CN117104549A - Unmanned aerial vehicle with cruise fixed wing - Google Patents
Unmanned aerial vehicle with cruise fixed wing Download PDFInfo
- Publication number
- CN117104549A CN117104549A CN202311333725.8A CN202311333725A CN117104549A CN 117104549 A CN117104549 A CN 117104549A CN 202311333725 A CN202311333725 A CN 202311333725A CN 117104549 A CN117104549 A CN 117104549A
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- Prior art keywords
- wing
- aerial vehicle
- unmanned aerial
- rudder
- machine body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 14
- 238000007689 inspection Methods 0.000 claims description 6
- 210000001015 abdomen Anatomy 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims description 2
- 230000005540 biological transmission Effects 0.000 claims 1
- 238000005096 rolling process Methods 0.000 abstract description 4
- 230000007547 defect Effects 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 5
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/50—Foldable or collapsible UAVs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
- B64U30/16—Variable or detachable wings, e.g. wings with adjustable sweep movable along the UAV body
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U40/00—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration
- B64U40/20—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration for in-flight adjustment of the base configuration
Abstract
The invention discloses a flight-patrol fixed wing unmanned aerial vehicle, which belongs to the technical field of aircrafts, wherein a rudder wing similar to a strake wing is arranged on a nose, the diameter of the rudder wing is slightly smaller than the external dimension constraint of a machine body, the rudder wing can be placed into a transmitting cylinder without folding, and the rudder wing is controlled to axially rotate along the machine body by a miniature servo motor; an X-shaped wing is arranged in the middle of the machine body, can be folded and stored backwards, is automatically unfolded after being ejected out of a cylinder by adopting a torsion spring, and is prevented from being folded forwards by a stop block after reaching a preset position, and a bolt ejects out of the locking wing; the heading, pitching and rolling of the aircraft are controlled by rotating rudder wings of the aircraft nose, so that flexible maneuvering can be realized.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a fly-inspection fixed wing unmanned aerial vehicle.
Background
The cruise fixed wing unmanned aerial vehicle is used as a traditional fixed wing flight carrier, and generates lift force by virtue of wings, so that the time for leaving the aircraft is long; the intelligent ammunition can be used for air patrol, reconnaissance monitoring and carrying explosive load as intelligent ammunition for accurate guidance, and meets the requirements of informationized battlefield.
Through development, the current unmanned aerial vehicle mainly comprises a fixed wing type, a folding wing type and a multi-rotor wing type; the fixed wing type unmanned aerial vehicle for patrol flight has three kinds: the first wing is not foldable and detachable, and has the defects of large volume, inconvenient carrying and barreled emission; the second wing is foldable, and has the defects of volume and weight brought by the tilting mechanism and the control surface; the third wing can be disassembled, and has the defects of incapability of being deployed immediately, disassembly and assembly before launching, long deployment time, complex operation and untimely response; the folding wing type unmanned aerial vehicle has the defects that the volume and the weight are brought by a tilting mechanism and a control surface; the multi-rotor type unmanned aerial vehicle for patrol flight has the defect of short endurance time, and indirectly causes the problem of short patrol flight distance; such as: the single-soldier hand-thrown type fly-round projectile (publication No. CN109323633A, 2019.02.12) with conventional fixed wing is adopted as lifting surface, and has reliable structure, high cruising speed, long time, limited volume, inconvenient carrying and lifting; a tandem individual patrol projectile (publication number CN115610653A, application date 2023.01.17) capable of being quickly assembled and disassembled provides a scheme for quickly assembling and disassembling front and rear wings and a vertical tail wing, wherein the scheme can take off only by manually installing the front and rear wings and the vertical tail wing before taking off, and cannot take off quickly and autonomously; a multi-rotor patrol projectile (publication number CN111056015a, application date 2020.04.24) proposes a rotor scheme in which an operator operates a rotor to perform a task in a target area after manually expanding a horn; the scheme takes off and land without being limited by terrain, can hover at fixed points, but has the defect of short endurance time of multiple rotors, and indirectly causes the problem of short cruising distance.
Disclosure of Invention
The invention provides a fly-patrol fixed-wing unmanned aerial vehicle, which controls the course, pitch and roll of an airplane through rotating rudder wings of a nose, and can achieve flexible maneuvering.
In order to achieve the above purpose, the invention adopts the following technical scheme:
the unmanned aerial vehicle with the fixed wing for patrol flight is characterized in that a rudder wing similar to a strake wing is arranged on a nose, the diameter of the rudder wing is slightly smaller than the external dimension constraint of a machine body, the rudder wing can be placed into a transmitting cylinder without folding, and the rudder wing is controlled by a miniature servo motor to rotate along the axial direction of the machine body; an X-shaped wing is arranged in the middle of the machine body, can be folded and stored backwards, is automatically unfolded after being ejected out of a cylinder by adopting a torsion spring, and is prevented from being folded forwards by a stop block after reaching a preset position, and a bolt ejects out of the locking wing;
the flight control and the data chain are arranged at the front end of the machine body, the rear part of the servo motor is arranged at the rear part of the machine body, a hatch is formed in the lower part of the front part and the rear part of the machine body, a load can be installed according to task requirements, a battery is positioned at the rear part of the machine body, quick replacement is realized through a battery cabin cover, a propeller is installed at the tail part of the machine body, a tail pushing force is adopted, and the propeller can be folded and stored forwards.
The beneficial effects are that: the invention provides a fly-patrol fixed wing unmanned aerial vehicle, which is flexible and mobile by designing a rotary rudder to control heading, pitching and rolling, eliminates a traditional vertical tail wing and a traditional horizontal tail wing, and has no control surface, so that the volume and the weight brought by a tail wing tilting mechanism and a control surface can be greatly reduced, and the requirement of enveloping appearance is met; the X-shaped wing can be folded, retracted and released, and is convenient to carry, transport and take off in a cylindrical manner; compared with a rotor wing type unmanned aerial vehicle for patrol flight, the unmanned aerial vehicle has the advantages of high flight speed, long endurance time and smaller envelope outline dimension.
Drawings
Fig. 1 is a schematic development diagram of a drone in an embodiment of the present invention;
fig. 2 is a schematic view of an expanded cross-section of a drone in an embodiment of the present invention;
FIG. 3 is a schematic view of a three-dimensional view of a drone in an embodiment of the present invention;
fig. 4 is a schematic view of a rudder wing skin of the unmanned aerial vehicle according to an embodiment of the present invention;
fig. 5 is a schematic view of the inside of a rudder wing of the unmanned aerial vehicle according to the embodiment of the invention;
FIG. 6 is a schematic view of a wing unfolding and folding mechanism of the unmanned aerial vehicle in an embodiment of the invention;
fig. 7 is a front view of an embodiment of the present invention in a deployed stage of the drone;
FIG. 8 is a side view of an embodiment of the present invention in a deployed stage of a drone;
fig. 9 is a top view of a drone deployment phase in an embodiment of the present invention;
fig. 10 is a bottom view of the drone in an embodiment of the present invention at a deployment stage;
FIG. 11 is an isometric view of a drone deployment stage in an embodiment of the present invention; the method comprises the steps of carrying out a first treatment on the surface of the
Fig. 12 is a front view of the unmanned aerial vehicle in a folded stowing stage in an embodiment of the present invention;
fig. 13 is a side view of the unmanned aerial vehicle in a folded stowing stage in an embodiment of the present invention;
fig. 14 is a top view of a folding stage of the drone in an embodiment of the present invention;
fig. 15 is a bottom view of the folding stage of the drone in an embodiment of the present invention;
the device comprises a 1-rudder wing, a 2-fuselage, a 3-wing, a 4-battery hatch cover, a 5-motor, a 6-propeller fixing seat, a 7-propeller, an 8-battery, a 9-GPS antenna, a 10-data chain antenna, an 11-load, a 12-data chain and a 13-flight control; 101-rudder wing shell fixing seats, 102-servo motors, 103-servo motor fixing seats and 104-rudder wing shells; 301-wing fixing seat, 302-torsion spring, 303-screw and 304-spring plunger pin.
Detailed Description
The invention is described in detail below with reference to the attached drawings and the specific embodiments:
as shown in fig. 1-6, a cruise fixed wing unmanned aerial vehicle comprises rudder wings 1, a fuselage 2, a wing system and a power system;
the rudder wing comprises a rudder wing shell 104, a servo motor 102, a rudder wing shell fixing seat 101 and a servo motor seat 103; the rudder wing shell 1 is provided with a pair of winglets on the surface, the direction of the nose deviation of the winglets can be adjusted by autorotation control lifting force during flight, and the wingspan of each winglet is slightly smaller than the diameter of the fuselage; as shown in fig. 4, in order to fit the winglet to the fuselage, a streamlined transition zone is designed at the junction of the winglet and the fuselage; in order to connect the rudder wing housing 104 with the servo motor 102, a rudder wing housing holder 101 is arranged in the rudder wing housing 104; the servo motor seat 103 is arranged at the front end of the machine body 2 and is fixedly connected with the servo motor 102, so that the rudder wing shell 104, the rudder wing shell fixing seat 101, the servo motor 102, the servo motor seat 103 and the machine body 2 are connected with each other;
the fuselage 2 comprises a fuselage shell 201, a battery hatch 4, a battery 8, a GPS antenna 9, a data link antenna 10, a load 11, a data link 12 and a flight control 13; the data link 12 and the flight control 13 are arranged at the front end in the fuselage shell 201, the load 11 is placed in a load cabin behind the data link 12 and the flight control 13, and the load 11 is placed in a load hatch below the fuselage; the rear end of the surface of the fuselage shell 201 is provided with a sinking area for wing storage; the battery 8 is arranged at the rear end in the body shell 201, and in order to facilitate the replacement of the battery 8 and the overhaul of equipment, a battery hatch 4 is arranged at the top of a rear end sinking area of the surface of the body shell 201; the GPS antenna 9 is arranged inside the body shell 201 and positioned in front of the head of the battery 8; the data link antenna 10 is arranged in front of the GPS antenna 9, and the foldable part of the data link antenna 10 is folded and accommodated below the belly of the sinking area of the machine body 2; the data chain antenna 10 is information receiving and transmitting equipment of the data chain 12; the information and the instruction of the flight control 13 are connected and exchanged with the ground station through the data link 12, and the position information obtained by the GPS antenna 9 is transmitted back to the flight control 13; the data link 12 is divided into a ground end and a sky end, the sky end is shown in the drawing, the sky end is arranged on the unmanned aerial vehicle and is used for transmitting information and instructions between a flight control 13 and a ground station on the unmanned aerial vehicle, the information and instructions are transmitted in two directions (for example, the ground station can transmit instructions to the flight control through the data link, and the flight control can feed back information to the ground station through the data link after receiving the instructions), the data link 12 is matched with the data link antenna 10 for use, and the information and instructions are transmitted through a feeder line; the flight control 13 controls the servo motor 102 to realize the take-off and landing and attitude control (such as pitching, yawing and rolling) of the unmanned aerial vehicle; the load 11 may be a device or a cartridge, which is delivered to a designated location by an unmanned aerial vehicle, in the drawings of this embodiment, the cartridge is detonated by a flight control; the battery 8 supplies power to all devices;
the wing system comprises a wing 3, a wing fixing seat 301, a torsion spring 302, a screw 303 and a spring plunger pin 304; the wing fixing seat 301 is arranged at the middle end of the fuselage, four wings 3 are respectively fixed on planes in four directions of the wing fixing seat 301 through screws 303, so that the wings 3 can be conveniently stored and unfolded; the torsion spring 302 is installed between the wing 3 and the wing fixing seat 301, and is used for controlling the wing 3 to pop up from a storage state to a unfolding state, and the spring plunger pin 304 installed on the side surface of the screw 303 can be matched with a clamping groove on the wing 3 to lock the position of the wing in the unfolding state when the wing 3 is unfolded to a proper position;
the power system comprises a power motor 5, a propeller fixing seat 6 and a propeller 7; the motor 5 is arranged at the tail end of the machine body through a motor mounting seat, and the propeller 7 is connected with the motor 5 through a propeller fixing seat 6; the propeller 7 can be folded back and forth, and is folded forward into the propeller sinking area of the body in the storage state, and is rotated and unfolded under the drive of the motor 5 in the unfolding state.
After the unmanned aerial vehicle is ejected, the X-shaped wing is changed into an unfolding state from a folding state under the drive of the tilting mechanism, the unmanned aerial vehicle is automatically unfolded after being ejected out of the cylinder by adopting the torsion spring, the X-shaped wing is prevented from being folded forwards by the stop block after reaching a preset position, and the bolt ejects out of the locking wing; the X-shaped wing provides lift force for the unmanned aerial vehicle and maintains stability of the unmanned aerial vehicle together with the rudder wing; the propeller is driven by the motor to rotate and spread, and the motor drives the propeller to provide power for the unmanned aerial vehicle; the rudder wing is controlled by the servo motor to realize heading, pitching and rolling of the unmanned aerial vehicle, so that flexible maneuvering can be realized.
The foregoing description is only a preferred embodiment of the present invention, and the present invention is not limited thereto, but it is to be understood that modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art, although the present invention has been described in detail with reference to the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The unmanned aerial vehicle with the fixed wing for the cruise flight is characterized in that a nose of the unmanned aerial vehicle is provided with a rudder wing similar to a strake wing, the diameter of the rudder wing is slightly smaller than the constraint of the outline dimension of a machine body, and the rudder wing is controlled by a miniature servo motor to rotate along the axial direction of the machine body; the wing system is arranged in the middle of the machine body, can be folded and stored backwards, is controlled by a torsion spring to be ejected out of the barrel and then automatically unfolded, and after the wing system reaches a preset position, the wing is prevented from being folded forwards by the stop block and locked.
2. The cruise control fixed wing unmanned aerial vehicle of claim 1, wherein the rudder wings comprise a rudder wing housing, a servo motor, a winglet; the rudder wing shell surface is provided with a pair of winglets which can adjust the deviation direction of the nose through autorotation control lifting force during flight, and the wingspan of each winglet is slightly smaller than the diameter of the fuselage; the servo motor is fixed in the rudder wing shell and fixedly connected with the unmanned aerial vehicle head.
3. The flying inspection fixed wing unmanned aerial vehicle of claim 2, wherein the servo motor is connected with the front end of the machine head through a servo motor fixing seat.
4. The cruise control wing drone of claim 2, wherein the winglet to rudder wing housing junction is a streamlined transition zone.
5. The flying inspection fixed wing unmanned aerial vehicle of claim 1, wherein the wing system comprises a wing, a wing mount, a torsion spring, a screw, a spring plunger pin; the wing fixing seat is arranged at the middle end of the fuselage, and four wings are respectively fixed on planes in four directions of the wing fixing seat through screws; the torsion spring is arranged between the wing and the wing fixing seat and used for controlling the wing to pop up from a storage state to a unfolding state, and the spring plunger pin arranged on the side surface of the screw can be matched with the clamping groove on the wing to lock the position of the wing in the unfolding state when the wing is unfolded to a proper position.
6. The cruise control wing unmanned aerial vehicle of claim 1 or 5, wherein the fuselage comprises a fuselage housing, a battery hatch, a battery, a GPS antenna, a data link antenna, a load, a data link, a flight control; the data chain and the flight control are arranged at the front end in the shell of the machine body, the load is placed in a load cabin behind the data chain and the flight control, and the load is placed in from a load hatch below the machine body; the rear end of the surface of the fuselage shell is provided with a sinking area for wing storage; the battery is arranged at the rear end in the body shell, and a battery cabin cover is arranged at the top of a rear end sinking area of the surface of the body shell; the GPS antenna is arranged in the shell of the machine body and positioned in front of the head of the battery; the data link antenna is arranged in front of the GPS antenna, and the foldable part of the data link antenna is folded and accommodated below the belly of the sinking area of the machine body.
7. The flying inspection fixed wing unmanned aerial vehicle according to claim 6, wherein the data chain antenna is information receiving and transmitting equipment of a data chain, information and data of the flying control are connected and exchanged with the ground station through the data chain, the flying control controls the unmanned aerial vehicle by controlling a servo motor, and information obtained by the GPS antenna is transmitted to the flying control.
8. The flying inspection fixed wing unmanned aerial vehicle of claim 7, wherein the data link is comprised of a ground end and a sky end, the sky end being mounted on the unmanned aerial vehicle, the sky end and the ground end being bi-directional transmissions.
9. The cruise control wing unmanned aerial vehicle of claim 1, wherein the unmanned aerial vehicle comprises a power system comprising a power motor, a propeller; the motor is arranged at the tail end of the machine body through a motor mounting seat; the screw is connected with the motor and is arranged at the rear of the motor.
10. The flying inspection fixed wing unmanned aerial vehicle according to claim 9, wherein the propeller can be folded back and forth, and folded forward into a propeller sinking area of the fuselage in the storage state, and unfolded rotationally under the drive of the motor 5 in the unfolded state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311333725.8A CN117104549A (en) | 2023-10-16 | 2023-10-16 | Unmanned aerial vehicle with cruise fixed wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311333725.8A CN117104549A (en) | 2023-10-16 | 2023-10-16 | Unmanned aerial vehicle with cruise fixed wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117104549A true CN117104549A (en) | 2023-11-24 |
Family
ID=88813069
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311333725.8A Pending CN117104549A (en) | 2023-10-16 | 2023-10-16 | Unmanned aerial vehicle with cruise fixed wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117104549A (en) |
-
2023
- 2023-10-16 CN CN202311333725.8A patent/CN117104549A/en active Pending
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