CN110307755B - High-power microwave source system of unmanned drone aircraft - Google Patents
High-power microwave source system of unmanned drone aircraft Download PDFInfo
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- CN110307755B CN110307755B CN201910415793.6A CN201910415793A CN110307755B CN 110307755 B CN110307755 B CN 110307755B CN 201910415793 A CN201910415793 A CN 201910415793A CN 110307755 B CN110307755 B CN 110307755B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J9/00—Moving targets, i.e. moving when fired at
- F41J9/08—Airborne targets, e.g. drones, kites, balloons
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B1/00—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission
- H04B1/02—Transmitters
- H04B1/04—Circuits
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Abstract
The invention provides a high-power microwave source system of an unmanned drone aircraft, which comprises a fixed power supply and control system and a microwave source emission subsystem, wherein the power supply and control system is electrically connected with the microwave source emission subsystem; the supporting bracket is of a hollow structure, and the side surface of the supporting bracket is provided with a reinforcing rib group. The power supply and control system comprises a base, a main control board, a battery and a battery box, wherein the battery box is fixedly arranged on the base, the main control board is fixed on the base and positioned outside the battery box, and the main control board is electrically connected with the battery. The microwave source emission subsystem comprises an antenna support, a servo system, an antenna, a conversion waveguide, an isolator and a magnetron, wherein the antenna, the conversion waveguide, the isolator and the magnetron are sequentially connected, the antenna is fixedly installed on the servo system, one side, away from the antenna, of the servo system is hinged to a support, the magnetron is fixedly connected with the antenna through the antenna support, and the magnetron is electrically connected with a main control board through a high-strength cable.
Description
Technical Field
The invention relates to the technical field of unmanned drone aircraft, in particular to a high-power microwave source system of an unmanned drone aircraft.
Background
The unmanned target drone is an important branch in the family of unmanned aerial vehicles, is mainly used for simulating the attack process of threat targets such as combat airplanes, missiles and the like, provides a vivid air target for the sensor, weapon test and training of an air defense weapon system, and is an indispensable important security equipment in the development, test, identification and training of the air defense weapon system.
The existing unmanned drone simulates the enemy aircraft or the incoming missile during military exercises or weapon test shooting by utilizing a remote control or a preset flight path and mode, and provides a hypothetical target and shooting opportunity for various artillery or missile systems.
The unmanned drone is usually provided with a microwave source at the head part for relevant flight calibration and drone flight test. The radiation signals generated by the microwave source are used for communicating with ground equipment, the ground equipment presets a route, and a certain deviation is set between the route and specific signals emitted by the microwave source, so that the ground missile is ensured to complete design training and the recycling of the unmanned drone aircraft can be protected.
However, the existing microwave source is large in size and heavy in weight, so that a serious burden is brought to the flight of the unmanned drone aircraft, the oil consumption of the unmanned drone aircraft is increased, the flight time is short, and the expected shooting training effect cannot be achieved; in the prior art, a movable joint is adopted for flexible connection when a magnetron is connected with an antenna, so that waveguide transmission is realized, the structure is complex, the dead weight is large, and the situation of unstable signals can occur; when the antenna is fixed, the antenna base is directly arranged at the bottom of the antenna to fix the antenna in the prior art, so that the structural weight is heavy, the structural length of a microwave source system is prolonged, the moment of a machine head is increased, and the anti-seismic effect is poor when the machine head vibrates; in addition, the support bracket between the movable part and the fixed part of the microwave source has enough structural support strength and good anti-seismic performance, but has an overlarge structure and an overlarge structure, or reduces the weight, but has insufficient support strength and poor anti-seismic performance, so that deviation is easy to occur, and the support bracket can not provide a good training environment for shooting training.
Disclosure of Invention
The invention aims to solve the defects in the prior art and provides the method.
In order to achieve the purpose, the invention adopts the following technical scheme:
a high-power microwave source system of an unmanned drone aircraft comprises a fixed power supply and control system and a rotatable microwave source emission subsystem, wherein the power supply and control system is electrically connected with the microwave source emission subsystem, and the power supply and control system is connected with the microwave source emission subsystem through a support bracket; the supporting bracket is of a hollow structure, a reinforcing rib group is arranged on the side face of the supporting bracket, and the reinforcing rib group points to one end of the supporting bracket connected with the microwave source emission subsystem from one end of the supporting bracket connected with the power supply and control system.
The power supply and control system comprises a base, a main control board, a battery and a battery box, wherein the battery is embedded in the battery box, the battery box is fixedly installed on the base, the main control board is fixed on the base and located outside the battery box, the main control board is electrically connected with the battery, and special silica gel is poured on the outer side of the main control board after the main control board is installed on the base, so that sealing between the main control board and the base is ensured.
The microwave source emission subsystem comprises an antenna, a conversion waveguide, an isolator, a magnetron, an antenna bracket and a servo system, the antenna is fixedly arranged on the servo system, one side of the servo system, which is far away from the antenna, is hinged with the supporting bracket, the conversion waveguide is fixedly connected with the access port of the antenna, one end of the conversion waveguide far away from the antenna is fixedly connected with the isolator, one end of the isolator, which is far away from the conversion waveguide, is fixedly connected with the magnetron, the antenna support is connected with the magnetron, the isolator and the antenna in series, the magnetron is fixedly connected with the bottom end of the antenna bracket, the isolator is fixedly connected with the middle part of the antenna bracket, the antenna is fixedly connected to the top end of the antenna bracket, and the magnetron is electrically connected with the main control board through a high-strength cable; the transition waveguide, the isolator, the magnetron, and the servo system are all located between the antenna and the base.
Preferably, the servo system comprises a first servo loop and a second servo loop; the first servo ring is provided with a pair of pitching adjusting lugs and a pair of orientation adjusting lugs, a connecting line between the pitching adjusting lugs and a connecting line between the orientation adjusting lugs are perpendicular to each other, the length of the connecting line is the same as the diameter of the first servo ring, the pitching adjusting lugs are positioned on the lower side of the first servo ring, and the orientation adjusting lugs are positioned on the upper side of the first servo ring; the second servo ring comprises a side ring and a supporting ring, the side ring is perpendicular to the supporting ring and wraps the outside of the supporting ring, the side ring is integrally connected with the supporting ring, the antenna is embedded in the second servo ring and is fixedly locked on the supporting ring through a screw, two supporting plates which are symmetrical by taking the circle center of the supporting ring as a symmetry point are arranged on the inner side of the supporting ring, a first fixing lug is arranged on one side, away from the antenna, of the supporting plate, the first fixing lug is hinged to the position adjusting lug through a first locking pointer screw, and the pitching adjusting lug is hinged to the supporting bracket through a second locking pointer screw.
Preferably, a second fixing lug is arranged on the first servo ring, and the second fixing lug is arranged on the same side as the pitching adjusting lug.
Preferably, a first arc-shaped groove is formed in the position adjusting lug, the first arc-shaped groove is located under the hinge of the first fixing lug and the position adjusting lug, a first threaded hole is formed in one end, far away from the supporting plate, of the first fixing lug, the first locking pointer screw comprises a first stud with a pointer, a first through hole is formed in the first stud, the center of the first through hole, the pointer of the first stud and the center of the hinge of the position adjusting lug and the first fixing lug are collinear, the first through hole is located on one side close to the pointer of the first stud, when the position adjusting lug is hinged to the first fixing lug, projections of the first threaded hole and the first through hole on the position adjusting lug fall on the first arc-shaped groove, and a first limiting screw is inserted into the first through hole, the first limiting screw penetrates through the first through hole and the first arc-shaped groove respectively and is locked in the first threaded hole, and a first adjusting scale is arranged below the first arc-shaped groove.
Preferably, the supporting bracket is in a hollow isosceles triangle shape, the supporting bracket comprises a bottom edge and a top end, the bottom edge is fixedly connected with the base, and the top end is hinged with the pitching adjusting lug; the reinforcing rib group comprises oblique reinforcing ribs and vertical reinforcing ribs, the oblique reinforcing ribs are arranged on two side edges of the supporting bracket, and the vertical reinforcing ribs are perpendicular to the bottom edge and are arranged on the side face of the supporting bracket.
Preferably, a second arc-shaped groove is formed in the top end, the second arc-shaped groove is located right below a hinged position of the pitching adjusting lug and the top end, a second threaded hole is formed in the pitching adjusting lug, the second locking pointer screw comprises a second stud with a pointer, a second through hole is formed in the second stud, the center of the second through hole, the pointer of the second stud and the center of the hinged position of the pitching adjusting lug and the top end are collinear, the second through hole is located on one side close to the pointer of the second stud, when the pitching adjusting lug is hinged to the top end of the supporting bracket, projections of the second threaded hole and the second through hole on the pitching adjusting lug fall on the second arc-shaped groove, a second limiting screw is inserted into the second through hole, the second limiting screw penetrates through the second through hole and the second arc-shaped groove and is locked in the second threaded hole, and a second adjusting scale is arranged below the second arc-shaped groove.
Preferably, the antenna support is Y-shaped and includes a bottom end and two identical limbs, the bottom end is fixedly connected with the magnetron, and the two limbs are fixedly connected with the antenna.
Preferably, the main control board is U-shaped and surrounds the outer side of the battery case.
Preferably, a high voltage power supply is arranged on the main control panel, the high voltage power supply is electrically connected with the battery, and the high voltage power supply is electrically connected with the magnetron.
Preferably, a plurality of empty grooves with different sizes are arranged on the base.
Compared with the prior art, the invention has the beneficial effects that: the structure is compact, the total weight is small, the anti-seismic performance is good, the small volume and the low weight can be realized, the high power can be transmitted simultaneously, and the integrated design of a comprehensive system is realized; by the ingenious design of the supporting bracket, the movable hinge joint is realized, the weight is reduced, the structural strength is ensured while the weight is lighter, and the whole system is more compact and small in structure and has good anti-seismic performance; the microwave source transmitting subsystem can realize the azimuth angle adjustment and the pitching angle adjustment of the microwave source transmitting subsystem while firmly fixing the antenna through the design of the servo system, the adjustment is more flexible and convenient, the fastening antenna can be embedded by utilizing the second servo ring of the servo system, the antenna is prevented from loosening, the weight of the whole machine is reduced, the center of gravity of the antenna is reduced, the overall length of the microwave source system is compressed, the anti-seismic performance of the antenna is improved, and the structural strength is improved; the antenna bracket is used for realizing the hard connection between the magnetron and the antenna, and the soft performance torsion of the high-strength cable connected with the magnetron is used for realizing the rotary reset, so that the traditional movable joint is replaced, the integral volume and weight are reduced, the length of the integral structure is reduced, and the durability of the system is improved; the servo system is connected with the base by utilizing the triangular support bracket, so that the structure is stable and compact, the dead weight is light, and the anti-seismic performance is good.
Drawings
Fig. 1 is a front view of the overall structure of a high-power microwave source system of a military unmanned drone aircraft.
Fig. 2 is a side view of the overall structure of a high-power microwave source system of a military drone aircraft.
Fig. 3 is a front view of a first servo loop of a high power microwave source system of a military drone aircraft according to the present invention.
Fig. 4 is a bottom view of a second servo loop of the high power microwave source system of the military drone aircraft according to the present invention.
Fig. 5 is a top view of a second servo loop of a high power microwave source system for a military drone aircraft according to the present invention.
Detailed Description
In order to further understand the objects, structures, features and functions of the present invention, the following embodiments are described in detail.
Referring to fig. 1, fig. 2, fig. 3, fig. 4 and fig. 5, fig. 1 is a front view of an overall structure of a high-power microwave source system of a military drone aircraft according to the present invention; FIG. 2 is a side view of the overall structure of a high power microwave source system of a military drone aircraft according to the present invention; FIG. 3 is a front view of a first servo loop of a high power microwave source system for a military drone aircraft according to the present invention; FIG. 4 is a bottom view of a second servo loop of a high power microwave source system for a military drone aircraft according to the present invention; fig. 5 is a top view of a second servo loop of a high power microwave source system for a military drone aircraft according to the present invention.
As shown in fig. 1, fig. 2, fig. 3, fig. 4 and fig. 5, a high power microwave source system of an unmanned drone aircraft according to an embodiment of the present invention includes a fixed power supply and control system 1 and a rotatable microwave source emission subsystem 2, the power supply and control system 1 is electrically connected to the microwave source emission subsystem 2 through a high strength cable 4, and the power supply and control system 1 is connected to the microwave source emission subsystem 2 through a support bracket 3; the supporting bracket 3 is of a hollow structure, the side face of the supporting bracket 3 is provided with a reinforcing rib group 31, and the reinforcing rib group 31 points to one end of the supporting bracket 3 connected with the microwave source emission subsystem 2 from one end of the supporting bracket 3 connected with the power supply and control system 1. When the microwave source system is used, the power supply and control system 1 is a fixed part and is fixed on a fixed seat at the rear end of the machine head, so that the whole microwave source system is fixed on the machine head; the microwave source emission subsystem 2 is hinged on the support bracket 3 and can be adjusted in a pitching mode on the support bracket 3. The advantage that high strength cable 4 is connected is that replace prior art's freely movable joint, directly utilize the torsion of high strength cable 4 to realize rotating, has realized the simplification of structure, has saved material cost, has reduced the weight of system, has improved the durability of structure, has reduced mechanical wear, and has improved the anti-seismic performance of structure. The hollow design of the support bracket 3 and the design of the reinforcing rib group 31 can ensure the structural strength of the support bracket 3, increase the structural stability and reduce the weight of the support bracket 3. Preferably, the supporting bracket 3 is in a hollow isosceles triangle shape, the structural stability of the supporting bracket 3 in the triangle shape is higher, the supporting bracket 3 comprises a bottom edge 32 and a top end 33, the bottom edge 32 is fixedly connected with the base 11, and the top end 33 is hinged with the pitching adjusting lug 2611; the reinforcing rib group 31 comprises an inclined reinforcing rib 311 and a vertical reinforcing rib 312; the inclined reinforcing ribs 311 are arranged on the two side edges of the supporting bracket 3, so that the structural strength of the side edges of the triangular supporting bracket 3 is further increased, and the structural stability is improved; the vertical reinforcing ribs 312 are perpendicular to the bottom edge 32 and arranged on the side surface of the support bracket 3, so that the connection strength of the bottom edge 32 and the main body of the support bracket 3 is improved, and the support bracket 3 is not easy to deform.
Because the invention is applied to the unmanned drone aircraft and the requirement on the weight of the product is strictly controlled for the unmanned drone aircraft, the accurate control of the oil quantity when the unmanned drone aircraft flies can be ensured, the flying time of the unmanned drone aircraft can be ensured, and the expected effect of the missile shooting training is further ensured, the volume and the weight of the unmanned drone aircraft are ensured while the preset function is realized.
The power supply and control system 1 comprises a base 11, a main control board 12, a battery 13 and a battery box 14, wherein the battery 13 is embedded in the battery box 14, the battery box 14 is fixedly installed on the base 11, the main control board 12 is fixed on the base 11 and located on the outer side of the battery box 14, the main control board 12 is electrically connected with the battery 13, and after the main control board is installed on the base, special silica gel is poured on the outer side of the main control board to ensure sealing between the main control board and the base. The special silica gel is poured on the main control board, so that good shock resistance, insulation and heat dissipation performance can be achieved, the weight reduction effect can be achieved while the main control board is sealed and waterproof, the connection stability of all devices on the main board can be guaranteed, and the main control board is protected. The base 11 is in a round cake shape and is adapted to the structural shape of the head of the target drone. The battery 13 is covered by the battery box 14, so that the structural stability of the battery 13 is ensured, and the anti-seismic performance is improved. Preferably, main control board 12 is the U-shaped and encircles in the outside of battery case 14, and main control board 12 encircles in the battery case 14 outside for power and control system 1 structure is compacter and smaller, guarantees compact structure, and the overall layout of being convenient for can save the quantity of connecting wire simultaneously, and then reduces the dead weight. Further, a high voltage power supply 121 is disposed on the main control board 12, the high voltage power supply 121 is electrically connected to the battery 13, and the high voltage power supply 121 is electrically connected to the magnetron 24. The high voltage power supply 121 is used for supplying power to the magnetron 24, and ensuring the normal operation of the microwave source emission subsystem 2. Furthermore, the base 11 is provided with a plurality of empty slots with different sizes, and the empty slots are arranged to reduce the weight of the base 11.
The microwave source emission subsystem 2 comprises an antenna 21, a conversion waveguide 22, an isolator 23, a magnetron 24, an antenna support 25 and a servo system 26, wherein the antenna 21 is fixedly arranged on the servo system 26, one side of the servo system 26 far away from the antenna 21 is hinged with the support 3, the conversion waveguide 22 is fixedly connected with an access port of the antenna 21, one end of the conversion waveguide 22 far away from the antenna 21 is fixedly connected with the isolator 23, one end of the isolator 23 far away from the conversion waveguide 22 is fixedly connected with the magnetron 24, the antenna support 25 is connected with the magnetron 24, the isolator 23 and the antenna 21 in series, the magnetron 24 is fixedly connected with the bottom end 251 of the antenna support 25, the isolator 23 is fixedly connected with the middle part of the antenna support 25, the antenna 21 is fixedly connected with the top end of the antenna support 25, fixing pieces parallel to the bottom end 251 are arranged at the top end and the middle part of the antenna support 25, and are integrally connected with the antenna support 25, the strength and the stability of the structure are ensured, the isolator is fixed on a fixing sheet positioned in the middle of the antenna bracket 25 through a fastening screw, the antenna 21 is fixed on the fixing sheet positioned at the top end of the antenna bracket 25 through the fastening screw, and the magnetron 24 is electrically connected with the main control board 12 through a high-strength cable 4; the transition waveguide 22, isolator 23, magnetron 24 and servo 26 are located between the antenna 21 and the base 11. The antenna 21, the conversion waveguide 22, the isolator 23 and the magnetron 24 are in hard link connection, so that the conversion waveguide 22, the isolator 23 and the magnetron 24 are adjusted along with the adjustment of the direction of the antenna 21, the stability of signal transmission is ensured, and then the rotation of the magnetron 24 driven by the antenna 21 is converted into the torsion of the high-strength cable 4 by utilizing the soft random torsion performance of the high-strength cable 4, so that the angle adjustment of the microwave source emission subsystem 2 is realized, the equipment cost is saved, and the equipment structure is simplified. The antenna 21 adopts a circular planar waveguide slot array antenna 21, and the radius of the antenna 21 is smaller than that of the base 11, so that the system can be conveniently and smoothly installed in the handpiece. The microwave source emission subsystem 2 is supported by a servo system 26 to ensure the balance of the center of gravity. When the antenna 21 is adjusted, firstly, pitching adjustment is carried out, at this time, the hinged position of the top end 33 of the support bracket 3 and the first servo ring 261 is taken as a rotation fulcrum of the whole microwave source emission subsystem 2, and at this time, the gravity center of the microwave source emission subsystem 2 falls on the first servo ring 261, so that balance of two ends of the microwave source emission subsystem 2 is ensured, and the situation that the anti-seismic performance is reduced due to the fact that one end of the microwave source emission subsystem 2 is too heavy can be avoided; the azimuth adjustment is to adjust only the antenna 21, i.e. to rotate the second servo loop 262, and the center of gravity of the microwave source emission subsystem 2 is located on the axis of the servo system 26, so as to ensure the balance of the center of gravity during the azimuth adjustment. Antenna support 25's setting, guaranteed magnetron 24, the connection between isolator 23 and the antenna 21 is the hard joint, can utilize the further enhancement of antenna support 25 self structural strength to connect on the basis of being connected between magnetron 24 of own and isolator 23, the stability and the shock resistance of structure have been improved, the structural length of microwave source emission subsystem 2 has been dwindled simultaneously, the moment of torsion has been reduced, and when rotatory, antenna 21 rotates and drives magnetron 24 and rotate, magnetron 24 rotates and drives the torsion of high strength cable 4, and then utilize the torsion of high strength cable 4 to realize the rotation of microwave source emission subsystem 2, thereby the cost of structure has been saved greatly, weight is reduced, the volume is reduced, its shock resistance and durability have been improved.
Preferably, the servo system 26 includes a first servo ring 261 and a second servo ring 262, both the first servo ring 261 and the second servo ring 262 are circular rings and are preferably made of aviation aluminum, and the servo system has a stable and reliable structure, high strength and light dead weight, and can be made of common aluminum materials; as shown in fig. 3, the first servo ring 261 is provided with a pair of pitch adjustment lugs 2611 and a pair of azimuth adjustment lugs 2612, a connecting line between the pitch adjustment lugs 2611 and a connecting line between the azimuth adjustment lugs 2612 are perpendicular to each other and have the same length as the diameter of the first servo ring 261, the pitch adjustment lugs 2611 are located on the lower side of the first servo ring 261, the azimuth adjustment lugs 2612 are located on the upper side of the first servo ring 261, and the pitch adjustment lugs 2611 and the azimuth adjustment lugs 2612 are respectively arranged on two sides of the first servo ring 261; as shown in fig. 4 and 5, the second servo ring 262 includes a side ring 2621 and a ring 2622, the side ring 2621 is perpendicular to the ring 2622 and wraps the outside of the ring 2622, and the side ring 2621 is integrally connected with the ring 2622; the antenna 21 is embedded in the second servo ring 262 and is fixedly locked on the supporting ring 2622 through a screw, namely the side ring 2621 is positioned outside the antenna 21 and tightly surrounds the antenna 21, the supporting ring 2622 is positioned below the antenna 21, so that a good fixing effect and a good anti-vibration effect can be achieved, the supporting ring 2622 is mainly fixed, and the side ring 2621 is mainly limited and anti-vibration; the inner side of the supporting ring 2622 is provided with two supporting plates 2623 which are symmetrical by taking the circle center of the supporting ring 2622 as a symmetrical point, one side of the supporting plate 2623, which is far away from the antenna 21, is provided with a first fixing ear 2624, the first fixing ear 2624 is hinged with the direction adjusting ear 2612 through a first locking pointer screw 263, and the first fixing ear 2624 is positioned at the inner side of the direction adjusting ear 2612 when the first fixing ear 2624 is hinged, so that the volume of the microwave source emission subsystem 2 is prevented from expanding outwards, and the direction adjustment of the microwave source emission subsystem 2 can be realized; the pitching adjusting lug 2611 is hinged to the supporting bracket 3 through a second locking pointer screw 264, and the pitching adjusting lug 2611 is located on the inner side of the supporting bracket 3 during hinging, so that the volume of the microwave source system is prevented from expanding outwards, and the maximum outer diameter of the microwave source emission subsystem 2 is ensured to be smaller than or equal to the outer diameter of the base 11. It should be noted that: the pitching adjustment indicated by the invention is up-down adjustment, the azimuth adjustment indicated by the invention is left-right adjustment, and the up-down direction and the left-right direction are vertical directions.
Preferably, the first servo ring 261 is provided with a second fixing lug 2613, and the second fixing lug 2613 is arranged on the same side as the pitch adjusting lug 2611. In an embodiment, after the second fixing lug 2613 is adjusted, the first servo ring 261 is further fixed by using a steel wire rope, in practical applications, a corresponding steel wire rope fixing hole 34 is formed in the support bracket 3, one end of the steel wire rope passes through the second fixing lug 2613 to be locked and fixed, and the other end of the steel wire rope passes through the corresponding steel wire rope fixing hole 34 in the support bracket 3 to be tensioned and then locked and fixed, so that the anti-seismic performance of the invention is further improved, and azimuth deviation caused by vibration is avoided.
Preferably, the orientation adjustment ear 2612 is provided with a first arc-shaped groove 2614, the first arc-shaped groove 2614 is located right below the hinge joint of the first fixing ear 2624 and the orientation adjustment ear 2612, the center of the first arc-shaped groove 2614 is the center of the hinge joint of the first fixing ear 2624 and the orientation adjustment ear 2612, one end of the first fixing ear 2624, which is far away from the supporting plate 2623, is provided with a first threaded hole 2625, the first locking pointer screw 263 comprises a first stud 2631 with a pointer, the first stud 2631 is provided with a first through hole 2632, the center of the first through hole 2632, the pointer of the first 26stud 31 and the center of the hinge joint of the orientation adjustment ear 2612 and the first fixing ear 2624 are collinear, the first through hole 2632 is located on one side of the pointer near the first stud 2631, when the orientation adjustment ear 2612 is hinged with the first fixing ear 2614, the projection of the first threaded hole 2625 and the first through hole 2632 on the orientation adjustment ear 2612 falls on the first arc-shaped groove 2614, and the first through hole 2633 is inserted in the first through hole 2632, the first limiting screw 2633 passes through the first through hole 2632 and the first arc-shaped groove 2614 respectively and is locked in the first threaded hole 2625, and a first adjusting scale 2615 is arranged below the first arc-shaped groove 2614. In an embodiment, the azimuth angle of the microwave source system, that is, the angle of rotation of the antenna 21 to the left and right, is adjusted by rotating the antenna 21 and the second servo loop 262, but because the internal space of the aircraft head is limited, the angle cannot be adjusted at will and needs to be adjusted within a certain range, the first arc-shaped groove 2614 functions to limit the range of azimuth adjustment, and the control of the azimuth adjustment angle is realized; the first limit screw 2633 passes through the first through hole 2632 and the first arc-shaped groove 2614 and is locked in the first threaded hole 2625, so that the first locking pointer screw 263 is locked on the first fixing lug 2624, so that the first locking pointer screw 263 rotates along with the rotation of the second servo ring 262, a pointer on the first locking pointer screw 263 is indicated on the first adjusting scale 2615, the rotation angle is accurately displayed, the first limit screw 2633 is arranged in the first arc-shaped groove 2614 in a penetrating manner, so that the first limit screw 2633 is limited to only swing in the first arc-shaped groove 2614, the first limit screw 2633 and the second servo ring 262 rotate integrally, so that the rotation angles of the second servo ring 262 and the antenna 21 are limited, and the azimuth adjusting angle range of the microwave source system is 10 degrees left and right respectively.
Preferably, the top end 33 is provided with a second arc-shaped slot 35, the second arc-shaped slot 35 is located right below the hinged position of the pitch adjustment lug 2611 and the top end 33, the pitch adjustment lug 2611 is provided with a second threaded hole 2616, the second locking pointer screw 264 comprises a second stud 2641 with a pointer, the second stud 2641 is provided with a second through hole 2642, the center of the second through hole 2642, the pointer of the second stud 2641 and the center of the hinged position of the pitch adjustment lug 2611 and the top end 33 are collinear, the second through hole 2642 is located on one side of the pointer close to the second stud 2641, when the pitch adjustment lug 2611 is hinged with the top end 33 of the support bracket 3, the projections of the second threaded hole 2616 and the second through hole 2642 on the pitch adjustment lug 2611 are all dropped on the second arc-shaped slot 35, a second limit screw 2643 is inserted into the second through hole 2642 and the second arc-shaped slot 35 and locked in the second threaded hole 2643, a second adjusting scale 36 is arranged below the second arc-shaped groove 35. In an embodiment, the pitching angle of the microwave source system, that is, the vertical rotation angle of the antenna 21, is adjusted by rotating the first servo loop 261, but since the space of the body inside the aircraft head is limited, the angle cannot be adjusted at will and needs to be adjusted within a certain range, the second arc-shaped groove 35 serves to limit the pitching adjustment range, and the pitching adjustment angle is controlled; the second limit screw 2643 passes through the second through hole 2642 and the second arc-shaped groove 35 and is locked in the second threaded hole 2616, so that the second locking pointer screw 264 is locked on the orientation adjusting lug 2612, the second locking pointer screw 264 rotates along with the rotation of the first servo ring 261, a pointer on the second locking pointer screw 264 indicates on the second adjusting scale 36, the second limit screw 2643 is arranged in the second arc-shaped groove 35 in a penetrating manner, so that the second limit screw 2643 is limited to only swing in the second arc-shaped groove 35, the second limit screw 2643 and the first servo ring 261 rotate integrally, the rotation angle of the first servo ring 261 is limited, and the pitch adjusting angle range of the microwave source system is 10 degrees up and down.
Preferably, the antenna support 25 is Y-shaped and comprises a base end 251 and two identical limbs 252, the base end 251 being fixedly connected to the magnetron 24 and the two limbs 252 being fixedly connected to the antenna 21. The Y-shaped antenna bracket 25 is stable in structure, is fixed on the antenna 21 by utilizing the two limbs 252, and the bottom end 251 is fixed on one side surface of the magnetron 24 connected with the isolator 23, so that the locking range is large, the structure is stable and reliable, the gravity center is more stable, good anti-seismic performance is achieved, an integral fixing support is replaced, and the dead weight is reduced while the structure is stable. The antenna support 25 is preferably milled out of aluminum. In addition, a plurality of evenly distributed holes 253 can be arranged on the antenna bracket 25, so that the self weight is further reduced while the structural strength is ensured.
Therefore, the high-power microwave source system of the unmanned drone aircraft has the advantages of compact structure, small total weight and good anti-seismic performance, can realize the simultaneous emission of high power with smaller volume and lower weight, and realizes the integrated design of a comprehensive system; by the ingenious design of the supporting bracket, the movable hinge joint is realized, the weight is reduced, the structural strength is ensured while the weight is lighter, and the whole system is more compact and small in structure and has good anti-seismic performance; the microwave source transmitting subsystem can realize the azimuth angle adjustment and the pitching angle adjustment of the microwave source transmitting subsystem while firmly fixing the antenna through the design of the servo system, the adjustment is more flexible and convenient, the fastening antenna can be embedded by utilizing the second servo ring of the servo system, the antenna is prevented from loosening, the weight of the whole machine is reduced, the center of gravity of the antenna is reduced, the overall length of the microwave source system is compressed, the anti-seismic performance of the antenna is improved, and the structural strength is improved; the antenna bracket is used for realizing the hard connection between the magnetron and the antenna, and the soft performance torsion of the high-strength cable connected with the magnetron is used for realizing the rotary reset, so that the traditional movable joint is replaced, the integral volume and weight are reduced, the length of the integral structure is reduced, and the durability of the system is improved; the servo system is connected with the base by utilizing the triangular support bracket, so that the structure is stable and compact, the dead weight is light, and the anti-seismic performance is good.
The present invention has been described in relation to the above embodiments, which are only exemplary of the implementation of the present invention. It should be noted that the disclosed embodiments do not limit the scope of the invention. Rather, it is intended that all such modifications and variations be included within the spirit and scope of this invention.
Claims (8)
1. A high-power microwave source system of an unmanned drone aircraft is characterized in that: the microwave source emission device comprises a fixed power supply and control system and a rotatable microwave source emission subsystem, wherein the power supply and control system is electrically connected with the microwave source emission subsystem, and the power supply and control system is connected with the microwave source emission subsystem through a support bracket; the supporting bracket is of a hollow structure, a reinforcing rib group is arranged on the side face of the supporting bracket, and the reinforcing rib group points to one end of the supporting bracket, which is connected with the microwave source emission subsystem, from one end of the supporting bracket, which is connected with the power supply and control system;
the power supply and control system comprises a base, a main control board, a battery and a battery box, wherein the battery is embedded in the battery box, the battery box is fixedly installed on the base, the main control board is fixed on the base and positioned outside the battery box, the main control board is electrically connected with the battery, and after the main control board is installed on the base, special silica gel is poured outside the main control board, so that the sealing between the main control board and the base is ensured;
the microwave source emission subsystem comprises an antenna, a conversion waveguide, an isolator, a magnetron, an antenna bracket and a servo system, the antenna is fixedly arranged on the servo system, one side of the servo system, which is far away from the antenna, is hinged with the supporting bracket, the conversion waveguide is fixedly connected with the access port of the antenna, one end of the conversion waveguide far away from the antenna is fixedly connected with the isolator, one end of the isolator, which is far away from the conversion waveguide, is fixedly connected with the magnetron, the antenna support is connected with the magnetron, the isolator and the antenna in series, the magnetron is fixedly connected with the bottom end of the antenna bracket, the isolator is fixedly connected with the middle part of the antenna bracket, the antenna is fixedly connected to the top end of the antenna bracket, and the magnetron is electrically connected with the main control board through a high-strength cable; the conversion waveguide, the isolator, the magnetron and the servo system are all positioned between the antenna and the base; the top and the middle part of the antenna bracket are both provided with a fixing sheet parallel to the bottom of the antenna bracket, the fixing sheet is integrally connected with the antenna bracket, the isolator is fixed on the fixing sheet in the middle of the antenna bracket through a fastening screw, and the antenna is fixed on the fixing sheet on the top of the antenna bracket through a fastening screw.
2. The high power microwave source system of unmanned drone aircraft of claim 1, characterized by: the servo system comprises a first servo loop and a second servo loop; the first servo ring is provided with a pair of pitching adjusting lugs and a pair of orientation adjusting lugs, a connecting line between the pitching adjusting lugs and a connecting line between the orientation adjusting lugs are perpendicular to each other, the length of the connecting line is the same as the diameter of the first servo ring, the pitching adjusting lugs are positioned on the lower side of the first servo ring, and the orientation adjusting lugs are positioned on the upper side of the first servo ring; the second servo ring comprises a side ring and a supporting ring, the side ring is perpendicular to the supporting ring and wraps the outside of the supporting ring, the side ring is integrally connected with the supporting ring, the antenna is embedded in the second servo ring and is fixedly locked on the supporting ring through a screw, two supporting plates which are symmetrical by taking the circle center of the supporting ring as a symmetry point are arranged on the inner side of the supporting ring, a first fixing lug is arranged on one side, away from the antenna, of the supporting plate, the first fixing lug is hinged to the position adjusting lug through a first locking pointer screw, and the pitching adjusting lug is hinged to the supporting bracket through a second locking pointer screw.
3. The high power microwave source system of unmanned drone aircraft of claim 2, characterized by: and a second fixing lug is arranged on the first servo ring, and the second fixing lug is positioned at the same side as the pitching adjusting lug.
4. The high power microwave source system of unmanned drone aircraft of claim 2, characterized by: the supporting bracket is in a hollow isosceles triangular frame shape and comprises a bottom edge and a top end, the bottom edge is fixedly connected with the base, and the top end is hinged with the pitching adjusting lug; the reinforcing rib group comprises oblique reinforcing ribs and vertical reinforcing ribs, the oblique reinforcing ribs are arranged on two side edges of the supporting bracket, and the vertical reinforcing ribs are perpendicular to the bottom edge and are arranged on the side face of the supporting bracket.
5. The high power microwave source system of unmanned drone aircraft of claim 1, characterized by: the antenna support is Y-shaped and comprises a bottom end and two identical limbs, the bottom end is fixedly connected with the magnetron, and the two limbs are fixedly connected with the antenna.
6. The high power microwave source system of unmanned drone aircraft of claim 1, characterized by: the main control board is U-shaped and surrounds the outer side of the battery box.
7. The high power microwave source system of unmanned drone aircraft of claim 1, characterized by: the main control board is provided with a high-voltage power supply, the high-voltage power supply is electrically connected with the battery, and the high-voltage power supply is electrically connected with the magnetron.
8. The high power microwave source system of unmanned drone aircraft of claim 1, characterized by: the base is provided with a plurality of empty grooves with different sizes.
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