CN115056972A - Liftable rotor wing fairing of composite wing aircraft - Google Patents
Liftable rotor wing fairing of composite wing aircraft Download PDFInfo
- Publication number
- CN115056972A CN115056972A CN202210986033.2A CN202210986033A CN115056972A CN 115056972 A CN115056972 A CN 115056972A CN 202210986033 A CN202210986033 A CN 202210986033A CN 115056972 A CN115056972 A CN 115056972A
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- China
- Prior art keywords
- fairing
- liftable
- wing aircraft
- rotor
- tail
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
Abstract
The invention discloses a liftable rotor wing fairing of a composite wing aircraft, which comprises a fixed fairing, wherein the fixed fairing is used for wrapping the composite wing aircraft; the head and the tail of the fixed fairing are respectively provided with a first groove and a second groove, and two rotors of the composite wing aircraft are respectively positioned at the tops of the first groove and the second groove; the head part of the fixed fairing is provided with a head part liftable fairing matched with the first groove, and the tail part of the fixed fairing is provided with a tail part liftable fairing matched with the second groove; the head liftable fairing and the tail liftable fairing are respectively positioned above the two rotors, and according to different flight modes of the composite wing aircraft, the head liftable fairing and the tail liftable fairing are controlled to descend and are matched with the first groove and the second groove, so that the flight resistance of the composite wing aircraft is reduced, the pneumatic efficiency of the composite wing aircraft is improved, the voyage and the time of voyage are increased, and the flight stability is improved.
Description
Technical Field
The invention relates to the technical field of composite wing aircrafts, in particular to a liftable rotor wing fairing of a composite wing aircraft.
Background
The composite wing aircraft is an aircraft combining the advantages of a fixed wing aircraft and a multi-rotor aircraft, and has the advantages of both the fixed wing aircraft and the multi-rotor aircraft. The aircraft can take off and land vertically without a runway, and is switched to a fixed wing high-speed flight mode after taking off, so that the energy consumption is reduced, the aircraft has the characteristics of flexibility and adaptability to complex environments, and has wide application prospects in the aspects of emergency rescue, aerial surveying and mapping, natural resource monitoring and the like.
The composite wing aircraft is divided into three working modes, namely a multi-rotor mode, a multi-rotor fixed wing transition mode and a fixed wing mode. Wherein, many rotors mode is used for unmanned aerial vehicle's take off and land and hover, and the fixed wing mode is used for unmanned aerial vehicle's level to fly and cruises, and under this mode, the rotor is out of work, and many rotors fixed wing transition mode mainly used is many rotors mode and the mode transition between the fixed wing mode switches. For the unmanned aerial vehicle in long voyage, the operation time of the horizontal flight mode is more than 90%.
The existing composite wing aircraft has irregular shapes of wing support arms, motors and rotors, and is usually arranged in the middle of wings, and the wing support arms, the motors and the rotors of the composite wing aircraft increase flight resistance in a horizontal flight mode, thereby shortening the flight distance and the flight time of the composite wing aircraft.
Disclosure of Invention
Aiming at the problems in the prior art, the invention aims to provide a liftable rotor wing fairing of a composite wing aircraft, which solves the problems that the flight distance and the flight time of the composite wing aircraft are shortened due to increased flight resistance of a wing support arm, a motor and a rotor wing in the horizontal flight mode of the existing composite wing aircraft.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:
the utility model provides a liftable rotor wing fairing of a composite wing aircraft, which comprises a fixed fairing, wherein the fixed fairing is used for wrapping the composite wing aircraft;
the head and the tail of the fixed fairing are respectively provided with a first groove and a second groove, and two rotors of the composite wing aircraft are respectively positioned at the tops of the first groove and the second groove;
the head part of the fixed fairing is provided with a head part liftable fairing matched with the first groove, and the tail part of the fixed fairing is provided with a tail part liftable fairing matched with the second groove; the head part liftable fairing and the tail part liftable fairing are respectively positioned above the two rotor wings.
The shapes of the fixed fairing, the head part liftable fairing and the tail part liftable fairing are all streamline, and the shapes of the head part liftable fairing and the tail part liftable fairing are in smooth transition with the shapes of the head part and the tail part of the fixed fairing.
The basic principle of the scheme is as follows: the composite wing aircraft comprises a support arm, wherein two ends of the support arm are respectively provided with a rotor and a rotor motor used for driving the rotor to rotate, the support arm and the rotor motor are arranged in a fixed fairing, the rotors are respectively positioned at the top of a first groove and a second groove, and the purpose is to ensure that the spatial position of the fixed fairing does not influence the rotation of the rotor of the composite wing aircraft.
When the composite wing aircraft is about to take off or is switched from a fixed wing mode to a rotor wing mode, the head liftable fairing and the tail liftable fairing ascend to specified positions, so that the spatial positions of the head liftable fairing and the tail liftable fairing do not influence the rotation of the rotor wing, and the rotor wing of the composite wing aircraft rotates to complete the mode switching work; when the composite wing aircraft will descend or switch to the fixed wing mode from the rotor mode, treat rotor stall back, head liftable fairing and afterbody liftable fairing descend to with the top cooperation back of first recess and second recess, the appearance of fixed fairing is streamlined, can reduce composite wing aircraft's flight resistance, promote composite wing aircraft range and time of navigating, and head liftable fairing and afterbody liftable fairing can cover rotor and rotor motor, realize the protect function to rotor and rotor motor.
Further, two wings of the composite wing aircraft are respectively arranged on two sides of the fixed fairing.
Furthermore, as a specific setting mode of ascending and descending of the head part liftable fairing and the tail part liftable fairing, the lower end faces of the head part liftable fairing and the tail part liftable fairing are both provided with electric push rods, the extending ends of the electric push rods are fixedly connected with the lower end face of the head part liftable fairing or the tail part liftable fairing, and the tail end of each electric push rod is fixedly connected with the inside of the fixed fairing.
Furthermore, the lower terminal surface of head liftable radome fairing and afterbody liftable radome fairing is matched with two electric putter, and the interval between two electric putter is greater than the diameter of rotation of rotor, avoids electric putter's setting to interfere the rotary motion of rotor.
The invention has the beneficial effects that: 1. the lifting rotor wing fairing of the composite wing aircraft in the scheme has the advantages that the fixed fairing, the head lifting fairing and the tail lifting fairing are streamline in appearance, airflow separation of wings near the support arm of the composite wing aircraft can be obviously weakened, airflow smoothly flows through the whole fairing and the surfaces of the wings, the pneumatic efficiency of the composite wing aircraft is improved, the voyage and the time of voyage are increased, and the flying stability is improved.
2. The lifting and descending of the head lifting fairing and the tail lifting fairing are realized through the vertical movement of the extending end of the electric push rod, the lifting process of the head lifting fairing and the tail lifting fairing is carried out after the composite wing aircraft enters a stable level flight state, the electric push rod and the rotor motor are not required to be synchronously controlled, and the control problem caused by mode switching does not exist. In addition, the lift force of the composite wing aircraft in the flat flight process can not be reduced in the descending process of the head liftable fairing and the tail liftable fairing, and extra flight control instructions and power can not be called to stabilize the posture of the composite wing aircraft.
3. When the composite wing aircraft is in a horizontal flight mode, the rotor and the rotor motor can be covered by the whole fairing in space, the composite wing aircraft can collide with birds, buildings and trees when flying at a high speed, the damage to the rotor and the rotor motor can be reduced by the fairing, and the protection functions of the two structures are realized. The head part liftable fairing and the tail part liftable fairing cover the upper portion of the rotor wing, and the head part liftable fairing and the tail part liftable fairing can play a role of rain sheltering in rainy days, so that the rotor wing motor is prevented from being out of work due to the fact that a large amount of rainwater is immersed into the rotor wing motor.
Drawings
Fig. 1 is a schematic view of the external structure of a liftable rotor fairing of a composite wing aircraft.
Fig. 2 is a schematic structural view of a liftable rotor fairing of the composite wing aircraft after the liftable fairing at the head part and the liftable fairing at the tail part are lifted.
Fig. 3 is a schematic view of the internal structure of a liftable rotor fairing of a compound wing aircraft.
Fig. 4 is a schematic structural view of a conventional composite wing aircraft without a fairing.
Wherein, 1, fixing a fairing; 2. a first groove; 3. a second groove; 4. the head part can lift the fairing; 5. the tail part can lift the fairing; 6. an electric push rod; 7. a rotor; 8. a rotor motor; 9. a support arm; 10. an airfoil.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and it will be apparent to those skilled in the art that various changes may be made without departing from the spirit and scope of the invention as defined and defined in the appended claims, and all matters produced by the invention using the inventive concept are protected.
As shown in fig. 1 to 4, the invention provides a liftable rotor fairing of a composite wing aircraft, which comprises a fixed fairing 1, wherein the fixed fairing 1 is used for wrapping the composite wing aircraft.
The composite wing aircraft comprises a support arm 9 and wings 10, wherein two ends of the support arm 9 are respectively provided with a rotor 7 and a rotor motor 8 for driving the rotor 7 to rotate, the support arm 9 and the rotor motor 8 are arranged inside the fixed fairing 1, and the two wings 10 of the composite wing aircraft are respectively arranged on two sides of the fixed fairing 1.
The head and the tail of the fixed fairing 1 are respectively provided with a first groove 2 and a second groove 3, and two rotors 7 of the composite wing aircraft are respectively positioned at the tops of the first groove 2 and the second groove 3.
The head part of the fixed fairing 1 is provided with a head part liftable fairing 4 matched with the first groove 2, and the tail part of the fixed fairing 1 is provided with a tail part liftable fairing 5 matched with the second groove 3; the head lifting fairing 4 and the tail lifting fairing 5 are respectively positioned above the two rotor wings 7. When the compound wing aircraft was in the horizontal flight mode, whole radome fairing can cover rotor 7 and rotor motor 8 in the space, and compound wing aircraft probably takes place the striking with bird, building, tree when high-speed flight, and the radome fairing can reduce the injury that rotor 7 and rotor motor 8 received, realizes the protect function to these two structures.
Simultaneously, head liftable fairing 4 and afterbody liftable fairing 5 cover in rotor 7 top, and in the rainy day, head liftable fairing 4 and afterbody liftable fairing 5 can play the effect of taking shelter from the rain, avoid a large amount of rainwater to dip rotor motor 8 and cause rotor motor 8 to become invalid.
The lower terminal surface of head liftable fairing 4 and afterbody liftable fairing 5 all is provided with two electric putter 6, and the interval between two electric putter 6 is greater than the diameter of rotation of rotor 7, avoids electric putter 6's setting to interfere the rotary motion of rotor 7, and the end that stretches out of every electric putter 6 and the lower terminal surface fixed connection of head liftable fairing 4 or afterbody liftable fairing 5, the tail end of electric putter 6 and the inside fixed connection of fixed fairing 1. The lifting and descending of the head lifting fairing 4 and the tail lifting fairing 5 are realized by controlling the vertical movement of the extending end of the electric push rod 6. The lifting process of the head lifting fairing 4 and the tail lifting fairing 5 is carried out after the composite wing aircraft enters a stable flat flying state, the control of the electric push rod 6 and the rotor motor 8 does not need to be carried out synchronously, and the control problem caused by mode switching does not exist. In addition, in the descending process of the head part liftable fairing 4 and the tail part liftable fairing 5, the lifting force of the composite wing aircraft in the flat flight process cannot be reduced, and extra flight control instructions and power cannot be called to stabilize the posture of the composite wing aircraft.
When the composite wing aircraft is about to take off or is switched from a fixed wing mode to a rotor wing mode, the electric push rod 6 drives the head liftable fairing 4 and the tail liftable fairing 5 to rise to the designated positions, so that the spatial positions of the head liftable fairing and the tail liftable fairing do not influence the rotation of the rotor wing 7, and the rotor wing 7 of the composite wing aircraft rotates to complete the mode switching work; when the compound wing aircraft will descend or switch to the fixed wing mode from the rotor mode, treat rotor 7 stall back, electric putter 6 drives head liftable fairing 4 and afterbody liftable fairing 5 and descends to with first recess 2 and second recess 3's top cooperation back, form a holistic fairing, compound wing aircraft's support arm 9, rotor motor 8 and rotor 7 are all wrapped up in holistic fairing, can reduce compound wing aircraft's flight resistance, promote compound wing aircraft range and when navigating, and head liftable fairing 4 and afterbody liftable fairing 5 can cover rotor 7 and rotor motor 8, realize the protect function to rotor 7 and rotor motor 8.
Preferably, but not limited to, the shapes of the fixed fairing 1, the head liftable fairing 4 and the tail liftable fairing 5 are streamline, the shapes of the head liftable fairing 4 and the tail liftable fairing 5 and the shapes of the head and the tail of the fixed fairing 1 are in smooth transition, the airflow separation of the wings 10 near the support arm 9 of the composite wing aircraft can be obviously weakened, the airflow smoothly flows through the whole fairing and the surfaces of the wings 10, the aerodynamic efficiency of the composite wing aircraft is improved, and the flight range and the flight time are increased, so that the flight stability is improved.
Claims (5)
1. A liftable rotor wing fairing of a composite wing aircraft is characterized by comprising a fixed fairing, wherein the fixed fairing is used for wrapping the composite wing aircraft;
the head and the tail of the fixed fairing are respectively provided with a first groove and a second groove, and two rotors of the composite wing aircraft are respectively positioned at the tops of the first groove and the second groove;
the head part of the fixed fairing is provided with a head part liftable fairing matched with the first groove, and the tail part of the fixed fairing is provided with a tail part liftable fairing matched with the second groove; the head part liftable fairing and the tail part liftable fairing are respectively positioned above the two rotor wings.
2. The liftable rotor fairing of a composite wing aircraft according to claim 1, wherein two wings of the composite wing aircraft are respectively disposed on both sides of the fixed fairing.
3. The liftable rotor wing fairing of the composite wing aircraft according to claim 1, wherein the lower end surfaces of the head liftable fairing and the tail liftable fairing are respectively provided with an electric push rod, the extending end of the electric push rod is fixedly connected with the lower end surface of the head liftable fairing or the tail liftable fairing, and the tail end of the electric push rod is fixedly connected with the inside of the fixed fairing.
4. The liftable rotor fairing of the composite wing aircraft according to claim 3, wherein the lower end surfaces of the head liftable fairing and the tail liftable fairing are matched with two electric push rods, and the distance between the two electric push rods is larger than the rotation diameter of the rotor.
5. The liftable rotor fairing of a composite wing aircraft according to claim 1, wherein the shapes of the fixed fairing, the head liftable fairing and the tail liftable fairing are streamline, and the shapes of the head liftable fairing and the tail liftable fairing are in smooth transition with the shapes of the head part and the tail part of the fixed fairing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210986033.2A CN115056972A (en) | 2022-08-17 | 2022-08-17 | Liftable rotor wing fairing of composite wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210986033.2A CN115056972A (en) | 2022-08-17 | 2022-08-17 | Liftable rotor wing fairing of composite wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115056972A true CN115056972A (en) | 2022-09-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210986033.2A Pending CN115056972A (en) | 2022-08-17 | 2022-08-17 | Liftable rotor wing fairing of composite wing aircraft |
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| CN (1) | CN115056972A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030136873A1 (en) * | 2000-10-03 | 2003-07-24 | Churchman Charles Gilpin | V/STOL biplane aircraft |
| CN103448910A (en) * | 2013-08-31 | 2013-12-18 | 西北工业大学 | Aircraft capable of vertically taking off and landing at high speed |
| EP3056425A1 (en) * | 2015-02-13 | 2016-08-17 | Airbus Defence and Space GmbH | Aircraft which can launch vertically |
| EP3335989A1 (en) * | 2015-08-12 | 2018-06-20 | Shanghai Fukun Aviation Technology Co., Ltd | Fixed-wing aircraft capable of taking off and landing vertically, and flight control method therefor |
| EP3431385A1 (en) * | 2017-07-21 | 2019-01-23 | General Electric Company | Vertical takeoff and landing aircraft |
| DE102019118023B3 (en) * | 2019-07-04 | 2020-07-23 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft |
| US10894599B1 (en) * | 2020-02-25 | 2021-01-19 | Uav Factory Sia | Retractable VTOL rotor systems and methods |
| CN113335504A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Rotor wing fairing of composite wing aircraft |
-
2022
- 2022-08-17 CN CN202210986033.2A patent/CN115056972A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030136873A1 (en) * | 2000-10-03 | 2003-07-24 | Churchman Charles Gilpin | V/STOL biplane aircraft |
| CN103448910A (en) * | 2013-08-31 | 2013-12-18 | 西北工业大学 | Aircraft capable of vertically taking off and landing at high speed |
| EP3056425A1 (en) * | 2015-02-13 | 2016-08-17 | Airbus Defence and Space GmbH | Aircraft which can launch vertically |
| EP3335989A1 (en) * | 2015-08-12 | 2018-06-20 | Shanghai Fukun Aviation Technology Co., Ltd | Fixed-wing aircraft capable of taking off and landing vertically, and flight control method therefor |
| EP3431385A1 (en) * | 2017-07-21 | 2019-01-23 | General Electric Company | Vertical takeoff and landing aircraft |
| DE102019118023B3 (en) * | 2019-07-04 | 2020-07-23 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft |
| US10894599B1 (en) * | 2020-02-25 | 2021-01-19 | Uav Factory Sia | Retractable VTOL rotor systems and methods |
| CN113335504A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Rotor wing fairing of composite wing aircraft |
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Application publication date: 20220916 |
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| RJ01 | Rejection of invention patent application after publication |