CN104417750A - Tandem tilt rotor aircraft - Google Patents
Tandem tilt rotor aircraft Download PDFInfo
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- CN104417750A CN104417750A CN201310412479.5A CN201310412479A CN104417750A CN 104417750 A CN104417750 A CN 104417750A CN 201310412479 A CN201310412479 A CN 201310412479A CN 104417750 A CN104417750 A CN 104417750A
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Abstract
The invention discloses a tandem tilt rotor aircraft. A left aircraft body and a right aircraft body are respectively connected to the middle section of a wing and a tail wing, and are kept in parallel; front and rear rotor wings and an engine are respectively arranged in the middles of front and rear support rods; two ends of the front and rear support rods are respectively arranged on the head parts and the rear sections of the left aircraft body and the right aircraft body; tension lines of the front and rear rotor wings and the engine can be wound around the axis of the front support rod upwards, tilt forwards and are kept synchronous; the front and rear rotor wings and the engine are the same, but the steering directions of the rotor wings are opposite; the distances from the axes of the front and rear support rods to the gravity center of the aircraft are equal; when the tandem tilt rotor aircraft vertically takes off and lands, and hovers, downwash flow of the rotor wings keeps away from the wing and most parts of the aircraft bodies; the overall aircraft is high in efficiency; a turbulent flow is not formed to avoid affecting the safety; if the two rotor wings generate a lift force difference; the aircraft only inclines forwards and backwards; the rotor wings of the aircraft are controlled to tilt, so that the aircraft obtains a certain forward velocity; and the lift force difference between the two rotor wings can be balanced by a control plane on the tail wing, so that the stable flying of the aircraft is ensured.
Description
Art
The present invention relates to a kind of can the aircraft of vertical takeoff and landing, especially adopt the aircraft of tilting rotor mode vertical takeoff and landing.
Background technology
Tilt rotor aircraft both can realize vertical takeoff and landing and hovering as helicopter, did not need runway, can fly again as fixed wing aircraft, and voyage, the speed of a ship or plane all far exceed helicopter, was the aircraft of a kind of broad-spectrum advanced person.
The tilt rotor aircraft of present practicality is all cross-arranging type, namely two rotors are laterally arranged on wing two ends respectively, in use just there is two problems like this: 1, when vertical takeoff and landing and hovering, wing is just in time arranged in the downwash flow of rotor, not only overall efficiency is very low, and be the flat transition period flying state at helicopter State Transferring, wing forms sinuous flow, affects safety.2, two rotor wide aparts of tilt rotor aircraft, when vertical takeoff and landing and hovering, if surface irregularity injustice causes the air flow condition of both sides, the asymmetric lift that makes is different, or two asymmetric lift caused of rotor are different, tilt rotor aircraft will be toppled over to side, affects safety.Flat fly state time, two asymmetric pulling force differences caused of rotor also can produce very large deflecting torque.Therefore, in order to ensure two rotor symmetries, must have mechanical connection between two rotors, complete machine structure is very complicated.
Summary of the invention
The object of the invention is to overcome now practical cross-arranging type tilt rotor aircraft Problems existing, provide a kind of lap siding tilt rotor aircraft, two rotors are longitudinally arranged on fuselage head and aft body respectively.
The technical solution adopted in the present invention is: lap siding tilt rotor aircraft is by left and right fuselage, and front rotor and driving engine, front support rod, rear rotor and driving engine, back support rod, wing stage casing, main machine body, the outer section of wing, empennage forms.Left and right fuselage to be connected on wing stage casing and empennage and keeping parallelism, front rotor and driving engine are arranged in the middle part of front support rod, front support rod two ends are arranged on left and right fuselage head respectively, front rotor and driving engine line of pull can around front support rod axis upwards and tilt forward, rear rotor and driving engine are arranged in the middle part of back support rod, back support rod two ends are arranged on left and right aft body respectively, rear rotor and driving engine line of pull can around back support rod axis upwards and tilt forward, front rotor and driving engine is identical with rear rotor and driving engine but rotor turns on the contrary, front rotor and driving engine and rear rotor and driving engine link and keep synchronous when verting, ensure that line of pull is parallel all the time, front support rod axis and back support rod axis to the center of gravity of airplane apart from equal, the spacing of left and right fuselage, front support rod axis is to wing stage casing leading edge distance, back support rod axis is all greater than the plane of rotation diameter of rotor to wing stage casing trailing edge distance, main machine body is positioned in the middle part of wing stage casing, main machine body can make wing body integral structure with wing stage casing, the outer section of wing is positioned at left and right fuselage outer side.
When lap siding tilt rotor aircraft vertical takeoff and landing and hovering, front rotor and driving engine line of pull and rear rotor and driving engine line of pull are all upwards tilted to upright position, before and after rotor produce one vertically upward and equal pulling force simultaneously, due to front support rod axis and back support rod axis to the center of gravity of airplane apart from equal, front and back rotor turns on the contrary, ensure the steady landing of aircraft or hovering, the weight of aircraft is born by rotor thrust completely.Because left and right fuselage distance, front support rod axis are to wing stage casing leading edge distance, back support rod axis to wing stage casing trailing edge apart from the plane of rotation diameter being all greater than rotor, therefore left and right fuselage and wing all avoid the downwash flow of rotor.
Lap siding tilt rotor aircraft is when transition flight, front rotor and driving engine line of pull and rear rotor and driving engine line of pull are all tilted to and are tilted to a certain position, front upper place, aircraft obtains certain speed of advance, and the weight of aircraft is by the vertical component shared of airfoil lift and rotor thrust.
Lap siding tilt rotor aircraft is flat when flying state flight, and front rotor and driving engine line of pull and rear rotor and driving engine line of pull are all tilted to level attitude, and the weight of aircraft is born by airfoil lift completely.
Compared with prior art, the invention has the beneficial effects as follows: when vertical takeoff and landing and hovering, the downwash flow of rotor avoids wing and the large portion of fuselage, overall efficiency is very high, it is the transition period of equalling the state that flies at helicopter State Transferring, can not form sinuous flow and affect safety, aircraft can low-speed operations under any rotor tilts angle.When vertical takeoff and landing and hovering, if the asymmetric lift that makes of the air flow condition before and after surface irregularity injustice causes is different, or two asymmetric lift caused of rotor are different, tilt rotor aircraft only can tilt forwards, backwards, aircraft is moved forward or backward, now operating aircraft rotor verts and makes aircraft enter transition flight state, aircraft obtains certain speed of advance, rudder face generation effect on empennage, the lift that the rudder face handled on empennage can balance two rotors is poor, ensure aircraft smooth flight, very safe.Flat fly state time, two asymmetric pulling force differences caused of rotor can not produce deflecting torque, and even a rotor stall also can ensure flight, and therefore, do not need mechanical connection between two rotors, complete machine structure simplifies greatly.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the present invention is further described.
Fig. 1 is keystone configuration figure of the present invention
Fig. 2 is that front support rod two ends of the present invention are arranged on constructional drawing on the front extension of main machine body respectively
Fig. 3 is that before and after the present invention, rotor and driving engine adopt culvert type rotor and engine structure figure
In figure: 1, left and right fuselage, 2, front support rod, 3, front rotor and driving engine, 4, wing stage casing, 5, main machine body, 6, the outer section of wing, 7, back support rod, 8, rear rotor and driving engine, 9, empennage, 10, the front extension of main machine body, 11, front culvert type rotor and driving engine, 12, rear culvert type rotor and driving engine.
In FIG, left and right fuselage (1) is connected to wing stage casing (4) and empennage (9) is gone up and keeping parallelism, front rotor and driving engine (3) are arranged on front support rod (2) middle part, front support rod (2) two ends are arranged on left and right fuselage (1) head respectively, front rotor and driving engine (3) line of pull can around front support rod (2) axis upwards and tilt forward, rear rotor and driving engine (8) are arranged on back support rod (7) middle part, back support rod (7) two ends are arranged on left and right fuselage (1) back segment respectively, rear rotor and driving engine (8) line of pull can around back support rod (7) axis upwards and tilt forward, front rotor and driving engine (3) is identical with rear rotor and driving engine (8) but rotor turns on the contrary, front rotor and driving engine (3) and rear rotor and driving engine (8) link and keep synchronous when verting, ensure that line of pull is parallel all the time, front support rod (2) axis and back support rod (7) axis to the center of gravity of airplane apart from equal, the spacing of left and right fuselage (1), front support rod (2) axis is to wing stage casing (4) leading edge distance, back support rod (7) axis is all greater than the plane of rotation diameter of rotor to wing stage casing (4) trailing edge distance, main machine body (5) is positioned at middle part, wing stage casing (4), main machine body (5) can make wing body integral structure with wing stage casing (4), the outer section (6) of wing is positioned at left and right fuselage (1) outside.
In fig. 2, front support rod (2) two ends are arranged on the front extension of main machine body (10) respectively, and left and right fuselage (1) is without head.
In figure 3, before and after rotor and driving engine adopt front culvert type rotor and driving engine (11) and rear culvert type rotor and driving engine (12), front and back duct is arranged in the middle part of front support rod (2) and back support rod (7) respectively.
Lap siding tilt rotor aircraft rotor and driving engine method of verting has two kinds: 1, front support rod (2) is fixedly connected with left and right fuselage (1) respectively with back support rod (7) two ends, front rotor and driving engine (3) are hinged with front support rod (2) middle part, rear rotor and driving engine (8) hinged with back support rod (7) middle part.2, front support rod (2) and back support rod (7) two ends are hinged with left and right fuselage (1) respectively, front rotor and driving engine (3) are fixedly connected with front support rod (2) middle part, and rear rotor and driving engine (8) are fixedly connected with back support rod (7) middle part.
Lap siding tilt rotor aircraft empennage (9) can adopt conventional levels empennage and vertical tail structure, also can adopt V-type or reverse V-shaped tail structure.
When lap siding tilt rotor aircraft is parked, the outer section (6) of wing can upwards fold, and parks area to reduce.
Claims (6)
1. a lap siding tilt rotor aircraft, it is characterized in that: aircraft is by left and right fuselage, front rotor and driving engine, front support rod, rear rotor and driving engine, back support rod, wing stage casing, main machine body, the outer section of wing, empennage forms, left and right fuselage to be connected on wing stage casing and empennage and keeping parallelism, front rotor and driving engine are arranged in the middle part of front support rod, front support rod two ends are arranged on left and right fuselage head respectively, front rotor and driving engine line of pull can around front support rod axis upwards and tilt forward, rear rotor and driving engine are arranged in the middle part of back support rod, back support rod two ends are arranged on left and right aft body respectively, rear rotor and driving engine line of pull can around back support rod axis upwards and tilt forward, front rotor and driving engine is identical with rear rotor and driving engine but rotor turns on the contrary, front rotor and driving engine and rear rotor and driving engine link and keep synchronous when verting, ensure that line of pull is parallel all the time, front support rod axis and back support rod axis to the center of gravity of airplane apart from equal, the spacing of left and right fuselage, front support rod axis is to wing stage casing leading edge distance, back support rod axis is all greater than the plane of rotation diameter of rotor to wing stage casing trailing edge distance, main machine body is positioned in the middle part of wing stage casing, main machine body can make wing body integral structure with wing stage casing, the outer section of wing is positioned at left and right fuselage outer side.
2. lap siding tilt rotor aircraft according to claim 1, is characterized in that: front support rod two ends are arranged on the front extension of main machine body respectively, and left and right fuselage is without head.
3. lap siding tilt rotor aircraft according to claim 1, it is characterized in that: front and back rotor and driving engine all adopt culvert type rotor and driving engine, front and back duct is arranged in the middle part of front support rod and back support rod respectively.
4. lap siding tilt rotor aircraft according to claim 1, it is characterized in that: rotor and driving engine method of verting has two kinds: A, front support rod is fixedly connected with left and right fuselage respectively with back support rod two ends, hinged in the middle part of front rotor and driving engine and front support rod, hinged in the middle part of rear rotor and driving engine and back support rod, B, front support rod and back support rod two ends are hinged with left and right fuselage respectively, front rotor and driving engine are fixedly connected with in the middle part of front support rod, and rear rotor and driving engine are fixedly connected with in the middle part of back support rod.
5. lap siding tilt rotor aircraft according to claim 1, is characterized in that: aircraft tail can adopt conventional levels empennage and vertical tail structure, also can adopt V-type or reverse V-shaped tail structure.
6. lap siding tilt rotor aircraft according to claim 1, is characterized in that: when aircraft is parked, and the outer section of wing can upwards fold.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310412479.5A CN104417750A (en) | 2013-09-03 | 2013-09-03 | Tandem tilt rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310412479.5A CN104417750A (en) | 2013-09-03 | 2013-09-03 | Tandem tilt rotor aircraft |
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|---|---|
| CN104417750A true CN104417750A (en) | 2015-03-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310412479.5A Pending CN104417750A (en) | 2013-09-03 | 2013-09-03 | Tandem tilt rotor aircraft |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105711832A (en) * | 2016-04-19 | 2016-06-29 | 北京航空航天大学 | Tilting three-rotor wing long-endurance composite aircraft |
| CN106139608A (en) * | 2015-04-08 | 2016-11-23 | 叶灵 | Fixed wing airplane model |
| CN106275420A (en) * | 2015-06-06 | 2017-01-04 | 杨林 | Uniclinal switch rotor fuselage holds up VTOL aircraft |
| CN107878746A (en) * | 2017-10-20 | 2018-04-06 | 西北工业大学 | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic |
| CN107953984A (en) * | 2017-11-29 | 2018-04-24 | 北京航空航天大学 | A kind of easy-to-mount reverse V-shaped empennage connection structure |
| CN109747822A (en) * | 2017-11-06 | 2019-05-14 | 南京福尔摩斯智能科技有限公司 | Implicitly hung down fixed-wing unmanned plane |
| CN114379774A (en) * | 2022-01-25 | 2022-04-22 | 天津斑斓航空科技有限公司 | Cross-structure aircraft and method thereof |
-
2013
- 2013-09-03 CN CN201310412479.5A patent/CN104417750A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106139608A (en) * | 2015-04-08 | 2016-11-23 | 叶灵 | Fixed wing airplane model |
| CN106275420A (en) * | 2015-06-06 | 2017-01-04 | 杨林 | Uniclinal switch rotor fuselage holds up VTOL aircraft |
| CN105711832A (en) * | 2016-04-19 | 2016-06-29 | 北京航空航天大学 | Tilting three-rotor wing long-endurance composite aircraft |
| CN107878746A (en) * | 2017-10-20 | 2018-04-06 | 西北工业大学 | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic |
| CN109747822A (en) * | 2017-11-06 | 2019-05-14 | 南京福尔摩斯智能科技有限公司 | Implicitly hung down fixed-wing unmanned plane |
| CN107953984A (en) * | 2017-11-29 | 2018-04-24 | 北京航空航天大学 | A kind of easy-to-mount reverse V-shaped empennage connection structure |
| CN107953984B (en) * | 2017-11-29 | 2020-10-30 | 北京航空航天大学 | Inverted V-shaped empennage connecting structure convenient to disassemble and assemble |
| CN114379774A (en) * | 2022-01-25 | 2022-04-22 | 天津斑斓航空科技有限公司 | Cross-structure aircraft and method thereof |
| CN114379774B (en) * | 2022-01-25 | 2023-09-19 | 天津斑斓航空科技有限公司 | Cross-structure aircraft and method thereof |
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| DD01 | Delivery of document by public notice |
Addressee: Yang Jiaxiong Document name: Notification that Application Deemed to be Withdrawn |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150318 |
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| WD01 | Invention patent application deemed withdrawn after publication |