advantages of high lift and low resistance of the flying wing layout plane are fully exerted.
The rear thrust is used as the main engine 4 to provide main power, and the forward duct is used in the takeoff and landing stage to provide direct lift force and pitching raising moment. The ducted fan 3 is located in front of the centre of gravity. A simple trailing edge flap 2 is arranged on the inner side of the trailing edge and used in the taking-off and landing stage; the outer side is provided with an aileron 6 which is used as a transverse control surface; in order to facilitate the large attack angle delay stall characteristic in the take-off and landing stage, a leading edge flap 5 is arranged in front of the wing.
In the taking-off and landing stage, the scheme can put down the simple wing flap at the rear edge according to the conventional layout and start the forward duct at the same time. The lift force generated by the forward culvert can offset part of the weight of the airplane, and the takeoff and landing distance can be shortened; because the forward culvert is positioned in front of the center of gravity, the generated head-up moment can balance the head-down moment generated by the trailing edge simple flap 2, and the takeoff and landing distance can be shortened by using the trailing edge simple flap 2 in the embodiment. Synthesize above-mentioned two aspects factors, consequently the utility model discloses can play the effect of short distance take off and land, remain the aerodynamic advantage of all-wing aircraft overall arrangement simultaneously.
The utility model has the advantages of as follows:
1. the technology is novel. The scheme of 'direct lift force + head-up moment' is provided, the characteristic that the wing flap at the trailing edge cannot be directly used in the flying wing layout is solved, and therefore the effect of 'short-distance take-off and landing' is achieved.
2. In the layout design of the scheme, the main propulsion engine and the ducted fan engine work independently, are mutually independent and controlled in a decoupling mode, and are convenient to control and easy to realize.
3. The forward ducted fan can be freely configured without considering power, so that the forward ducted fan can have the characteristic of needing larger direct force and moment at the optimal design point, thereby realizing short-distance takeoff.
4. In the landing stage, the main engine is placed in a slow vehicle or parking state, the forward duct works, and the short-distance landing function can still be realized.
Claims (6)
1. The utility model provides a can realize unmanned all-wing aircraft of short distance take-off and landing which characterized in that includes: the wing body fusion body comprises a fuselage and wings, a trailing edge simple flap, a ducted fan and a main engine;
wherein the ducted fan and the main engine are powered by the aircraft; the central line of the ducted fan is positioned in the longitudinal symmetrical plane of the machine body; the simple wing flap of the trailing edge is positioned at the inner side of the trailing edge of the wing close to the symmetrical plane; the main engine is located at the rear end of the fuselage.
2. The unmanned flying wing capable of achieving short take-off and landing according to claim 1, further comprising: a leading edge flap at the leading edge of the wing.
3. The unmanned flying wing capable of achieving short take-off and landing according to claim 1, further comprising: an aileron located outboard of the trailing edge of the wing from the plane of symmetry.
4. The unmanned flying wing capable of achieving short take-off and landing according to claim 1, further comprising: the vertical tails are positioned at two sides of the wingtip of the wing.
5. The unmanned flying wing capable of achieving short take-off and landing according to claim 1, wherein the center line of the ducted fan is further located at a longitudinal position of the fan between a connection line of the nose and the center of gravity.
6. The unmanned flying wing capable of achieving short take-off and landing according to claim 1, wherein the main engine is symmetrical along a longitudinal symmetry plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922351608.XU CN212797324U (en) | 2019-12-24 | 2019-12-24 | Unmanned flying wing capable of achieving short-distance take-off and landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922351608.XU CN212797324U (en) | 2019-12-24 | 2019-12-24 | Unmanned flying wing capable of achieving short-distance take-off and landing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212797324U true CN212797324U (en) | 2021-03-26 |
Family
ID=75079685
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922351608.XU Active CN212797324U (en) | 2019-12-24 | 2019-12-24 | Unmanned flying wing capable of achieving short-distance take-off and landing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212797324U (en) |
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2019
- 2019-12-24 CN CN201922351608.XU patent/CN212797324U/en active Active
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