CN107776892B - Light-duty collapsible scouting and beating integrative unmanned aerial vehicle - Google Patents
Light-duty collapsible scouting and beating integrative unmanned aerial vehicle Download PDFInfo
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- CN107776892B CN107776892B CN201711223016.9A CN201711223016A CN107776892B CN 107776892 B CN107776892 B CN 107776892B CN 201711223016 A CN201711223016 A CN 201711223016A CN 107776892 B CN107776892 B CN 107776892B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
- B64D1/12—Releasing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0063—Fuselage structures substantially made from particular materials from wood
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
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- 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
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Abstract
The invention relates to the field of unmanned aerial vehicles, in particular to a light foldable scouting and hitting integrated unmanned aerial vehicle which comprises a body, wings, a folding mechanism, a horizontal and vertical tail, a scouting cradle head and a throwing mechanism, wherein the body comprises a front section body, a rear section body, a central wing box, a wing main beam, a body connecting box and a tail connecting box; the wing comprises an inner section wing and an outer section wing; the two pairs of wings are symmetrically arranged on two sides of the fuselage; the folding mechanism comprises a wing folding mechanism and a fuselage folding mechanism; the wing folding mechanism is provided with two pairs. The invention provides a scouting and batting integrated unmanned aerial vehicle which can be folded and unfolded quickly, has low cost, simple structure and easy repair, has excellent maneuverability and certain putting load, can be used for carrying out military scouting actions and executing quick and accurate batting tasks, and can also be applied to the field of civil scientific research, such as atmospheric exploration, surface mapping and the like.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a light foldable scouting and batting integrated unmanned aerial vehicle.
Background
Unmanned aerial vehicle is mostly the fixed wing aircraft, and hand throw takes off or short distance takes off, mostly is electronic, small light in weight. Generally, metal materials and some advanced composite materials are used for reducing the weight of the structure, but the shapes of the materials are irregular, most of the materials have larger sizes than a rotor unmanned aerial vehicle, and the materials are difficult to pack and carry. Meanwhile, most unmanned aerial vehicles have poor instant repairability and are not cheap, generally more than $ 5000. A prior art unmanned aerial vehicle, such as a variable aspect ratio scout and peck integrated unmanned aerial vehicle with patent application number CN201420040752.6, includes a fuselage, an outer wing section, a middle wing section, an empennage, and a power system; the wing outer section wing and the wing middle section wing are connected through the connecting mechanism, and the connecting structure is separable. As a reconnaissance and attack integrated unmanned aerial vehicle, the unmanned aerial vehicle can carry out strategic, battle and tactical reconnaissance, monitors a battlefield, provides information for the operation action of troops, and can be used as an attack unmanned aerial vehicle for attacking and intercepting ground and aerial targets according to the change of operation tasks; after the outer wing section is thrown off, two fighting modes can be provided. This unmanned aerial vehicle adopts the conventional overall arrangement of stationary vane, for the needs that adapt to different battlefield environment, adjusts the aerodynamic characteristics of aircraft through the aspect ratio that changes the aircraft. The specific implementation scheme is that two sections of wings are adopted, a 5mm steel cylinder is inserted into an inner section wing main beam, the outer section wing and the inner section wing are fixedly connected through a hook and a steel wire, the steel wire is pulled to unlock when the wing lifting device is used, and the outer section wing is thrown away under the action of a lifting force. However, in the whole process of the unmanned aerial vehicle, the aspect ratio of the aircraft is reduced from 14 to 5.6, the wing load is increased, the lateral stability is reduced, and the corresponding rolling speed is increased.
Disclosure of Invention
The invention aims to provide a light foldable scouting and batting integrated unmanned aerial vehicle, which can effectively solve the problems that the unmanned aerial vehicle in the prior art is expensive and difficult to maintain, is difficult to repair quickly due to damage in actual combat and cannot be put into use again, and the existing unmanned aerial vehicle is large in weight, large in size, inconvenient to carry and poor in maneuverability; the invention provides a scouting and batting integrated unmanned aerial vehicle which can be folded and unfolded quickly, has low cost and simple structure, is easy to repair, has excellent maneuverability, can carry a certain load to be thrown, can be used for carrying out military scouting actions and executing quick and accurate batting tasks, and can also be applied to the field of civil scientific research, such as atmospheric exploration, surface mapping and the like.
The purpose of the invention is realized by the following technical scheme:
the light foldable scouting and hitting integrated unmanned aerial vehicle comprises a body, wings, a folding mechanism, a horizontal vertical tail, a scouting cradle head and a throwing mechanism, wherein the body comprises a front section body, a rear section body, a central wing box, a wing main beam, a body connecting box and a tail connecting box;
the wing comprises an inner section wing and an outer section wing; the two pairs of wings are symmetrically arranged on two sides of the fuselage;
the folding mechanism comprises a wing folding mechanism and a fuselage folding mechanism; the wing folding mechanism is provided with two pairs;
the front-section machine body is connected with the front end of a machine body connecting box through a machine body folding mechanism, the rear end of the machine body connecting box is fixedly connected with a rear-section machine body, the rear end of the rear-section machine body is fixedly connected with a machine tail connecting box, and the rear end of the machine tail connecting box is fixedly connected with a horizontal vertical tail;
the middle end of the front-section fuselage is fixedly provided with a central wing box and a wing main girder; the two ends of the central wing box and the wing main beam are respectively connected with inner section wings in the left auxiliary wing and the right auxiliary wing, and the outer sides of the two auxiliary inner section wings are respectively connected with an auxiliary outer section wing through an auxiliary wing folding mechanism;
the reconnaissance cradle head is arranged at the tail part of the front-section fuselage; the throwing mechanism is arranged in the middle of the front-section fuselage and is positioned under the wing main beam.
The inner section wing and the outer section wing respectively adopt an NACA4412 wing profile and an NACA6412 wing profile, the wing tip of the outer section wing has 3-degree negative torsion relative to the wing root of the inner section wing, and the chord length ratio of the wing tip to the wing root is 1: 1.778, the wingspan of the inner wing and the outer wing is 1332mm, the wing area of the inner wing and the outer wing is 0.337 square meter, the aspect ratio is 5.273, the front edge of the inner wing and the outer wing is straight, no upper reverse exists and no winglet exists.
The outer section of the wing adopts a single-beam force bearing mode, uses a round carbon tube with the outer diameter of 8mm and the inner diameter of 6mm as a wing beam, penetrates through the wing rib and is bonded with the wing rib.
The front section fuselage is a wooden frame fuselage; the rear section fuselage is a carbon fiber tube fuselage.
The wing folding mechanism comprises a spring steel connecting sheet, a metal spring hinge and a folding reinforcing box; one end of the folding reinforcing box is connected to the wing rib of the inner section wing, and the other end of the folding reinforcing box is connected to the wing rib of the outer section wing; the upper surface of the inner section wing and the upper surface of the outer section wing are connected through two spring steel connecting sheets; the lower surface of the inner section wing and the lower surface of the outer section wing are connected through a metal spring hinge; the spring steel connecting piece is a buckling and locking steel piece made of 2mm spring steel material, one end of the spring steel connecting piece is fixed on the inner section wing through screws, and the other end of the spring steel connecting piece is fixed on the outer section wing through screws.
The machine body folding mechanism comprises a spring hinge and a steel hasp; the upper surface of the front section machine body is connected with the upper surface of the machine body connecting box through a spring hinge with the width of 25 mm; the left end and the right end of the front-section machine body are respectively provided with a steel hasp, and the rear end hasps of the steel hasps are arranged at the left end and the right end of the machine body connecting box.
The reconnaissance cradle head comprises two cradle head coaxial pitching steering engines, a cradle head rolling steering engine and a camera pod; the two tripod heads are coaxial with each other, and the two tripod heads are coaxial with each other and fixed on the reinforcing side plates on two sides in the front-section body through screws respectively; the coaxial pitching steering engine of the holder is coaxial with the pitching shaft; the cradle head rolling steering engine is fixedly arranged on the pitching shaft; and a rocker arm of the pan-tilt rolling steering engine is fixedly connected to the upper wall of the camera pod.
The throwing mechanism comprises a front wall supporting plane, a rotating shaft support, a blocking piece, a throwing steering engine, a rocker arm, a connecting rod and a throwing bin; the throwing bin is fixed in the middle of the front-section machine body; the front wall of the throwing bin is connected with a front wall supporting plane; the rotating shaft support is fixed at the lower part of the rear wall of the throwing bin; the rotating shaft penetrates through the rotating shaft support; the lower part of the rotating shaft is sleeved with a baffle plate; the throwing steering engine is arranged on the rear wall of the throwing bin through a throwing steering engine support, and a rocker arm of the throwing steering engine is parallel to the blocking piece; the rocker arm is connected with the baffle plate through a connecting rod.
When the wings are unfolded, the outer section wings are bounced open under the torsion action of the metal spring hinges fixed on the lower surfaces, and the screws on the upper surfaces of the outer section wings are embedded into the extension holes in the spring steel connecting sheets in the inner section wings, so that the unfolding is completed.
The rotating shaft support and the throwing steering engine support are formed by adopting 3D printing; the diameter of the rotating shaft is 3mm, and the length of the rotating shaft is 40 mm; the baffle plate is formed by milling a carbon fiber plate with the thickness of 1.5 mm.
The invention has the beneficial effects that: the unmanned aerial vehicle can effectively solve the problems that the unmanned aerial vehicle in the prior art is expensive and difficult to maintain, is difficult to repair quickly and cannot be put into use again due to damage in actual combat, and the problems that the existing unmanned aerial vehicle is large in weight, large in size, inconvenient to carry and poor in maneuverability; the invention provides a scouting and batting integrated unmanned aerial vehicle which can be folded and unfolded quickly, has low cost and simple structure, is easy to repair, has excellent maneuverability, can carry a certain load to be thrown, can be used for carrying out military scouting actions and executing quick and accurate batting tasks, and can also be applied to the field of civil scientific research, such as atmospheric exploration, surface mapping and the like.
The invention adopts the layout of double vertical tails of forward swept wings, the total weight of the machine is 1.85kg, the double-generator brushless motor is configured, and the thrust-weight ratio can reach 1.6. The sectional wing can be folded by adopting a wood structure, can be unfolded within 5 seconds, and the cost of the whole aircraft is controlled within 1000 yuan RMB. Due to the adoption of a wooden structure and a modular design, the airplane can be quickly repaired or replaced when local damage occurs, and the airplane can better adapt to the severe environment of a battlefield. Meanwhile, the variable-wing type sweepforward wing and the wing torsion design enable the airplane to have excellent maneuverability and unusual load carrying capacity. In addition, the airplane adopts the cracking type flap, so that the minimum horizontal flight speed is greatly reduced, a higher thrust-weight ratio is relied on, the flight speed range of the airplane is larger, the target can be stably detected and hit is ensured, meanwhile, the high penetration capability is still achieved, and the success rate of tasks is ensured.
The invention has the advantages that:
1. high maneuverability, high load pneumatic design: the forward swept wing aerodynamic layout is adopted, wing profile variation is assisted by wing tip negative torsion, the lift coefficient is improved, and meanwhile the structural weight is reduced.
2. The whole machine folding mechanism comprises: the wings and the fuselage are provided with three folding mechanisms, so that the whole fuselage can be placed in a regular cuboid box after being folded, the space occupancy rate exceeds 50%, and the internal residual space can be distributed to random equipment. The plane in the folded state is taken out of the box body, no tool is needed, recovery can be completed within 5 seconds under the cooperation of two persons, and recovery can be completed within 8 seconds by one person.
3. The releasing mechanism comprises: the separation blade feeding mechanism controlled by a single steering engine is convenient and time-saving to load and feed, and has high reliability.
Compared with the unmanned aerial vehicle in the prior art, the unmanned aerial vehicle has the advantages of high maneuverability, easiness in carrying and the like. In the existing scheme, the aspect ratio of the airplane is reduced by throwing the outer section of the wing down. The large-span airplane has good load-carrying performance and flight stability in a large-span state, but the maneuverability is poor, and after the outer-section wing is thrown down, the aerodynamic characteristics and the flight stability of the airplane are adversely affected by the change of the aspect ratio and the sudden change of the tail volume. The invention aims to improve the maneuverability of the reconnaissance unmanned aerial vehicle, so that the aerodynamic layout with small aspect ratio is selected, but the loss of lift coefficient caused by the reduction of the aspect ratio under the equivalent wing area is made up through the novel forward swept wing design. In the aerodynamic simulation calculation of XFLR5, the lift coefficient of the airplane can reach 1.2 at an attack angle of 10 degrees. Meanwhile, the rapid deployment device has the great advantages of being convenient to carry and rapid in deployment, the aircraft can be rapidly deployed within 5 seconds of preparation time, and the battlefield reconnaissance efficiency is greatly improved.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a front view of the present invention;
FIG. 3 is a schematic view of the internal wing-fold mechanism of the present invention;
FIG. 4 is a schematic structural view of the inner reconnaissance holder of the present invention;
FIG. 5 is a front view of the inner surveillance camera head of the present invention;
FIG. 6 is a schematic structural view of the internal dispensing mechanism of the present invention;
FIG. 7 is a bottom view of the internal delivery mechanism of the present invention;
FIG. 8 is a right side view of the release mechanism within the present invention;
FIG. 9 is a front view of the internal release mechanism of the present invention;
in the figure: 1-a front fuselage; 2-inner section wing; 3-outer section wing; 4-wing folding mechanism; 5-a body folding mechanism; 6-horizontal vertical tails; 7-carbon fiber tube rear body; 8-scouting the cloud deck; 9-a throwing mechanism; 10-spring steel connecting sheet; 11-a screw; 12-an elongated well; 13-the pan-tilt coaxial pitching steering engine; 14-a pan-tilt rolling steering engine; 15-camera pod; 16-front wall support plane; 17-a rotating shaft support; 18-a baffle plate; 19-the baffle plate drives the steering engine; 20-a rocker arm; 21-connecting rod.
Detailed Description
The invention is described in further detail below with reference to figures 1-9.
The first embodiment is as follows:
as shown in fig. 1-9, the light foldable scouting and hitting integrated unmanned aerial vehicle comprises a fuselage, wings, a folding mechanism, a horizontal vertical tail 6, a scouting cradle head 8 and a throwing mechanism 9, wherein the fuselage comprises a front section fuselage 1, a rear section fuselage 7, a central wing box, a wing main beam, a fuselage connecting box and a tail connecting box; the wing comprises an inner section wing 2 and an outer section wing 3; the two pairs of wings are symmetrically arranged on two sides of the fuselage; the folding mechanism comprises a wing folding mechanism 4 and a fuselage folding mechanism 5; the wing folding mechanism 4 is provided with two pairs; the front-section machine body 1 is connected with the front end of a machine body connecting box through a machine body folding mechanism 5, the rear end of the machine body connecting box is fixedly connected with a rear-section machine body 7, the rear end of the rear-section machine body 7 is fixedly connected with a machine tail connecting box, and the rear end of the machine tail connecting box is fixedly connected with a horizontal vertical tail 6; the middle end of the front-section fuselage 1 is fixedly provided with a central wing box and a wing main girder; the two ends of the central wing box and the wing main beam are respectively connected with inner section wings 2 in the left auxiliary wing and the right auxiliary wing, and the outer sides of the two auxiliary inner section wings 2 are respectively connected with an auxiliary outer section wing 3 through an auxiliary wing folding mechanism 4; the reconnaissance cradle head 8 is arranged at the tail part of the front-section fuselage 1; the throwing mechanism 9 is arranged in the middle of the front-section fuselage 1, and the throwing mechanism 9 is located right below the main girder of the wing.
The inner section wing 2 and the outer section wing 3 respectively adopt a NACA4412 wing type and a NACA6412 wing type, the wing tip of the outer section wing 3 has 3-degree negative torsion relative to the wing root of the inner section wing 2, and the ratio of the wing root to the wing tip is 1: 1.778, the wingspan of the inner wing 2 and the outer wing 3 is 1332mm, the wing area of the inner wing 2 and the outer wing 3 is 0.337 square meter, the aspect ratio is 5.273, the front edge of the inner wing 2 and the outer wing 3 is straight, and the wingless winglet has no upper reverse and no wingtip.
The outer section of the wing 3 adopts a single-beam force bearing mode, uses a round carbon tube with the outer diameter of 8mm and the inner diameter of 6mm as a wing beam, penetrates through the wing rib and is bonded with the wing rib.
The front-section fuselage 1 is a wooden frame fuselage; the rear section fuselage 7 is a carbon fiber tube fuselage.
The wing folding mechanism 4 comprises a spring steel connecting sheet 10, a metal spring hinge and a folding reinforcing box; one end of the folding reinforcing box is connected to the wing rib of the inner section wing 2, and the other end of the folding reinforcing box is connected to the wing rib of the outer section wing 3; the upper surface of the inner section wing 2 is connected with the upper surface of the outer section wing 3 through two spring steel connecting sheets 10; the lower surface of the inner section wing 2 is connected with the lower surface of the outer section wing 3 through a metal spring hinge; the spring steel connecting piece 10 is a buckling and locking steel piece made of 2mm spring steel material, one end of the spring steel connecting piece 10 is fixed on the inner section wing 2 through a screw 11, and the other end of the spring steel connecting piece is fixed on the outer section wing 3 through the screw 11.
The machine body folding mechanism 5 comprises a spring hinge and a steel hasp; the upper surface of the front section machine body 1 is connected with the upper surface of the machine body connecting box through a spring hinge with the width of 25 mm; the left end and the right end of the front-section machine body 1 are respectively provided with a steel hasp, and the rear end hasps of the steel hasps are arranged at the left end and the right end of the machine body connecting box.
The reconnaissance cradle head 8 comprises two cradle head coaxial pitch steering engines 13, a cradle head rolling steering engine 14 and a camera pod 15; the two tripod heads are coaxial with the pitching steering engines 13, and the two tripod heads are coaxial with the pitching steering engines 13 and are respectively fixed on the reinforcing side plates on two sides in the front section fuselage 1 through screws; the coaxial pitching steering engine 13 of the tripod head is coaxial with a pitching shaft; the pan-tilt-roll steering engine 14 is fixedly arranged on the pitch shaft; the rocker arm of the pan-tilt roll steering engine 14 is fixedly connected to the upper wall of the camera pod 15.
The throwing mechanism 9 comprises a front wall supporting plane 16, a rotating shaft support 17, a blocking piece 18, a throwing steering engine 19, a rocker arm 20, a connecting rod 21 and a throwing bin; the throwing bin is fixed in the middle of the front-section machine body 1; the front wall of the throwing bin is connected with a front wall supporting plane 16; the rotating shaft support 17 is fixed at the lower part of the rear wall of the throwing bin; the rotating shaft penetrates through the rotating shaft support 17; a baffle plate 18 is sleeved at the lower part of the rotating shaft; the throwing steering engine 19 is mounted on the rear wall of the throwing bin through a throwing steering engine support, and a rocker arm 20 of the throwing steering engine 19 is parallel to the blocking piece 18; the rocker arm 20 is connected to the flap 18 by a link 21.
When the wings are unfolded, the outer section wings 3 are bounced open under the torsion action of the metal spring hinges fixed on the lower surfaces, and the screws 11 on the upper surfaces of the outer section wings 3 are embedded into the extension holes 12 on the spring steel connecting sheets 10 in the inner section wings 2, so that the wings are unfolded.
The rotating shaft support 17 and the throwing steering engine support are formed by adopting 3D printing; the diameter of the rotating shaft is 3mm, and the length of the rotating shaft is 40 mm; the baffle plate is formed by milling a carbon fiber plate with the thickness of 1.5 mm.
The second embodiment is as follows:
the invention discloses a light foldable scouting and batting integrated unmanned aerial vehicle, which comprises the following pneumatic layout and parameters:
in order to arrange a pilot cabin at the head of the airplane and ensure a high enough thrust-weight ratio, the airplane adopts a double-engine power design. The wing of the airplane is divided into an inner end and an outer end, two wing profiles of NACA4412 and NACA6412 are respectively adopted, the wing tip has 3-degree negative torsion relative to the wing root, the root tip ratio is 1.778, the wingspan is 1332mm, the wing area is 0.337 square meter, the aspect ratio is 5.273, the wing leading edge is straight, no upper reflection exists, no wing tip winglet exists, and the capacity of the horizontal tail is 0.531.
The existing small unmanned reconnaissance aircraft mostly adopts a single-engine up-down design with a large aspect ratio, the wing area is not large, and the aircraft wing load is directly large due to the fact that the weight of the aircraft and various electronic devices is large. Although the design has better flight stability and smaller minimum horizontal flight speed, the maneuverability of the airplane is poorer, and the most intuitive reflection is that the radius of the stable disk is larger and the roll rate is low. This leads to the aircraft can't change the reconnaissance route in the time of carrying out the reconnaissance task in a flexible way, because unmanned aerial vehicle itself location lies in carrying out the short-range reconnaissance of advancing into the enemy promptly, if can not discover the target and advance with the fastest speed, not only probably increase the possibility that is hit down by oneself, more probably delay the fighter plane.
Therefore, the reconnaissance aircraft design goal of the invention is to enable the aircraft to have excellent maneuverability by reducing wing loads and adopting a lower aspect ratio, so that a reconnaissance route can be more flexibly re-planned at any time and quickly reach a target. However, in order to carry enough equipment and put load, the load-carrying performance of the airplane needs to be guaranteed, so that the design of a forward swept wing is adopted, and the lift coefficient is improved by utilizing the large-camber airfoil NACA 6412. Therefore, the wings need to be designed with certain wing tip negative torsion to prevent the ailerons from losing efficacy, and the design also enables the local lift force of each section on the full span to be distributed more uniformly, thereby lightening the burden of the subsequent structural design.
The structure design of the loader: the whole machine adopts a basswood laminate and a light wood structure, the main bearing part adopts a carbon fiber composite material, and the wing uses a thermal shrinkage skin to support the wing section. Because the whole machine has less metal material application, the weight is lighter, the no-load is 1.85kg, and the carrying is convenient. Meanwhile, the manufacturing process is simple and easy to repair.
Wing structure: the outer wing section adopts a single-beam force bearing mode, uses a round carbon tube with the outer diameter of 8 × 6mm as a wing beam, penetrates through the wing rib and is bonded with the wing rib. The inner section of the wing adopts a single carbon beam bearing force and auxiliary wood beam torsion resistant structure, and the main beam adopts a carbon tube with the outer diameter being 12 x 10 mm. The left and right inner section wing girders of the airplane penetrate through the airplane body, and the wing boxes are positioned on the upper part of the middle part of the airplane body and belong to the middle single wing layout. Two most inner wing ribs of the left and right inner section wings use 4mm basswood laminates, the inner sides of the two most inner wing ribs are embedded into a wing root groove of the fuselage, the thicknesses of the rest wing ribs are 2mm, the basswood laminates are used on the inner side and the outer side and at the positions where the steering engines are installed, and the rest wing ribs are made of balsawood.
The fuselage structure: the airplane body is divided into a front airplane body and a rear airplane body, wherein the front airplane body is a carrier for accommodating a scout nacelle and throwing a load, an electric control device for placing an airplane is arranged, and a frame structure is adopted;
the latter uses carbon tube with outer diameter of 14 x 12mm to connect the front frame and the flat tail box. The two sections of the machine bodies are connected with the hasps by metal spring hinges and can be folded and unfolded quickly for fixing.
Design of a folding mechanism: although the existing small-sized fixed-wing unmanned aerial vehicle is considerable in size, the unmanned aerial vehicle cannot be placed in a container with small enough size and regular shape, and therefore even though the unmanned aerial vehicle is convenient to load and carry, the unmanned aerial vehicle is not easy to carry about to enter a battlefield. At this time, if the size of the whole aircraft is reduced to an order of easy carrying, the operational performance of the aircraft itself must be greatly impaired, such as endurance, range, payload, and the like.
Therefore, the invention enables the airplane to be arranged in the regular box with the sum of length, width and height of 1.5 meters without reducing the operation performance of the airplane by designing the skillful wings and the folding mechanism of the airplane body, and the airplane can be easily carried by a single person. Meanwhile, the folding mechanisms are very convenient to unfold, the three folding mechanisms can be completely unfolded and take off immediately within 5 seconds under the cooperation of two persons, the response time is extremely short, and the folding mechanism can be more suitable for the severe environment which is changeable in a battlefield. If the movable-wing reconnaissance aircraft is applied to the civil field, the movable-wing reconnaissance aircraft which is easy to carry is also favored by the majority of researchers.
The design of the folding mechanism is one of the greatest innovation points of the invention, the folding mechanism of the airplane has three positions, the outer section of the wing is folded downwards, and the rear fuselage is folded upwards at the joint of the inner section and the outer section of the left wing and the right wing and the joint of the front fuselage and the rear fuselage.
The wing folding adopts a spring hinge and manganese steel sheet buckling and locking mechanism, a folding and reinforcing box is clamped between No. 7 and No. 8 wing ribs on the outer side of the inner section of the wing and between No. 9 and No. 10 wing ribs on the inner side of the outer section of the wing, the lower surface of the folding and reinforcing box is connected by a metal spring hinge with the length of 50mm, the front edge and the rear edge of the upper surface of the folding and reinforcing box are made of two buckling and locking steel sheets made of 2mm spring steel materials and fixed on the inner section of the wing by screws, and the screws. When the wing is unfolded, the outer section wing bounces under the torsion action of the spring, the screw on the upper surface is embedded into the extension hole on the spring steel sheet of the inner section wing, after the wing is fastened, the folding is loosened, the spring steel sheet needs to be slightly pried by using a steel sheet or a blade, and the screw can be unscrewed.
The folding of fuselage adopts spring steel sheet and two hasp mechanisms, and two sections fuselages around the fuselage upper surface uses 25mm wide spring hinge to connect. Steel hasps are respectively arranged on two sides of the machine body, and the two people can be matched to fasten in about 3 seconds when the machine body is unfolded.
Design of a reconnaissance mechanism: the reconnaissance mechanism is positioned at the tail part of the front machine body, two coaxial steering engines are used for driving the integral pitching folding and unfolding of the cradle head, another steering engine is arranged on a pitching shaft, and the rocker arm is attached to and fixed on the upper wall of the camera cabin and used for controlling the rolling of the camera. Therefore, the whole holder device can freely rotate within the range of pitch angle of 85 degrees and roll angle of plus or minus 60 degrees. Specifically, two pitching steering engines are symmetrically arranged on bulkheads on two sides of the reconnaissance cabin, and the rocker arms are inward. The two rocker arms are fixedly connected with a rolling steering engine seat which can coaxially rotate with the rotating shafts of the two rocker arms, the rolling steering engine is installed on the support, and the rocker arms are connected and fixed with the camera cabin backwards. When the whole double-shaft holder is retracted into the body, the camera is backward, and the camera is laid down and the viewing angle is forward.
The design of the releasing mechanism: the throwing bin is positioned at the lower side of the front-section fuselage and has a cuboid cabin volume of 782.21cm3And the geometric center is positioned right below the main wing beam of the airplane, so that the integral gravity center of the airplane does not obviously deviate after the air drop of the airplane is finished. The front wall of putting in the storehouse is equipped with horizontal fixed stay plane, and the back wall bottom is equipped with 3D and prints the throwing in pivot base that forms and put in the steering wheel support, utilizes the long 40 mm's of diameter 3mm steel column as the pivot, and the separation blade that 1.5mm thick carbon fiber board milled its bottom suit, steering wheel rocking arm and separation blade coplanar utilize the rotation of steering wheel control separation blade. When the rotation angle of the blocking piece is larger than a certain angle, the blocking piece is determined according to the size of the loaded object, the loaded object is separated from the blocking piece, the gravity center of the loaded object is not in the front wall supporting plane, the loaded object rolls backwards and falls down, air drop is completed, and the blocking piece resets. It is worth noting that since the loading object is separated from the throwing bin in a backward overturning manner, the front part of the loading object can rotate upwards at the moment of separation, so that in order to prevent the loading object from rubbing and pressing the upper wall of the throwing bin, an upward concave space needs to be arranged at the front upper part of the throwing bin, and the loading object cannot be loaded.
The third concrete implementation mode:
according to the wing folding mechanism, the lower surface of the wing adopts the metal spring hinge and is used for connecting two sections of wings and providing torque for rebounding the wings to be folded. The upper surface utilizes the fixed of 65 manganese steel sheets of customization to accomplish after the wing rebounds, specifically, the steel sheet extends out from the inner segment wing, and the outside has an external diameter dimension and the extension hole that the connecting screw top external diameter on the outer segment wing is the same, and when outer single wing rebounded upwards, the outer segment screw will be automatic block in the extension hole, along with the wing rebounds completely and resets, the screw is locked with the extension hole outer fringe. The mechanism can also be replaced by a structure similar to a clip, for example, a transverse sheet is placed on the outer section of the wing, a space is reserved between the upper part and the lower part, a semi-sawtooth-shaped clamp capable of bouncing upwards is installed on the inner section of the wing, in the process of folding the outer section of the wing, the inclined plane at the front part of the clamp bounces upwards by being extruded with the outer section of the wing sheet, the wing is continuously folded, and the clamp and the sheet are fastened and locked while resetting.
It is to be understood that the above description is not intended to limit the present invention, and the present invention is not limited to the above examples, and that various changes, modifications, additions and substitutions which are within the spirit and scope of the present invention and which may be made by those skilled in the art are also within the scope of the present invention.
Claims (6)
1. Light-duty collapsible scouting and beating integrative unmanned aerial vehicle includes fuselage, wing, folding mechanism, flat vertical fin (6), reconnaissance cloud platform (8) and input mechanism (9), its characterized in that: the fuselage comprises a front fuselage section (1), a rear fuselage section (7), a central wing box, a wing main beam, a fuselage connecting box and a tail connecting box; the wings comprise an inner section wing (2) and an outer section wing (3); the two pairs of wings are symmetrically arranged on two sides of the fuselage; the folding mechanism comprises a wing folding mechanism (4) and a fuselage folding mechanism (5); the wing folding mechanism (4) is provided with two pairs; the front-section machine body (1) is connected with the front end of a machine body connecting box through a machine body folding mechanism (5), the rear end of the machine body connecting box is fixedly connected with a rear-section machine body (7), the rear end of the rear-section machine body (7) is fixedly connected with a machine tail connecting box, and the rear end of the machine tail connecting box is fixedly connected with a horizontal vertical tail (6); the middle end of the front-section fuselage (1) is fixedly provided with a central wing box and a wing main girder; the two ends of the central wing box and the wing main beam are respectively connected with inner section wings (2) in the left auxiliary wing and the right auxiliary wing, and the outer sides of the two auxiliary inner section wings (2) are respectively connected with an auxiliary outer section wing (3) through an auxiliary wing folding mechanism (4); the reconnaissance cradle head (8) is arranged at the tail part of the front-section fuselage (1); the throwing mechanism (9) is arranged in the middle of the front-section fuselage (1), and the throwing mechanism (9) is positioned right below the main girder of the wing;
the inner section wing (2) and the outer section wing (3) respectively adopt an NACA4412 wing type and an NACA6412 wing type, the wing tip of the outer section wing (3) has 3-degree negative torsion relative to the wing root of the inner section wing (2), and the chord length ratio of the wing tip to the wing root is 1: 1.778, the wingspan of the inner wing (2) and the outer wing (3) is 1332mm, the wing area of the inner wing (2) and the outer wing (3) is 0.337 square meter, the aspect ratio is 5.273, the front edges of the inner wing (2) and the outer wing (3) are straight, no upper reverse exists and no winglet exists;
the wing folding mechanism (4) comprises a spring steel connecting sheet (10), a metal spring hinge and a folding reinforcing box; one end of the folding reinforcing box is connected to the wing rib of the inner section wing (2), and the other end of the folding reinforcing box is connected to the wing rib of the outer section wing (3); the upper surface of the inner section wing (2) is connected with the upper surface of the outer section wing (3) through two spring steel connecting sheets (10); the lower surface of the inner section wing (2) is connected with the lower surface of the outer section wing (3) through a metal spring hinge; the spring steel connecting piece (10) is a buckling and locking steel piece made of 2mm spring steel material, one end of the spring steel connecting piece (10) is fixed on the inner section wing (2) through a screw (11), and the other end of the spring steel connecting piece is fixed on the outer section wing (3) through the screw (11);
the throwing mechanism (9) comprises a front wall supporting plane (16), a rotating shaft support (17), a blocking piece (18), a throwing steering engine (19), a rocker arm (20), a connecting rod (21) and a throwing bin; the throwing bin is fixed in the middle of the front-section machine body (1); the front wall of the throwing bin is connected with a front wall supporting plane (16); the rotating shaft support (17) is fixed at the lower part of the rear wall of the throwing bin; the rotating shaft penetrates through the rotating shaft support (17); a baffle plate (18) is sleeved at the lower part of the rotating shaft; the throwing steering engine (19) is mounted on the rear wall of the throwing bin through a throwing steering engine support, and a rocker arm (20) of the throwing steering engine (19) is parallel to the blocking piece (18); the rocker arm (20) is connected with the baffle plate (18) through a connecting rod (21);
when the wings are unfolded, the outer section wings (3) are bounced open under the torsion action of the metal spring hinges fixed on the lower surfaces, screws (11) on the upper surfaces of the outer section wings (3) are embedded into extension holes (12) in spring steel connecting sheets (10) on the upper surfaces of the inner section wings (2), and unfolding is completed.
2. The light-duty collapsible reconnaissance and play integrative unmanned aerial vehicle of claim 1, characterized in that: the outer section wing (3) adopts a single-beam force bearing mode, uses a round carbon tube with the outer diameter of 8mm and the inner diameter of 6mm as a wing beam, penetrates through the wing rib and is bonded with the wing rib.
3. The light-duty collapsible reconnaissance and play integrative unmanned aerial vehicle of claim 1, characterized in that: the front-section fuselage (1) is a wooden frame fuselage; the rear section fuselage (7) is a carbon fiber tube fuselage.
4. The light-duty collapsible reconnaissance and play integrative unmanned aerial vehicle of claim 1, characterized in that: the machine body folding mechanism (5) comprises a spring hinge and a steel hasp; the upper surface of the front section machine body (1) is connected with the upper surface of the machine body connecting box through a spring hinge with the width of 25 mm; the left end and the right end of the front-section machine body (1) are respectively provided with a steel hasp, and the rear end hasps of the steel hasps are arranged at the left end and the right end of the machine body connecting box.
5. The light-duty collapsible reconnaissance and play integrative unmanned aerial vehicle of claim 1, characterized in that: the reconnaissance cradle head (8) comprises two cradle head coaxial pitch steering engines (13), a cradle head rolling steering engine (14) and a camera pod (15); the two tripod heads are coaxial with the pitching steering engines (13), and the two tripod heads are coaxial with the pitching steering engines (13) and are respectively fixed on the reinforcing side plates on the two sides in the front section fuselage (1) through screws; the coaxial pitching steering engine (13) of the tripod head is coaxial with a pitching shaft; the pan-tilt rolling steering engine (14) is fixedly arranged on the pitch shaft;
and a rocker arm of the pan-tilt rolling steering engine (14) is fixedly connected to the upper wall of the camera nacelle (15).
6. The light-duty collapsible reconnaissance and play integrative unmanned aerial vehicle of claim 1, characterized in that: the rotating shaft support (17) and the throwing steering engine support are formed by adopting 3D printing; the diameter of the rotating shaft is 3mm, and the length of the rotating shaft is 40 mm; the baffle plate is formed by milling a carbon fiber plate with the thickness of 1.5 mm.
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| CN108773490B (en) * | 2018-04-26 | 2021-02-19 | 华南农业大学 | Solar agricultural unmanned aerial vehicle and agricultural condition remote sensing monitoring method |
| CN112061376B (en) * | 2020-08-24 | 2022-09-09 | 西北工业大学 | Independently fix a position collapsible freight transportation glider |
| CN112267955B (en) * | 2020-09-18 | 2021-09-10 | 中国航发四川燃气涡轮研究院 | Cantilever force bearing device for combined spray pipe |
| CN112977797B (en) * | 2021-02-23 | 2022-02-01 | 四川大学 | High-strength light detachable fixed-wing scouting and hitting unmanned aerial vehicle |
| CN113371175A (en) * | 2021-06-26 | 2021-09-10 | 中国民用航空飞行学院 | Fixed wing scouting and hitting integrated unmanned aerial vehicle model and design method thereof |
| CN114291247A (en) * | 2022-01-20 | 2022-04-08 | 北京航空航天大学 | Foldable full-motion film wing micro unmanned aerial vehicle system |
| CN114802738A (en) * | 2022-05-05 | 2022-07-29 | 吉林大学 | Small-size three rotor fixed wing unmanned aerial vehicle that vert |
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