CN111452948B - Self-destructible fixed wing unmanned aerial vehicle based on electromagnetic force - Google Patents
Self-destructible fixed wing unmanned aerial vehicle based on electromagnetic force Download PDFInfo
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- CN111452948B CN111452948B CN202010187801.9A CN202010187801A CN111452948B CN 111452948 B CN111452948 B CN 111452948B CN 202010187801 A CN202010187801 A CN 202010187801A CN 111452948 B CN111452948 B CN 111452948B
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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
- B64C1/061—Frames
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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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
Abstract
The utility model provides a but self-destruction fixed wing unmanned aerial vehicle based on electromagnetic force, relates to a for military use unmanned aerial vehicle technique, in order to solve current self-destruction method and need unmanned aerial vehicle self to carry initiating explosive device and initiating explosive device explosion can produce the influence to the normal pedestrian activity on ground, and initiating explosive device can additionally increase the problem of unmanned aerial vehicle weight simultaneously. The controller is used for controlling the normally open switch of the electromagnetic relay to be closed after receiving the self-destruction remote control signal or automatically starting the self-destruction program, so that the energy storage circuit supplies power to the electromagnetic coil; the inner rod coil and the outer rod coil are respectively fixed in the framework, and are coaxial and close to each other; when the current of the inner rod coil is the same as that of the outer rod coil, the winding directions of the inner rod coil and the outer rod coil are opposite; when the currents of the inner rod coil and the outer rod coil are opposite, the winding directions of the inner rod coil and the outer rod coil are the same. The safety coefficient is high, and the controllability is strong, moreover more environmental protection.
Description
Technical Field
The invention relates to a military unmanned aerial vehicle technology.
Background
With the development of the unmanned aerial vehicle technology, the unmanned aerial vehicle is widely applied to the fields of natural disaster prevention and treatment, urban and rural construction and planning, scientific observation, public security frontier defense, express transportation, maritime affairs, petroleum, electric power, agriculture, forestry, performance and the like. Meanwhile, the frequency of the crash accidents of the unmanned aerial vehicle is higher and higher due to the performance problem of the unmanned aerial vehicle or the fact that the unmanned aerial vehicle is interfered and attacked; the crash consequence of the unmanned aerial vehicle is serious, on one hand, information carried by the unmanned aerial vehicle is leaked, and confidentiality and privacy cannot be effectively protected; on the other hand, the ground pedestrian or the ground building is easily damaged, and great economic loss is brought; therefore, the drone needs to have a self-destruction function. At present, the self-destruction function is mainly used for weapons such as military missiles, rockets and the like, and self-destruction is realized by utilizing a self-destruction program to detonate self-destruction initiating explosive devices.
This kind of current self-destruction method needs unmanned aerial vehicle self to carry the initiating explosive device, and the initiating explosive device itself has certain danger, and unmanned aerial vehicle belongs to low-altitude aircraft, and low-altitude explodes and to produce the influence to the normal pedestrian activity on ground certainly, and the initiating explosive device can additionally increase unmanned aerial vehicle weight moreover.
Disclosure of Invention
The invention aims to solve the problems that the existing self-destruction method needs the unmanned aerial vehicle to carry initiating explosive devices, the normal activities of pedestrians on the ground can be influenced by the explosion of the initiating explosive devices, and meanwhile, the weight of the unmanned aerial vehicle can be additionally increased by the initiating explosive devices; but provide a self-destruction fixed wing unmanned aerial vehicle based on electromagnetic force.
The invention relates to an electromagnetic force-based self-destructible fixed wing unmanned aerial vehicle, which comprises a machine head, a machine body, a first wing, a second wing and a plurality of frameworks, wherein the machine head is connected with the machine body through a first connecting rod;
the aircraft nose is fixed at the front end of the aircraft body through a framework, and the first wing and the second wing are respectively fixed at the left end and the right end of the aircraft body through the framework;
the fixed-wing unmanned aerial vehicle also comprises a self-destruction device; the self-destruction devices are respectively arranged in each framework;
the self-destruction device comprises an energy storage circuit, an electromagnetic coil, an electromagnetic relay, a controller and a mounting assembly;
the electromagnetic relay is a normally open type electromagnetic relay;
the controller is used for controlling the normally open switch of the electromagnetic relay to be closed after receiving the self-destruction remote control signal or automatically starting the self-destruction program, so that the energy storage circuit supplies power to the electromagnetic coil;
the electromagnetic coil comprises an inner rod coil and an outer rod coil; the mounting assembly comprises an inner rod mounting assembly and an outer rod mounting assembly; the inner rod coil is fixed in the framework through the inner rod mounting assembly, the outer rod coil is fixed in the framework through the outer rod mounting assembly, the inner rod coil and the outer rod coil are coaxially arranged along the framework, and one end of the inner rod coil is close to one end of the outer rod coil; the current directions of the energized inner rod coil and the energized outer rod coil are the same, and the winding directions of the inner rod coil and the outer rod coil are opposite; when the current flow directions of the energization of the inner rod coil and the outer rod coil are opposite, the winding directions of the inner rod coil and the outer rod coil are the same.
The working principle of the invention is as follows: after this fixed wing unmanned aerial vehicle's controller received the self-destruction remote control signal or this fixed wing unmanned aerial vehicle has the crash risk and can't save the time, controller control electromagnetic relay's normally open switch is closed for the energy storage circuit is the solenoid power supply, the profile center of interior pole coil and outer pole coil can produce opposite direction's electromagnetic field this moment, interior pole coil and outer pole coil separate under the interact power of electromagnetic field, thereby lead to the skeleton to disintegrate, finally make this fixed wing unmanned aerial vehicle self-destruction.
The invention has the advantages that the self-destruction device is manufactured by using the electromagnetic force as the explosive force, and compared with the existing self-destruction device which is detonated by depending on initiating explosive devices, the self-destruction device has high safety coefficient, strong controllability and more environmental protection; the fixed-wing unmanned aerial vehicle with the self-destruction device self-destroys the unmanned aerial vehicle by acquiring the flight state of the unmanned aerial vehicle and starting the self-destruction device immediately before the crash, so that the damage and damage to ground pedestrians and buildings are reduced, the safety factor of the aircraft is improved, and meanwhile, the information carried by the unmanned aerial vehicle is protected; the self-destruction device converts electric energy into kinetic energy, the conversion efficiency is high, and excessive energy loss cannot be brought to the unmanned aerial vehicle; the mounting assembly of the self-destruction device can be made into a bearing beam structure of the unmanned aerial vehicle, and the fixed wing unmanned aerial vehicles with different length wingspans are all suitable.
Drawings
Fig. 1 is a schematic overall structure diagram of a self-destructible fixed wing drone based on electromagnetic force according to a first embodiment;
fig. 2 is a schematic diagram of an explosive structure of a self-destructible fixed wing drone based on electromagnetic force according to one embodiment;
fig. 3 is a schematic diagram of a split structure of a self-destructible fixed wing drone based on electromagnetic force according to a first embodiment;
FIG. 4 is a circuit diagram illustrating a self-destruction principle of a self-destruction apparatus according to one embodiment;
FIG. 5 is a sectional view of a portion of a planar construction of a mounting assembly according to one embodiment;
FIG. 6 is a schematic external view of a mounting assembly according to one embodiment;
FIG. 7 is a perspective sectional view of a mounting assembly according to one embodiment;
fig. 8 is a circuit diagram of a charging circuit in the third embodiment.
Detailed Description
The first specific implementation way is as follows: the embodiment is described with reference to fig. 1 to 7, and the fixed-wing drone capable of self-destruction based on electromagnetic force according to the embodiment includes a nose 101, a fuselage 102, a first wing 103, and a second wing 104;
the aircraft nose 101 is fixed at the front end of the aircraft body 102, and the first wing 103 and the second wing 104 are respectively fixed at the left end and the right end of the aircraft body 102 through frameworks;
the fixed wing unmanned aerial vehicle also comprises a self-destruction device 2; the self-destruction devices 2 are respectively arranged in each framework;
the self-destruction device 2 comprises an energy storage circuit 8, an electromagnetic coil 4, an electromagnetic relay 6, a controller 9 and a mounting component 3;
the electromagnetic relay 6 is a normally open type electromagnetic relay;
the controller 9 is used for controlling the normally open switch of the electromagnetic relay 6 to be closed after receiving the self-destruction remote control signal or automatically starting the self-destruction program, so that the energy storage circuit 8 supplies power to the electromagnetic coil 4;
the electromagnetic coil 4 includes an inner rod coil 401 and an outer rod coil 402; the mounting assembly 3 comprises an inner rod mounting assembly 302 and an outer rod mounting assembly 303; the inner rod coil 401 is fixed in the framework through the inner rod mounting component 302, the outer rod coil 402 is fixed in the framework through the outer rod mounting component 303, the inner rod coil 401 and the outer rod coil 402 are coaxially arranged along the framework, and one end of the inner rod coil 401 is close to one end of the outer rod coil 402; the current flow directions of the energization of the inner rod coil 401 and the outer rod coil 402 are the same, and the winding directions of the inner rod coil 401 and the outer rod coil 402 are opposite; when the currents applied to the inner rod coil 401 and the outer rod coil 402 are opposite in direction, the inner rod coil 401 and the outer rod coil 402 are wound in the same direction.
In the embodiment, the fixed-wing unmanned aerial vehicle is simultaneously provided with a camera, an infrared probe, an ultrasonic real-time monitoring system and an inertial sensor, wherein the inertial sensor acquires attitude, speed and acceleration data of the unmanned aerial vehicle in real time, and the camera, the infrared probe and the ultrasonic real-time monitoring system monitor the flight environment of the unmanned aerial vehicle in real time; the controller 9 judges whether to autonomously start the self-destruction program according to the information; therefore, the fixed-wing unmanned aerial vehicle has two self-destruction modes, wherein one mode is a remote artificial remote control self-destruction mode, the other mode is an autonomous control self-destruction mode, and the priority of the remote artificial remote control self-destruction mode is higher than that of the autonomous control self-destruction mode; wherein, the manual remote control self-destruction mode is to send a self-destruction remote control signal to the controller 9 through a remote controller; each group of inner rod coils 401 and outer rod coils 402 form a blasting point, and the position of the blasting point is adjusted according to the frame of the airplane body; the blasting intensity of each blasting point is controllable, the blasting intensity is determined by the current intensity obtained by the inner rod coil 401 and the outer rod coil 402 and the number of turns of the inner rod coil 401 and the outer rod coil 402, and the blasting intensity is adjustable before the fixed-wing unmanned aerial vehicle takes off; the energy storage circuit 8 provides a strong pulse circuit for the inner rod coil 401 and the outer rod coil 402, and the on-off of the circuit is controlled by the flight controller 9 through the electromagnetic relay 6, so that the starting reliability of the self-destruction device 2 is ensured. In the installation process, the inner rod coil 401 and the outer rod coil 402 need to be wound tightly, the number of turns of each coil is more than 100, and the energizing current of the inner rod coil 401 and the outer rod coil 402 is more than 3A; the fixed wing unmanned aerial vehicle has high strength, and the current and the number of turns of a coil need to be increased to increase the electromagnetic force, so that the explosive force is increased; the method of increasing the current is to increase the capacitance in the tank circuit 8. Meanwhile, when the magnetic pole coil is installed, the magnetic force surfaces of the inner pole coil 401 and the outer pole coil 402 are coaxial and cannot be overlapped, and the distance between the two magnetic force surfaces is 1mm-5mm; the lengths of the inner rod mounting assembly 302 and the outer rod mounting assembly 303 are matched with the power-on time length, and the current pulse time width is equal to the separation time length of the inner rod mounting assembly 302 and the outer rod mounting assembly 303.
In the embodiment, the inner rod coil 401 and the outer rod coil 402 are separated under the interaction force of the electromagnetic field, so that the framework is disassembled, and finally the fixed-wing unmanned aerial vehicle is self-destructed; the interaction force of the electromagnetic field can also be derived from the fact that the single coil is connected with variable current, induced current is generated in the other coil, and the two coils can still generate the interaction force, so that a group of driving circuits can be reduced; besides the unidirectional magnetic field interaction force, a linkage structure can be additionally arranged on the mechanical structure, so that the blasting effect of the magnetic field interaction force is fully exerted.
The second embodiment is as follows: the present embodiment is further defined by the electromagnetic force-based self-destructible fixed wing drone of the first embodiment, wherein the frame comprises spars, stringers and ribs;
an inner rod coil 401 and an outer rod coil 402 are fixed in the spar and the stringer respectively.
The third concrete implementation mode: the present embodiment is described with reference to fig. 8, and is further limited to the first embodiment of the self-destructible fixed wing drone based on electromagnetic force, in the present embodiment, the energy storage circuit 8 is provided with a charging interface 7, and the self-destruct device 2 further includes a charging circuit 5;
the charging circuit 5 comprises a power supply VCC, a boosting module 501 and a rectifying module 502;
the power input end of the boost module 501 is connected with the output end of the power VCC, and the grounding end of the boost module 501 is grounded; the positive output end of the boosting module 501 is connected with the positive input end of the rectifying module 502, and the negative output end of the boosting module 501 is connected with the negative input end of the rectifying module 502; the ground terminal of the rectifier module 502 is grounded, and the interface output terminal of the rectifier module 502 is connected to the charging interface 7. The boost module 501 and the rectifier module 502 can realize the quick and smooth charging function of the low-voltage power supply.
In the present embodiment, one charging circuit 5 may charge a plurality of tank circuits 8; the charging circuit 5 can be installed on the fixed-wing unmanned aerial vehicle, can also be independent of the self-destruction device 2, is not installed on the fixed-wing unmanned aerial vehicle, and only needs to be charged with electricity to the energy storage circuit 8 before the fixed-wing unmanned aerial vehicle takes off, so that the load of the fixed-wing unmanned aerial vehicle is reduced.
The fourth concrete implementation mode: in this embodiment, the self-destructible fixed wing drone based on electromagnetic force according to the first embodiment is further defined, in this embodiment, the mounting assembly 3 further includes an inner rod lead 301 and an outer rod lead 304;
the inner rod lead 301 is connected with one end of the inner rod coil 401 and one end of the outer rod coil 402 respectively and is led out from the end part of the inner rod installation component 302; the outer rod lead 304 is connected to the other end of the inner rod coil 401 and the other end of the outer rod coil 402, respectively, and is led out from the end of the outer rod mounting assembly 303.
The fifth concrete implementation mode is as follows: the embodiment is further limited to the first specific embodiment, in which the inner rod mounting assembly 302 is a circular tube or a square tube; the outer pole mounting assembly 303 is a round tube or a square tube.
In this embodiment, the shapes of the inner rod mounting assembly 302 and the outer rod mounting assembly 303 may be adjusted according to the requirements of the fixed wing drone; the shape of inner pole coil 401 and outer pole coil 402 coil can also be adjusted according to this fixed wing unmanned aerial vehicle demand.
Claims (5)
1. A self-destructible fixed wing drone based on electromagnetic force, the fixed wing drone comprises a nose (101), a fuselage (102), a first wing (103), a second wing (104) and a plurality of skeletons;
the aircraft nose (101) is fixed at the front end of the aircraft body (102) through a framework, and the first wing (103) and the second wing (104) are respectively fixed at the left end and the right end of the aircraft body (102) through the framework;
the fixed wing unmanned aerial vehicle is characterized by also comprising a self-destruction device (2); the self-destruction devices (2) are respectively arranged in each framework;
the self-destruction device (2) comprises an energy storage circuit (8), an electromagnetic coil (4), an electromagnetic relay (6), a controller (9) and a mounting component (3);
the electromagnetic relay (6) is a normally open electromagnetic relay;
the controller (9) is used for controlling the normally open switch of the electromagnetic relay (6) to be closed after receiving the self-destruction remote control signal or automatically starting the self-destruction program, so that the energy storage circuit (8) supplies power to the electromagnetic coil (4);
the electromagnetic coil (4) comprises an inner rod coil (401) and an outer rod coil (402); the mounting component (3) comprises an inner rod mounting component (302) and an outer rod mounting component (303); the inner rod coil (401) is fixed in the framework through the inner rod mounting component (302), the outer rod coil (402) is fixed in the framework through the outer rod mounting component (303), the inner rod coil (401) and the outer rod coil (402) are coaxially arranged along the framework, and one end of the inner rod coil (401) is close to one end of the outer rod coil (402); the current flow directions of the energization of the inner rod coil (401) and the outer rod coil (402) are the same, and the winding directions of the inner rod coil (401) and the outer rod coil (402) are opposite; when the current flow directions of the energization of the inner rod coil (401) and the outer rod coil (402) are opposite, the winding directions of the inner rod coil (401) and the outer rod coil (402) are the same.
2. The electromagnetic force based self-destructible fixed wing drone of claim 1, wherein the skeleton comprises spars, stringers and ribs;
an inner rod coil (401) and an outer rod coil (402) are fixed in the spar and the stringer respectively.
3. The self-destructible fixed wing drone based on electromagnetic force according to claim 1, characterised by the fact that the energy storage circuit (8) is provided with a charging interface (7) and the self-destruct device (2) further comprises a charging circuit (5);
the charging circuit (5) comprises a power supply VCC, a boosting module (501) and a rectifying module (502);
the power supply input end of the boost module (501) is connected with the output end of the power supply VCC, and the grounding end of the boost module (501) is grounded; the positive output end of the boosting module (501) is connected with the positive input end of the rectifying module (502), and the negative output end of the boosting module (501) is connected with the negative input end of the rectifying module (502); the grounding end of the rectifying module (502) is grounded, and the interface output end of the rectifying module (502) is connected with the charging interface (7).
4. The self-destructible fixed wing drone based on electromagnetic force according to claim 1, characterised by the mounting assembly (3) further comprising an inner pole wire (301) and an outer pole wire (304);
the inner rod lead (301) is connected with one end of the inner rod coil (401) and one end of the outer rod coil (402) respectively and is led out from the end part of the inner rod mounting component (302); and the outer rod lead (304) is connected with the other end of the inner rod coil (401) and the other end of the outer rod coil (402) respectively and is led out from the end part of the outer rod mounting component (303).
5. The self-destructible fixed wing drone based on electromagnetic force of claim 1, characterized by the inner rod mounting assembly (302) being a circular or square tube; the outer rod mounting component (303) is a round pipe or a square pipe.
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| CN202010187801.9A CN111452948B (en) | 2020-03-17 | 2020-03-17 | Self-destructible fixed wing unmanned aerial vehicle based on electromagnetic force |
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| CN202010187801.9A CN111452948B (en) | 2020-03-17 | 2020-03-17 | Self-destructible fixed wing unmanned aerial vehicle based on electromagnetic force |
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| CN111452948B true CN111452948B (en) | 2023-02-17 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US10604251B2 (en) * | 2016-09-29 | 2020-03-31 | Mcafee, Llc | Apparatus and methods for unmanned aerial vehicle servicing of modular device assembly |
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| US4651955A (en) * | 1984-05-07 | 1987-03-24 | Deutsche Airbus Gmbh | Device for automatically controllable unloading of aircraft wings |
| GB201214896D0 (en) * | 2012-08-21 | 2012-10-03 | Messier Dowty Ltd | A brake assembly and a method of operating a brake assembly |
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