CN114248915A - Rotor aircraft for assisting vertical take-off and landing of fixed-wing aircraft - Google Patents
Rotor aircraft for assisting vertical take-off and landing of fixed-wing aircraft Download PDFInfo
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- CN114248915A CN114248915A CN202111450056.3A CN202111450056A CN114248915A CN 114248915 A CN114248915 A CN 114248915A CN 202111450056 A CN202111450056 A CN 202111450056A CN 114248915 A CN114248915 A CN 114248915A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The utility model relates to a rotor craft for assisting fixed wing aircraft VTOL, including central machine box, many rotor arms and many flank jibs, many rotor arms are symmetrically arranged and the level is arranged in week side of central machine box, the tip that the rotor arm kept away from central machine box is provided with the motor installation shell, install the rotating electrical machines that the output shaft arranged down in the motor installation shell, the output shaft of rotating electrical machines has the screw of level arrangement, many flank jibs symmetric design, the both ends of flank jibs are connected between two adjacent motor installation shells wherein, the upper surface of flank jibs is provided with the reconfiguration device that possesses the automatic locking function after butt joint fixed wing aircraft's wing bottom and butt joint are accomplished, the upper surface of flank jibs still is provided with the camera, be provided with power supply and control module in the central machine box. The application has the following expected technical effects: the fixed wing aircraft is convenient to butt joint and separate, and the stable and efficient vertical take-off and landing of the fixed wing aircraft are assisted.
Description
Technical Field
The application relates to the technical field of aircraft general design, in particular to a rotor aircraft for assisting vertical take-off and landing of a fixed-wing aircraft.
Background
In the field of aviation aircrafts, fixed-wing aircrafts often take off in a running mode, take off and the like, and land often in a running mode, a parachuting mode, a net hitting mode and the like, so that the take-off and landing of the fixed-wing aircrafts have high requirements on external conditions such as fields, auxiliary devices and the like.
The vertical take-off and landing fixed wing aircraft developed in recent years adopts a coupled power system design, generally adopts a combined type and a tilting type layout, and is additionally provided with a vertical take-off and landing system of a rotor aircraft, so that the fixed wing aircraft can conveniently take off and land.
Although the taking-off and landing process of the fixed-wing aircraft can be made to have small requirements on the site, the following negative effects are brought at the same time: the additional vertical take-off and landing system on the fixed-wing aircraft can destroy the aerodynamic characteristics of the fixed-wing aircraft, the aerodynamic efficiency is low, and meanwhile, the self weight of the fixed-wing aircraft during cruise is increased, so that the effective load of the fixed-wing aircraft is reduced, the cruise distance is shortened, and the cruise time is shortened, and therefore improvement is needed.
Disclosure of Invention
In order to improve the problems of low aerodynamic efficiency, small effective load, short cruising distance, short cruising flight time and the like of a common fixed-wing aircraft with a vertical take-off and landing system, the application provides a rotor aircraft for assisting the vertical take-off and landing of the fixed-wing aircraft.
The application provides a rotor craft for assisting fixed wing aircraft VTOL adopts following technical scheme:
the utility model provides a rotor craft for assisting fixed wing aircraft VTOL, includes central quick-witted box, many rotor arms and many flank jibs, many the rotor arm symmetrical arrangement and level are arranged in week side of central quick-witted box, the tip that the center machine box was kept away from to the rotor arm is provided with the motor installation shell, install the rotating electrical machines that the output shaft arranged down in the motor installation shell, the output shaft of rotating electrical machines has the screw of level arrangement, many the flank jibs designs for this rotor craft symmetry, the both ends of flank jibs are connected in wherein between two adjacent motor installation shells, the upper surface of flank jibs is provided with the reconfiguration device that has automatic locking function after butt joint fixed wing aircraft's wing bottom and butt joint are accomplished, the upper surface of flank jibs still is provided with the camera, be provided with power supply and control module in the center machine box, when the rotor aircraft is close to the fixed-wing aircraft, the camera is used for shooting and identifying the wing position of the fixed-wing aircraft in real time.
Furthermore, the rotor arm, the rotating motor and the propeller are provided with four groups, six groups or eight groups, and the two side wing arm frames are arranged in parallel.
Furthermore, the side wing arm support and the motor installation shell are integrally formed.
Further, the end part of the rotor arm and the motor mounting shell are movably assembled, and the length of the rotor arm can be freely adjusted.
Furthermore, the inside of the rotor arm is hollow, two ends of the rotor arm are respectively communicated to the inside of the side wing arm support and the inside of the central case, and an internal cavity of the rotor arm is used for wiring.
Further, the main fuselage of the rotorcraft is made of a light high-strength material, the light high-strength material includes but is not limited to glass fiber or carbon fiber, and the main fuselage of the rotorcraft includes but is not limited to the central box, the rotor arms, the wing arm supports and the propellers.
Furthermore, the reconfiguration device includes two butt joint guide rails and locking connector, two the butt joint guide rail all follows the length direction of flank cantilever crane arranges and is parallel to each other, the locking connector is located the one end of butt joint guide rail just is used for the wing of butt joint fixed wing aircraft.
Furthermore, 2-4 cameras are arranged on each side wing arm support, the cameras are evenly arranged at intervals along the length direction of the butt joint guide rails, and the cameras are located between the two butt joint guide rails.
Furthermore, the control module is installed at the central position in the central case, and the power source is provided with a plurality of groups and is uniformly and symmetrically arranged around the control module.
Further, the power source is a lithium battery or an oil-electricity hybrid power source.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the advantages of vertical take-off and landing and hovering of the rotor craft are utilized, and a mode of separating and reconstructing the rotor craft and the fixed-wing craft in the air is adopted, so that the convenient vertical take-off and landing requirement of the fixed-wing craft is met, the self weight of the fixed-wing craft during cruise can be greatly reduced, the original efficient cruise and large load advantages are exerted, and the rotary-wing craft has important military and civil application prospects;
2. the structural design is more stable, and the control is also more convenient.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a schematic top view of a rotary wing aircraft for assisting in vertical take-off and landing of a fixed wing aircraft according to an embodiment of the present disclosure.
Figure 2 is a schematic side view of a rotary wing aircraft for assisting in vertical take-off and landing of a fixed wing aircraft according to an embodiment of the present disclosure.
Description of reference numerals:
1. a center machine box; 2. a rotor arm; 3. a side wing arm support; 4. a motor mounting case; 5. a rotating electric machine; 6. a propeller; 7. a reconstitution device; 71. butting guide rails; 72. locking the connector; 8. a camera; 9. a power source; 10. and a control module.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects to be solved by the present application clearer, the present application is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.
It will be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship indicated in the drawings that is solely for the purpose of facilitating the description and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be considered as limiting the present application.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.
The present application is described in further detail below with reference to figures 1-2.
The embodiment of the application discloses a rotor craft for assisting vertical take-off and landing of a fixed-wing aircraft. Referring to fig. 1 and 2, the rotorcraft for assisting the vertical take-off and landing of the fixed-wing aircraft comprises a central casing 1, a plurality of rotor arms 2 and a plurality of wing arm supports 3, wherein the plurality of rotor arms 2 are symmetrically arranged and horizontally arranged on the periphery of the central casing 1, the end part of each rotor arm 2 far away from the central casing 1 is provided with a motor mounting shell 4, a rotating motor 5 with an output shaft arranged downwards is mounted in each motor mounting shell 4, the output shaft of each rotating motor 5 is connected with a horizontally arranged propeller 6, the plurality of wing arm supports 3 are symmetrically designed relative to the rotorcraft, two ends of each wing arm support 3 are connected between two adjacent motor mounting shells 4, the upper surface of each wing arm support 3 is provided with a reconstruction device 7 which is butted with the bottom of the fixed-wing aircraft and has an automatic locking function after the butting is completed, and the upper surface of each wing arm support 3 is further provided with a camera 8, a power source 9 and a control module 10 are arranged in the central case 1, and when the rotor aircraft is close to the fixed-wing aircraft, the camera 8 is used for shooting and identifying the wing position of the fixed-wing aircraft in real time.
In this embodiment, the central casing 1 is a square casing, four corners of the central casing are all set to be circular arc-shaped, four groups of the rotor arms 2, the rotating electrical machine 5 and the propellers 6 are provided (in other embodiments, six or eight groups are also provided), two and parallel side wing arm supports 3 are provided, and the four rotor arms 2 are connected to the four circular arc-shaped corners of the central casing 1. The rotor craft of the design is simpler in structure and lighter in self weight.
Adopt rotating electrical machines 5+ screw 6 to provide lift for rotor craft, lift should can satisfy the demand that rotor craft and fixed wing aircraft combination VTOL, and flight time should satisfy twice combination aircraft at least and can VTOL.
The camera 8 is high-definition optical camera lens specifically, and when the rotor craft is close to the fixed wing craft through GPS guide relative distance, camera lens is used for shooting and identifying the fixed wing craft in real time, and calculates the relative position by the control system, and accurate relative position measurement and calculation are realized.
The matched vertical take-off and landing process of the rotor aircraft and the fixed-wing aircraft is approximately as follows:
s1, enabling the fixed wing aircraft and the rotor aircraft to vertically take off to a preset safe take-off height in a combined mode by means of the rotor aircraft; s2, activating the flight control of the fixed-wing aircraft, starting a power system, and enabling the fixed-wing aircraft and the rotary-wing aircraft to fly forwards in a combined mode; s3, when the forward flying speed reaches the takeoff speed of the fixed-wing aircraft, the combined body is divided into the fixed-wing aircraft and the rotor aircraft, the fixed-wing aircraft executes the flying task according to the preset air route, and the rotor aircraft lands until the fixed-wing aircraft is appointed to land; s4, the fixed wing aircraft sends a return command to the ground control station after completing a flight task, the ground control station activates the rotary wing aircraft after receiving the command, starts a power system of the rotary wing aircraft, flies to the vicinity of a preset landing route of the fixed wing, and performs coarse alignment by means of navigation information such as a GPS (global positioning system); s5, when the relative distance between the fixed wing aircraft and the rotor aircraft reaches a certain value, fine alignment is carried out by means of computer vision positioning, electronic information positioning and the like; and S6, after the fine alignment is finished, locking the docking device on the wing of the fixed-wing aircraft by the reconstruction device 7 on the rotor aircraft, reconstructing the fixed-wing aircraft into a combined aircraft, and landing the combined aircraft to the designated landing area.
The implementation principle of the rotor aircraft for assisting the vertical take-off and landing of the fixed-wing aircraft in the embodiment of the application is as follows: the advantages of vertical take-off and landing and hovering of the rotor aircraft are utilized, the mode that the rotor aircraft and the fixed-wing aircraft are split and reconstructed in the air is adopted, the convenient vertical take-off and landing requirement of the fixed-wing aircraft is met, meanwhile, the self weight of the fixed-wing aircraft during cruise can be greatly reduced, the original efficient cruise and heavy load advantages are brought into play, and the rotary-wing aircraft has important military and civil application prospects.
In the embodiment of the application, the side wing arm support 3 and the motor mounting shell 4 are integrally formed, so that the side wing arm support 3 and the motor mounting shell 4 are higher in connection firmness and better in integrity.
In the embodiment of the application, movable assembly between tip and the motor installation shell 4 of rotor arm 2, rotor arm 2's length can freely be adjusted, and then can carry out corresponding adjustment according to the model size of the fixed wing aircraft of supplementary take-off and landing, and adaptability is better.
In the embodiment of the application, the inside cavity design of rotor arm 2, the both ends of rotor arm 2 communicate respectively to the inside of flank cantilever crane 3 and the inside of central machine box 1, and the inside cavity of rotor arm 2 is used for walking the line, and then the cable can not appear in this rotor craft's surface, and this kind of hidden design of cable is more reasonable, is favorable to this rotor craft to fly in the air.
In the embodiment of the application, the main body of the rotorcraft is made of a light high-strength material, the light high-strength material comprises but is not limited to glass fiber or carbon fiber, the main body of the rotorcraft comprises but is not limited to a central case 1, a rotor arm 2, a wing arm support 3 and a propeller 6, when the rotorcraft is ensured to have good structural firmness, the self weight of the rotorcraft can be greatly reduced, and the advantages of efficient cruising and heavy load can be further brought into play.
In the embodiment of the present application, the reconfiguration device 7 includes two docking guide rails 71 and a locking connector 72, the two docking guide rails 71 are all arranged along the length direction of the wing arm support 3 and are parallel to each other, the locking connector 72 is disposed at one end of the docking guide rails 71 and is used for docking wings of the fixed-wing aircraft, the reconfiguration device 7 of the above structural design is convenient to dock and lock with the wings of the fixed-wing aircraft, docking and locking technologies are performed on the wings of the fixed-wing aircraft, docking reconfiguration technologies in the field of space satellites can be referred to, because the technologies are relatively common and can be traced, in this embodiment, more detailed description is not performed on the reconfiguration device 7.
In the embodiment of the application, 3 cameras 8 (the number can be 2 or 4 in other embodiments) are arranged on each side wing arm support 3, the multiple cameras 8 are evenly arranged at intervals along the length direction of the butt joint guide rails 71, the multiple cameras 8 are located between the two butt joint guide rails 71, and the designed cameras 8 are beneficial to shooting and identifying the wing positions of the fixed-wing aircraft in real time and are more beneficial to accurate butt joint reconstruction between the fixed-wing aircraft and the rotor aircraft.
In the embodiment of the application, control module 10 installs the central point department of putting in central machine box 1, and power supply 9 is provided with the multiunit and winds the even symmetrical arrangement of control module 10, and power supply 9 is lithium cell or oil-electricity hybrid power source, and more power supply 9 are loaded as far as possible in the above-mentioned symmetrical formula design, and central machine box 1's focus is close to central point more moreover and is favorable to this rotor craft to fly steadily.
The present invention is not intended to be limited to the particular embodiments shown and described, but is to be accorded the widest scope consistent with the principles and novel features herein disclosed.
Claims (10)
1. A rotor craft for assisting in vertical take-off and landing of a fixed-wing craft, characterized in that: the aircraft comprises a central machine box (1), a plurality of rotor arms (2) and a plurality of wing arm frames (3), wherein the rotor arms (2) are symmetrically arranged and horizontally arranged on the peripheral side of the central machine box (1), the end part of the rotor arms (2) far away from the central machine box (1) is provided with a motor installation shell (4), a rotating motor (5) with an output shaft arranged downwards is installed in the motor installation shell (4), the output shaft of the rotating motor (5) is connected with a horizontally arranged propeller (6), the plurality of wing arm frames (3) are symmetrically designed relative to the rotor aircraft, two ends of the wing arm frames (3) are connected between two adjacent motor installation shells (4), the upper surface of each wing arm frame (3) is provided with a reconstruction device (7) which is butted with the bottom of a fixed wing aircraft and has an automatic locking function after the butt joint is completed, the upper surface of the flank arm support (3) is further provided with a camera (8), a power source (9) and a control module (10) are arranged in the central case (1), and when the rotor aircraft is close to the fixed-wing aircraft, the camera (8) is used for shooting and identifying the wing position of the fixed-wing aircraft in real time.
2. A rotary-wing aircraft for assisting in the vertical takeoff and landing of a fixed-wing aircraft according to claim 1, wherein: the rotary wing arms (2), the rotating motor (5) and the propellers (6) are provided with four groups, six groups or eight groups, and the side wing arm supports (3) are provided with two groups and arranged in parallel.
3. A rotary-wing aircraft for assisting in the vertical takeoff and landing of a fixed-wing aircraft according to claim 1, wherein: the side wing arm support (3) and the motor mounting shell (4) are integrally formed.
4. A rotary-wing aircraft for assisting in the vertical takeoff and landing of a fixed-wing aircraft according to claim 3, wherein: the end part of the rotor arm (2) is movably assembled with the motor mounting shell (4), and the length of the rotor arm (2) can be freely adjusted.
5. A rotary-wing aircraft for assisting in the vertical takeoff and landing of a fixed-wing aircraft according to claim 3, wherein: the rotor arm (2) is hollow, two ends of the rotor arm (2) are respectively communicated to the inside of the side wing arm support (3) and the inside of the central case (1), and an inner cavity of the rotor arm (2) is used for wiring.
6. A rotary-wing aircraft for assisting in the vertical takeoff and landing of a fixed-wing aircraft according to claim 1, wherein: the main body of the rotorcraft is made of light high-strength materials including but not limited to glass fibers or carbon fibers, and the main body of the rotorcraft includes but not limited to the central case (1), the rotor arms (2), the side wing arm supports (3) and the propellers (6).
7. A rotary-wing aircraft for assisting in the vertical takeoff and landing of a fixed-wing aircraft according to claim 1, wherein: the reconfiguration device (7) comprises two butt joint guide rails (71) and a locking connector (72), wherein the butt joint guide rails (71) are arranged along the length direction of the wing arm support (3) and are parallel to each other, and the locking connector (72) is arranged at one end of the butt joint guide rails (71) and is used for butt joint of wings of a fixed-wing aircraft.
8. A rotary-wing aircraft for assisting in the vertical takeoff and landing of a fixed-wing aircraft according to claim 7, wherein: the number of the cameras (8) on each side wing arm support (3) is 2-4, the cameras (8) are uniformly arranged at intervals along the length direction of the butt joint guide rails (71), and the cameras (8) are located between the two butt joint guide rails (71).
9. A rotary-wing aircraft for assisting in the vertical takeoff and landing of a fixed-wing aircraft according to claim 1, wherein: the control module (10) is installed at the central position in the central case (1), and the power source (9) is provided with a plurality of groups which are uniformly and symmetrically arranged around the control module (10).
10. A rotary-wing aircraft for assisting in the vertical takeoff and landing of a fixed-wing aircraft according to claim 1, wherein: the power source (9) is a lithium battery or an oil-electricity hybrid power source.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111450056.3A CN114248915A (en) | 2021-12-01 | 2021-12-01 | Rotor aircraft for assisting vertical take-off and landing of fixed-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111450056.3A CN114248915A (en) | 2021-12-01 | 2021-12-01 | Rotor aircraft for assisting vertical take-off and landing of fixed-wing aircraft |
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| Publication Number | Publication Date |
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| CN114248915A true CN114248915A (en) | 2022-03-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111450056.3A Pending CN114248915A (en) | 2021-12-01 | 2021-12-01 | Rotor aircraft for assisting vertical take-off and landing of fixed-wing aircraft |
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Citations (7)
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| CN106904281A (en) * | 2017-03-10 | 2017-06-30 | 佛山市神风航空科技有限公司 | One kind combination aircraft and its landing mode |
| CN106915451A (en) * | 2017-03-10 | 2017-07-04 | 佛山市神风航空科技有限公司 | A kind of composite aircraft and its landing mode |
| US20170274997A1 (en) * | 2016-03-22 | 2017-09-28 | Hood Technology Corporation | Rotorcraft-assisted system and method for launching and retrieving a fixed-wing aircraft into and from free flight |
| CN109502018A (en) * | 2018-12-27 | 2019-03-22 | 湖北航天飞行器研究所 | A kind of Combined unmanned aircraft |
| CN208731225U (en) * | 2018-08-16 | 2019-04-12 | 上海重塑能源科技有限公司 | Take-off system |
| US20190329886A1 (en) * | 2016-12-13 | 2019-10-31 | Ryan Evaristo Pinto | System and method for capturing and releasing fixed-wing aircraft |
| CN112722284A (en) * | 2021-01-15 | 2021-04-30 | 南京航空航天大学 | Auxiliary vertical take-off and landing method and device for fixed-wing aircraft |
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2021
- 2021-12-01 CN CN202111450056.3A patent/CN114248915A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170274997A1 (en) * | 2016-03-22 | 2017-09-28 | Hood Technology Corporation | Rotorcraft-assisted system and method for launching and retrieving a fixed-wing aircraft into and from free flight |
| US20190329886A1 (en) * | 2016-12-13 | 2019-10-31 | Ryan Evaristo Pinto | System and method for capturing and releasing fixed-wing aircraft |
| CN106904281A (en) * | 2017-03-10 | 2017-06-30 | 佛山市神风航空科技有限公司 | One kind combination aircraft and its landing mode |
| CN106915451A (en) * | 2017-03-10 | 2017-07-04 | 佛山市神风航空科技有限公司 | A kind of composite aircraft and its landing mode |
| CN208731225U (en) * | 2018-08-16 | 2019-04-12 | 上海重塑能源科技有限公司 | Take-off system |
| CN109502018A (en) * | 2018-12-27 | 2019-03-22 | 湖北航天飞行器研究所 | A kind of Combined unmanned aircraft |
| CN112722284A (en) * | 2021-01-15 | 2021-04-30 | 南京航空航天大学 | Auxiliary vertical take-off and landing method and device for fixed-wing aircraft |
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