CN119058983A - Modular drone - Google Patents
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- CN119058983A CN119058983A CN202411258334.9A CN202411258334A CN119058983A CN 119058983 A CN119058983 A CN 119058983A CN 202411258334 A CN202411258334 A CN 202411258334A CN 119058983 A CN119058983 A CN 119058983A
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- 235000014676 Phragmites communis Nutrition 0.000 description 6
- 238000000034 method Methods 0.000 description 4
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- 239000004744 fabric Substances 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/40—Modular UAVs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/50—Launching from storage containers, e.g. from submarine missile tubes
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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
- B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
- B64U2101/18—UAVs specially adapted for particular uses or applications for conventional or electronic warfare for dropping bombs; for firing ammunition
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Abstract
本发明涉及飞行器技术领域，尤其涉及一种模块化无人机，包括前段机身、旋转基座、桨叶模块、后段机身和机翼模块，后段机身连接于前段机身的轴向方向上，无人机可通过前段机身和后段机身形成轴线型结构，旋转基座套设于所述前段机身并与前段机身转动连接，桨叶模块设置于旋转基座的圆周方向并收缩于旋转基座，机翼模块连接于后段机身并收缩于后段机身，桨叶模块和机翼模块分别通过收缩于旋转基座和后段机身，使得无人机实际形成静态棒状结构，便于填入诸如火箭炮或者火炮等管状器物内，进而使得无人机可有效配合火箭炮、火炮和战机的战场发射与投放，使无人机能够即时到达预设战位。
The present invention relates to the technical field of aircraft, and in particular to a modular unmanned aerial vehicle, comprising a front fuselage, a rotating base, a blade module, a rear fuselage and a wing module, wherein the rear fuselage is connected in the axial direction of the front fuselage, and the unmanned aerial vehicle can form an axis-type structure through the front fuselage and the rear fuselage, the rotating base is sleeved on the front fuselage and is rotatably connected to the front fuselage, the blade module is arranged in the circumferential direction of the rotating base and is retracted on the rotating base, the wing module is connected to the rear fuselage and is retracted on the rear fuselage, and the blade module and the wing module are respectively retracted on the rotating base and the rear fuselage, so that the unmanned aerial vehicle actually forms a static rod-shaped structure, which is convenient for filling into tubular objects such as rocket launchers or artillery, so that the unmanned aerial vehicle can effectively cooperate with the battlefield launch and delivery of rocket launchers, artillery and fighter planes, so that the unmanned aerial vehicle can reach a preset battle position in real time.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a modularized unmanned aerial vehicle.
Background
High-tech accurate informationized battlefield reconnaissance information, intelligent remote command and accurate damage have become key factors for determining true win or lose. Due to advantages in terms of concealment, environmental adaptability, control requirements and the like, unmanned aerial vehicles are necessarily replaced with piloted aircraft to become an important combat platform in future warfare.
The active military fixed wing unmanned plane and the fly-following projectile basically adopt the integrated design of the fixed fuselage and the rigid wing, so that the external dimensions, particularly the transverse space occupation of the wingspan, of the fixed fuselage and the rigid wing are large, and the fixed wing unmanned plane and the fly-following projectile cannot be shrunk and filled into tubular objects such as rocket cannons or artillery, so that high-speed rocket shooting and instant shooting are realized. And is also uncomfortable to be thrown by hanging or bundling in the air of the fighter plane. And the machine type has single function and common deviation of universality.
Disclosure of Invention
In view of the above, it is necessary to provide a modularized unmanned aerial vehicle, which solves the technical problems that the unmanned aerial vehicle in the prior art is difficult to adapt to high-speed arrow shooting and fighter aircraft temporary suspension throwing or bundling throwing.
In order to achieve the technical purpose, the technical scheme of the invention provides a modularized unmanned aerial vehicle, which comprises the following components:
a forward section fuselage;
the rotating base is sleeved on the front section machine body and is rotationally connected with the front section machine body;
The paddle module is arranged in the circumferential direction of the rotating base, can be contracted in the rotating base and can be unfolded during flight;
a rear section body connected to the front section body and extending in an axial direction of the front section body, and
The wing module is connected with the rear section fuselage, can be contracted in the rear section fuselage and can be unfolded in flight.
Further, the paddle module comprises a plurality of paddles and a plurality of elastic pieces, each paddle is arranged in the circumferential direction of the rotating base at intervals and hinged with the rotating base, each paddle is contracted in the rotating base, one end of each elastic piece is connected with the rotating base, and each elastic piece is used for driving each paddle to be unfolded when the unmanned aerial vehicle flies.
Further, the unmanned aerial vehicle also comprises a lock, wherein the lock comprises a fairing or a projectile shell.
Further, the front section fuselage includes direction head, power base and afterbody connecting seat, the direction head the power base with the afterbody connecting seat is connected in proper order, rotatory base cover is located the power base, and the accessible the drive of power base rotates, the back section fuselage connect in the afterbody connecting seat.
Further, the tail connecting seat is hinged with the power base, the front section machine body further comprises a steering driving module, and the steering driving module is arranged on the tail connecting seat and is in driving connection with the power base and used for driving the power base to rotate.
Further, the steering driving module comprises a plurality of trip rods and a plurality of steering engines, the trip rods are arranged at intervals along the circumferential direction of the tail connecting seat, one end of each trip rod is hinged with the power base, and each steering engine is arranged in the tail connecting seat and is connected with the other end of each trip rod respectively.
Further, the wing module comprises two wing bags, the two wing bags are respectively connected to two sides of the rear-section fuselage and are wound on the rear-section fuselage, the modularized unmanned aerial vehicle further comprises an inflation source, and the inflation source is connected with the two wing bags and is used for inflating the two wing bags to enable the two wing bags to be unfolded.
Further, the modularized unmanned aerial vehicle further comprises an antenna, wherein the antenna is hinged with the rear-section fuselage and can press the two wing bags in a winding state through rotation around the rear-section fuselage.
Further, the rear section fuselage is kept away from the one end of anterior segment fuselage is provided with the spacing groove, the spacing groove is followed the axial direction of rear section fuselage extends, the antenna articulated in the spacing groove, and the accessible is around the rotation expansion of rear section fuselage.
Further, the wing-envelope comprises a envelope, which is connected to the rear fuselage for deployment when inflated, and plastic flaps (with limit ties), which are attached to the envelope.
Compared with the prior art, the modularized unmanned aerial vehicle has the beneficial effects that the front section of the unmanned aerial vehicle, the rotating base, the blade module, the rear section of the unmanned aerial vehicle and the wing module are arranged, the rear section of the unmanned aerial vehicle is connected to the axial direction of the front section of the unmanned aerial vehicle, the unmanned aerial vehicle can form an axial structure through the front section of the unmanned aerial vehicle and the rear section of the unmanned aerial vehicle, the rotating base is sleeved on the front section of the unmanned aerial vehicle and is rotationally connected with the front section of the unmanned aerial vehicle, the blade module is arranged in the circumferential direction of the rotating base and is contracted on the rotating base, the wing module is connected with the rear section of the unmanned aerial vehicle and is contracted on the rear section of the unmanned aerial vehicle, the blade module and the wing module are respectively contracted on the rotating base and the rear section of the unmanned aerial vehicle, so that the unmanned aerial vehicle can fill in tubular objects such as rocket cannons or artillery, the unmanned aerial vehicle can realize high-speed rocket cannon and cannon firing through the rocket cannon, and the unmanned aerial vehicle can be unfolded after starting, the rotating base drives the blade module to rotate, the unmanned aerial vehicle can be enabled to keep normal flight, and the unmanned aerial vehicle can effectively match with the ground to fast launch and launch through the preset high-speed, reach the landing and the target, and can reach the aircraft through the impulse, and the high-speed can reach the fight and the target, and the target can be directly and the fighted and the target can be directly increased, and the target can be directly and the fighted by the high against the aircraft and the fight and the aircraft.
Drawings
Fig. 1 is a front view of a modular drone provided by an embodiment of the present invention;
fig. 2 is an exploded view of a modular unmanned aerial vehicle provided by an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a modular unmanned aerial vehicle in a flight state according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a rocket shooting state of a modularized unmanned aerial vehicle according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a modular unmanned plane mother machine projection state according to an embodiment of the present invention.
Wherein, each reference sign in the figure:
10-front section fuselage 11-guide head 12-power base
13-Tail connecting seat 14-steering driving module 20-rotating base
30-Blade module 31-blade 40-aft fuselage
41-Limit slot 50-wing module 51-wing bag
60-Fairing 70-antenna 131-hinge ball
141-Steering engine 511-bag clothes 512-plastic wing panel
513-Limit lacing wire 10 a-rocket 20 a-master machine
21 A-launch bay.
Detailed Description
The following detailed description of preferred embodiments of the application is made in connection with the accompanying drawings, which form a part hereof, and together with the description of the embodiments of the application, are used to explain the principles of the application and are not intended to limit the scope of the application.
The current unmanned aerial vehicle mostly adopts non-folding wings or non-deformable wings, when the remote battlefield reconnaissance and accurate striking tasks are executed, the unmanned aerial vehicle can only fly in a fixed wing aircraft mode, the flying speed is low, the flying track is single, the high-speed burst prevention capability is weak, the unmanned aerial vehicle is easily found by battlefield detection radars, the interception probability is high, the task success rate is low, the launch of the current part of unmanned aerial vehicles adopts a launch mode, but the design of the foldable wing unmanned aerial vehicle is independent of the research of a launch system, and the effective combination of the foldable wing unmanned aerial vehicle, the unmanned aerial vehicle missile-borne system and the launch device cannot be realized well.
The embodiment of the invention provides a modularized unmanned aerial vehicle, which can be arranged in a tubular object such as a rocket gun or an artillery through the structural design before taking off, so that high-speed rocket shooting and cannon shooting of the unmanned aerial vehicle can be realized through the rocket gun or the artillery, and the technical problems that the unmanned aerial vehicle in the prior art is difficult to adapt to high-speed rocket shooting and cannon shooting and the aircraft is in overhead suspension or cluster shooting are solved.
To achieve the above technical objective, as shown in fig. 1-5, the modularized unmanned aerial vehicle provided by the embodiment of the invention comprises a front-section fuselage 10, a rotating base 20, a paddle module 30, a rear-section fuselage 40 and a wing module 50, wherein the rotating base 20 is sleeved on the front-section fuselage 10 and is rotationally connected with the front-section fuselage 10, the paddle module 30 is arranged in the circumferential direction of the rotating base 20 and can be contracted in the rotating base 20, the paddle module 30 can be unfolded during flight, the rear-section fuselage 40 is connected with the front-section fuselage 10 and extends towards the axial direction of the front-section fuselage 10, the wing module 50 is connected with the rear-section fuselage 40 and can be contracted in the rear-section fuselage 40, and the wing module 50 can be unfolded during flight.
Specifically, by arranging the front section fuselage 10, the rotating base 20, the blade module 30, the rear section fuselage 40 and the wing module 50, the rear section fuselage 40 is connected to the axial direction of the front section fuselage 10, the unmanned aerial vehicle can form an axial structure through the front section fuselage 10 and the rear section fuselage 40, the rotating base 20 is sleeved on the front section fuselage 10 and is rotationally connected with the front section fuselage 10, the blade module 30 is arranged in the circumferential direction of the rotating base 20 and is contracted in the rotating base 20, the wing module 50 is connected to the rear section fuselage 40 and is contracted in the rear section fuselage 40, the blade module 30 and the wing module 50 are respectively contracted in the rotating base 20 and the rear section fuselage 40, so that the unmanned aerial vehicle can be filled in tubular objects such as rocket cannons or artillery, and further high-speed rocket and gun shooting of the unmanned aerial vehicle can be realized through the rocket cannons or artillery, accelerating unmanned aerial vehicle's start, make unmanned aerial vehicle can reach the battle place of predetermineeing in the twinkling of an eye, unmanned aerial vehicle starts the back, paddle module 30 and wing module 50 expand, and swivel base 20 drives paddle module 30 rotation, paddle module 30 provides unmanned aerial vehicle flight's power through the rotation, wing module 50 guarantees the equilibrium of flight state, make unmanned aerial vehicle keep normal flight, through above structure, make unmanned aerial vehicle can effectively cooperate rocket gun, artillery and fight's battle field emission and throwing, the traction flight of rethread self power and the high-lift of wing coast, can increase its flight course and dead time notably, better to carry out investigation, battle field tasks such as electronic war, can directly attack or destroy enemy high-value target even.
It is understood that the front-stage body 10 may have any axial structure, and the front-stage body 10 may drive the rotating base 20 to rotate by providing a driving device such as a motor connected to the rotating base 20.
In one embodiment, as shown in fig. 1-5, the front section of the body 10 includes a guiding head 11, a power base 12 and a tail connecting seat 13, the guiding head 11, the power base 12 and the tail connecting seat 13 are sequentially connected, the rotating base 20 is sleeved on the power base 12 and can rotate by driving of the power base 12, and the rear section of the body 40 is connected to the tail connecting seat 13. Specifically, the front end of the guiding head 11 is in a conical or curved structure, so that the flight resistance of the unmanned aerial vehicle is reduced, the unmanned aerial vehicle is guided to fly, the power base 12 can be connected with the rotating base 20 and drives the rotating base 20 to rotate, so as to drive the blade module 30 to rotate, the tail connecting seat 13 can be connected with the rear-section machine body 40, and the guiding head 11, the power base 12 and the tail connecting seat 13 can be sequentially connected to form an axial structure of the front-section machine body 10.
In this embodiment, the power base 12 is a stator of a motor, the rotating base 20 is a rotor of the motor, and the power base 12 drives the rotating base 20 to rotate by a magnetic force acting on the rotor.
In this embodiment, the tail connecting seat 13 may be fixedly connected with the power base 12, and connected in a rotational connection manner.
In this embodiment, the guide head 11 is a front section of the fuselage 10 that provides substantial guiding.
In this embodiment, the power base 12 and the tail connector 13 may be used to install a guided flight control system device, a power source, and a gas source, which are actually the middle fuselage of the central control portion of the unmanned aerial vehicle.
In this embodiment, the aft fuselage 40 is a mission module section, such as a scout warfare cabin, an electronics warfare cabin, a high explosive bomb cabin, and a warm-pressure bomb cabin.
In one embodiment, as shown in fig. 1-5, the tail connecting seat 13 is hinged with the power base 12, and the front section of the body 10 further comprises a steering driving module 14, wherein the steering driving module 14 is installed on the tail connecting seat 13 and is in driving connection with the power base 12, so as to drive the power base 12 to rotate. Specifically, the tail connecting seat 13 is hinged to the power base 12, so that the tail connecting seat 13 can turn around the power base 12, when the unmanned aerial vehicle flies, the steering driving module 14 drives the power base 12 to rotate, and therefore the power base 12 and the guide head can be driven to steer, and further the unmanned aerial vehicle steering control is realized.
In one embodiment, as shown in fig. 2, a ball groove is formed at one end of the power base 12 near the tail connection seat 13, and a hinge ball 131 is formed at one end of the tail connection seat 13 near the power base 12, where the hinge ball 131 is hinged to the ball groove.
In one embodiment, as shown in fig. 1-5, the steering driving module 14 includes a plurality of trip bars 141 and a plurality of steering gears, each trip bar 141 is disposed at intervals along the circumferential direction of the tail connecting seat 13, one end of each trip bar 141 is hinged with the power base 12, and each steering gear is disposed inside the tail connecting seat 13 and is respectively connected with the other end of each trip bar 141. Specifically, each of the traveling bars 141 is connected to the power base 12, and the steering engine can respectively provide a pulling force for each of the traveling bars 141, so that each of the traveling bars 141 drives the power base 12 to swing, and each of the traveling bars 141 drives the power base 12, thereby realizing steering of the unmanned aerial vehicle.
In this embodiment, as shown in fig. 1-5, the number of the free rods 141 is 4, two free rods 141 on the left and right sides are used for controlling the steering of the unmanned aerial vehicle in the left and right direction, and two free rods 141 on the upper and lower sides are used for controlling the steering of the unmanned aerial vehicle in the up and down direction, so that the omnidirectional vector adjustment capability of 360 ° head shaking is provided.
In this embodiment, when the unmanned aerial vehicle needs to be adjusted according to its own seeker information or a background flight control instruction, the information instruction is first decomposed into different electrical signals by the AI intelligent electronic annunciator (comprehensive electrical control), and the electrical signals are distributed to the (4 steering engines) of the vector maneuvering instruction executing mechanism to respectively perform pushing and pulling actions of different strokes, and then the specific deflection of the power base 12 is jointly regulated by the real-time vector through the swimming control of the flight control pull rod connecting device, when the two forms a certain included angle, the power base 12 can generate a new swinging head pointing direction, and the propeller blade 31 of the middle power base 12 can also directly generate pulling force on the new pointing direction, so that the flight direction or flight attitude of the whole unmanned aerial vehicle is timely changed, thereby realizing the self intelligent adjustment or the rear instruction flight control of the unmanned aerial vehicle.
The fixed wing unmanned aerial vehicle is different from a fixed wing unmanned aerial vehicle which adopts a plurality of flight control steering engines to respectively control horizontal and vertical control surfaces in active service, and the flight direction and the gesture of the unmanned aerial vehicle can be slowly adjusted by changing the direction of the control surfaces to influence the air flow of the control surfaces. The steering flight control system of the modularized unmanned aerial vehicle provided by the embodiment of the invention can jointly and rapidly adjust the swing head direction of the front-section fuselage 10 (and the nose) by a vector, and the propeller blades 31 can directly exert force in a new direction to complete instant regulation and control, so that the modularized unmanned aerial vehicle is an unmanned aerial vehicle which directly completes vector flight control through main power, and has the advantages of sensitive response and flexible maneuvering.
It will be appreciated that the blade module 30 may be deployed under the centrifugal effect of the rotation of the rotating base 20 or by the elastic force of the auxiliary elastic member.
In one embodiment, as shown in fig. 1-5, the paddle module 30 includes a plurality of paddles 31 and a plurality of elastic members (not shown), each paddle 31 is disposed at intervals in a circumferential direction of the rotating base 20 and hinged to the rotating base 20, each paddle 31 is retracted in the rotating base 20, one end of each elastic member is connected to the rotating base 20, and each elastic member is used for driving each paddle 31 to be extended when the unmanned aerial vehicle flies. Specifically, the paddle module 30 is provided with the paddles 31 and the elastic members, when the unmanned aerial vehicle is in a flying state, each paddle 31 is unfolded under the elastic force action of the elastic members, so that power is provided for the flying of the unmanned aerial vehicle, the elastic members can not only provide power for the unfolding of the paddles 31, but also adaptively adjust the angles of the paddles 31 according to the rotating speed of the paddles 31, and therefore the stable flying of the unmanned aerial vehicle is ensured.
In this embodiment, the elastic member is actually a deformable strip spring reed, one end of the spring reed far away from the hinge at the root of the blade 31 is fixed on the rotating base 20, and the other end of the spring reed is in a free state. When the blade 31 is folded, the reed is flattened, and when the blade 31 is released, the elastic reed bounces to assist, and after the blade is erected, the free end of the elastic reed props against the root of the blade 31, so that the blade 31 is prevented from being stressed to fall back.
It will be appreciated that each blade 31 may be retracted within the rotating base 20 by a restraining action of a locking ring or the like.
In one embodiment, as shown in fig. 1, the drone also includes a lock that includes a fairing 60 or a projectile shell. Specifically, the unmanned aerial vehicle simplifies the structure of the unmanned aerial vehicle by using a fairing of a rocket or a projectile shell of an artillery. The unmanned aerial vehicle starts the working process of starting, when unmanned aerial vehicle is launched or put into ideal start position, generally set up in rocket, the highest point or the furthest point of the trajectory of the gun-carried bullet, after the shell is thrown in the automatic fracture of the radome of the gun-carried bullet or the bullet shell of the gun-carried bullet. The propeller blades 31 of the unmanned aerial vehicle are then sprung and spread by the pushing of the elastic member, and generate flying power as the rotating base 20 rotates.
In one embodiment, as shown in fig. 1-5, the wing module 50 includes two wing bags 51, where the two wing bags 51 are respectively connected to two sides of the aft fuselage 40 and wound around the aft fuselage 40, and the modular unmanned aerial vehicle further includes an inflation source (not shown) connected to the two wing bags 51 for inflating the two wing bags 51 to expand the two wing bags 51. Specifically, the two wing bags 51 are wound around the rear-section fuselage 40, so that the contraction of the rear-section fuselage 40 is realized, and in the take-off stage of the unmanned aerial vehicle, the two wing bags 51 are inflated by the inflation source, so that the wing bags 51 are inflated to be unfolded, and the wing bags 51 in the unfolded state can provide balance and lifting force for the flight of the unmanned aerial vehicle.
In one embodiment, as shown in FIG. 3, wing bladder 51 includes a bladder skin 511 and a plastic flap 512, bladder skin 511 being connected to aft section fuselage 40 for deployment upon inflation, plastic flap 512 being attached to bladder skin 511. Specifically, the bag cover 511 has better flexibility and air tightness, the wing structure can be formed by the inflated bag body, the plastic wing 512 is made of semi-hard material, the plastic wing 512 has certain elastic performance, and the bag cover 511 can be shaped, so that the bag cover 511 is prevented from being wrinkled in a winding state.
In this embodiment, the bag cover 511 is made of glued fabric, the glued fabric has better flexibility and air tightness, and the semi-hard plastic wing pieces 512 are externally or internally attached to the bag cover 511, have certain rebound performance, help the bag cover 511 to be unfolded, and form an exoskeleton structure of the bag cover 511.
In this embodiment, as shown in fig. 3, a plurality of spacing lacing wires 513 with different heights are arranged between the wings to strengthen the structure of the wing-bag 51, thereby facilitating shaping of the wing-bag 51.
In this embodiment, as shown in fig. 3, the inflated wing bladder 51 is configured as a delta wing by the shaping action of the limit tie 513. The longitudinal section of the filled aerofoil 51 is a smooth wing shape, which is beneficial to aerodynamics and lift force of flight, and the transverse section is a triangle with high middle and low outer and is beneficial to enhancing the loading capacity of the wing.
In one embodiment, as shown in fig. 1-5, the modular unmanned aerial vehicle further includes an antenna 70, the antenna 70 being hinged to the aft fuselage 40 and operable to compress the two wing bladders 51 in a rolled configuration by rotation about the aft fuselage 40. Specifically, the antenna 70 can compress the two wing bags 51 in the winding state to limit the wing bags 51, so that the wing bags 51 are stably wound on the rear-section fuselage 40, and the antenna 70 of the unmanned aerial vehicle can lock the wing bags 51 in the two winding states without setting other locking structures, thereby simplifying the unmanned aerial vehicle structure.
In this embodiment, when the flexible wing airbag 51 in the curl tightening is loosened after losing the grip of whip antenna 70, and is pushed by the rebound stress of its superficial semi-rigid plastic wing 512, and the airbag 51 is deployed under inflation of the inflation source.
In this embodiment, the antenna 70 is limited by a lock frame on the outer side, the lock frame can be any locking structure such as an electromagnetic valve which can lock the antenna 70, the lock frame locks the antenna 70, further presses the wing bags 51, the wing bags 51 are in a tightened state, after the unmanned aerial vehicle casts or projects, the lock frame unlocks the antenna, the antenna 70 is sprung out, and is separated from the pressing of the wing bags 51, so that the wing bags 51 are loosened, the wing bags 51 loose after losing the limit of the whip antenna 70, and are pushed by the rebound stress of the semi-rigid plastic wings 512 on the surface layers of the wing bags, and the two wing bags 51 are unfolded under the inflation of the two wing bags 51 by the inflation source.
In one embodiment, as shown in fig. 2-3, a limit groove 41 is provided at an end of the rear body 40 remote from the front body 10, the limit groove 41 extends in an axial direction of the rear body 40, and an antenna 70 is hinged to the limit groove 41 and can be unfolded by rotating around the rear body 40. Specifically, by the limiting action of the limiting groove 41, the unfolded antenna 70 extends along the axial direction of the rear section of the fuselage 40, and the trimming of the whole machine is provided for the flight of the unmanned aerial vehicle.
It can be understood that the antenna 70 may be sprung through its own elastic force, or the elastic force of the elastic sheet disposed between the antenna 70 and the rear-section body 40, and the sprung antenna 70 may be kept horizontal with the rear-section body 40 by the limit of the limit slot 41 or the elastic force of the elastic sheet.
The specific working principle of the unmanned aerial vehicle provided by the embodiment of the invention is that the unmanned aerial vehicle has the characteristics of static rod-shaped structure, no span of transverse occupying size before starting, and the like by the characteristics of the curling of the inflatable wing bags 51, the folding of the paddles 31 and the like, so that the unmanned aerial vehicle can be suitable for being filled into or rocket cannon, artillery and other tubular objects, and high-speed starting of rocket shooting, cannon shooting or aircraft projection is realized,
As shown in fig. 4, when the unmanned aerial vehicle performs rocket 10a rocket firing, the rod-shaped unmanned aerial vehicle is accommodated in the fairing 60 and is mounted on the rocket 10a, after the rocket 10a is launched to make the unmanned aerial vehicle start, when the unmanned aerial vehicle is launched or put into an ideal starting position, the fairing 60 of the rocket gun carrier or the projectile shell of the rocket gun carrier (generally set at the highest point or the farthest point of the trajectory of the rocket gun or the gun carrier) automatically cracks and throws the shell, and the paddle 31 is unfolded;
As shown in fig. 5, when the unmanned aerial vehicle is thrown in the mother aircraft 20a, the unmanned aerial vehicle in the throwing cabin 21a of the mother aircraft 20a is thrown in the mother aircraft 20a in the flying process, and when the unmanned aerial vehicle falls to a certain height, the blades 31 are unfolded;
The paddle 31 rotates under the drive of the power base 12 to generate flying power to pull the unmanned aerial vehicle to fly, meanwhile, the antenna 70 bounces and swings to keep level with the rear section of the fuselage, the whole machine is balanced, the wing bags 51 of the flexible wings in the curling and tightening process loose when the flexible wings lose the clamping limit of the whip antenna 70 and are pushed by the rebound stress of the semi-rigid plastic wings 512 on the surface layers of the wing bags, the wing bags 51 are expanded under the inflation of the inflation source to lift and slide the unmanned aerial vehicle, the quality of the unmanned aerial vehicle can be reduced through the structural arrangement of the wing bags 51 and the like, the unmanned aerial vehicle structure is simplified, the flight range and the idle time of the unmanned aerial vehicle are remarkably increased, further, the more on-time stable execution of the work task of the unmanned aerial vehicle is guaranteed, after the unmanned aerial vehicle enters a cruising flight state, a flight scheme is determined by an on-board computer according to the task requirement and the current environment, and task decomposition and distribution are carried out, and auxiliary on-board, reconnaissance and hit modules are respectively started to execute on-board reconnaissance, target following, remote or other preset tasks and temporary tasks.
According to the modularized unmanned aerial vehicle, the characteristics of effective curling of the inflatable flexible wing, folding of the propeller blades and the like are utilized to realize an actual static rod-shaped structure, and the span of the transverse space occupation size is avoided before starting. And fully combines the flexible selection of the mission module of the rear section fuselage 40. Is particularly suitable for being filled in tubular objects such as rocket guns, artillery guns and the like, and realizes the battlefield instant in place of high-speed rocket shooting and gun shooting. The method is also suitable for hanging throwing or bundling throwing of the fighter in the sky.
Meanwhile, the modularized flexible-wing unmanned aerial vehicle effectively cooperates with battlefield launching and throwing of rocket guns, artillery and fighters, and the flight range and the air-stagnation time of the unmanned aerial vehicle can be obviously increased through traction flight of the blades 31 and lift-increasing sliding of the wing bags 51, so that battlefield tasks such as investigation, electronic warfare and the like can be better executed, and even enemy high-value targets can be directly attacked or detonated in a gap to be destroyed.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the technical scope of the present invention should be included in the scope of the present invention.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411258334.9A CN119058983A (en) | 2024-09-09 | 2024-09-09 | Modular drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411258334.9A CN119058983A (en) | 2024-09-09 | 2024-09-09 | Modular drone |
Publications (1)
| Publication Number | Publication Date |
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| CN119058983A true CN119058983A (en) | 2024-12-03 |
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ID=93631199
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202411258334.9A Pending CN119058983A (en) | 2024-09-09 | 2024-09-09 | Modular drone |
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| Country | Link |
|---|---|
| CN (1) | CN119058983A (en) |
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2024
- 2024-09-09 CN CN202411258334.9A patent/CN119058983A/en active Pending
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