CN204310029U - A kind of can in length and breadth break-in flight aircraft - Google Patents
A kind of can in length and breadth break-in flight aircraft Download PDFInfo
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- CN204310029U CN204310029U CN201420760684.0U CN201420760684U CN204310029U CN 204310029 U CN204310029 U CN 204310029U CN 201420760684 U CN201420760684 U CN 201420760684U CN 204310029 U CN204310029 U CN 204310029U
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Abstract
The utility model belongs to field of flight vehicle design, relates to a kind of aircraft that can realize longitudinal, horizontal break-in flight aloft.A kind of can in length and breadth break-in flight aircraft, aircraft is by forming around two parts up and down of the relative half-twist of normal axis, upper part comprises propulsion module and vertical fin, bottom is divided into wing body integrate body, realizes horizontal flight and Longitudinal Flight by relatively rotating the geometry relativeness changing the upper part longitudinal axis and lower part transverse axis.The beneficial effects of the utility model are, use existing aircraft materials and technique can realize needing to change distribution form according to task awing, obtain more excellent long cruise and anti-airworthiness of dashing forward at a high speed, weight and space cost little, non-deface continuity, be convenient to internal placement, be conducive to stealthy realization.
Description
Technical field
The utility model belongs to field of flight vehicle design, relates to a kind of aircraft that can realize longitudinal, horizontal break-in flight aloft.
Background technology
Aircraft has different requirements when performing different aerial missions to airworthiness, and the distribution form of airworthiness and aircraft is closely related.Adapt to various aerial mission with a kind of fixing distribution form, then aircraft usually can not realize optimum airworthiness in a certain particular task.A typical performance requirement difference is: perform task of cruising, meet the requirement of large voyage, aircraft should possess high 1ift-drag ratio; And perform prominent anti-task, meet the requirement of large speed, aircraft should possess little resistance.On a kind of aircraft of fixing layout, normally there is fundamental contradiction in high 1ift-drag ratio and little resistance.Therefore, the aircraft that a class can change distribution form in flight course is devised and solves this contradiction.
At present, what the most generally apply in this kind of aircraft is variable sweep aircraft, namely in flight course, needs the sweepback angle changing wing according to task, the F-14 airplane carrier fighter of the such as U.S. and Muscovite figure-16 0 strategic bomber etc.Variable sweep aircraft arranges rotating shaft and actuation mechanism at this load maximum position of wing root, has paid larger weight and space cost, counteracts most by the income changing distribution form and bring.
The another kind of application occurred is folded wing aircraft, namely in flight course, needs the dihedral angle changing the outer section of wing according to task, the XB-70 bomber of the such as U.S..Folded wing aircraft arranges rotating shaft and is disconnected by internal and external section wing in the middle part of wing, affects the layout of the inner integral tank of wing on the one hand, reduces aircraft fuel load, destroy the continuity of aerofoil surface on the other hand, be unfavorable for the realization that aircraft is stealthy.
The intelligent variant aircraft concept many employings intelligent material structure occurred in recent years and micro-drive technology, be intended to make aircraft continuous print in flight course change aircraft configuration.But the structural materials that this technology relies on and actuator are still in the exploratory stage, how tentative application on small size checking aircraft, the method for there is no meets the load of complete aircraft, life-span and maintainable requirement.
Summary of the invention
For solving high lift-drag ratio long cruise and slight drag prominent anti-contradiction at a high speed, the utility model proposes a kind ofly can aloft to realize longitudinally, the aircraft of horizontal break-in flight, obtain with low design cost and good Project Realization and improve by changing the airworthiness that distribution form brings in-flight.
The utility model solves the technical scheme that its technical matters adopts:
A kind of can in length and breadth break-in flight aircraft, aircraft is by forming around two parts up and down of the relative half-twist of normal axis, upper part comprises propulsion module and vertical fin, bottom is divided into wing body integrate body, realizes horizontal flight and Longitudinal Flight by relatively rotating the geometry relativeness changing the upper part longitudinal axis and lower part transverse axis.
Adopt horizontal flight during aircraft long cruise, the upper part longitudinal axis is vertical with lower part transverse axis, and aircraft layout has large aspect ratio.Adopt Longitudinal Flight when aircraft is dashed forward anti-at a high speed, the upper part longitudinal axis is parallel with lower part transverse axis, and aircraft layout has little cross sections and amasss.
The profile of described propulsion module is hexahedron, and cross-sectional plane is up-narrow and down-wide isosceles trapezoid, the parallel sweepback of front/rear end, and front end face arranges air-inlet grille, and inner installation jet engine, bottom is connected by ring-like seat ring with described wing body integrate body and relatively rotates.
Described vertical fin is positioned at propulsion module upper back, comprises the left vertical fin of symmetrical flare and right vertical fin, and left vertical fin and right vertical fin adopt the frontier and rear of sweepback, and at trailing edge arranged direction rudder.
The aspect of described wing body integrate body cuts point before and after the wide quadrangle in narrow left and right before and after being, Mirror Symmetry all around, elevating rudder before horizontal flying is arranged in front end is also arranged and vertical is flown left complete dynamic wing tip outside it, elevating rudder after horizontal flying is arranged in rear end is also arranged and vertical is flown right complete dynamic wing tip outside it, elevating rudder after left end arranges vertical flying also arranges that outside it wing tip is moved entirely in horizontal left side that flies, and elevating rudder before right-hand member arranges vertical flying also arranges that outside it wing tip is moved entirely in horizontal right side that flies.
Flown front elevating rudder by horizontal and horizontally flown rear elevating rudder and control pitch attitude during aircraft horizontal flight, flown left complete dynamic wing tip by horizontal and horizontally flown right complete dynamic wing tip and control roll attitude, controlling yaw attitude by yaw rudder.
Flown front elevating rudder by vertical and vertically flown rear elevating rudder and control pitch attitude during aircraft Longitudinal Flight, flown left complete dynamic wing tip by vertical and vertically flown right complete dynamic wing tip and control roll attitude, controlling yaw attitude by yaw rudder.
The beneficial effects of the utility model are, use existing aircraft materials and technique can realize needing to change distribution form according to task awing, obtain more excellent long cruise and anti-airworthiness of dashing forward at a high speed, weight and space cost little, non-deface continuity, be convenient to internal placement, be conducive to stealthy realization.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the utility model is further illustrated.
Fig. 1 is horizontal flight three-dimensional view of the present utility model.
Fig. 2 is Longitudinal Flight three-dimensional view of the present utility model.
Fig. 3 is horizontal flight front elevation of the present utility model.
Fig. 4 is horizontal flight left view of the present utility model.
Fig. 5 is horizontal flight backplan of the present utility model.
Fig. 6 is that this realizes novel longitudinal, horizontal flight conversion driving system.
Detailed description of the invention
In FIG, aircraft is by forming around two parts up and down of the relative half-twist of normal axis 6, upper part comprises propulsion module 1 and vertical fin 2, and bottom is divided into wing body integrate body 3, realizes horizontal flight and Longitudinal Flight by relatively rotating the geometry relativeness changing the upper part longitudinal axis 5 and lower part transverse axis 4.
As shown in Figure 1, adopt horizontal flight during aircraft long cruise, the upper part longitudinal axis 5 is vertical with lower part transverse axis 4, and aircraft layout has large aspect ratio, thus obtains high 1ift-drag ratio.As shown in Figure 2, adopt Longitudinal Flight when aircraft is dashed forward anti-at a high speed, the upper part longitudinal axis 5 is parallel with lower part transverse axis 4, and aircraft layout has little cross sections and amasss, thus obtains little resistance.
As shown in Figure 2, the profile of described propulsion module 1 is hexahedron, and front end face arranges air-inlet grille 7, and bottom is connected by ring-like seat ring 8 with described wing body integrate body 3 and relatively rotates.As shown in Figure 3, the cross-sectional plane of propulsion module (1) is up-narrow and down-wide isosceles trapezoid.As shown in Figure 4, the parallel sweepback of front/rear end of propulsion module 1, inner installation jet engine 9.
As shown in Figure 2, described vertical fin 2 is positioned at propulsion module 1 upper back, comprises the left vertical fin of symmetrical flare and right vertical fin, and left vertical fin and right vertical fin adopt the frontier and rear of sweepback.As shown in Figure 4, at trailing edge arranged direction rudder 10.
As shown in Figure 5, the aspect of described wing body integrate body 3 cuts point before and after the wide quadrangle in narrow left and right before and after being, Mirror Symmetry all around, elevating rudder 11 before horizontal flying is arranged in front end is also arranged and vertical is flown left complete dynamic wing tip 12 outside it, elevating rudder 15 after horizontal flying is arranged in rear end also vertically outside it flies right complete dynamic wing tip 16, elevating rudder 13 after left end arranges vertical flying also arranges that outside it wing tip 14 is moved entirely in horizontal left side that flies, and elevating rudder 17 before right-hand member arranges vertical flying also arranges that outside it wing tip 18 is moved entirely in horizontal right side that flies.
As shown in Figure 5, during aircraft horizontal flight by around horizontal fly that front elevating rudder rotating shaft about 19 deflects horizontal fly front elevating rudder 11 and deflect around rear elevating rudder rotating shaft about 23 horizontally fly rear elevating rudder 15 and control pitch attitude, by around horizontal fly that left complete dynamic wing tip rotating shaft about 22 deflects horizontal fly left complete dynamic wing tip 14 and around horizontal fly that right complete dynamic wing tip rotating shaft about 26 deflects horizontally fly right complete dynamic wing tip 18 and control roll attitude, control yaw attitude by yaw rudder 10.During aircraft Longitudinal Flight by around vertical fly that front elevating rudder rotating shaft about 25 deflects vertical fly front elevating rudder 17 and around vertical fly that rear elevating rudder rotating shaft about 21 deflects vertically fly rear elevating rudder 13 and control pitch attitude, by around vertical fly that left complete dynamic wing tip rotating shaft about 20 deflects vertical fly left complete dynamic wing tip 12 and around vertical fly that right complete dynamic wing tip rotating shaft about 24 deflects vertically fly right complete dynamic wing tip 16 and control roll attitude, control yaw attitude by yaw rudder 10.
As shown in Figure 6, the conversion of aircraft Longitudinal Flight and horizontal flight, by jet engine 9 output shaft power, drives rotation action shaft 27 to drive described propulsion module 1 to be realized around the relative half-twist of normal axis 6 by ring-like seat ring 8 with wing body integrate body 3.
Claims (7)
1. one kind can in length and breadth break-in flight aircraft, it is characterized in that, aircraft is by forming around two parts up and down of the relative half-twist of normal axis, upper part comprises propulsion module and vertical fin, bottom is divided into wing body integrate body, realizes horizontal flight and Longitudinal Flight by relatively rotating the geometry relativeness changing the upper part longitudinal axis and lower part transverse axis.
2. as claimed in claim 1 a kind of can in length and breadth break-in flight aircraft, it is characterized in that, during aircraft long cruise adopt horizontal flight, the upper part longitudinal axis is vertical with lower part transverse axis, and aircraft layout has large aspect ratio; Adopt Longitudinal Flight when aircraft is dashed forward anti-at a high speed, the upper part longitudinal axis is parallel with lower part transverse axis, and aircraft layout has little cross sections and amasss.
3. as claimed in claim 2 a kind of can in length and breadth break-in flight aircraft, it is characterized in that, the profile of described propulsion module is hexahedron, cross-sectional plane is up-narrow and down-wide isosceles trapezoid, the parallel sweepback of front/rear end, front end face arranges air-inlet grille, and inner installation jet engine, bottom is connected by ring-like seat ring with described wing body integrate body and relatively rotates.
4. as claimed in claim 2 a kind of can in length and breadth break-in flight aircraft, it is characterized in that, described vertical fin is positioned at propulsion module upper back, comprises the left vertical fin of symmetrical flare and right vertical fin, left vertical fin and right vertical fin adopt the frontier and rear of sweepback, and at trailing edge arranged direction rudder.
5. as claimed in claim 2 a kind of can in length and breadth break-in flight aircraft, it is characterized in that, the aspect of described wing body integrate body cuts point before and after the wide quadrangle in narrow left and right before and after being, Mirror Symmetry all around, elevating rudder before horizontal flying is arranged in front end is also arranged and vertical is flown left complete dynamic wing tip outside it, elevating rudder after horizontal flying is arranged in rear end is also arranged and vertical is flown right complete dynamic wing tip outside it, elevating rudder after left end arranges vertical flying also arranges that outside it wing tip is moved entirely in horizontal left side that flies, and elevating rudder before right-hand member arranges vertical flying also arranges that outside it wing tip is moved entirely in horizontal right side that flies.
6. as described in one of claim 1-5 a kind of can in length and breadth break-in flight aircraft, it is characterized in that, during aircraft horizontal flight by horizontal fly front elevating rudder and horizontal fly rear elevating rudder control pitch attitude, entirely entirely move wing tip control roll attitude in dynamic wing tip and the horizontal right side that flies by the horizontal left side that flies, control yaw attitude by yaw rudder.
7. as described in one of claim 1-5 a kind of can in length and breadth break-in flight aircraft, it is characterized in that, flown front elevating rudder and indulge to fly rear elevating rudder control pitch attitude by vertical during aircraft Longitudinal Flight, fly the complete dynamic wing tip control roll attitude in the right side by the vertical complete dynamic wing tip in a left side that flies with vertical, control yaw attitude by yaw rudder.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420760684.0U CN204310029U (en) | 2014-12-05 | 2014-12-05 | A kind of can in length and breadth break-in flight aircraft |
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| CN201420760684.0U CN204310029U (en) | 2014-12-05 | 2014-12-05 | A kind of can in length and breadth break-in flight aircraft |
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| CN204310029U true CN204310029U (en) | 2015-05-06 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116520868A (en) * | 2023-04-14 | 2023-08-01 | 成都飞机工业（集团）有限责任公司 | Aircraft attitude angle boundary mutation correction method |
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- 2014-12-05 CN CN201420760684.0U patent/CN204310029U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116520868A (en) * | 2023-04-14 | 2023-08-01 | 成都飞机工业（集团）有限责任公司 | Aircraft attitude angle boundary mutation correction method |
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Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |