CN221367511U - Split type wing tip chain wing aerial combination unmanned aerial vehicle - Google Patents
Split type wing tip chain wing aerial combination unmanned aerial vehicle Download PDFInfo
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- CN221367511U CN221367511U CN202323067786.2U CN202323067786U CN221367511U CN 221367511 U CN221367511 U CN 221367511U CN 202323067786 U CN202323067786 U CN 202323067786U CN 221367511 U CN221367511 U CN 221367511U
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- 238000003032 molecular docking Methods 0.000 claims abstract description 24
- 210000001503 joint Anatomy 0.000 claims abstract description 3
- 239000000178 monomer Substances 0.000 abstract description 7
- 238000004891 communication Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000009966 trimming Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
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Abstract
The utility model provides a split wing tip chain wing aerial combined unmanned aerial vehicle which comprises a wing tip aerial butt joint device, a main wing module, a nacelle type fuselage, a pluggable tail wing module, a tail wing rotary actuator, an auxiliary solar cell module, a main battery pack and an additional battery pack. The utility model provides a split-type wing tip chain wing aerial combined unmanned aerial vehicle, which has smaller monomer size, is convenient for scattered take-off and landing, combines a plurality of monomers in flight through a wing tip aerial docking device, and changes the aerodynamic characteristics and effective load of the unmanned aerial vehicle combination, so that the unmanned aerial vehicle combination can have the flight performance of a high-altitude long-endurance unmanned aerial vehicle.
Description
Technical Field
The utility model belongs to the technical field of aircraft design, and particularly relates to a split wing tip chain wing air combined unmanned aerial vehicle.
Background
The unmanned aerial vehicle can realize long-distance, large-range, all-day and all-weather reconnaissance, and is more and more widely used in the fields of information collection, ground striking and the like.
In order to ensure the long endurance capacity of the unmanned aerial vehicle, the existing unmanned aerial vehicle has huge body and a span of over 40m, so that the unmanned aerial vehicle has the problems of inconvenient taking off and landing, weak wind resistance and the like.
Disclosure of utility model
Aiming at the defects in the prior art, the utility model provides a split type wing tip chain wing aerial combined unmanned aerial vehicle which can effectively solve the problems.
The technical scheme adopted by the utility model is as follows:
the utility model provides a split wing tip chain wing air combined unmanned aerial vehicle, which comprises a wing tip air butt joint device (1), a main wing module (2), a nacelle type fuselage (3), a pluggable tail wing module (4), a tail wing rotary actuator (5), an auxiliary solar cell module (6), a main battery pack (7) and an additional battery pack (8);
The main wing modules (2) are symmetrically inserted into two sides of the nacelle type machine body (3) in a left-right mode;
The tail wing rotary actuator (5) is arranged at the tail part of the nacelle type fuselage (3), the front end of the pluggable tail wing module (4) is connected with the tail wing rotary actuator (5), and the pluggable tail wing module (4) is driven to rotate through the tail wing rotary actuator (5);
the wing tip aerial docking device (1) is arranged at the tail end of the main wing module (2);
-said main battery (7) and said additional battery (8) being distributed inside said main wing module (2);
The auxiliary solar cell module (6) comprises an on-wing solar cell panel and a power manager; the solar cell panel on the wing is laid on the upper surface of the main wing module (2), and the power manager is installed in the nacelle type fuselage (3).
Preferably, the inner wing section and the outer wing section of the main wing module (2) adopt different wing sections.
Preferably, a trailing edge control surface (2-1) is provided on the rear side of the main wing module (2).
Preferably, the main battery (7) is not detachable from the inside of the main wing module (2); the additional battery (8) is detachable from the inside of the main wing module (2).
Preferably, the additional battery (8) is arranged in the main wing module (2) close to the wing root.
The split wing tip chain wing air combined unmanned aerial vehicle provided by the utility model has the following advantages:
The utility model provides a split-type wing tip chain wing aerial combined unmanned aerial vehicle, which has smaller monomer size, is convenient for scattered take-off and landing, combines a plurality of monomers in flight through a wing tip aerial docking device, and changes the aerodynamic characteristics and effective load of the unmanned aerial vehicle combination, so that the unmanned aerial vehicle combination can have the flight performance of a high-altitude long-endurance unmanned aerial vehicle.
Drawings
Fig. 1 is a state change diagram of a split wing tip chain wing air combined unmanned aerial vehicle provided by the utility model;
Fig. 2 is a perspective view of the split wing tip chain wing air combined unmanned aerial vehicle provided by the utility model;
FIG. 3 is a top view of a split wing tip link wing air-borne unmanned aerial vehicle provided by the present utility model;
FIG. 4 is a bottom view of the split wing tip chain wing air-borne unmanned aerial vehicle provided by the present utility model;
FIG. 5 is a side view of the split wing tip chain wing air-borne unmanned aerial vehicle provided by the present utility model;
FIG. 6 is an enlarged view of a portion of the wing tip aerial docking device provided by the present utility model at an angle;
FIG. 7 is an enlarged view of a portion of the wing tip aerial docking device provided by the present utility model at another angle;
FIG. 8 is a schematic view of a wing tip aerial docking device provided by the present utility model;
FIG. 9 is an assembly view of a pluggable tail module and tail rotary actuator of the wing tip air docking device provided by the present utility model;
Fig. 10 is an enlarged view of the tail rotary actuator of fig. 9.
Detailed Description
In order to make the technical problems, technical schemes and beneficial effects solved by the utility model more clear, the utility model 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 for purposes of illustration only and are not intended to limit the scope of the utility model.
The utility model provides a split-type wing tip chain wing aerial combined unmanned aerial vehicle, which has smaller monomer size, is convenient for scattered take-off and landing, combines a plurality of monomers in flight through a wing tip aerial docking device, and changes the aerodynamic characteristics and effective load of the unmanned aerial vehicle combination, so that the unmanned aerial vehicle combination can have the flight performance of a high-altitude long-endurance unmanned aerial vehicle.
Referring to fig. 1-10, the utility model provides a split wing tip chain wing aerial combined unmanned aerial vehicle, which comprises a wing tip aerial docking device 1, a main wing module 2, a nacelle type fuselage 3, a pluggable tail wing module 4, a tail wing rotary actuator 5, an auxiliary solar cell module 6, a main battery pack 7 and an additional battery pack 8;
The nacelle type fuselage 3 is mainly used for bearing a power device and a tail wing rotary actuator 5, is used for connecting a left main wing module 2, a right main wing module 2, a belly modularized load cabin and a pluggable tail wing module 4 through the tail wing rotary actuator 5, is formed by integrally adopting a low-resistance streamline body to twist a string, and has small resistance;
The main wing module 2 is a main module for providing lift force and basic control moment, can independently bear the flight of the nacelle type fuselage, and is inserted into the two sides of the nacelle type fuselage 3 in a bilateral symmetry manner; the inner wing section and the outer wing section of the main wing module 2 adopt different wing sections to balance the pitching moment generated by the main wing module, so that the total longitudinal rolling moment is zero, and the flying without tail layout is facilitated. The rear side of the main wing module 2 is provided with a rear edge control surface 2-1, and as a specific structure, the rear edge control surface 2-1 can be respectively arranged on the upper surface and the lower surface of each main wing module 2, therefore, an unmanned plane is provided with four rear edge control surfaces, the rear edge control surfaces can be independently controlled, and the four rear edge control surfaces can realize the functions of a conventional aircraft aileron, a flap, an elevator and a rudder by mixed deflection, and provide all control moments required by maintaining flight; the main wing module 2 adopts a distributed load arrangement mode, and most avionics loads including power battery packs are distributed and installed in the main wing module 2.
The tail wing rotary actuator 5 is arranged at the tail part of the nacelle type fuselage 3 and is integrally manufactured with the nacelle type fuselage 3; the front end of the pluggable tail module 4 is connected with a tail rotary actuator 5, and the pluggable tail module 4 is driven to rotate through the tail rotary actuator 5; specifically, the pluggable tail module 4 mainly comprises a tail stay bar and a full-motion tail, and forms a rotary tail system together with the tail rotary actuator 5. The pluggable tail wing module 4 is connected with the nacelle type fuselage 3 in a pluggable manner, in addition, the pluggable tail wing module 4 can rotate under the drive of the tail wing rotary actuator 5 and can also be locked through a locking ring to serve as a conventional tail wing which does not rotate. Thus, when the nacelle fuselage 3 is fitted with a pluggable tail module 4, if it is rotatable, a rotary tail module is constituted, if it is locked against rotation, a conventional tail module is constituted; when the nacelle type fuselage 3 is not assembled with the pluggable tail wing module 4, the unmanned aerial vehicle is used as a tailless unmanned aerial vehicle, and can be flexibly replaced according to the requirement. The wing tip aerial docking device 1 is arranged at the tail end of the main wing module 2; the wing tip aerial docking device 1 is used for realizing connection and fixation of two main wing modules 2 in the air, and is shown in fig. 6 to 8, and is a structure diagram of a specific wing tip aerial docking device, and it is emphasized that the specific structure of the adopted wing tip aerial docking device is not limited, and various structures can be flexibly adopted, for example, the wing tip aerial docking device comprises a rectification guide plate, a rectification guide plate retracting mechanism and a locking mechanism, and the rectification guide plate can be unfolded by the rectification guide plate retracting mechanism during docking, so that pneumatic stability is provided for mechanical alignment and two approaching machines during docking; the locking mechanism locks the two machines to each other after alignment and provides about 15 degrees of freedom of roll for the two machines when flown in the docked state. Therefore, the rectification guide plate needs to be unfolded to carry out pneumatic rectification and mechanical alignment before docking, and the rectification guide plate is retracted after docking, so that the docking device is locked.
A main battery 7 and an additional battery 8, forming a power battery, distributed inside the main wing module 2; wherein the main battery 7 is not detachable from the inside of the main wing module 2; the additional battery pack 8 is detachable from the inside of the main wing module 2, and can be detached and optionally installed as required. For example, the main battery pack 7 and the additional battery packs 8 are arranged in a distributed arrangement manner at a position in front of a main wing beam in the main wing module 2, and the additional battery packs 8 are arranged in the main wing module 2 at a position close to a wing root, so that the insertion and the extraction are convenient.
The auxiliary solar cell module 6 comprises an on-wing solar cell panel and a power manager; the solar cell panel on the wing is laid on the upper surface of the main wing module 2, and the power manager is arranged in the nacelle type machine body 3 and used for controlling the solar cell panel on the wing and automatically charging the power battery pack with redundant electric energy on the premise of meeting the power requirement of an electric appliance.
The utility model provides a split wing tip chain wing air combined unmanned aerial vehicle, which has the following characteristics:
The wing tip chain wing type aerial docking mode is used for realizing the capability of reconstructing aerial layout, the mode allows the same unmanned aerial vehicle with multiple frames to freely dock and separate in the flying process by using the wing tip aerial docking device, so that the lift resistance characteristic of an unmanned aerial vehicle combination formed by the multiple frames of unmanned aerial vehicles is improved along with the increase of the number of combinations, and the effective load can be changed by the combination and replacement among the unmanned aerial vehicle monomers, thereby changing the functions of the combination;
The system comprises a pluggable tail wing module and a tail wing rotary actuator, wherein the pluggable tail wing module consists of a carbon fiber tail stay bar and a symmetrical full-motion control surface, the carbon fiber tail stay bar is arranged on the tail wing rotary actuator and can be driven by the carbon fiber tail stay bar to perform 360-degree controllable rotation, the pitching and yaw stability of a horizontal stabilizer and a vertical stabilizer in a conventional tail wing are synthesized through the rotary motion of the pluggable tail wing module and the deflection motion of the full-motion control surface, and the pitching and yaw control moment of an elevator and a rudder in the conventional horizontal tail wing are synthesized, so that the unmanned aerial vehicle is endowed with sufficient stability and operability by the smaller pneumatic control surface relative to the conventional tail wing;
The design of ground reconfigurable layout is also adopted on the basis of realizing the reconstruction of the aerial layout in an aerial docking mode, and two pluggable tail modules of the aircraft can be plugged and replaced according to the requirement, so that the unmanned aircraft can carry out ground reconstruction among the rotary tail layout, the conventional layout and the tailless layout, the main wing module of the aircraft is subjected to trimming design, the additional head lifting moment is restrained, and the complete pitching, rolling and yawing control can be realized due to the mixed action of the rear edge control surface of the main wing, so that the pluggable tail modules can be removed to serve as a tailless layout aircraft to fly under the condition that the gravity center position is proper;
The working mode is as follows:
In an independent flight mode, the unmanned aerial vehicle can independently execute tasks as a small unmanned aerial vehicle;
under the combined body flight mode, all unmanned aerial vehicles participating in the combination need to be cooperatively controlled to stabilize the combined body flight attitude;
under the combined body flight mode, the combined body lift-drag ratio is gradually increased along with the combined quantity, the cruising energy consumption is gradually reduced, the power management module carries out MPPT control on the solar cell module to share the output power of the battery until the cruising energy consumption is reduced until the output power of the auxiliary solar cell module is larger than the cruising required power, at the moment, the combined body enters a solar power flight mode, and the redundant energy carries out balanced charging on the power battery pack under the control of the power management module to maintain the continuous flight of the combined body. Therefore, a long-endurance is realized by adopting a power supply mode of combining solar energy and a battery.
The utility model provides a split type wing tip chain wing air combined unmanned aerial vehicle, which is an unmanned aerial vehicle with variable lift limit and maneuverability, can achieve the flight performance of a solar high-altitude unmanned aerial vehicle, and solves the problems existing in the traditional unmanned aerial vehicle by utilizing an air docking technology. The raising limit of the communication relay platform is expanded from low altitude to high altitude or even high altitude, the endurance is expanded from about 50min to semi-permanent remaining, and the communication relay platform can provide flexible communication relay service for any position, so that the communication relay platform has the advantages of meeting requirements, and has larger use value and application potential in the civil and military fields.
The foregoing is merely a preferred embodiment of the present utility model and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present utility model, which is also intended to be covered by the present utility model.
Claims (5)
1. The split wing tip chain wing aerial combined unmanned aerial vehicle is characterized by comprising a wing tip aerial butt joint device (1), a main wing module (2), a nacelle type fuselage (3), a pluggable tail wing module (4), a tail wing rotary actuator (5), an auxiliary solar cell module (6), a main battery pack (7) and an additional battery pack (8);
The main wing modules (2) are symmetrically inserted into two sides of the nacelle type machine body (3) in a left-right mode;
The tail wing rotary actuator (5) is arranged at the tail part of the nacelle type fuselage (3), the front end of the pluggable tail wing module (4) is connected with the tail wing rotary actuator (5), and the pluggable tail wing module (4) is driven to rotate through the tail wing rotary actuator (5);
the wing tip aerial docking device (1) is arranged at the tail end of the main wing module (2);
-said main battery (7) and said additional battery (8) being distributed inside said main wing module (2);
The auxiliary solar cell module (6) comprises an on-wing solar cell panel and a power manager; the solar cell panel on the wing is laid on the upper surface of the main wing module (2), and the power manager is installed in the nacelle type fuselage (3).
2. A split wing tip link wing air-borne unmanned aerial vehicle according to claim 1, wherein the inner wing section and the outer wing section of the main wing module (2) adopt different wing profiles.
3. A split wing tip link wing air-borne unmanned aerial vehicle according to claim 1, wherein the rear side of the main wing module (2) is provided with a trailing edge control surface (2-1).
4. A split wing tip link wing air-borne unmanned aerial vehicle according to claim 1, wherein the main battery (7) is not detachable from the inside of the main wing module (2); the additional battery (8) is detachable from the inside of the main wing module (2).
5. A split wing tip link wing air-borne unmanned aerial vehicle according to claim 1, wherein the additional battery (8) is arranged within the main wing module (2) close to the wing root.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323067786.2U CN221367511U (en) | 2023-11-14 | 2023-11-14 | Split type wing tip chain wing aerial combination unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323067786.2U CN221367511U (en) | 2023-11-14 | 2023-11-14 | Split type wing tip chain wing aerial combination unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221367511U true CN221367511U (en) | 2024-07-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323067786.2U Active CN221367511U (en) | 2023-11-14 | 2023-11-14 | Split type wing tip chain wing aerial combination unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN221367511U (en) |
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2023
- 2023-11-14 CN CN202323067786.2U patent/CN221367511U/en active Active
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