An intelligent unmanned flight system with signal shielding function

Abstract

The present invention provides an intelligent unmanned flight system with a signal shielding function, which relates to the technical field of weaponry and equipment. It includes a mother aircraft and multiple daughter drones. The daughter drones are equipped with radio shielding devices and are carried inside the mother aircraft. The daughter drones have a tail rotor, a middle front engine, a middle rear engine, and a head. The daughter drones achieve hovering and formation functions through the tail rotor; the daughter drones achieve dive acceleration functions through the middle rear engine; the daughter drones achieve recoil deceleration functions through the middle front engine; and the mother aircraft automatically disintegrates after reaching a predetermined position. The solution provided by the present invention uses the mother missile to carry a large number of daughter drones with electromagnetic shielding functions, and can land stably on the ground for radio shielding.

Description

Technical Field

[0001] The present invention relates to the technical field of weaponry and equipment, and particularly to an intelligent unmanned flight system with a signal shielding function. Background Art

[0002] At present, conventional warfare is developing towards the direction of intelligence. The current modern warfare is in the stage of information warfare mainly aiming at paralyzing the combat system and marked by network and information systems. In military warfare, the military power systems and communication systems of various countries are indispensable in military operations. During the actual combat process, each unit needs to conduct necessary information exchange through the use of wireless communication technology, monitor the operation status in real time, and flexibly change the operation plan. Therefore, in every military operation, it is very necessary to disrupt the enemy's communication system and cut off the connection between the enemy and the headquarters. Radio shielding technology is the key to achieving an initial victory in military operations.

[0003] At present, radio signal shielding technology is developing rapidly towards multi-functional and multi-spectrum shielding. With the continuous development of radio technology, radio security has received increasing attention, and radio signal shielding technology will occupy an extremely important position in the radio field. Moreover, the degree of attention of our country to information warfare has also been greatly improved. So far, the main equipment of our country's strategic support force includes early warning radars, interference unmanned aerial vehicles, and command and communication systems. The interference unmanned aerial vehicles mainly include communication interference unmanned aerial vehicles, radar interference unmanned aerial vehicles, and anti-radiation unmanned aerial vehicles. Once these unmanned aerial vehicles start flying in the air, the enemy's communication system will be invisible and unable to connect, becoming useless. However, the existing communication interference unmanned aerial vehicles usually have a small quantity, and when shielding radio waves in the air, they have a large target and are easily detected by the enemy. As the protagonist of the future intelligent battlefield, the research and development of unmanned combat systems has set off an unprecedented upsurge. Among them, the "swarm" combat system, as a typical representative of unmanned combat systems, has become a popular field for world military powers to compete in research. However, the functions of the "swarm" combat system mainly focus on strategic strikes and destroying enemy targets. The movement process is to continuously accelerate after launch until the target is destroyed, and it is impossible to achieve communication interference and shielding effects. Based on this, there is an urgent need for a new type of intelligent unmanned flight system with a signal shielding function to solve the above problems. Summary of the Invention

[0004] The purpose of the present invention is to provide an intelligent unmanned flight system with a signal shielding function to solve the problems existing in the above-mentioned prior art. A large number of sub-body unmanned aerial vehicles with electromagnetic shielding functions are carried by a mother missile, and can land stably on the ground for radio shielding.

[0005] To achieve the above purpose, the present invention provides the following solutions:

[0006] The present invention provides an intelligent unmanned flight system with a signal shielding function, including a mother aircraft and a plurality of daughter drones. The daughter drones are equipped with radio shielding devices, and the daughter drones are carried inside the mother aircraft. The daughter drones are provided with a tail rotor, a middle front engine, a middle rear engine, and a head. The daughter drones achieve hovering and queuing functions through the tail rotor; the daughter drones achieve dive acceleration functions through the middle rear engine; the daughter drones achieve recoil deceleration functions through the middle front engine;

[0007] After the mother aircraft reaches a predetermined position, it automatically disassembles. A plurality of the daughter drones hover and queue up. After queuing up, the tail rotor at the tail of the daughter drones automatically falls off, and the dive acceleration function is achieved through the middle rear engine. When the distance from the ground reaches a set threshold value, the head falls off, and the middle front engine is used for recoil deceleration until it lands on the ground.

[0008] Preferably, the middle front engine and the middle rear engine are small turbojet engines.

[0009] Preferably, the mother aircraft limits a plurality of the daughter drones through a fixing plate. A plurality of limiting holes are formed in the fixing plate. The fixing plate is movably arranged inside the mother aircraft along the axial direction of the mother aircraft. The fixing plate is driven to move by a linear driving device. When the fixing plate moves towards the head of the daughter drone and exceeds the head, the daughter drone can escape from the fixing plate and perform a free fall motion;

[0010] Before the fixing plate moves, the mother aircraft disassembles from the middle first.

[0011] Preferably, the daughter drone includes the tail rotor, an intermediate body, and the head connected in sequence. The middle front engine and the middle rear engine are respectively arranged at both ends of the intermediate body; the tail rotor and the intermediate body, and the head and the intermediate body are connected through separation devices, and the separation devices can achieve the separation of the tail rotor and the intermediate body and the separation of the head and the intermediate body.

[0012] Preferably, the separation device includes a shape memory alloy wire, a stud, a compression spring, and an energizing mechanism. Both ends of the shape memory alloy wire are fixedly connected to a stud, the stud is coaxial with the shape memory alloy wire, the compression spring is sleeved on the shape memory alloy wire between the two studs, and under the pressure of the stud, the compression spring is always in a compressed state. The energizing mechanism is used to energize the shape memory alloy wire. After the shape memory alloy wire is energized, it heats itself and shrinks, thereby overcoming the restoring force of the compression spring and bringing the two studs closer to each other.

[0013] The separation device is fixed on the tail rotor or the intermediate body. A groove matching the stud is provided on the tail rotor or the intermediate body where the separation device is not fixed. Under normal conditions, the end of the stud abuts against the groove to realize the connection between the tail rotor and the intermediate body. When separation is required, control the energizing mechanism to energize the shape memory alloy wire so that the stud disengages from the groove to achieve separation between the two.

[0014] The separation device is fixed on the head or the intermediate body. A groove matching the stud is provided on the head or the intermediate body where the separation device is not fixed. Under normal conditions, the end of the stud abuts against the groove to realize the connection between the head and the intermediate body. When separation is required, control the energizing mechanism to energize the shape memory alloy wire so that the stud disengages from the groove to achieve separation between the two.

[0015] Preferably, each tail rotor includes two wing rods, namely a first wing rod and a second wing rod. The first wing rod and the second wing rod are connected by a hinge. Under normal conditions, the included angle between the first wing rod and the second wing rod is 90 degrees. The first wing rod is made of a shape memory alloy material. The energizing mechanism can energize the first wing rod and heat it to shrink, pulling the second wing rod. The second wing rod extends to be parallel to the first wing rod under the action of the pulling force and centrifugal force.

[0016] Preferably, the first wing rod is hinged to the hinge, the second wing rod is fixedly connected to the hinge. An installation hole is provided at the end of the first wing rod. An inner spring and a boss are installed in the installation hole in sequence from the inside to the outside. Under normal conditions, the boss abuts against the side of the hinge under the elastic force of the inner spring to lock the hinge. When the second wing rod extends, the hinge rotates and compresses the boss into the installation hole. A clamping hole adapted to the boss is provided at the end of the hinge. When the second wing rod extends to be parallel to the first wing rod, the boss moves outwards under the restoring force of the inner spring and extends into the clamping hole to lock the hinge to the first wing rod.

[0017] The present invention has achieved the following technical effects compared with the prior art:

[0018] The functions of existing missile-type unmanned aerial vehicles mainly focus on strategic strikes and destroying enemy targets. The movement process is to continuously accelerate after launch until the target is destroyed, and it is impossible to achieve the states of fast, slow, and stop in flight speed, and the functions are relatively single. However, the present invention proposes an intelligent unmanned flight system with a signal shielding function. A large number of sub-body unmanned aerial vehicles with electromagnetic shielding functions are carried by the mother aircraft and quickly reach the designated position. Subsequently, the mother aircraft disintegrates. The sub-body unmanned aerial vehicles hover and form a formation by deploying their tail rotors. After the formation is completed, the tail rotors fall off, and the tail accelerates through a small turbojet engine. When approaching the ground, the head falls off, and the middle front engine is used for reverse thrust deceleration until it lands on the ground. After reaching the ground, the radio shielding device starts to function, thus realizing a landing process with fast, slow, and stop functions and being able to achieve the function of electronically shielding enemy equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0020] Figure 1 It is a schematic structural diagram of the intelligent unmanned flight system with a signal shielding function provided by the present invention;

[0021] Figure 2 It is a schematic structural diagram of the fixed plate for fixing the sub-body unmanned aerial vehicle;

[0022] Figure 3 It is a schematic structural diagram of the sub-body unmanned aerial vehicle when the tail rotor is in a folded state;

[0023] Figure 4 It is a schematic diagram of the position of the internal engine of the intermediate body of the sub-body unmanned aerial vehicle;

[0024] Figure 5 It is a schematic structural diagram of the intermediate body and the separation devices at both ends;

[0025] Figure 6 It is a schematic structural diagram of the separation device;

[0026] Figure 7 For Figure 6 Cross-sectional view taken along line A-A in

[0027] Figure 8 It is an exploded view of the tail rotor;

[0028] Figure 9 It is a schematic structural diagram of a tail rotor;

[0029] Figure 10 It is Figure 9 the sectional view taken along the A-A direction in

[0030] Figure 11 It is Figure 10 the enlarged partial view in

[0031] Figure 12 It is a conceptual model diagram when the intelligent unmanned flight system with signal shielding function provided by the present invention is in use;

[0032] Figure 13 It is a flow chart of the intelligent unmanned flight system with signal shielding function provided by the present invention;

[0033] In the figure: 100 - mother aircraft; 200 - son unmanned aircraft;

[0034] 1 - head; 2 - intermediate body; 3 - tail rotor; 31 - first wing rod; 32 - second wing rod; 33 - hinge; 34 - boss; 35 - clamping hole; 36 - inner spring; 37 - mounting hole; 4 - intermediate front engine; 5 - intermediate rear engine; 6 - separation device; 61 - pin; 62 - shape memory alloy wire; 63 - compression spring; 7 - fixed disk; 8 - linear drive device. Specific embodiments

[0035] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0036] The purpose of the present invention is to provide an intelligent unmanned flight system with signal shielding function to solve the problems existing in the above-mentioned prior art. The mother missile carries a large number of son unmanned aircraft with electromagnetic shielding function and can land stably on the ground for radio shielding.

[0037] To make the above objects, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0038] The present invention provides an intelligent unmanned flight system with signal shielding function, such as Figures 1 to 4 , Figure 12 and Figure 13As shown in the figure, it includes a mother aircraft 100 and multiple daughter unmanned aerial vehicles 200. The daughter unmanned aerial vehicles 200 are equipped with radio shielding devices. The daughter unmanned aerial vehicles 200 are carried inside the mother aircraft 100. The daughter unmanned aerial vehicles 200 are provided with a tail rotor 3, a middle front engine 4, a middle rear engine 5 and a head 1; the daughter unmanned aerial vehicles 200 achieve hovering and queuing functions through the tail rotor 3; the daughter unmanned aerial vehicles 200 achieve dive acceleration functions through the middle rear engine 5; the daughter unmanned aerial vehicles 200 achieve recoil deceleration functions through the middle front engine 4.

[0039] The mother aircraft 100 is a missile-type aircraft and can fly at high speed into the air.

[0040] The middle front engine 4 and the middle rear engine 5 are preferably small turbojet engines, and more preferably J45 microturbine engines.

[0041] After the mother aircraft 100 reaches a predetermined position (i.e., the enemy camp), it automatically disassembles. Multiple daughter unmanned aerial vehicles 200 hover and queue up. After queuing up, the tail rotor 3 at the tail of the daughter unmanned aerial vehicle 200 automatically falls off, and the dive acceleration function is achieved through the middle rear engine 5. When the distance from the ground reaches the set threshold, the head 1 falls off, and the recoil deceleration is achieved through the middle front engine 4 until it lands on the ground.

[0042] The intelligent unmanned flight system with signal shielding function provided by the present invention carries a large number of daughter unmanned aerial vehicles 200 with electromagnetic shielding functions through the mother aircraft 100, quickly reaches the designated position, and then the mother aircraft 100 disassembles. The daughter unmanned aerial vehicles 200 hover and form a formation by deploying their own tail rotors 3. After the formation is completed, the tail rotor 3 falls off, the tail accelerates through a small turbojet engine, the head 1 falls off when approaching the ground, and the recoil deceleration is achieved through the middle front engine 4 until it lands on the ground, ensuring that the radio shielding device inside the intermediate body 2 will not be damaged. After reaching the ground, the radio shielding device starts to play a role, thus realizing a landing process with fast, slow and stop functions, and can realize the function of electronically shielding the enemy's equipment.

[0043] The radio shielding device is arranged between the middle front engine 4 and the middle rear engine 5.

[0044] In a specific embodiment, as Figures 5 to 7 shown, the daughter unmanned aerial vehicle 200 includes a tail rotor 3, an intermediate body 2 and a head 1 connected in sequence. The middle front engine 4 and the middle rear engine 5 are respectively arranged at both ends of the intermediate body 2; the tail rotor 3 and the intermediate body 2, the head 1 and the intermediate body 2 are all connected through a separation device 6, and the separation device 6 can realize the separation of the tail rotor 3 and the intermediate body 2 and the separation of the head 1 and the intermediate body 2.

[0045] Among them, the separation device 6 includes a shape memory alloy wire 62, a stud 61, a compression spring 63 and an energizing mechanism. Both ends of the shape memory alloy wire 62 are fixedly connected with a stud 61. The stud 61 is coaxial with the shape memory alloy wire 62. The compression spring 63 is sleeved on the shape memory alloy wire 62 between the two studs 61. Under the pressure of the stud 61, the compression spring 63 is always in a compressed state. The energizing mechanism is used to energize the shape memory alloy wire 62. After the shape memory alloy wire 62 is energized, it heats itself and shrinks, thereby overcoming the restoring force of the compression spring 63 and causing the two studs 61 to approach each other;

[0046] The separation device 6 is fixed on the tail rotor 3 or the intermediate body 2. A groove matching the stud 61 is provided on the tail rotor 3 or the intermediate body 2 where the separation device 6 is not fixed. Under normal conditions, the end of the stud 61 abuts against the groove to realize the connection between the tail rotor 3 and the intermediate body 2; When separation is required, the energizing mechanism is controlled to energize the shape memory alloy wire 62, so that the stud 61 is disengaged from the groove to realize the separation of the two;

[0047] The separation device 6 is fixed on the head 1 or the intermediate body 2. A groove matching the stud 61 is provided on the head 1 or the intermediate body 2 where the separation device 6 is not fixed. Under normal conditions, the end of the stud 61 abuts against the groove to realize the connection between the head 1 and the intermediate body 2; When separation is required, the energizing mechanism is controlled to energize the shape memory alloy wire 62, so that the stud 61 is disengaged from the groove to realize the separation of the two.

[0048] As Figures 8 to 11 shown, each tail rotor 3 includes two wing rods, namely a first wing rod 31 and a second wing rod 32. The first wing rod 31 and the second wing rod 32 are connected by a hinge 33. Under normal conditions, the included angle between the first wing rod 31 and the second wing rod 32 is 90 degrees. The first wing rod 31 is made of a shape memory alloy material. The energizing mechanism can energize the first wing rod 31 and heat it to shrink and pull the second wing rod 32. The second wing rod 32 extends to be parallel to the first wing rod 31 under the action of the pulling force and the centrifugal force.

[0049] The first wing rod 31 is hinged to the hinge 33, and the second wing rod 32 is fixedly connected to the hinge 33. An installation hole 37 is provided at the end of the first wing rod 31. An inner spring 36 and a boss 34 are installed in the installation hole 37 from the inside to the outside in sequence; Under normal conditions, the boss 34 abuts against the side of the hinge 33 under the elastic force of the inner spring 36 and locks the hinge 33; When the second wing rod 32 extends, the hinge 33 rotates and compresses the boss 34 into the installation hole 37. A clamping hole 35 adapted to the boss 34 is provided at the end of the hinge 33. When the second wing rod 32 extends to be parallel to the first wing rod 31, the boss 34 moves outwards under the restoring force of the inner spring 36 and extends into the clamping hole 35 to lock the hinge 33 to the first wing rod 31.

[0050] In some embodiments, the mother aircraft 100 positions a plurality of daughter UAVs 200 through a fixed disk 7. A plurality of limiting holes are provided on the fixed disk 7. The fixed disk 7 is movably arranged inside the mother aircraft 100 along the axial direction of the mother aircraft 100. The fixed disk 7 is driven to move by a linear driving device 8. When the fixed disk 7 moves towards the head 1 of the daughter UAV 200 and exceeds the head 1, the daughter UAV 200 can escape from the fixed disk 7 and perform a free fall motion.

[0051] Before the fixed disk 7 moves, the mother aircraft 100 first disintegrates from the middle.

[0052] Of course, in other embodiments, a plurality of daughter UAVs 200 can also be directly stacked side by side in the mother aircraft 100.

[0053] In some embodiments, the tail rotor 3 is a pair of coaxial double tail rotors. There is a brushless motor at the upper and lower positions of the two tail rotors 3 respectively to ensure the rotation of the tail rotor 3.

[0054] Overall operation process

[0055] After receiving the superior instruction to shield the enemy battlefield, the ground personnel launch the mother aircraft 100 into the air. The mother aircraft 100 independently judges whether it is within the enemy position and whether to disperse the daughter UAVs 200. If it is within its range, the daughter UAVs 200 are released. The daughter UAVs 200 perform autonomous formation in the air. When the system determines that the formation of the daughter UAVs 200 is stable and hovering, a first separation of the daughter UAVs 200 is carried out, and the tail including the tail rotor 3 and the tail rotor 3 motor falls off. The middle rear engine 5 burns and dives towards the ground. When the daughter UAVs 200 detect that they are at a certain distance from the ground, a second separation is carried out. And in the initial separation stage, the middle front engine 4 acts on the head 1 and generates a reverse force, so that the intermediate body 2 buffers and decelerates. Subsequently, it decelerates under the continuous recoil action of the middle front engine 4, and the intermediate body 2 with a radio shielding device slowly descends. After the daughter UAVs 200 land smoothly, the radio shielding is realized, and the function of controlling the battlefield is completed, and the whole process is completed.

[0056] In the present invention, specific examples are used to elaborate the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. An intelligent unmanned flight system with signal shielding function, characterized in that: It includes a mother aircraft and multiple son drones. The son drones are equipped with radio shielding devices. The son drones are carried inside the mother aircraft. The son drones have tail rotors, middle front engines, middle rear engines, and heads. The son drones achieve hovering and queuing functions through the tail rotors. The son drones achieve dive acceleration functions through the middle rear engines. The son drones achieve recoil deceleration functions through the middle front engines. After the mother aircraft reaches a predetermined position, it automatically disassembles. Multiple son drones hover and queue up. After queuing up, the tail rotors at the tails of the son drones automatically fall off. They achieve dive acceleration functions through the middle rear engines. When the distance from the ground reaches the set threshold, the heads fall off, and they achieve recoil deceleration through the middle front engines until they land on the ground.

2. The intelligent unmanned flight system with signal shielding function according to claim 1, characterized in that: The middle front engine and the middle rear engine are small turbojet engines.

3. The intelligent unmanned flight system with signal shielding function according to claim 1, characterized in that: The mother aircraft limits the positions of multiple son drones through a fixing plate. Multiple limiting holes are provided on the fixing plate. The fixing plate is movably arranged inside the mother aircraft along the axial direction of the mother aircraft. The fixing plate is driven to move by a linear driving device. When the fixing plate moves towards the head of the son drone and exceeds the head, the son drone can escape from the fixing plate and perform a free fall motion. Before the fixing plate moves, the mother aircraft first disassembles from the middle.

4. The intelligent unmanned flight system with signal shielding function according to claim 1, characterized in that: The son drone includes the tail rotor, intermediate body, and head connected in sequence. The middle front engine and the middle rear engine are respectively arranged at both ends of the intermediate body. The tail rotor and the intermediate body, and the head and the intermediate body are all connected through separation devices. The separation devices can achieve the separation of the tail rotor and the intermediate body and the separation of the head and the intermediate body.

5. The intelligent unmanned flight system with signal shielding function according to claim 4, characterized in that: The separation device includes shape memory alloy wires, pin shafts, compression springs, and an energizing mechanism. Both ends of the shape memory alloy wire are fixedly connected with a pin shaft. The pin shaft is coaxial with the shape memory alloy wire. The compression spring is sleeved on the shape memory alloy wire between the two pin shafts. And under the pressure of the pin shaft, the compression spring is always in a compressed state. The energizing mechanism is used to energize the shape memory alloy wire. After the shape memory alloy wire is energized, it heats itself and shrinks, thereby overcoming the rebound force of the compression spring and making the two pin shafts approach each other. The separation device is fixed on the tail rotor or the intermediate body. Grooves matching the pin shafts are provided on the tail rotor or the intermediate body where the separation device is not fixed. Under normal conditions, the end of the pin shaft abuts against the groove to realize the connection between the tail rotor and the intermediate body. When separation is required, control the energizing mechanism to energize the shape memory alloy wire so that the pin shaft escapes from the groove to realize the separation of the two. The separation device is fixed on the head or the intermediate body. A groove matching the stud is provided on the head or the intermediate body where the separation device is not fixed. Under normal conditions, the end of the stud abuts against the groove to connect the head and the intermediate body. When separation is required, the energizing mechanism is controlled to energize the shape memory alloy wire so that the stud is withdrawn from the groove, thereby achieving the separation of the two.

6. The intelligent unmanned flight system with signal shielding function according to claim 5, characterized in that: Each tail rotor includes two wing rods, namely a first wing rod and a second wing rod. The first wing rod and the second wing rod are connected by a hinge. Under normal conditions, the included angle between the first wing rod and the second wing rod is 90 degrees. The first wing rod is made of shape memory alloy material. The energizing mechanism can energize the first wing rod and heat it to shrink, pulling the second wing rod. The second wing rod extends to be parallel to the first wing rod under the action of the pulling force and centrifugal force.

7. The intelligent unmanned flight system with signal shielding function according to claim 6, characterized in that: The first wing rod is hinged to the hinge, and the second wing rod is fixedly connected to the hinge. The end of the first wing rod is disposed in an installation hole, and an inner spring and a boss are sequentially installed in the installation hole from the inside to the outside. Under normal conditions, the boss abuts against the side of the hinge under the elastic force of the inner spring and locks the hinge. When the second wing rod extends, the hinge rotates and compresses the boss into the installation hole. A clamping hole adapted to the boss is provided at the end of the hinge. When the second wing rod extends to be parallel to the first wing rod, the boss moves outward under the rebounding force of the inner spring and extends into the clamping hole to lock the hinge to the first wing rod.

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