CN204297059U - A kind of variable wing plane - Google Patents
A kind of variable wing plane Download PDFInfo
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- CN204297059U CN204297059U CN201420789073.9U CN201420789073U CN204297059U CN 204297059 U CN204297059 U CN 204297059U CN 201420789073 U CN201420789073 U CN 201420789073U CN 204297059 U CN204297059 U CN 204297059U
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- 230000005540 biological transmission Effects 0.000 claims abstract description 10
- 230000033001 locomotion Effects 0.000 claims description 7
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- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 2
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Abstract
A kind of variable wing plane, belongs to aviation aircraft technical field.Comprise upper limb, bottom wing, empennage, power set, undercarriage and fuselage.Left section of upper limb, left section of bottom wing and composition left wing of Left Drive mechanism assembly; Right section of upper limb, right section of bottom wing and right transmission mechanism composition right flank assembly.Left wing's assembly is identical with right flank assembly structure and be symmetrically arranged in the left and right sides of fuselage.Axis rotate under the control of control system drive left-hand rotation arm and right-hand rotation arm synchronous axial system thus control upper limb and bottom wing closed or open.When upper limb and bottom wing close, this aircraft has become monoplane; When upper limb and bottom wing are opened, this aircraft becomes biplane.Unit machine pattern is applicable to cruising, and efficiency is higher; Biplane pattern is applicable to short take-off and landing or Ultra-Low Speed flight.This invention aircraft is relatively applicable to low-speed operations, is well suited for making trainer aircraft, a tractor serves several purposes, cost-saving.
Description
Technical field
A kind of variable wing plane, belongs to aviation aircraft technical field, particularly relates to a kind of aircraft.
Background technology
Traditional monoplane is more difficult realizes short take-off and landing, and the critical stalling angle of wing is little, easy stall, unsuitable high-angle-of-attack flight; When traditional biplane cruises, airfoil efficiency is lower, and stability is bad; Traditional trainer aircraft or be single-blade, or be double-vane, need the different aircraft of two framves to teach out to fly in a monoplane and the student of biplane, instruction cost is high.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming traditional monoplane, the especially traditional trainer aircraft of traditional biplane, invent a kind of can short take-off and landing, cruise efficiency high and be more suitable for doing the variable wing plane of trainer aircraft.
A kind of variable wing plane, comprises upper limb, bottom wing, empennage, power set, undercarriage and fuselage.Control system and airborne equipment is furnished with in fuselage.Bikini wheel undercarriage after undercarriage adopts.Power set comprise energy supplyystem and propeller.The mode that propeller adopts piston engine to add the mode of screw or motor to add screw.Piston engine fuel oil provides the energy; Adopt the lithium battery power supply using convenient charging during motor.Upper limb divides left section of upper limb and right section of upper limb, and they are symmetrically arranged in the left and right sides of fuselage; Bottom wing divides left section of bottom wing and right section of bottom wing, and they are also symmetrically arranged in the left and right sides of fuselage; The rear portion of the close wing tip section of left section of bottom wing and right section of bottom wing is configured with respectively can movable port aileron and starboard aileron.Left section of upper limb is connected by Left Drive mechanism with left section of bottom wing, and right section of upper limb is connected by right transmission mechanism with right section of bottom wing.Left section of upper limb, left section of bottom wing and composition left wing of Left Drive mechanism assembly; Right section of upper limb, right section of bottom wing and right transmission mechanism composition right flank assembly.Left wing's assembly is identical with right flank assembly structure and be symmetrically arranged in the left and right sides of fuselage.Left Drive mechanism comprises left-hand rotation arm, upper left axle, upper left sprocket wheel, upper left chain, left first middle sprocket, lower-left axle, lower-left sprocket wheel, lower-left chain and left second middle sprocket; Right transmission mechanism comprises right-hand rotation arm, upper right axle, upper right sprocket wheel, upper right chain, right first middle sprocket, bottom right axle, bottom right sprocket wheel, bottom right chain and right second middle sprocket.Upper left axle level is fixed on the root of left section of upper limb, and lower-left axle level is fixed on the root of left section of bottom wing.Axial ratio lower-left, upper left axial length some.Upper left sprocket wheel is fixedly mounted on the right-hand member of upper left axle; Left first middle sprocket is contained on axis by bearing holder (housing, cover), and is fixed on the left side of fuselage with fuselage; Left first middle sprocket is connected by upper left chain with upper left sprocket wheel; The gearratio of left first middle sprocket and upper left sprocket wheel is 1: 1.Lower-left sprocket wheel is fixedly mounted on the right-hand member of lower-left axle; Left second middle sprocket is contained on axis by bearing holder (housing, cover), and is connected with left first middle sprocket; Left second middle sprocket is connected by lower-left chain with lower-left sprocket wheel; The gearratio of left second middle sprocket and lower-left sprocket wheel is 1: 1.Can not relative motion be there is each other in left first middle sprocket, left second middle sprocket and fuselage.The two ends up and down of left-hand rotation arm are respectively by bearing and the upper left axle stage casing that be connected in upper left axle and lower-left axle vertical with lower-left axle.Upper right axle level is fixed on the root of right section of upper limb, and bottom right axle level is fixed on the root of right section of bottom wing.Upper right axial ratio bottom right axial length some.Upper right sprocket wheel is fixedly mounted on the left end of upper right axle; Right first middle sprocket is contained on axis by bearing holder (housing, cover), and is fixed on the right side of fuselage with fuselage; Right first middle sprocket is connected by upper right chain with upper right sprocket wheel; The gearratio of right first middle sprocket and upper right sprocket wheel is 1: 1.Bottom right sprocket wheel is fixedly mounted on the left end of bottom right axle; Right second middle sprocket is contained on axis by bearing holder (housing, cover), and is connected with right first middle sprocket; Right second middle sprocket is connected by bottom right chain with bottom right sprocket wheel; The gearratio of right second middle sprocket and bottom right sprocket wheel is 1: 1.Can not relative motion be there is each other in right first middle sprocket, right second middle sprocket and fuselage.The two ends up and down of right-hand rotation arm are respectively by bearing and the upper right axle stage casing that be connected in upper right axle and bottom right axle vertical with bottom right axle.Axis is horizontally disposed, and vertical with the longitudinal vertical plane of symmetry of fuselage, and its two ends, left and right are the middle part that be fixed on left-hand rotation arm and right-hand rotation arm vertical with right-hand rotation arm with left-hand rotation arm respectively.Upper left chain, lower-left chain, upper right chain are all vertical with axis with the plane of movement of bottom right chain.A breach matched with lower nose of wing is had below upper limb trailing edge, when rotating middle shaft makes left-hand rotation arm and right-hand rotation arm be horizontal, bottom wing and upper limb is end to end is in closure state, upper limb is front, bottom wing is rear, and upper limb and bottom wing form the longer large wing of a chord length; Rotate backward axis when making left-hand rotation arm and right-hand rotation arm be in vertical position, upper limb and bottom wing are in open mode, upper limb upper, bottom wing under, upper limb and bottom wing substantially parallel.In central axis process, the angle of attack of upper limb and bottom wing is substantially constant.
A kind of variable wing plane of the present invention has two kinds of patterns: monoplane pattern and biplane pattern.Axis rotate under the control of control system drive left-hand rotation arm and right-hand rotation arm synchronous axial system thus control upper limb and bottom wing closed or open.When upper limb and bottom wing close, this aircraft has become monoplane; When upper limb and bottom wing are opened, this aircraft becomes biplane.Unit machine pattern is applicable to cruising, and efficiency is higher; Biplane pattern is applicable to short take-off and landing or Ultra-Low Speed flight.
Empennage comprises tailplane and vertical tail, and tailplane is made up of the standing part of leading portion and horizontal stabilizer and back segment movable part and elevator, and vertical tail is made up of the standing part of leading portion and fixed fin and back segment movable part and rudder.Elevator can deflect up and down under the manipulation of control system, upward deflects and this aircraft can be made to come back, realize facing upward; The change of team of elevator downward bias makes this aircraft bow, and realizes nutation.Rudder is deflection under the manipulation of control system, and this aircraft can be made to go off course to the left or to the right.Manipulation port aileron and the upper and lower differential deflection of starboard aileron, horizontal rolling about this aircraft can be made; Manipulation port aileron and starboard aileron deflect down simultaneously, and this airplane ascensional force can be made to increase, favourable landing or climb.
A kind of variable wing plane of this invention is relatively applicable to low-speed operations, is well suited for making trainer aircraft, a tractor serves several purposes, cost-saving.
Accompanying drawing explanation
Fig. 1 is a kind of variable wing plane upper limb of the present invention and bottom wing schematic top plan view when opening; Fig. 2 is that schematic diagram is looked on a kind of variable wing plane upper limb of the present invention and bottom wing left side when opening; Fig. 3 is that schematic diagram is looked on the left side be exaggerated of the left wing assembly that with the left end of axis be connected of upper limb when opening with bottom wing; Fig. 4 is that schematic diagram is looked on the left side be exaggerated of the right flank assembly that with the right-hand member of axis be connected of upper limb when opening with bottom wing; Fig. 5 is a kind of variable wing plane upper limb of the present invention and bottom wing front-view schematic diagram when opening; Fig. 6 is the enlarged drawing of a-quadrant in Fig. 5; Fig. 7 is the enlarged drawing in B region in Fig. 5.
Fig. 8 is a kind of variable wing plane upper limb of the present invention and bottom wing schematic top plan view when closing; Fig. 9 is the enlarged drawing in C region in Fig. 8; Figure 10 is the enlarged drawing in D region in Fig. 8; Figure 11 is that schematic diagram is looked on a kind of variable wing plane upper limb of the present invention and bottom wing left side when closing; Figure 12 is that schematic diagram is looked on the left side be exaggerated of the left wing assembly that with the left end of axis be connected of upper limb when closing with bottom wing; Figure 13 is that schematic diagram is looked on the left side be exaggerated of the right flank assembly that with the right-hand member of axis be connected of upper limb when closing with bottom wing; Figure 14 is a kind of variable wing plane upper limb of the present invention and bottom wing front-view schematic diagram when closing.
In figure, left section of 1-upper limb, 11-upper limb left section of leading edge, 12-upper limb left section of trailing edge, 13-upper left axle, 14-upper left sprocket wheel, 15-upper left chain, left first middle sprocket of 16-; Left section of 2-bottom wing, 21-bottom wing left section of leading edge, 22-bottom wing left section of trailing edge, 23-lower-left axle, 24-lower-left sprocket wheel, 25-lower-left chain, left second middle sprocket of 26-, 27-port aileron; Right section of 3-upper limb, 31-upper limb right section of leading edge, 32-upper limb right section of trailing edge, 33-upper right axle, 34-upper right sprocket wheel, 35-upper right chain, right first middle sprocket of 36-; Right section of 4-bottom wing, 41-bottom wing right section of leading edge, 42-bottom wing right section of trailing edge, 43-bottom right axle, 44-bottom right sprocket wheel, 45-bottom right chain, right second middle sprocket of 46-, 47-starboard aileron; 5-propeller; 6-tailplane, 61-horizontal stabilizer, 62-elevator; 7-vertical tail, 71-fixed fin, 72-rudder; 8-fuselage, 81-undercarriage; 9-axis, 91-left-hand rotation arm, 92-right-hand rotation arm.
Detailed description of the invention
Now 1 ~ 14 couple of the present invention is illustrated by reference to the accompanying drawings: a kind of variable wing plane, comprises upper limb, bottom wing, empennage, power set, undercarriage 81 and fuselage 8.Control system and airborne equipment is furnished with in fuselage 8.Undercarriage 81 adopts rear bikini wheel undercarriage.Power set comprise energy supplyystem and propeller 5, and propeller 5 adopts piston engine to add the mode of screw.Upper limb divides upper limb left section 1 and upper limb right section 3, they are symmetrically arranged in the left and right sides of fuselage 8; Bottom wing divides bottom wing left section 2 and bottom wing right section 4, they are also symmetrically arranged in the left and right sides of fuselage 8; The rear portion of the close wing tip section of bottom wing left section 2 and bottom wing right section 4 is configured with respectively can movable port aileron 27 and starboard aileron 47.Upper limb is connected by Left Drive mechanism for left section 2 with bottom wing for left section 1, and upper limb is connected by right transmission mechanism for right section 4 with bottom wing for right section 3.Upper limb left section 1, bottom wing left section 2 and composition left wing of Left Drive mechanism assembly; Upper limb right section 3, bottom wing right section 4 and right transmission mechanism composition right flank assembly.Left wing's assembly is identical with right flank assembly structure and be symmetrically arranged in the left and right sides of fuselage 8.Left Drive mechanism comprises left-hand rotation arm 91, upper left axle 13, upper left sprocket wheel 14, upper left chain 15, left first middle sprocket 16, lower-left axle 23, lower-left sprocket wheel 24, lower-left chain 25 and left second middle sprocket 26; Right transmission mechanism comprises right-hand rotation arm 92, upper right axle 33, upper right sprocket wheel 34, upper right chain 35, right first middle sprocket 36, bottom right axle 43, bottom right sprocket wheel 44, bottom right chain 45 and right second middle sprocket 46.Upper left axle 13 level is fixed on the root of upper limb left section 1, and lower-left axle 23 level is fixed on the root of bottom wing left section 2.Upper left axle 13 is more longer than lower-left axle 23.Upper left sprocket wheel 14 is fixedly mounted on the right-hand member of upper left axle 13; Left first middle sprocket 16 is contained on axis 9 by bearing holder (housing, cover), and is fixed on the left side of fuselage 8 with fuselage 8; Left first middle sprocket 16 is connected by upper left chain 15 with upper left sprocket wheel 14; The gearratio of left first middle sprocket 16 and upper left sprocket wheel 14 is 1: 1.Lower-left sprocket wheel 24 is fixedly mounted on the right-hand member of lower-left axle 23; Left second middle sprocket 26 is contained on axis 9 by bearing holder (housing, cover), and is connected with left first middle sprocket 16; Left second middle sprocket 26 is connected by lower-left chain 25 with lower-left sprocket wheel 24; The gearratio of left second middle sprocket 26 and lower-left sprocket wheel 24 is 1: 1.Can not relative motion be there is each other in left first middle sprocket 16, left second middle sprocket 26 with fuselage 8.The two ends up and down of left-hand rotation arm 91 are respectively by bearing and upper left axle 13 stage casing that be connected in upper left axle 13 and lower-left axle 23 vertical with lower-left axle 23.Upper right axle 33 level is fixed on the root of upper limb right section 3, and bottom right axle 43 level is fixed on the root of bottom wing right section 4.Upper right axle 33 is more longer than bottom right axle 43.Upper right sprocket wheel 34 is fixedly mounted on the left end of upper right axle 33; Right first middle sprocket 36 is contained on axis 9 by bearing holder (housing, cover), and is fixed on the right side of fuselage 8 with fuselage 8; Right first middle sprocket 36 is connected by upper right chain 35 with upper right sprocket wheel 34; The gearratio of right first middle sprocket 36 and upper right sprocket wheel 34 is 1: 1.Bottom right sprocket wheel 44 is fixedly mounted on the left end of bottom right axle 43; Right second middle sprocket 46 is contained on axis 9 by bearing holder (housing, cover), and is connected with right first middle sprocket 36; Right second middle sprocket 46 is connected by bottom right chain 45 with bottom right sprocket wheel 44; The gearratio of right second middle sprocket 46 and bottom right sprocket wheel 44 is 1: 1.Can not relative motion be there is each other in right first middle sprocket 36, right second middle sprocket 46 with fuselage 8.The two ends up and down of right-hand rotation arm 92 are respectively by bearing and upper right axle 33 stage casing that be connected in upper right axle 33 and bottom right axle 43 vertical with bottom right axle 43.Axis 9 is horizontally disposed, and vertical with fuselage 8 longitudinal vertical plane of symmetry, and its two ends, left and right are the middle part that be fixed on left-hand rotation arm 91 and right-hand rotation arm 92 vertical with right-hand rotation arm 92 with left-hand rotation arm 91 respectively.Upper left chain 15, lower-left chain 25, upper right chain 35 are all vertical with axis 9 with the plane of movement of bottom right chain 45.A breach matched with lower nose of wing is had below upper limb trailing edge, when rotating middle shaft 9 makes left-hand rotation arm 91 and right-hand rotation arm 92 be horizontal, bottom wing and upper limb is end to end is in closure state, upper limb is front, bottom wing is rear, and upper limb and bottom wing form the longer large wing of a chord length; Rotate backward axis 9 when making left-hand rotation arm 91 and right-hand rotation arm 92 be in vertical position, upper limb and bottom wing are in open mode, upper limb upper, bottom wing under, upper limb and bottom wing substantially parallel.In axis 9 rotation process, the angle of attack of upper limb and bottom wing is substantially constant.
A kind of variable wing plane of the present invention has two kinds of patterns: monoplane pattern and biplane pattern.Axis 9 rotate under the control of control system drive left-hand rotation arm 91 and right-hand rotation arm 92 synchronous axial system thus control upper limb and bottom wing closed or open.When upper limb and bottom wing close, this aircraft has become monoplane; When upper limb and bottom wing are opened, this aircraft becomes biplane.Unit machine pattern is applicable to cruising, and efficiency is higher; Biplane pattern is applicable to short take-off and landing or Ultra-Low Speed flight.
Empennage comprises tailplane 6 and vertical tail 7, tailplane 6 is made up of the standing part of leading portion and horizontal stabilizer 61 and back segment movable part and elevator 62, and vertical tail 7 is made up of the standing part of leading portion and fixed fin 71 and back segment movable part and rudder 72.Elevator 62 can deflect up and down under the manipulation of control system, upward deflects and this aircraft can be made to come back, realize facing upward; The change of team of elevator 62 downward bias makes this aircraft bow, and realizes nutation.Rudder 72 is deflection under the manipulation of control system, and this aircraft can be made to go off course to the left or to the right.Manipulation port aileron 27 and the differential deflection of starboard aileron about 47, horizontal rolling about this aircraft can be made; Manipulation port aileron 27 and starboard aileron 47 deflect down simultaneously, and this airplane ascensional force can be made to increase, favourable landing or climb.
Claims (5)
1. a variable wing plane, is characterized in that: comprise upper limb, bottom wing, empennage, power set, undercarriage (81) and fuselage (8); Fuselage is furnished with control system and airborne equipment in (8); Undercarriage (81) adopts wheel undercarriage; Power set comprise energy supplyystem and propeller (5); Upper limb divides upper limb left section (1) and right section of upper limb (3), and they are symmetrically arranged in the left and right sides of fuselage (8); Bottom wing divides bottom wing left section (2) and right section of bottom wing (4), and they are also symmetrically arranged in the left and right sides of fuselage (8); Left section of upper limb (1) and bottom wing left section (2) are connected by Left Drive mechanism, and right section of upper limb (3) and bottom wing right section (4) are connected by right transmission mechanism; Left section of upper limb (1), bottom wing left section (2) and composition left wing of Left Drive mechanism assembly; Right section of upper limb (3), bottom wing right section (4) and right transmission mechanism composition right flank assembly; Left wing's assembly is identical with right flank assembly structure and be symmetrically arranged in the left and right sides of fuselage (8); Left Drive mechanism comprises left-hand rotation arm (91), upper left axle (13), upper left sprocket wheel (14), upper left chain (15), left first middle sprocket (16), lower-left axle (23), lower-left sprocket wheel (24), lower-left chain (25) and left second middle sprocket (26); Right transmission mechanism comprises right-hand rotation arm (92), upper right axle (33), upper right sprocket wheel (34), upper right chain (35), right first middle sprocket (36), bottom right axle (43), bottom right sprocket wheel (44), bottom right chain (45) and right second middle sprocket (46); Upper left axle (13) level is fixed on the root of upper limb left section (1), and lower-left axle (23) level is fixed on the root of bottom wing left section (2); Upper left sprocket wheel (14) is fixedly mounted on the right-hand member of upper left axle (13); Left first middle sprocket (16) is contained on axis (9) by bearing holder (housing, cover), and is fixed on the left side of fuselage (8) with fuselage (8); Left first middle sprocket (16) is connected by upper left chain (15) with upper left sprocket wheel (14); The gearratio of left first middle sprocket (16) and upper left sprocket wheel (14) is 1: 1; Lower-left sprocket wheel (24) is fixedly mounted on the right-hand member of lower-left axle (23); Left second middle sprocket (26) is contained on axis (9) by bearing holder (housing, cover), and is connected with left first middle sprocket (16); Left second middle sprocket (26) is connected by lower-left chain (25) with lower-left sprocket wheel (24); The gearratio of left second middle sprocket (26) and lower-left sprocket wheel (24) is 1: 1; The two ends up and down of left-hand rotation arm (91) are respectively by bearing and upper left axle (13) stage casing that be connected in upper left axle (13) and lower-left axle (23) vertical with lower-left axle (23); Upper right axle (33) level is fixed on the root of upper limb right section (3), and bottom right axle (43) level is fixed on the root of bottom wing right section (4); Upper right sprocket wheel (34) is fixedly mounted on the left end of upper right axle (33); Right first middle sprocket (36) is contained on axis (9) by bearing holder (housing, cover), and is fixed on the right side of fuselage (8) with fuselage (8); Right first middle sprocket (36) is connected by upper right chain (35) with upper right sprocket wheel (34); The gearratio of right first middle sprocket (36) and upper right sprocket wheel (34) is 1: 1; Bottom right sprocket wheel (44) is fixedly mounted on the left end of bottom right axle (43); Right second middle sprocket (46) is contained on axis (9) by bearing holder (housing, cover), and is connected with right first middle sprocket (36); Right second middle sprocket (46) is connected by bottom right chain (45) with bottom right sprocket wheel (44); The gearratio of right second middle sprocket (46) and bottom right sprocket wheel (44) is 1: 1; The two ends up and down of right-hand rotation arm (92) are respectively by bearing and upper right axle (33) stage casing that be connected in upper right axle (33) and bottom right axle (43) vertical with bottom right axle (43); Axis (9) is horizontally disposed, and vertical with fuselage (8) longitudinal vertical plane of symmetry, and its two ends, left and right are the middle part that be fixed on left-hand rotation arm (91) and right-hand rotation arm (92) vertical with right-hand rotation arm (92) with left-hand rotation arm (91) respectively; Upper left chain (15), lower-left chain (25), upper right chain (35) are all vertical with axis (9) with the plane of movement of bottom right chain (45); A breach matched with lower nose of wing is had below upper limb trailing edge, when rotating middle shaft (9) makes left-hand rotation arm (91) and right-hand rotation arm (92) be horizontal, bottom wing and upper limb is end to end is in closure state, upper limb is front, bottom wing is rear, and upper limb and bottom wing form the longer large wing of a chord length; Rotate backward axis (9) when making left-hand rotation arm (91) and right-hand rotation arm (92) be in vertical position, upper limb and bottom wing are in open mode, upper limb upper, bottom wing under, upper limb and bottom wing substantially parallel; In axis (9) rotation process, the angle of attack of upper limb and bottom wing is substantially constant.
2. a kind of variable wing plane according to claim 1, is characterized in that: the rear portion of the close wing tip section of bottom wing left section (2) and bottom wing right section (4) is configured with port aileron (27) and starboard aileron (47) respectively.
3. a kind of variable wing plane according to claim 1, is characterized in that: the mode that propeller (5) adopts piston engine to add the mode of screw or motor to add screw; Piston engine fuel oil provides the energy; Adopt the lithium battery power supply using convenient charging during motor.
4. a kind of variable wing plane according to claim 1, is characterized in that: bikini wheel undercarriage after undercarriage (81) adopts.
5. a kind of variable wing plane according to claim 1, is characterized in that: upper left axle (13) is more longer than lower-left axle (23); Upper right axle (33) is more longer than bottom right axle (43).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789073.9U CN204297059U (en) | 2014-12-15 | 2014-12-15 | A kind of variable wing plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789073.9U CN204297059U (en) | 2014-12-15 | 2014-12-15 | A kind of variable wing plane |
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| Publication Number | Publication Date |
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| CN204297059U true CN204297059U (en) | 2015-04-29 |
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| CN201420789073.9U Withdrawn - After Issue CN204297059U (en) | 2014-12-15 | 2014-12-15 | A kind of variable wing plane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443353A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Wing-changeable airplane |
-
2014
- 2014-12-15 CN CN201420789073.9U patent/CN204297059U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443353A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Wing-changeable airplane |
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Granted publication date: 20150429 Effective date of abandoning: 20160831 |
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