CN203975217U - A kind of double-deck rotor aircraft - Google Patents
A kind of double-deck rotor aircraft Download PDFInfo
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- CN203975217U CN203975217U CN201420452861.9U CN201420452861U CN203975217U CN 203975217 U CN203975217 U CN 203975217U CN 201420452861 U CN201420452861 U CN 201420452861U CN 203975217 U CN203975217 U CN 203975217U
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- limb
- bottom wing
- normal limb
- propelling unit
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Abstract
A double-deck rotor aircraft, relates to a kind of aeronautical technology field, relates in particular to a kind of double-deck rotor aircraft.It comprises upper limb, bottom wing, left normal limb, right normal limb, rear normal limb, engine installation, alighting gear and fuselage.Upper limb is comprised of the fixed part and the elevating rudder that are positioned at the place ahead.Rear normal limb is comprised of forward fixed part and yaw rudder.Right section of left section of bottom wing and bottom wing be the symmetrical left and right sides, front lower place that is fixed on fuselage respectively, and the wing tip place that left section of bottom wing and bottom wing are right section has configured port aileron and starboard aileron.Two of the left and right tip end portion of the lap of the vertical direction of upper limb and bottom wing respectively symmetry left normal limb and right normal limb are housed.Control the deflection of left normal limb and right normal limb and can control aircraft sidesway.Left propelling unit and right propelling unit rear portion add respectively lobus sinister grid and the lobus dexter grid of horizontal water conservancy diversion.This Flight Vehicle Structure is compact, and efficiency is high, can carry out high-angle-of-attack flight, conveniently realizes very short takeoff and landing and Ultra-Low Speed flight.
Description
Technical field
A double-deck rotor aircraft, belongs to aeronautical technology field, relates in particular to a kind of double-deck rotor aircraft.
Background technology
The more difficult short take-off and landing of realizing of traditional biplane, and have a longer tail, take up room large; The efficiency of wing is low, and easily stall, and critical stalling incidence is little, poor stability.
Summary of the invention
The object of the invention is to overcome the above-mentioned deficiency of traditional biplane, invent a kind of double-deck rotor aircraft without long-tail bar and energy short take-off and landing.
A double-deck rotor aircraft, comprises upper limb, bottom wing, left normal limb, right normal limb, rear normal limb, engine installation, alighting gear and fuselage.In fuselage, be furnished with maneuvering system and airborne equipment.Bikini wheel undercarriage before alighting gear adopts.Engine installation comprises left propelling unit and the right propelling unit of energy supplyystem and the identical switched in opposite of two nested structures, and left propelling unit and right propelling unit have three kinds of forms: one, motor adds ducted fan formula screw propeller; Two, piston engine adds ducted fan formula screw propeller; Three, fanjet.Front a kind of motor is by lithium battery power supply, and latter two driving engine provides the energy with fuel oil.Upper limb is placed in the top, rear portion of fuselage, and upper limb is that elevating rudder form by the fixed part that is positioned at the place ahead with the moving part that is positioned at rear, and upper limb is connected with fuselage by the middle part of its fixed part.The upper and lower deflection of elevating rudder energy under the controlling of maneuvering system, upward deflects and can make this aircraft come back, and realization is faced upward; The change of team of elevating rudder downward bias is bowed this aircraft, realizes nutation.It is stable that upper limb fixed part also plays level except producing lift.The midway location top, rear portion of upper limb fixed part is provided with rear normal limb, and the moving part of rear normal limb by forward fixed part and after leaning on is that yaw rudder forms, and yaw rudder is deflection under the controlling of maneuvering system, can make this aircraft left and driftage to the right.Bottom wing is comprised of right section of left section of bottom wing and bottom wing, and right section of left section of bottom wing and bottom wing be the symmetrical left and right sides, front lower place that is fixed on fuselage respectively, and the rear portion at the wing tip place that left section of bottom wing and bottom wing are right section has configured respectively port aileron and starboard aileron that can be movable.Control the upper and lower differential deflection of port aileron and starboard aileron, can make this laterally rolling of aircraft left and right; Control port aileron and starboard aileron deflects down simultaneously, can make this aircraft lift increase, favourable landing or climb.Two of the left and right tip end portion of the lap of the vertical direction of upper limb and bottom wing respectively symmetry left normal limb and right normal limb are housed, left normal limb is flexibly connected with upper limb and bottom wing respectively up and down by left normal limb axle, and right normal limb is flexibly connected with upper limb and bottom wing respectively up and down by right normal limb axle.Left normal limb axle is near the leading edge of left normal limb, and right normal limb axle is near the leading edge of right normal limb.When this aircraft grounding or forward rectilinear flight, left normal limb, right normal limb and rear normal limb are parallel to each other, and parallel with longitudinal plane of symmetry of this aircraft.The effect of left normal limb and right normal limb at least shows following four aspects: one, be connected upper limb and bottom wing, play booster action; Two, hinder the generation of wing tip vortex, be conducive to improve the efficiency of upper limb and bottom wing; Three, surround two the oblong air flues in left and right with upper limb, bottom wing and fuselage, adjust the convenient flight attitude of handling this aircraft of air-flow vector of these two air flues; Four, form rear bikini fixed fin with rear normal limb, play stable aircraft.Control the deflection of left normal limb and right normal limb and can control aircraft sidesway, fuselage keeps the constant and side-to-side movement of occurred level direction of fore-and-aft direction.The synchronous suitable angle of deflection left of the trailing edge of left normal limb and the trailing edge of right normal limb, aircraft is by drift to the right; The synchronous suitable angle of deflection to the right of the trailing edge of left normal limb and the trailing edge of right normal limb, aircraft is by drift left.The symmetrical the right and left that is installed on fuselage of left propelling unit and right propelling unit, installs near upper nose of wing and near bottom wing trailing edge place, and is fixed on the lower surface of upper limb and the upper surface of bottom wing.Left propelling unit and right angle of rake rear portion add respectively lobus sinister grid and the lobus dexter grid of horizontal water conservancy diversion, are conducive to improve output gas flow quality.Left propelling unit and right propelling unit forward air inlet are accelerated bottom wing upper surface air-flow, are conducive to bottom wing and produce larger lift, are conducive to postpone bottom wing upper surface burbling; Accelerate the downwash flow of upper limb simultaneously, be also conducive to postpone the separation of the upper surface air-flow of upper limb, can carry out high-angle-of-attack flight, conveniently realize very short takeoff and landing and Ultra-Low Speed flight.Owing to clinging to without long-tail, therefore this Flight Vehicle Structure is compact.The center of gravity of this aircraft was roughly positioned at the intersection point place of perpendicular and this aircraft longitudinal axis of nose of wing.
Accompanying drawing explanation
Fig. 1 is the schematic top plan view of a kind of double-deck rotor aircraft of the present invention; Fig. 2 is the schematic side view of a kind of double-deck rotor aircraft of the present invention; Fig. 3 is the front-view schematic diagram of a kind of double-deck rotor aircraft of the present invention.
In figure, 1-upper limb, 11-elevating rudder, 2-bottom wing, left section of 21-bottom wing, 211-port aileron, right section of 22-bottom wing, 221-starboard aileron, the left normal limb of 31-, the left normal limb axle of 311-, the right normal limb of 32-, the right normal limb axle of 321-, normal limb after 4-, 41-yaw rudder, the left propelling unit of 51-, the right propelling unit of 52-, 61-lobus sinister grid, 62-lobus dexter grid, 7-alighting gear, 8-fuselage.
The specific embodiment
Now 1 ~ 3 couple of the present invention is illustrated by reference to the accompanying drawings: a kind of double-deck rotor aircraft, comprises upper limb 1, bottom wing 2, left normal limb 31, right normal limb 32, rear normal limb 4, engine installation, alighting gear 7 and fuselage 8.In fuselage 8, be furnished with maneuvering system and airborne equipment.Bikini wheel undercarriage before alighting gear 7 adopts.Engine installation comprises left propelling unit 51 and the right propelling unit 52 of energy supplyystem and the identical switched in opposite of two nested structures, and left propelling unit 51 and right propelling unit 52 all adopt piston engine to add the form of ducted fan formula screw propeller, with fuel oil, provide the energy.Upper limb 1 is placed in the top, rear portion of fuselage 8, and upper limb 1 is that elevating rudder 11 form by the fixed part that is positioned at the place ahead with the moving part that is positioned at rear, and upper limb 1 is connected with fuselage 8 by the middle part of its fixed part.The upper and lower deflection of elevating rudder 11 energy under the controlling of maneuvering system, upward deflects and can make this aircraft come back, and realization is faced upward; The change of team of elevating rudder downward bias is bowed this aircraft, realizes nutation.It is stable that upper limb 1 fixed part also plays level except producing lift.The midway location top, rear portion of upper limb 1 fixed part is provided with rear normal limb 4, the moving part of rear normal limb 4 by forward fixed part and after leaning on is that yaw rudder 41 forms, yaw rudder 41 deflection under the controlling of maneuvering system, can make this aircraft left and driftage to the right.Bottom wing 2 is comprised of for right section 22 left section 21 of bottom wing and bottom wing, right section 22 of left section 21 of bottom wing and bottom wing be the symmetrical left and right sides, front lower place that is fixed on fuselage 8 respectively, and the rear portion at the wing tip place that left section 21 of bottom wing and bottom wing are right section 22 has configured respectively port aileron 211 and starboard aileron 221 that can be movable.Control the upper and lower differential deflection of port aileron 211 and starboard aileron 221, can make this laterally rolling of aircraft left and right; Control port aileron 211 and starboard aileron 221 deflects down simultaneously, can make this aircraft lift increase, favourable landing or climb.Two of the left and right tip end portion of the lap of the vertical direction of upper limb 1 and bottom wing 2 respectively symmetry left normal limb 31 and right normal limb 32 are housed, left normal limb 31 is flexibly connected with upper limb 1 and bottom wing 2 respectively up and down by left normal limb axle 311, and right normal limb 32 is flexibly connected with upper limb 1 and bottom wing 2 respectively up and down by right normal limb axle 321.Left normal limb axle 311 is near the leading edge of left normal limb 31, and right normal limb axle 321 is near the leading edge of right normal limb 32.When this aircraft grounding or forward rectilinear flight, left normal limb 31, right normal limb 32 and rear normal limb 4 are parallel to each other, and parallel with longitudinal plane of symmetry of this aircraft.The effect of left normal limb 31 and right normal limb 32 has following four aspects at least: one, be connected upper limb 1 and bottom wing 2, play booster action; Two, hinder the generation of wing tip vortex, be conducive to improve the efficiency of upper limb 1 and bottom wing 2; Three, surround two the oblong air flues in left and right with upper limb 1, bottom wing 2 and fuselage 8, adjust the convenient flight attitude of handling this aircraft of air-flow vector of these two air flues; Four, form rear bikini fixed fin with rear normal limb 4, play stable aircraft.Control the deflection of left normal limb 31 and right normal limb 32 and can control aircraft sidesway, fuselage 8 keeps the constant and side-to-side movement of occurred level direction of fore-and-aft directions.Synchronous suitable angle of deflection left of trailing edge of the trailing edge of left normal limb 31 and right normal limb 32, aircraft is by drift to the right; Synchronous suitable angle of deflection to the right of trailing edge of the trailing edge of left normal limb 31 and right normal limb 32, aircraft is by drift left.The symmetrical the right and left that is installed on fuselage 8 of left propelling unit 51 and right propelling unit 52, installs near upper limb 1 leading edge and near bottom wing 2 trailing edge places, and is fixed on the lower surface of upper limb 1 and the upper surface of bottom wing 2.The rear portion of left propelling unit 51 and right propelling unit 52 adds respectively lobus sinister grid 61 and the lobus dexter grid 62 of horizontal water conservancy diversion, is conducive to improve output gas flow quality.Left propelling unit 51 and right propelling unit 52 forward air inlet are accelerated bottom wing 2 upper surface air-flows, are conducive to bottom wing 2 and produce larger lift, are conducive to postpone bottom wing 2 upper surface burbling; Accelerate the downwash flow of upper limb 1 simultaneously, be also conducive to postpone the separation of the upper surface air-flow of upper limb 1, can carry out high-angle-of-attack flight, conveniently realize very short takeoff and landing and Ultra-Low Speed flight.Owing to clinging to without long-tail, therefore this Flight Vehicle Structure is compact.The center of gravity of this aircraft was roughly positioned at the intersection point place of perpendicular and this aircraft longitudinal axis of upper limb 1 leading edge.
Claims (8)
1. a double-deck rotor aircraft, comprise upper limb (1), bottom wing (2), left normal limb (31), right normal limb (32), rear normal limb (4), engine installation, alighting gear (7) and fuselage (8), it is characterized in that: fuselage is furnished with maneuvering system and airborne equipment in (8); Engine installation comprises left propelling unit (51) and the right propelling unit (52) of energy supplyystem and the identical switched in opposite of two nested structures; Upper limb (1) is placed in the top, rear portion of fuselage (8), and upper limb (1) is that elevating rudder (11) form by the fixed part that is positioned at the place ahead with the moving part that is positioned at rear, and upper limb (1) is connected with fuselage (8) by the middle part of its fixed part; The midway location top, rear portion of upper limb (1) fixed part is provided with rear normal limb (4), and the moving part of rear normal limb (4) by forward fixed part and after leaning on is that yaw rudder (41) forms; Bottom wing (2) is comprised of bottom wing left section (21) and bottom wing right section (22), bottom wing left section (21) and bottom wing right section (22) respectively symmetry are fixed on the left and right sides, front lower place of fuselage (8), and the rear portion at the wing tip place of bottom wing left section (21) and bottom wing right section (22) has configured respectively port aileron (211) and starboard aileron (221) that can be movable; Two of the left and right tip end portion of the lap of the vertical direction of upper limb (1) and bottom wing (2) respectively symmetry left normal limb (31) and right normal limb (32) are housed, left normal limb (31) is flexibly connected with upper limb (1) and bottom wing (2) respectively up and down by left normal limb axle (311), and right normal limb (32) is flexibly connected with upper limb (1) and bottom wing (2) respectively up and down by right normal limb axle (321); Left normal limb (31), right normal limb (32) and rear normal limb (4) are parallel to each other, and parallel with longitudinal plane of symmetry of this aircraft; Left propelling unit (51) and the symmetrical the right and left that is installed on fuselage of right propelling unit (52); Near upper limb (1) leading edge and near bottom wing (2) trailing edge place, install, and be fixed on the lower surface of upper limb (1) and the upper surface of bottom wing (2).
2. a kind of double-deck rotor aircraft according to claim 1, is characterized in that: bikini wheel undercarriage before alighting gear (7) adopts.
3. a kind of double-deck rotor aircraft according to claim 1, is characterized in that: left propelling unit (51) and right propelling unit (52) all adopt motor to add ducted fan formula screw propeller, and motor is by lithium battery power supply.
4. a kind of double-deck rotor aircraft according to claim 1, is characterized in that: left propelling unit (51) and right propelling unit (52) all adopt piston engine to add ducted fan formula screw propeller.
5. a kind of double-deck rotor aircraft according to claim 1, is characterized in that: left propelling unit (51) and right propelling unit (52) all adopt fanjet.
6. a kind of double-deck rotor aircraft according to claim 1, is characterized in that: left normal limb axle (311) is near the leading edge of left normal limb (31), and right normal limb axle (321) is near the leading edge of right normal limb (32).
7. a kind of double-deck rotor aircraft according to claim 1, is characterized in that: the rear portion of left propelling unit (51) and right propelling unit (52) adds respectively lobus sinister grid (61) and the lobus dexter grid (62) of horizontal water conservancy diversion.
8. a kind of double-deck rotor aircraft according to claim 1, is characterized in that: the center of gravity of this aircraft was roughly positioned at the perpendicular of upper limb (1) leading edge and the intersection point place of this aircraft longitudinal axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420452861.9U CN203975217U (en) | 2014-08-12 | 2014-08-12 | A kind of double-deck rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420452861.9U CN203975217U (en) | 2014-08-12 | 2014-08-12 | A kind of double-deck rotor aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN203975217U true CN203975217U (en) | 2014-12-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420452861.9U Withdrawn - After Issue CN203975217U (en) | 2014-08-12 | 2014-08-12 | A kind of double-deck rotor aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN203975217U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104108464A (en) * | 2014-08-12 | 2014-10-22 | 佛山市神风航空科技有限公司 | Double-layer-wing aircraft |
-
2014
- 2014-08-12 CN CN201420452861.9U patent/CN203975217U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104108464A (en) * | 2014-08-12 | 2014-10-22 | 佛山市神风航空科技有限公司 | Double-layer-wing aircraft |
| CN104108464B (en) * | 2014-08-12 | 2015-11-11 | 佛山市神风航空科技有限公司 | A kind of double-deck rotor aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141203 Effective date of abandoning: 20151111 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |