Airborne multimode fusion digital air emergency communication command device

Abstract

The invention belongs to the technical field of digital communication, and particularly relates to an airborne multi-mode fusion digital air emergency communication command device which comprises an unmanned aerial vehicle body, a base and a satellite antenna which are sequentially stacked and installed into a whole. The bottom of the unmanned aerial vehicle body is provided with lifting supporting legs used for rising and falling supporting and a cable used for conducting electric energy and data transmission with ground equipment. The cable is formed by stacking a magnetic rubber layer, an insulating layer and a wire group layer, an elastic metal wire penetrates through the insulating layer, the insulating layer is attached to one end of the bottom of the base to be bent into a spiral shape, and the elastic metal wire is spirally attached through magnetic attraction force of the magnetic rubber layer; a linkage rod used for regulating and controlling the signal receiving angle of the satellite antenna is arranged between the foot root of the lifting supporting leg and the bottom of the satellite antenna. The satellite antenna with the specific diameter can be carried through the mooring unmanned aerial vehicle, the satellite antenna can be stably suspended in the air, meanwhile, the signal receiving angle can be adjusted according to needs in the using process, the influence of severe weather is small, and the satellite antenna can more stably work in the air.

Description

Technical Field

[0001] This invention belongs to the field of digital communication technology, specifically relating to an airborne multi-mode fusion digital airborne emergency communication and command device. Background Technology

[0002] Tethered drones, with their core advantages of long endurance, large payload, and stable power supply, have demonstrated irreplaceable application value in multiple fields. Especially in areas with signal obstruction such as mountainous regions and densely populated urban areas, they can act as aerial relay stations, extending communication coverage. They also support self-organizing network technology, automatically optimizing multi-hop routes to achieve data connectivity.

[0003] However, existing tethered drones cannot effectively carry satellite antennas for operation. Since satellite antennas are generally large, their stability after takeoff is low, and their signal reception angle cannot be adjusted well, resulting in poor satellite signal reception and failure to meet expectations. Secondly, in areas with signal obstruction such as mountainous areas and densely populated urban areas, the drone's dedicated cable is suspended in the air for extended periods. When affected by severe weather, the cable sways continuously, and the cable at the tethered drone end cannot be retracted or extended in time, which can easily lead to loss of balance due to excessive traction and ultimately a crash. Summary of the Invention

[0004] The purpose of this invention is to provide an airborne multi-mode fusion digital aerial emergency communication and command device that can carry a satellite antenna of a specific diameter on a tethered UAV and keep it stable in the air. During use, the signal receiving angle can be adjusted as needed, and it is less affected by severe weather, enabling it to work more stably in the air.

[0005] The specific technical solution adopted by this invention is as follows: An airborne multi-mode fusion digital aerial emergency communication and command device includes an unmanned aerial vehicle body, a base, and a satellite antenna that are stacked and installed together in sequence; The bottom of the unmanned aerial vehicle is equipped with lifting outriggers for take-off and landing support, as well as cables for transmitting electrical energy and data with ground equipment. The cable is composed of a magnetic adhesive layer, an insulation layer, and a wire assembly layer, and an elastic metal wire is threaded inside the insulation layer. The cable is bent into a spiral shape at one end of the bottom of the base and is attached to the base by the magnetic attraction of the magnetic adhesive layer. An angle adjustment mechanism is provided between the drone body and the lifting outriggers, and a linkage rod for adjusting the signal receiving angle of the satellite antenna is provided between the heel of the lifting outriggers and the bottom of the satellite antenna.

[0006] As a preferred embodiment, the unmanned aerial vehicle includes an upper support plate, a lower support plate, and a rotor assembly mounted on the arms of the two vertically stacked components. A processor module is built between the upper support plate and the lower support plate. The processor module is provided with a multi-pin interface and is electrically connected to the rotor assembly via wires.

[0007] As a preferred embodiment, a support arm is integrally formed on the base, the support arm is arranged in a circumferential array on the base, and a limiting groove is formed at the center of the array.

[0008] As a preferred embodiment, the satellite antenna includes a reflector body, an upper housing, and a first reflector, a second reflector, and a third reflector stacked vertically inside it. The reflector body is inverted conical in shape, and the first reflector, the second reflector, and the third reflector are stacked in a tower-like conical shape and connected to each other by a focusing column.

[0009] As a preferred embodiment, at least three sets of support arms are provided on the base and are made of elastic material. The reflective body is movably embedded inside the support arm and fits against its inner wall. The bottom end of the reflective body is embedded in the limiting groove to limit its position. The linkage rod is provided between adjacent gaps of the support arm.

[0010] As a preferred embodiment, the angle adjustment mechanism includes an upper support mounted on the bottom surface of the lower support plate and a servo motor mounted on one side of the upper support. The power output end of the upper support is directly connected to a push rod, and the end of the push rod away from the servo motor is rotatably connected to a connecting frame. A support rod is vertically fixedly mounted on the end of the upper support, and the top of the lifting leg is rotatably connected to the support rod and rotatably connected to the bottom end of the connecting frame.

[0011] As a preferred embodiment, a connecting ring is fixedly installed near the spiral section of the cable, and a pull rope is bolted to the connecting ring and threaded through the lifting leg, so as to adjust the tightening state of the spiral section of the connecting ring by means of the pull rope. The lifting leg is provided with a winding mechanism for adjusting the length of the pull rope.

[0012] As a preferred embodiment, the winding mechanism includes a winding roller fixedly installed at the heel of the lifting outrigger and a roller assembly installed on the inner wall of the lifting outrigger. The end of the pull rope is fixed to the winding roller and passes through the roller assembly. The winding roller is equipped with a winding motor for adjusting the length of the pull rope.

[0013] As a preferred embodiment, the rotor unit is provided with at least three sets, and the lifting outriggers and the linkage rods are installed in the gap between two adjacent sets of rotor units, and the number of sets is the same as that of the rotor units.

[0014] As a preferred embodiment, the linkage rod is a spring shock absorber rod, the bottom surface of the reflector body is integrally formed with an upper support leg, the heel of the lifting support leg is welded to the lower support leg, one end of the linkage rod is rotatably connected to the upper support leg, and the other end is rotatably connected to the lower support leg.

[0015] The technical effects achieved by this invention are as follows: This invention utilizes a satellite antenna, lifting outriggers, and a linkage rod in a coordinated manner. During landing, a servo motor drives the lifting outriggers to rotate to the landing position, and the linkage rod then resets the satellite antenna within the support arm, placing it stably. This ensures the satellite antenna remains stable during landing, preventing damage. Furthermore, after takeoff, the servo motor lifts the lifting outriggers, releasing the satellite antenna from the support arm's limit. The coordinated movement of multiple lifting outriggers allows for adjustment of the satellite antenna's hover angle, thereby enabling satellite signal reception and transmission and ensuring signal stability.

[0016] This invention utilizes lifting outriggers in conjunction with cables. A magnetic adhesive layer and elastic metal wires are used to magnetically attract one end of the cable near the drone body, mimicking a spiral shape. A pull rope further restricts this spiral. During flight, when the cable tension exceeds a threshold, the take-up roller is released. The flight tension is then used to straighten the spiral section of the cable, buffering the tension and preventing it from acting directly on the drone body. This ensures the drone's flight stability and, consequently, the stability of the satellite antenna's signal reception. After the tension dissipates, the take-up roller rewinds the pull rope, and the spiral section of the cable resets under the rebound force of the elastic metal wire and the magnetic attraction of the magnetic adhesive layer. This repeated buffering of cable tension during flight ensures the drone's continuous flight stability. Attached Figure Description

[0017] Figure 1 This is a three-dimensional structural schematic diagram of an embodiment of the present invention; Figure 2 This is a side sectional view of an embodiment of the present invention; Figure 3 This is an exploded view of an embodiment of the present invention; Figure 4 This is a schematic diagram of the structure of the unmanned aerial vehicle in an embodiment of the present invention; Figure 5 This is a partial structural diagram of the unmanned aerial vehicle in an embodiment of the present invention; Figure 6 This is a schematic diagram of the base structure in an embodiment of the present invention; Figure 7 This is a schematic diagram of the internal structure of the satellite antenna in an embodiment of the present invention; Figure 8 This is an exploded view of the satellite antenna in an embodiment of the present invention; Figure 9 This is a schematic diagram of the combined structure of the lifting outrigger and the linkage rod in an embodiment of the present invention; Figure 10 This is a schematic diagram of the structure of the lifting outrigger components in an embodiment of the present invention; Figure 11 This is a schematic diagram of the cable structure in an embodiment of the present invention; Figure 12 This is a schematic diagram of the cross-sectional structure of the cable in an embodiment of the present invention; Figure 13 This is the present invention. Figure 2 A magnified view of part A in the middle.

[0018] The attached diagram lists the components represented by each number as follows: 1. Unmanned aerial vehicle (UAV) body; 11. Upper support plate; 12. Lower support plate; 13. Mounting plate; 14. Rotor unit; 15. Processor module; 2. Base; 21. Support arm; 22. Limiting groove; 3. Satellite antenna; 31. Reflector body; 32. Upper shell; 33. First reflector; 34. Second reflector; 35. Third reflector; 36. Upper support leg; 4. Lifting outriggers; 41. Upper support; 42. Servo motor; 43. Push rod; 44. Connecting frame; 45. Support rod; 46. Lower support leg; 5. Cables; 51. Magnetic adhesive layer; 52. Insulating layer; 53. Wire assembly layer; 54. Elastic metal wire; 55. Connecting ring; 56. Pull rope; 57. Take-up roller; 58. Roller assembly; 6. Linkage rod. Detailed Implementation

[0019] To make the objectives and advantages of this invention clearer, the invention will be specifically described below with reference to embodiments. It should be understood that the following text is merely used to describe one or more specific embodiments of the invention and does not strictly limit the scope of protection specifically claimed by the invention.

[0020] like Figures 1-13As shown, an airborne multi-mode fusion digital aerial emergency communication command device includes a UAV body 1, a base 2, and a satellite antenna 3 stacked together. By mounting the satellite antenna 3 on the UAV body 1 via the base 2, it can remain airborne to solve signal blockage areas such as mountainous areas and densely populated urban areas. This allows ground equipment to receive and transmit satellite signals in emergency situations. At the same time, the UAV body 1 is a tethered UAV, which ensures that the UAV body 1 can receive sufficient power supply for long-term airborne operation and can reduce its load, allowing it to carry more equipment for takeoff.

[0021] See attached document Figures 4-6 The unmanned aerial vehicle 1 includes an upper support plate 11 and a lower support plate 12 vertically stacked and mounted on the arms of the two. A processor module 15 is built between the upper support plate 11 and the lower support plate 12. The processor module 15 is provided with a multi-pin interface and is electrically connected to the rotor assembly 14 through wires. By providing a multi-pin interface, the device can connect to more devices as needed, thereby meeting communication requirements and enabling more emergency functions to be used in emergency situations, thus facilitating mission execution.

[0022] In this embodiment, four sets of rotor units 14 are provided. Correspondingly, four sets of wing arms are provided on the upper support plate 11 and the lower support plate 12. The four sets of rotor units 14 work together to make the unmanned aircraft 1 more stable in the air and easier to control. Of course, in other embodiments, the number of rotor units 14 can be selected according to the size of the aircraft. However, to ensure stability, at least four sets should be selected to ensure force balance and flight stability.

[0023] See attached document Figure 7 and Figure 8 The satellite antenna 3 includes a reflector body 31, an upper housing 32, and a first reflector 33, a second reflector 34, and a third reflector 35 vertically stacked inside it. The reflector body 31 is inverted conical in shape, with its inner wall parabolic, and is covered with tin foil. Tin foil is used to reflect and refract radio waves emitted or reflected by the first reflector 33, the second reflector 34, and the third reflector 35. Tin foil can stably and efficiently refract radio waves and minimize radio wave energy loss, largely achieving lossless refraction of radio waves. Furthermore, tin foil is inexpensive, further reducing costs.

[0024] Furthermore, the first reflector 33, the second reflector 34, and the third reflector 35 are stacked in a tower-like cone shape and connected to each other through a focusing column and a feed line. The focusing column can concentrate radio wave energy and concentrate the transmission of radio wave signals. Both the reflectors and the focusing column are made of copper, which makes the satellite signal more concentrated and focused on the focusing column to form a concentrated microwave signal, which is then output through the feed line to realize signal reception and transmission in satellite communication.

[0025] See attached document Figure 2 and Figure 6 The base 2 is fixedly installed on the top surface of the upper support plate 11. At the same time, a support arm 21 is integrally formed on the base 2 and the support arm 21 is arranged in a circumferential array on the base 2. A limiting groove 22 is formed at the center of the array. In the take-off state, the reflector 31 can be embedded into the rotating hole formed by the circumferential array of the support arm 21 and into the limiting groove 22. At the same time, the bottom surface is in contact with the inner wall of the support arm 21, thereby stably placing the satellite antenna 3 on the top surface of the UAV body 1. This ensures that the UAV body 1 remains stable during take-off, avoids falling, and ensures safe use.

[0026] It should be noted that in this embodiment, four sets of support arms 21 are provided, and they are made of elastic metal materials such as stainless steel. During the placement of the satellite antenna 3, the elastic deformation of the support arms 21 can be used to clamp and limit it, and to buffer the impact force during the receiving process, so as to avoid damaging the satellite antenna 3. Of course, in some other embodiments, at least three sets of support arms 21 are provided on the base 2, which can be selected according to specific usage requirements.

[0027] See attached document Figure 1 as well as Figure 3 The bottom of the drone body 1 is equipped with lifting legs 4, which can support the drone body 1 when it lands, and fold up after it takes off. The foldable feature of the lifting legs 4 can be used to adjust the signal receiving angle of the satellite antenna 3 and make it stable in the air.

[0028] Further, refer to the appendix. Figures 9-10The lower support plate 12 of the UAV body 1 has an integrally formed mounting plate 13 on its edge. An upper support 41 is fixedly installed on the bottom surface of the lower support plate 12. A servo motor 42 is fixedly installed on one side of the upper support 41. A push rod 43 is directly connected to the power output end of the upper support 41. A connecting frame 44 is rotatably connected to the end of the push rod 43 away from the servo motor 42. A support rod 45 is vertically fixedly installed at the end of the upper support 41. The top of the lifting leg 4 is rotatably connected to the support rod 45 and rotatably connected to the bottom of the connecting frame 44. The servo motor 42 can push the lifting leg 4 to rotate around the upper support 41 via the push rod 43, so that it can be deployed to support the UAV body 1 when it lands and retracted when it is in the air.

[0029] See attached document Figure 2 as well as Figures 9-10 To allow for greater adjustment of the signal reception of the satellite antenna 3 while it is suspended in the air, a linkage rod 6 is provided between the heel of the lifting leg 4 and the bottom of the satellite antenna 3. In this embodiment, the linkage rod 6 is a spring-loaded shock absorber. The bottom surface of the reflector body 31 is integrally formed with an upper support leg 36, and the heel of the lifting leg 4 is welded to the lower support leg 46. By rotating one end of the linkage rod 6 to the upper support leg 36 and the other end to the lower support leg 46, the placement state of the satellite antenna 3 can be changed during the rotation of the lifting leg 4, as detailed below: During the landing process, the lifting outrigger 4 is adjusted to the lowest support state by the servo motor 42. At this time, the satellite antenna 3 can be pulled into the support groove formed by the support arm 21 by the linkage rod 6, so that it remains stable during the landing process. When landing, the spring shock absorber can buffer the landing impact force, thereby improving the landing stability and protecting the UAV body 1 and the satellite antenna 3.

[0030] During ascent, as during descent, the lifting outriggers 4 can be adjusted to their lowest support state via the servo motor 42. At this time, the satellite antenna 3 can be pulled into the support groove formed by the support arm 21 via the linkage rod 6, thereby keeping it stable during ascent and preventing abnormalities from the satellite due to the huge shaking during ascent.

[0031] It should be noted that in this embodiment, the lifting outrigger 4 and the linkage rod 6 are installed in the gap between two adjacent sets of rotor units 14, and are located between adjacent gaps of the support arm 21, so that they will not interfere with each other during operation, and the number of sets is the same as that of the rotor units 14, which is four sets.

[0032] During the hovering process, four sets of servo motors 42 are used to lift the lifting legs 4, thereby causing the satellite antenna 3 to leave the limited space of the support arm 21, thus enabling it to gain adjustment freedom in the hovering state. Then, by using the four sets of servo motors 42, the lifting legs 4 and the linkage rod 6 in coordination, the deployment angle of the lifting legs 4 in different directions can be adjusted synchronously according to the signal reception requirements, thereby completing the adjustment of the tilt angle of the satellite antenna 3, enabling accurate reception and transmission of satellite signals, and ensuring the stable operation of emergency work.

[0033] See attached document Figure 2 , Figure 3 as well as Figure 11 The unmanned aerial vehicle body 1 is a tethered unmanned aerial vehicle, and a cable 5 is connected to its bottom surface to transmit electrical power and data with ground equipment.

[0034] Please refer to the appendix for details. Figure 12 In order to buffer the tension of the cable 5 during the hovering, take-off and landing of the UAV body 1, the cable 5 is composed of a magnetic adhesive layer 51, an insulating layer 52 and a wire group layer 53. An elastic metal wire 54 is threaded inside the insulating layer 52 and is bent into a spiral shape at one end of the base 2. It is attached to the base 2 by the magnetic attraction of the magnetic adhesive layer 51. In this way, when the tension of the cable 5 exceeds the threshold, the tension can be buffered by stretching the spiral layer, so as to avoid the tension affecting the normal flight of the UAV body 1.

[0035] It should be noted that the magnetic adhesive layer 51 can be a rubber layer embedded with neodymium iron boron permanent magnet particles, and the elastic metal wire 54 can be a nickel-titanium shape memory alloy wire with a recovery deformation rate of more than 90%; of course, other materials can be used as needed in other embodiments.

[0036] See attached document Figure 2 , Figure 11 as well as Figure 13 To facilitate control over the state changes of the spiral segment of cable 5, a connecting ring 55 is fixedly installed near the spiral segment of cable 5. A pull rope 56, which passes through the lifting leg 4, is attached to the connecting ring 55, and four sets of these ropes are provided. Correspondingly, a take-up roller 57 is fixedly installed inside the heel of the lifting leg 4, and a roller assembly 58 is installed on the inner wall of the lifting leg 4. By fixing the end of the pull rope 56 to the take-up roller 57 and threading it between the roller assemblies 58, and with a take-up motor mounted on the take-up roller 57, the pull rope 56 can be extended and released by rotating the take-up roller 57, thereby controlling the state changes of the spiral segment of cable 5. Specifically: Under normal conditions, the winding motor drives the winding roller 57 to rotate and tighten the pull rope 56. At the same time, the cable 5 remains in a spiral-fitted state under the action of the elastic metal wire 54 rebound force and the magnetic attraction force of the magnetic adhesive layer 51. At this time, pulling the cable 5 will not cause the state of the spiral section of the cable 5 to change.

[0037] During the ascent and hovering of cable 5, when the tension exceeds the threshold, the winding motor drives the winding roller 57 to rotate in the opposite direction to loosen the pull rope 56. At this time, under the action of tension, cable 5 will stretch the spiral section, making it unfold into a straight state, thereby buffering the tension and preventing the tension from acting directly on the UAV body 1 through cable 5, ensuring the hovering stability of UAV body 1, and thus ensuring the signal reception stability of satellite antenna 3. After the tension disappears, the winding roller 57 winds up the pull rope 56, and the spiral section of cable 5 resets under the action of the elastic metal wire 54 rebound force and the magnetic attraction force of magnetic adhesive layer 51, so as to repeatedly utilize the continuous buffering of cable 5 tension during the hovering process to ensure the continuous hovering stability of UAV body 1.

[0038] It should be noted that the tension of cable 5 is detected by the bottom device and fed back to the control system, which then controls the winding state of the winding roller 57 by controlling the winding motor, thereby changing the state of the tension rope 56 from relaxed to tense; at the same time, the servo motor 42 receives satellite signal strength data, which is then processed by the processor module 15 to calculate the target tilt angle, and then the extension and retraction control is achieved by adjusting the extension and retraction of the linkage rod 6.

[0039] The working principle of this invention is as follows: First, during the ascent, the lifting outrigger 4 is adjusted to the lowest support state by the servo motor 42. At this time, the satellite antenna 3 can be pulled into the support groove formed by the support arm 21 by the linkage rod 6, so that it remains stable during the ascent and will not cause any abnormalities to the satellite due to the huge shaking during the ascent.

[0040] Secondly, during the hovering process, four sets of servo motors 42 are used to lift the lifting legs 4, thereby causing the satellite antenna 3 to leave the limited space of the support arm 21, thus enabling it to gain adjustment freedom in the hovering state. Then, by using the four sets of servo motors 42, the lifting legs 4 and the linkage rod 6 in coordination, the deployment angle of the lifting legs 4 in different directions can be adjusted synchronously according to the signal reception requirements, thereby completing the adjustment of the tilt angle of the satellite antenna 3, enabling accurate reception and transmission of satellite signals, and ensuring the stable operation of emergency work.

[0041] Secondly, during the landing process, the servo motor 42 adjusts the lifting outrigger 4 to the lowest support state. At this time, the linkage rod 6 can pull the satellite antenna 3 into the support groove formed by the support arm 21, so that it remains stable during the landing process. When landing, the spring shock absorber can buffer the landing impact force, thereby improving landing stability and protecting the UAV body 1 and the satellite antenna 3.

[0042] Finally, when encountering severe weather during flight and loitering, if the tension of cable 5 exceeds the threshold, the winding motor drives the winding roller 57 to rotate in the opposite direction to loosen the pull rope 56. At this time, under the action of tension, the spiral section of cable 5 will stretch and unfold into a straight state, thereby buffering the tension and preventing the tension from acting directly on the UAV body 1 through cable 5, ensuring the loitering stability of UAV body 1, and thus ensuring the signal reception stability of satellite antenna 3. After the tension disappears, the winding roller 57 winds up the pull rope 56, and the spiral section of cable 5 resets under the action of the elastic metal wire 54 rebound force and the magnetic attraction force of magnetic adhesive layer 51, so as to repeatedly utilize the continuous buffering of cable 5 tension during loitering to ensure the continuous loitering stability of UAV body 1.

[0043] The above description is merely a preferred embodiment of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention. Structures, devices, and operating methods not specifically described or explained in this invention are implemented according to conventional methods in the art unless otherwise specified or limited.

Claims

1. An airborne multi-mode fusion digital airborne emergency communication and command device, characterized in that, Includes an unmanned aerial vehicle body (1), a base (2), and a satellite antenna (3) that are stacked and installed together in sequence; The unmanned aerial vehicle (1) is equipped with lifting outriggers (4) for take-off and landing support and cables (5) for transmitting electrical energy and data with ground equipment at its bottom. The cable (5) is composed of a magnetic adhesive layer (51), an insulation layer (52) and a wire assembly layer (53) stacked together. An elastic metal wire (54) is inserted inside the insulation layer (52). The cable (5) is attached to the bottom of the base (2) and bent into a spiral shape. It is attached to the base by the magnetic attraction of the magnetic adhesive layer (51). An angle adjustment mechanism is provided between the unmanned aerial vehicle body (1) and the lifting leg (4), and a linkage rod (6) for adjusting the signal receiving angle of the satellite antenna (3) is provided between the foot of the lifting leg (4) and the bottom of the satellite antenna (3).

2. The airborne multi-mode fusion digital airborne emergency communication and command device according to claim 1, characterized in that: The unmanned aerial vehicle (1) includes an upper support plate (11), a lower support plate (12) and a rotor assembly (14) mounted on the arms of the two vertically stacked. A processor module (15) is built between the upper support plate (11) and the lower support plate (12). The processor module (15) is provided with a multi-pin interface and is electrically connected to the rotor assembly (14) through wires.

3. The airborne multi-mode fusion digital airborne emergency communication and command device according to claim 1, characterized in that: The base (2) has an integrally formed support arm (21), which is arranged in a circumferential array on the base (2) and has a limiting groove (22) formed at the center of the array.

4. The airborne multi-mode fusion digital airborne emergency communication and command device according to claim 3, characterized in that: The satellite antenna (3) includes a reflector body (31), an upper housing (32), and a first reflector plate (33), a second reflector plate (34), and a third reflector plate (35) stacked vertically inside it. The reflector body (31) is inverted cone shape, and the first reflector plate (33), the second reflector plate (34), and the third reflector plate (35) are stacked in a tower-like cone shape and connected to each other by a focusing column.

5. The airborne multi-mode fusion digital airborne emergency communication and command device according to claim 4, characterized in that: The support arm (21) is provided in at least three sets on the base (2) and is made of elastic material. The reflective body (31) is movably embedded in the support arm (21) and fits against its inner wall. The bottom end of the reflective body (31) is embedded in the limiting groove (22) to complete its limiting. The linkage rod (6) is provided between the adjacent gaps of the support arm (21).

6. The airborne multi-mode fusion digital airborne emergency communication and command device according to claim 2, characterized in that: The angle adjustment mechanism includes an upper support (41) installed on the bottom surface of the lower support plate (12) and a servo motor (42) installed on one side of the upper support (41). The power output end of the upper support (41) is directly connected to a push rod (43). The end of the push rod (43) away from the servo motor (42) is rotatably connected to a connecting frame (44). A support rod (45) is vertically fixedly installed at the end of the upper support (41). The top of the lifting leg (4) is rotatably connected to the support rod (45) and rotatably connected to the bottom end of the connecting frame (44).

7. The airborne multi-mode fusion digital airborne emergency communication and command device according to claim 1, characterized in that: A connecting ring (55) is fixedly installed near the spiral section of the cable (5). A pull rope (56) is attached to the connecting ring (55) and passes through the lifting leg (4) to adjust the tightening state of the spiral section of the connecting ring (55) by means of the pull rope (56). A winding mechanism for adjusting the length of the pull rope (56) is provided inside the lifting leg (4).

8. The airborne multi-mode fusion digital airborne emergency communication and command device according to claim 7, characterized in that: The winding mechanism includes a winding roller (57) fixedly installed at the heel of the lifting leg (4) and a roller assembly (58) installed on the inner wall of the lifting leg (4). The end of the pull rope (56) is fixed to the winding roller (57) and passes through the roller assembly (58). The winding roller (57) is equipped with a winding motor for adjusting the length of the pull rope (56).

9. An airborne multi-mode fusion digital airborne emergency communication and command device according to claim 2, characterized in that: The rotor unit (14) is provided with at least three sets. The lifting outrigger (4) and the linkage rod (6) are installed in the gap between two adjacent sets of rotor units (14) and the number of sets is the same as that of the rotor unit (14).

10. An airborne multi-mode fusion digital airborne emergency communication and command device according to claim 4, characterized in that: The linkage rod (6) is a spring shock absorber rod. The bottom surface of the reflector body (31) is integrally formed with an upper support leg (36). The heel of the lifting support leg (4) is welded to the lower support leg (46). One end of the linkage rod (6) is rotatably connected to the upper support leg (36), and the other end is rotatably connected to the lower support leg (46).

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