CN106741888B - Bionic unmanned reconnaissance helicopter - Google Patents
Bionic unmanned reconnaissance helicopter Download PDFInfo
- Publication number
- CN106741888B CN106741888B CN201710079930.4A CN201710079930A CN106741888B CN 106741888 B CN106741888 B CN 106741888B CN 201710079930 A CN201710079930 A CN 201710079930A CN 106741888 B CN106741888 B CN 106741888B
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- tail
- mechanical
- duct
- helicopter
- machine body
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/04—Power-plant nacelles, fairings, or cowlings associated with fuselages
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Abstract
The invention discloses a bionic unmanned reconnaissance helicopter, which comprises the following components: the machine head comprises two symmetrically arranged 270-degree waterproof ultra-high definition cameras with an infrared night vision function and a differential GPS positioning system; the landing gear comprises four mechanical arms symmetrically arranged at the bottoms of two sides of the machine body and mechanical claws at the bottoms of the mechanical arms, and the mechanical arms and the mechanical claws are used for realizing the autonomous grabbing of the landing points; the front end and the tail end of the tail duct are respectively provided with a plurality of air inlets and air outlets, and a duct fan for air suction rectification is arranged in the tail duct; the center of the bottom of the mechanical arm is provided with a telescopic and expandable vacuum sucker, and the sucker structure is adopted to realize the buffer effect of attaching to a vertical wall surface and achieving ground landing; the top of the propeller hub is provided with an acoustic wave interference device to realize noise elimination and noise reduction during flying. The invention is miniature and reliable, has quick response, no dead angle in infrared shooting, realizes landing on any angle surface by the design of imitating the appearance of a dragonfly, and has unique concealing performance and higher safety performance.
Description
Technical Field
The invention relates to a bionic unmanned reconnaissance helicopter, and belongs to the technical field of aviation aircrafts.
Background
21. Since century, unmanned aerial vehicles as "wings of a soldier" have become a trend of future war, and it has become a mainstream to perform aerial reconnaissance and combat tasks such as target positioning, battle condition evaluation, fire power calibration, etc. by using unmanned aerial vehicles. Meanwhile, along with the continuous development of society, various disaster relief faced by fire-fighting forces are increasingly complex, and particularly, special relief such as high altitude, mountain relief, flood fighting relief and the like are difficult to meet the relief requirement of conventional fire-fighting equipment.
Therefore, the person skilled in the art is dedicated to develop a bionic unmanned reconnaissance helicopter with small volume and agile response, which is suitable for reconnaissance or monitoring in various fields, especially in local environments, such as fish-water.
Disclosure of Invention
The invention aims to: in order to overcome the defects in the prior art, the invention provides the bionic unmanned reconnaissance helicopter, which has the characteristics of miniature reliability, agility in response, no dead angle in infrared shooting and the like, realizes the landing of the helicopter on any angle surface through the design of simulating the dragonfly appearance, and ensures the maneuverability and safety of the unmanned aerial vehicle through the design of no tail rotor.
The technical scheme is as follows: in order to achieve the above purpose, the invention adopts the following technical scheme:
a bionic unmanned reconnaissance helicopter comprises a helicopter body, a rotor wing, a nose and a landing gear, wherein the rotor wing, the nose and the landing gear are arranged on the helicopter body;
the machine head comprises two symmetrically arranged 270-degree waterproof ultra-high definition cameras and a differential GPS positioning system, and the waterproof ultra-high definition cameras have an infrared night vision function, so that ultra-high definition shooting and infrared detection without dead angles at 360 degrees are realized, the advanced differential GPS positioning system can acquire accurate coordinates of the unmanned aerial vehicle, and further information acquisition and reconnaissance identification in various fields are realized through real-time data transmission in an operation range;
the landing gear comprises four mechanical arms and mechanical claws, wherein the mechanical arms are symmetrically arranged at the bottoms of the two sides of the machine body, the mechanical claws are used for realizing the automatic grabbing of a falling point and the supporting and fixing of the machine body, and the mechanical arms are bent backwards to meet the use requirement of being attached to the machine body when flying, so that the resistance of taking off is reduced; the landing gear structure design is realized by simulating the landing function of the dragonfly on any angle surface, so that the helicopter can be fixed on the wall surface or the tree tip, hidden reconnaissance and emergency forced landing in a war are facilitated, and the landing gear structure design also has the functions of a common landing gear (shock absorption, crash prevention, energy absorption and the like).
The tail part of the machine body is of a hollow structure to form a tail duct, the top of the front end of the tail duct is provided with a plurality of air inlets, the right side of the tail end of the tail duct is provided with a plurality of air outlets, and a duct fan for air suction rectification is arranged in the tail duct.
According to experimental data, compared with a helicopter with a tail rotor, the noise level of the helicopter without the tail rotor is reduced by 25% -40% in a same ratio, the possibility that the tail rotor of the helicopter with the tail rotor hits an obstacle and is damaged by the outside is eliminated, meanwhile, the size of the helicopter body is reduced, the tail transmission mechanism is greatly simplified, and the maneuverability of the unmanned aerial vehicle is further improved.
The structure is that through the open pore at the front end of the hollow tail beam, when the helicopter flies forward, the wake flow of the rotor wing is beaten on the fuselage, the airflow is sucked into the tail duct from the front air inlet, and after the airflow is rectified and accelerated by the duct fan, the airflow is discharged from the tail air outlet in a uniform manner, so that the torque for balancing the pneumatic reactive torque of the rotor wing is generated.
Preferably, the center of the bottom of the mechanical arm is provided with a telescopic and expandable vacuum chuck, and the chuck structure is adopted to realize the buffer effect of attaching to a vertical wall surface and achieving ground landing. When the helicopter falls on an elongated object such as a branch, the vacuum chuck is contracted into the mechanical arm, and the object is gripped by the forward mechanical arm and the mechanical claw to finish falling; when the helicopter is forced to land on the water surface, the vacuum suction cups extend out and enlarge, and land on the water surface through the four suction cups.
Preferably, the rotor includes the rotor hub and installs the paddle on the rotor hub, and the rotor hub top is provided with the acoustic wave interference ware, receives and analyzes the noise frequency that the rotor produced through the acoustic wave interference ware to produce corresponding interference frequency and offset with it, reach the purpose of noise elimination and noise reduction, be favorable to concealing reconnaissance and reduce environmental disturbance.
Preferably, the lower abdomen of the machine body is provided with a concealed fire arm system, the lower cabin door is automatically opened when the concealed fire arm system is to be used for carrying out concealed fire, and the bullet shooting tube rapidly extends out of the machine body and aims at a target, so that accurate striking and rapid evacuation are carried out.
Preferably, the surface of the machine body is covered with a solar battery for supplying power, so that the endurance time of the scout can be greatly prolonged, and the machine is suitable for field emergency combat readiness requirements.
Preferably, the machine head further comprises an ultrasonic damage probe, and after the helicopter lands, whether the machine body, the blades and the like are damaged or not can be automatically detected.
The beneficial effects are that: compared with the prior art, the bionic unmanned reconnaissance helicopter provided by the invention has the following advantages: 1. the method is miniature, reliable, quick in response, ultra-clear in shooting, infrared detection and real-time transmission, so that information acquisition and reconnaissance identification in various fields, in particular navigation tasks of missiles, are realized; 2. the helicopter can land on any angle surface through the design of imitating the dragonfly shape, thereby being beneficial to the hidden reconnaissance and the emergency forced landing in the war and reducing the requirement of the helicopter on the landing environment; 3. the noise elimination and noise reduction of the helicopter during flight are realized through the acoustic wave interference device, and the helicopter has unique concealment performance; 4. the working efficiency of the unmanned reconnaissance helicopter is improved through solar charging and cruising, and the safety of the unmanned reconnaissance helicopter is improved through the damage detection system.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a bionic unmanned reconnaissance helicopter;
FIG. 2 is a side view of a biomimetic unmanned reconnaissance helicopter of the present invention;
FIG. 3 is a schematic diagram of the structure of a nose in a bionic unmanned reconnaissance helicopter;
FIG. 4 is a schematic diagram of the structure of a tail duct in a bionic unmanned reconnaissance helicopter according to the present invention;
FIG. 5 is a schematic view of the landing gear in a biomimetic unmanned reconnaissance helicopter according to the present invention;
FIG. 6 is a schematic diagram of the structure of the bottom of a mechanical arm in a bionic unmanned reconnaissance helicopter according to the present invention;
the drawings include: 1. the device comprises a machine body, a waterproof ultra-high definition camera, a differential GPS positioning system, a propeller hub, a propeller blade, a mechanical arm, a mechanical claw, a vacuum chuck, a tail duct, a duct fan and a duct fan, wherein the machine body, the waterproof ultra-high definition camera, the differential GPS positioning system, the propeller hub, the propeller blade, the mechanical arm, the mechanical claw, the vacuum chuck, the tail duct and the duct fan are arranged in sequence, and the duct fan is arranged in sequence.
Description of the embodiments
The invention will be further described with reference to the accompanying drawings and examples.
Fig. 1 shows a bionic unmanned reconnaissance helicopter, which comprises a fuselage 1, and a rotor wing, a nose and a landing gear which are arranged on the fuselage 1;
the machine head comprises two symmetrically arranged 270-degree waterproof ultra-high-definition cameras 2, an ultrasonic damage probe and a differential GPS positioning system 3, and the waterproof ultra-high-definition cameras 2 have an infrared night vision function;
the landing gear comprises four mechanical arms 6 symmetrically arranged at the bottoms of two sides of the machine body 1 and mechanical claws 7 at the bottoms of the mechanical arms 6, the mechanical arms 6 and the mechanical claws 7 are used for realizing the automatic grabbing of landing points and the supporting and fixing of the machine body 1, and the mechanical arms 6 meet the use requirement of bending backwards to be attached to the machine body 1 during flying;
the tail part of the machine body 1 is of a hollow structure to form a tail duct 9, three air inlets 10 are formed in the top of the front end of the tail duct 9, three air outlets 11 are formed in the right side of the tail end of the tail duct 9, and a duct fan 12 for air suction rectification is arranged in the tail duct 9.
In this embodiment, the bottom center of the mechanical arm 6 is provided with a telescopic and expandable vacuum chuck 8, and the chuck structure is adopted to achieve the buffering effect of attaching to a vertical wall surface and achieving ground landing.
In this embodiment, the rotor includes the rotor hub 4 and installs four blades 5 on the rotor hub 4, and the rotor hub 4 top is provided with the sound wave interference ware, receives and analyzes the noise frequency that the rotor produced through the sound wave interference ware to produce corresponding interference frequency and offset with it, thereby reach the purpose of noise elimination and noise reduction.
In the embodiment, the lower abdomen of the machine body 1 is provided with a concealed fire arm system, so that accurate concealed killing can be performed; the surface of the body 1 is covered with a solar cell.
The specific embodiments of the present invention are as follows:
when the helicopter takes off and flies, the mechanical arm 6 automatically bends backwards to be attached to the helicopter body, so that the resistance during taking off is reduced; when the helicopter normally falls on the ground, the four mechanical arms 6 are simultaneously supported; when the helicopter falls on an elongated object such as a branch, the mechanical arm 6 extends forwards, the vacuum chuck 8 is contracted into the mechanical arm 6 and then holds the object tightly by the mechanical claw 7, so that the falling is completed; when the helicopter is forced to land on the water surface, the vacuum chucks 8 extend and amplify, and land on the water surface through the four vacuum chucks 8. Therefore, the bionic unmanned reconnaissance helicopter can realize landing on any angle surface through the mechanical arm 6, the mechanical claw 7 at the bottom of the mechanical arm and the vacuum chuck 8, and is beneficial to the hidden reconnaissance and the emergency forced landing in the war.
During reconnaissance, the unmanned aerial vehicle realizes 360-degree ultra-clear shooting without dead angles through two symmetrically arranged 270-degree waterproof ultra-high-definition cameras, tasks can be executed at night by infrared night vision, and the differential GPS positioning system 3 can acquire an accurate coordinate route of the unmanned aerial vehicle, so that information acquisition and reconnaissance identification in various fields are realized through real-time data remote transmission.
During flying, the noise frequency generated by the rotor wing is received and analyzed through the acoustic wave interference device, and corresponding interference frequency is generated to offset the noise frequency, so that the purposes of silencing and reducing noise are achieved, and hidden reconnaissance and environmental interference reduction are facilitated; after falling, the damage detection of the machine body is realized through the ultrasonic damage probe, so that corresponding operations (maintenance of the machine body and the blades and the like) are adopted according to the health state of the machine body, and the safety of the unmanned reconnaissance helicopter is greatly improved.
The future bionic unmanned reconnaissance aircraft designed by the invention adopts a flight mode of a helicopter, and can land on a wall surface at any angle at fixed points during vertical take-off and landing. In the process of overall layout design, the method is mainly aimed at meeting the performance requirements in the aspects of pneumatic and structural aspects on the basis of functions. The fuselage adopts smooth streamline modeling and good maneuvering performance, so that the unmanned aerial vehicle can freely come and go on the front edge array. For larger or more targets, the unmanned reconnaissance helicopter integrates a plurality of unmanned aerial vehicles to track and hit the targets in a multi-machine cooperative mode.
The group system structure of the unmanned aerial vehicle is based on a distributed architecture of local perception or communication, a distributed control strategy is adopted, the group has self-organizing coordination energy control capability, and the group system is insensitive to local individual failure and faults, so that the system has strong expandability and robustness.
The foregoing is only a preferred embodiment of the invention, it being noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the invention.
Claims (4)
1. The bionic unmanned reconnaissance helicopter is characterized by comprising a fuselage (1), and a rotor wing, a nose and a landing gear which are arranged on the fuselage (1);
the machine head comprises two symmetrically arranged 270-degree waterproof ultra-high definition cameras (2) and a differential GPS positioning system (3), and the waterproof ultra-high definition cameras (2) have an infrared night vision function;
the landing gear comprises four mechanical arms (6) symmetrically arranged at the bottoms of two sides of the machine body (1) and mechanical claws (7) at the bottoms of the mechanical arms (6), the mechanical arms (6) and the mechanical claws (7) are used for realizing the automatic grabbing of landing points and the supporting and fixing of the machine body (1), and the mechanical arms (6) meet the use requirement of bending backwards to be attached to the machine body (1) in flying;
the tail part of the machine body (1) is of a hollow structure to form a tail duct (9), the top of the front end of the tail duct (9) is provided with a plurality of air inlets (10), the right side of the tail end of the tail duct (9) is provided with a plurality of air outlets (11), and a duct fan (12) for air suction rectification is arranged in the tail duct (9);
the center of the bottom of the mechanical arm (6) is provided with a telescopic and expandable vacuum sucker (8);
the rotor comprises a rotor hub (4) and a plurality of blades (5) arranged on the rotor hub (4), wherein an acoustic wave interference device is arranged at the top of the rotor hub (4), and is used for receiving and analyzing noise frequency generated by the rotor and generating corresponding interference frequency to offset the noise frequency.
2. A biomimetic unmanned reconnaissance helicopter according to claim 1, wherein the lower abdomen of the fuselage (1) is provided with a concealed firearm system.
3. A biomimetic unmanned reconnaissance helicopter according to claim 1, wherein the surface of the fuselage (1) is covered with solar cells.
4. The biomimetic unmanned reconnaissance helicopter of claim 1, wherein said handpiece further comprises an ultrasonic damage probe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710079930.4A CN106741888B (en) | 2017-02-15 | 2017-02-15 | Bionic unmanned reconnaissance helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710079930.4A CN106741888B (en) | 2017-02-15 | 2017-02-15 | Bionic unmanned reconnaissance helicopter |
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| Publication Number | Publication Date |
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| CN106741888A CN106741888A (en) | 2017-05-31 |
| CN106741888B true CN106741888B (en) | 2023-09-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710079930.4A Active CN106741888B (en) | 2017-02-15 | 2017-02-15 | Bionic unmanned reconnaissance helicopter |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109866917A (en) * | 2017-12-04 | 2019-06-11 | 中国飞机强度研究所 | A kind of bionic leg undercarriage |
| CN108545192B (en) * | 2018-05-18 | 2023-11-03 | 深圳市易飞方达科技有限公司 | Unmanned aerial vehicle bullet throwing system and method |
| CN109036078A (en) * | 2018-06-13 | 2018-12-18 | 佛山市三水区希望火炬教育科技有限公司 | A kind of dedicated dragonfly reconnaissance plane of teenager's defence education |
| CN111959749B (en) * | 2020-07-16 | 2022-04-19 | 南京航空航天大学 | Helicopter four-foot undercarriage with terrain self-adaptive take-off, landing and walking capabilities |
| CN114408160B (en) * | 2021-12-17 | 2023-08-29 | 海丰通航科技有限公司 | Tail support pipe and unmanned aerial vehicle |
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| DE102015008256A1 (en) * | 2015-06-26 | 2016-12-29 | Diehl Bgt Defence Gmbh & Co. Kg | Defense drone to ward off small drones |
| CN206590107U (en) * | 2017-02-15 | 2017-10-27 | 南京航空航天大学 | A kind of bionical unmanned reconnaissance helicopter |
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2017
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Patent Citations (7)
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| CN1065632A (en) * | 1991-12-30 | 1992-10-28 | 王福生 | The anser type single autogyro of the duct oar is installed |
| CN101107162A (en) * | 2004-12-23 | 2008-01-16 | 阿克特有限公司 | Wire strike system |
| US20090069957A1 (en) * | 2005-03-28 | 2009-03-12 | Yamaha Hatsudoki Kabushiki Kaisha | Unmanned helicopter |
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| CN106741888A (en) | 2017-05-31 |
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