Coaxial multi-rotor patrol bomb

Abstract

The invention relates to the technical field of intelligent ammunition, and discloses a coaxial multi-rotor patrol ammunition which comprises an integrated control part, an ammunition body part and an integrated power part, a plurality of first propeller blades and second propeller blades are connected to the integrated power part, and a seeker is connected to the outer wall of the integrated control part; the adjustable shielding mechanism is connected to the other end of the projectile body part in a sliding manner; the elastic energy releasing mechanism is connected between the adjustable shielding mechanism and the projectile body part; the shape of the adjustable shielding and preventing mechanism can be adjusted according to the flight attitude, and when entering an attack state, the adjustable shielding and preventing mechanism is in an unfolded state, so that a conical protective cover is formed, the whole projectile body part and the flight structure can be effectively covered for protection, wind resistance is reduced, and the service life of the projectile body part is prolonged. And meanwhile, the elastic energy release mechanism can be used for partially converting the resistance generated by the attack on the conical shield into reverse jet power, so that the kinetic energy loss during the attack of the flying projectile is effectively reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of smart ammunition, and more particularly to a coaxial multi-rotor cruise missile. Background Art

[0002] A cruise missile is a precision munition that can cruise over a target area and execute combat orders. It is also the product of the organic combination of drone technology and ammunition technology. It mainly undertakes combat missions such as battlefield reconnaissance, target indication, precision strikes, damage assessment, communication relay, electronic countermeasures, air surveillance and special payload delivery.

[0003] A cruise missile is a lightweight, intelligent space missile between a cruise missile and a drone. Its biggest feature is that it can fly in the target area for a period of time and conduct reconnaissance, and then launch an attack after the operator determines the target.

[0004] When an existing cruise missile executes an attack command, each blade generates a pulling force consistent with the direction of gravity; this pulling force and gravity act together on the missile body, producing an attack acceleration greater than one g (g is 9.8m / s2), thereby achieving a rapid and precise strike. However, in this process, there is still the possibility of being counterattacked by the target and crashing. Summary of the Invention

[0005] The purpose of the present invention is to provide a coaxial multi-rotor cruise missile in order to solve the above problems.

[0006] The present invention provides a coaxial multi-rotor cruise missile, comprising: An integrated control unit, wherein the ends of the integrated control unit are respectively connected to the projectile unit and the integrated power unit, and the integrated power unit is connected to a plurality of propeller blades 1 and propeller blades 2, and the integrated power unit is used to drive the plurality of propeller blades 1 and propeller blades 2 to rotate around the central axis of the integrated power unit at a set speed and direction. A guide head is connected to the outer wall of the integrated control unit; an adjustable shielding mechanism, the adjustable shielding mechanism being slidably connected to the other end of the body portion, such that when the adjustable shielding mechanism is in an extended state, the integrated control unit, the body portion, the integrated power unit, the plurality of propeller blades one, and the plurality of propeller blades two are all within a protective coverage area of the adjustable shielding mechanism; An elastic energy release mechanism is connected between the adjustable shielding mechanism and the elastic body portion, and is used to buffer the resistance exerted on the adjustable shielding mechanism in the direction toward the elastic body portion.

[0007] As a further optimization scheme of the present invention, the integrated control unit includes a shell one, an integrated control circuit board arranged in the shell one, a battery and an attitude adjustment component arranged in the shell one, and the projectile body, integrated power unit, attitude adjustment component and guide head are all electrically connected to the integrated control circuit board.

[0008] As a further optimization scheme of the present invention, the integrated power unit includes a shell two, a power motor arranged in the shell two, a bearing part, a transmission gear one connected to the output end of the power motor, and a transmission gear two connected to the bearing part. Several of the propeller blades one are connected to the bearing part, and several propeller blades two are connected to a sleeve ring. The sleeve ring is movably connected to the bearing part through a rotating shaft. The attitude adjustment component is hinged to the sleeve ring, and the attitude adjustment component is used to control the sleeve ring to rotate around the rotating shaft to a set angle.

[0009] As a further optimization scheme of the present invention, the adjustable shielding mechanism includes a sliding support assembly, several spliced protection assemblies hinged on the sliding support assembly, and an adjustment assembly connected to the sliding support assembly. Several of the spliced protection assemblies are connected to the adjustment assembly, and the adjustment assembly is used to adjust the distribution posture of several spliced protection assemblies on the sliding support assembly.

[0010] As a further optimization scheme of the present invention, the sliding support assembly includes a supporting slide rod, a conical head connected to one end of the supporting slide rod, and several hinged rods fixedly connected to the outer surface of the supporting slide rod near the conical head. The other end of the supporting slide rod passes through the elastic energy release mechanism and extends to the interior of the elastic body. The interior of the elastic body is provided with a chamber for the other end of the supporting slide rod to move.

[0011] As a further optimization scheme of the present invention, the spliced protective assembly includes a shielding panel, a hinged rod 2 fixedly connected at the narrow end of the shielding panel, and a hinged rod 3 fixedly connected at the flared end of the shielding panel. The other end of the hinged rod 2 is hinged to the other end of the hinged rod 1. The shielding panel is matched with the conical head. When the narrow ends of several of the shielding panels are in contact with the conical head, a conical protective cover is formed.

[0012] As a further optimization scheme of the present invention, the adjustment component includes a sliding ring 1 and a sliding ring 2 slidingly connected to the supporting slide rod, a plurality of hinged rods 4 hinged on the sliding ring 1, a plurality of hinged rods 5 hinged on the sliding ring 2, a fixed connecting plate fixedly connected to the supporting slide rod, an integrated motor 1 and an integrated motor 2 fixedly mounted on the fixed connecting plate, a screw 1 and a screw 2 respectively connected to the output ends of the integrated motor 1 and the integrated motor 2, the screw 1 is threadedly connected to the sliding ring 1, the screw 2 is threadedly connected to the sliding ring 2, the sliding ring 1 is provided with a through hole 1 for the screw 2 to pass through, and the sliding ring 2 is provided with a through hole 2 for the screw 1 to pass through.

[0013] As a further optimization scheme of the present invention, the elastic energy release mechanism includes an elastic gas storage component and a one-way exhaust component arranged on the elastic gas storage component. When the elastic gas storage component is compressed, the internal gas is only discharged toward the direction of the elastic body.

[0014] As a further optimization scheme of the present invention, the elastic air storage assembly includes a connecting ring plate, a bellows connected to the connecting ring plate and a spring 1. The connecting ring plate is sleeved on the supporting slide rod, and a seal is provided between the connecting ring plate and the supporting slide rod. The other ends of the bellows and spring 1 are fixedly connected to spring 1, and a sealed air storage chamber is formed between the connecting ring plate, the bellows and the fixed connecting plate.

[0015] As a further optimization scheme of the present invention, the one-way exhaust assembly includes an air guide cavity 1 and an air guide cavity 2 arranged inside the support slide rod, two splicing mounting brackets detachably connected to the support slide rod, a one-way valve body installed in the splicing mounting bracket, a multi-way air guide pipe connected to the other end of the support slide rod, and a plurality of exhaust holes arranged on the body part, the exhaust holes are along the central axis direction of the body part, and the plurality of exhaust holes are connected to the multi-way air guide pipe. One end of the air guide cavity 1 and the air guide cavity 2 is located on the support slide rod. At a position close to the fixed connecting plate, the two spliced mounting brackets are respectively connected to the first air guide channel and the second air guide channel. The two one-way valve bodies are distributed in opposite directions. The other end of the second air guide channel is located on the conical head, and the other end of the first air guide channel is connected to the multi-way air guide tube. The one-way valve body adapted to the first air guide channel is used to limit the gas in the sealed air storage chamber to flow only into the first air guide channel, and the one-way valve body adapted to the second air guide channel is used to limit the gas in the second air guide channel to flow only into the sealed air storage chamber. The one-way valve body includes a central shell, a ventilation ring plate connected to the exhaust end of the central shell, a spring 2 connected to the ventilation ring plate, a sealing ring connected to a hollow stepped shaft body and an outer wall of the central shell, and the hollow stepped shaft body is used to block the air inlet end of the central shell.

[0016] The beneficial effects of the present invention are that the adjustable shielding mechanism provided in the present invention can adjust its shape according to the flight posture. When entering the attack state, the adjustable shielding mechanism is in the expanded state, thereby forming a conical shield, which can effectively cover the entire missile body and flight structure to provide protection and reduce wind resistance. At the same time, the resistance generated by the attack on the conical shield can be partially converted into reverse jet power through the elastic energy release mechanism, thereby effectively reducing the kinetic energy loss during the missile attack. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall structure of the present invention; Figure 2 The present invention Figure 1 Front view of Figure 3 This is a diagram showing the coordination of the adjustable shielding mechanism and the elastic energy release mechanism of the present invention; Figure 4 It is a structural schematic diagram of the elastic energy release mechanism of the present invention; Figure 5 The present invention Figure 4 Magnified view at point A in the middle; Figure 6 It is a cross-sectional view of the one-way valve body of the present invention.

[0018] In the figure: 1. Integrated control unit; 2. Projectile body; 3. Integrated power unit; 4. Propeller blade 1; 5. Propeller blade 2; 6. Seeker; 7. Adjustable shielding mechanism; 701. Support slide bar; 702. Conical head; 703. Articulated rod 1; 704. Articulated rod 2; 705. Shielding plate; 706. Articulated rod 3; 707. Sliding collar 1; 708. Sliding collar 2; 709. Articulated rod 4; 710. Articulated rod 5; 711. Fixed connection Connecting plate; 712, integrated motor 1; 713, screw 1; 714, integrated motor 2; 8, elastic energy release mechanism; 801, connecting ring plate; 802, bellows; 803, spring 1; 804, air guide cavity 1; 805, air guide cavity 2; 806, spliced mounting frame; 807, one-way valve body; 8070, center-through shell; 8071, ventilation ring plate; 8072, hollow stepped shaft; 8073, spring 2; 8074, sealing ring. DETAILED DESCRIPTION

[0019] The subject matter described herein will now be discussed with reference to example embodiments. It should be understood that these embodiments are discussed solely to enable those skilled in the art to better understand and implement the subject matter described herein. Additionally, features described with respect to some examples may also be combined in other examples.

[0020] like Figures 1-6 As shown, a coaxial multi-rotor cruise missile comprises: An integrated control unit 1, with the projectile body 2 and the integrated power unit 3 connected to its two ends, and a plurality of propeller blades 1 4 and 2 5 connected to the integrated power unit 3. The integrated power unit 3 is used to drive the plurality of propeller blades 1 4 and 2 5 to rotate around the central axis of the integrated power unit 3 at a set speed and direction. A guide head 6 is connected to the outer wall of the integrated control unit 1; An adjustable shielding mechanism 7 is slidably connected to the other end of the body portion 2. When the adjustable shielding mechanism 7 is in the deployed state, the integrated control unit 1, the body portion 2, the integrated power unit 3, the plurality of propeller blades 1 4, and the plurality of propeller blades 2 5 are all within the protective coverage area of the adjustable shielding mechanism 7. The elastic energy release mechanism 8 is connected between the adjustable shielding mechanism 7 and the elastic body 2 . The elastic energy release mechanism 8 is used to buffer the resistance exerted on the adjustable shielding mechanism 7 in the direction toward the elastic body 2 .

[0021] The projectile body 2 can be a variety of types of projectiles, and can be equipped with different types of seekers 6, such as a platform seeker, a strapdown seeker, a visible light seeker, a laser seeker, and a radar seeker. By configuring different seekers 6, it is possible to achieve locking and tracking tasks for different target types in different weather environments.

[0022] It should be noted that, when in the patrol state, the adjustable shielding mechanism 7 is in a gathered state. At this time, the adjustable shielding mechanism 7 will not generate a large flight resistance in any flight state. When the attack target is locked and the attack process is entered, the integrated control unit 1 adjusts the rotation speed, rotation direction and posture of the propeller blade 1 4 and the propeller blade 2 5, thereby adjusting the posture and flight path of the integrated control unit 1, the missile body 2 and the integrated power unit 3, and flies quickly toward the attack target with a precise flight trajectory. At this time, the adjustable shielding mechanism 7 is in an expanded state. When the adjustable shielding mechanism 7 is in the expanded state, the integrated control unit 1 can be lowered. 1, the wind resistance suffered by the projectile body 2 and the integrated power unit 3 during flight. At the same time, the integrated control unit 1, the projectile body 2, the integrated power unit 3, the propeller blade 1 4 and the propeller blade 2 5 can be within the protection range of the adjustable shielding mechanism 7, which can effectively reduce the damage caused by the counterattack of the target to the integrated control unit 1, the projectile body 2, the integrated power unit 3, the propeller blade 1 4 and the propeller blade 2 5, and can effectively improve the stability of the striking process. The elastic energy release mechanism 8 can convert part of the resistance generated when the adjustable shielding mechanism 7 is struck into reverse jet power, thereby effectively reducing the kinetic energy loss during the striking process, so that the projectile body 2 can maintain rapid movement.

[0023] In an optional embodiment of the present invention, Figure 1 and2 As shown, the integrated control unit 1 includes a shell, an integrated control circuit board arranged in the shell, a battery and an attitude adjustment component arranged in the shell. The projectile body 2, the integrated power unit 3, the attitude adjustment component and the seeker 6 are all electrically connected to the integrated control circuit board.

[0024] The integrated power unit 3 includes a shell 2, a power motor arranged in the shell 2, a bearing part, a transmission gear 1 connected to the output end of the power motor, and a transmission gear 2 connected to the bearing part. Several propeller blades 1 4 are connected to the bearing part, and several propeller blades 2 5 are connected to a sleeve ring. The sleeve ring is movably connected to the bearing part through a rotating shaft. The attitude adjustment component is hinged to the sleeve ring, and the attitude adjustment component is used to control the sleeve ring to rotate around the rotating shaft to a set angle.

[0025] It should be noted that this is existing technology and will not be described in detail here. The posture adjustment component can adopt a linear drive component or a crank rocker mechanism. The specific structure is not shown. It can be customized or designed according to the specific space inside the shell two and the design parameters.

[0026] In an optional embodiment of the present invention, Figure 1 and Figure 3 As shown, the adjustable shielding mechanism 7 includes a sliding support assembly, a plurality of spliced protection assemblies hinged on the sliding support assembly, and an adjustment assembly connected to the sliding support assembly. The plurality of spliced protection assemblies are all connected to the adjustment assembly, and the adjustment assembly is used to adjust the distribution posture of the plurality of spliced protection assemblies on the sliding support assembly.

[0027] The sliding support assembly includes a supporting slide 701, a conical head 702 connected to one end of the supporting slide 701, and several hinged rods 703 fixedly connected to the outer surface of the supporting slide 701 near the conical head 702. The other end of the supporting slide 701 passes through the elastic energy release mechanism 8 and extends to the interior of the body 2. The interior of the body 2 is provided with a chamber for the other end of the supporting slide 701 to move.

[0028] The spliced protective assembly includes a shielding panel 705, a hinged rod 2 704 fixedly connected at the narrow end of the shielding panel 705, and a hinged rod 3 706 fixedly connected at the flared end of the shielding panel 705. The other end of the hinged rod 2 704 is hinged to the other end of the hinged rod 1 703. The shielding panel 705 is matched with the conical head 702. When the narrow ends of several shielding panels 705 are in contact with the conical head 702, a conical protective cover is formed.

[0029] The adjustment component includes a sliding ring 1 707 and a sliding ring 2 708 slidingly connected to the support slide 701, a plurality of hinged rods 4 709 hinged on the sliding ring 1 707, a plurality of hinged rods 5 710 hinged on the sliding ring 2 708, a fixed connecting plate 711 fixedly connected to the support slide 701, an integrated motor 1 712 and an integrated motor 2 714 fixedly mounted on the fixed connecting plate 711, a screw 1 713 and a screw 2 connected to the output ends of the integrated motor 1 712 and the integrated motor 2 714 respectively, the screw 1 713 being threadedly connected to the sliding ring 1 707, the screw 2 being threadedly connected to the sliding ring 2 708, the sliding ring 1 707 being provided with a through hole 1 for the screw 2 to pass through, and the sliding ring 2 708 being provided with a through hole 2 for the screw 1 713 to pass through.

[0030] It should be noted that, as mentioned above, when the distribution state of several spliced protective components is adjusted by the adjustment component to form a conical protective cover or to put several spliced protective components in a bundled state, specifically, when the conical protective cover is formed, the screw rod 713 is first driven to rotate by the integrated motor 712. At this time, the sliding collar 707 threadedly connected to the screw rod 713 can be driven by the screw rod 713 to move along the support slide rod 701 toward the conical head 702. During the movement, it can drive the hinge rod 3 706 to move in the direction away from the support slide rod 701 through the hinge rod 4 709, and under the linkage action, the narrow end of the shielding plate 705 is driven to rotate around the hinge point between the hinge rod 2 704 and the hinge rod 1 703 until the narrow end of the shielding plate 705 is aligned with the conical head 702. When the conical head 702 is in close contact and generates a set force, the integrated motor 1 712 stops working, and then the screw 2 is driven to rotate by the integrated motor 2 714. When the integrated motor 1 712 rotates, it can drive the sliding collar 2 708 to move toward the conical head 702, and drive the flared end of the corresponding shielding plate 705 to move in the direction away from the supporting slide bar 701 through the hinge rod 5 710, and make the narrow end of the shielding plate 705 rotate around the hinge point of the hinge rod 2 704 and the hinge rod 1 703 until the narrow end of the shielding plate 705 contacts the conical head 702 and generates a set force, and the integrated motor 2 714 stops working. At this time, all the shielding plates 705 are in the set position and form a complete conical shield with the conical head 702. When adjusting several shielding panels 705 to the gathered state, the integrated motor 2 714 is first used to drive the screw 2 to reverse, so that the sliding collar 2 708 moves back and drives the corresponding shielding panels 705 to return to their initial positions. Then, the integrated motor 1 712 is used to drive the screw 1 713 to reverse, so that the corresponding shielding panels 705 are restored to their initial positions. When the several shielding panels 705 linked with the sliding collar 2 708 and the several shielding panels 705 linked with the sliding collar 1 707 are in the same circular distribution area in the initial position, forming a cross-distribution state, which can effectively prevent the several shielding panels 705 from obstructing each other's travel.

[0031] In an optional embodiment of the present invention, Figure 1 as well as Figure 3-Figure 6 As shown, the elastic energy release mechanism 8 includes an elastic gas storage component and a one-way exhaust component provided on the elastic gas storage component. When the elastic gas storage component is compressed, the internal gas is discharged only toward the direction of the elastic body 2.

[0032] The elastic air storage component includes a connecting ring plate 801, a bellows 802 connected to the connecting ring plate 801, and a spring 803. The connecting ring plate 801 is sleeved on the supporting slide rod 701, and a seal is provided between the connecting ring plate 801 and the supporting slide rod 701. The other ends of the bellows 802 and the spring 803 are fixedly connected to the spring 803. A sealed air storage chamber is formed between the connecting ring plate 801, the bellows 802 and the fixed connecting plate 711.

[0033] The one-way exhaust assembly includes an air guide channel 1 804 and an air guide channel 2 805 provided inside the support slide 701, two splicing mounting brackets 806 detachably connected to the support slide 701, a one-way valve body 807 installed in the splicing mounting bracket 806, a multi-way air guide pipe connected to the other end of the support slide 701, and a plurality of exhaust holes provided on the body portion 2. The exhaust holes are along the central axis direction of the body portion 2. The plurality of exhaust holes are connected to the multi-way air guide pipe. One end of the air guide channel 1 804 and the air guide channel 2 805 is located on the support slide 701 near the fixed connecting plate 711. At the position, two spliced mounting brackets 806 are respectively connected to the first gas guide channel 804 and the second gas guide channel 805. The two one-way valve bodies 807 are distributed in opposite directions. The other end of the second gas guide channel 805 is located on the conical head 702, and the other end of the first gas guide channel 804 is connected to the multi-way gas guide tube. The one-way valve body 807 adapted to the first gas guide channel 804 is used to limit the gas in the sealed gas storage chamber to flow only into the first gas guide channel 804, and the one-way valve body 807 adapted to the second gas guide channel 805 is used to limit the gas in the second gas guide channel 805 to flow only into the sealed gas storage chamber. The one-way valve body 807 includes a central shell 8070, a ventilation ring plate 8071 connected to the exhaust end of the central shell 8070, a spring 2 8073 connected to the ventilation ring plate 8071, a sealing ring 8074 connected to the hollow stepped shaft 8072 and the outer wall of the central shell 8070. The hollow stepped shaft 8072 is used to seal the air inlet end of the central shell 8070.

[0034] It should be noted that, as described above, when the adjustable shielding mechanism 7 is in the expanded state and forms a conical shield, when the counterattack of the target hits the adjustable shielding mechanism 7, the force exerted on the entire adjustable shielding mechanism 7 drives the supporting slide bar 701 to move toward the inside of the projectile body 2, and drives the fixed connecting plate 711 to squeeze the bellows 802 and the spring 1 803. At this time, the space inside the sealed air storage chamber is reduced, and the internal air pressure increases, squeezing the one-way valve body 807 that cooperates with the air guide channel 1 804. The hollow stepped shaft 8072 in the middle moves the hollow stepped shaft 8072 toward the ventilation ring plate 8071 and squeezes the second spring 8073, so that the air guide channel 1 804 is connected to the space inside the sealed air storage chamber through the middle shell 8070. The gas inside the sealed air storage chamber can flow into the air guide channel 1 804 and, under the action of air pressure, is discharged along the multi-channel air guide pipe to the several exhaust holes on the projectile body 2, thereby forming a jet power in the opposite direction to the striking force, which can effectively buffer the force exerted on the adjustable shielding mechanism 7 and reduce the loss of the overall flight kinetic energy. When the impact force exerted on the adjustable shielding mechanism 7 is slowly released, the spring 1 803 is restored, thereby increasing the space inside the sealed air storage chamber and generating negative pressure inside. The negative pressure can adsorb the hollow stepped shaft 8072 in the one-way valve body 807 that cooperates with the second air guide cavity 805 toward the ventilation ring plate 8071, thereby connecting the second air guide cavity 805 with the sealed air storage chamber. At this time, the external gas can flow from the second air guide cavity 805 to the sealed air storage chamber under the action of negative pressure suction, thereby replenishing the gas for the next impact and buffering use.

[0035] The above describes this embodiment, but this embodiment is not limited to the above-mentioned specific implementation methods. The above-mentioned specific implementation methods are merely illustrative and not restrictive. Ordinary technicians in this field can also make many forms based on the inspiration of this embodiment, all of which are protected by this embodiment.

Claims

1. A coaxial multi-rotor cruise missile, characterized in that: include: An integrated control unit (1), wherein both ends of the integrated control unit (1) are respectively connected to a body unit (2) and an integrated power unit (3), and the integrated power unit (3) is connected to a plurality of propeller blades one (4) and propeller blade two (5), the integrated power unit (3) is used to drive the plurality of propeller blades one (4) and propeller blade two (5) to rotate around a central axis of the integrated power unit (3) at a set speed and direction, and a guide head (6) is connected to an outer wall of the integrated control unit (1); An adjustable shielding mechanism (7), wherein the adjustable shielding mechanism (7) is slidably connected to the other end of the body portion (2); when the adjustable shielding mechanism (7) is in an unfolded state, the integrated control portion (1), the body portion (2), the integrated power portion (3), the plurality of propeller blades (4) and the plurality of propeller blades (5) are all within a protective coverage area of the adjustable shielding mechanism (7); An elastic energy release mechanism (8), wherein the elastic energy release mechanism (8) is connected between the adjustable shielding mechanism (7) and the elastic body portion (2), and the elastic energy release mechanism (8) is used to buffer the resistance exerted on the adjustable shielding mechanism (7) in a direction toward the elastic body portion (2).

2. The coaxial multi-rotor cruise missile according to claim 1, characterized in that: The integrated control unit (1) comprises a housing, an integrated control circuit board arranged in the housing, a battery, and a posture adjustment component arranged in the housing; the projectile body (2), the integrated power unit (3), the posture adjustment component, and the seeker (6) are all electrically connected to the integrated control circuit board.

3. The coaxial multi-rotor cruise missile according to claim 2, characterized in that: The integrated power unit (3) includes a housing 2, a power motor arranged in the housing 2, a bearing unit, a transmission gear 1 connected to the output end of the power motor, and a transmission gear 2 connected to the bearing unit. A plurality of propeller blades 1 (4) are connected to the bearing unit, and a plurality of propeller blades 2 (5) are connected to a sleeve ring. The sleeve ring is movably connected to the bearing unit through a rotating shaft. The attitude adjustment component is hinged to the sleeve ring, and the attitude adjustment component is used to control the sleeve ring to rotate around the rotating shaft to a set angle.

4. The coaxial multi-rotor cruise missile according to claim 3, characterized in that: The adjustable shielding mechanism (7) comprises a sliding support assembly, a plurality of spliced protection assemblies hinged on the sliding support assembly, and an adjustment assembly connected to the sliding support assembly, wherein the plurality of spliced protection assemblies are connected to the adjustment assembly, and the adjustment assembly is used to adjust the distribution posture of the plurality of spliced protection assemblies on the sliding support assembly.

5. The coaxial multi-rotor cruise missile according to claim 4, characterized in that: The sliding support assembly comprises a supporting slide bar (701), a conical head (702) connected to one end of the supporting slide bar (701), and a plurality of hinged rods (703) fixedly connected to the outer surface of the supporting slide bar (701) near the conical head (702). The other end of the supporting slide bar (701) passes through the elastic energy release mechanism (8) and extends to the interior of the elastic body (2). The interior of the elastic body (2) is provided with a chamber for the other end of the supporting slide bar (701) to move.

6. The coaxial multi-rotor cruise missile according to claim 5, characterized in that: The spliced protective assembly comprises a shielding plate (705), a hinged rod 2 (704) fixedly connected to the narrow end of the shielding plate (705), and a hinged rod 3 (706) fixedly connected to the flared end of the shielding plate (705), the other end of the hinged rod 2 (704) being hinged to the other end of the hinged rod 1 (703), the shielding plate (705) being matched with the conical head (702), and when the narrow ends of several shielding plates (705) are in contact with the conical head (702), a conical protective shield is formed.

7. The coaxial multi-rotor cruise missile according to claim 6, characterized in that: The adjustment assembly includes a sliding ring 1 (707) and a sliding ring 2 (708) slidably connected to the support slide bar (701), a plurality of hinged rods 4 (709) hinged to the sliding ring 1 (707), a plurality of hinged rods 5 (710) hinged to the sliding ring 2 (708), a fixed connecting plate (711) fixedly connected to the support slide bar (701), an integrated motor 1 (712) fixedly mounted on the fixed connecting plate (711), and an integrated motor 1 (713). The integrated motor 2 (714) is provided with a screw 1 (713) and a screw 2 connected to the output ends of the integrated motor 1 (712) and the integrated motor 2 (714), respectively; the screw 1 (713) is threadedly connected to the sliding ring 1 (707); the screw 2 is threadedly connected to the sliding ring 2 (708); the sliding ring 1 (707) is provided with a through hole 1 for the screw 2 to pass through; the sliding ring 2 (708) is provided with a through hole 2 for the screw 1 (713) to pass through.

8. The coaxial multi-rotor cruise missile according to claim 7, characterized in that: The elastic energy release mechanism (8) comprises an elastic gas storage component and a one-way exhaust component provided on the elastic gas storage component. When the elastic gas storage component is compressed, the gas inside the elastic gas storage component is discharged only in the direction of the elastic body (2).

9. The coaxial multi-rotor loitering missile according to claim 8, characterized in that: The elastic gas storage component includes a connecting ring plate (801), a bellows (802) connected to the connecting ring plate (801), and a spring (803); the connecting ring plate (801) is sleeved on the supporting slide bar (701), and a sealing member is provided between the connecting ring plate (801) and the supporting slide bar (701); the other ends of the bellows (802) and the spring (803) are fixedly connected to the spring (803); and a sealed gas storage chamber is formed between the connecting ring plate (801), the bellows (802) and the fixed connecting plate (711).

10. The coaxial multi-rotor cruise missile according to claim 9, characterized in that: The one-way exhaust assembly includes an air guide channel 1 (804) and an air guide channel 2 (805) provided inside the support slide bar (701), two splicing type mounting frames (806) detachably connected to the support slide bar (701), a one-way valve body (807) installed in the splicing type mounting frame (806), a multi-way air guide tube connected to the other end of the support slide bar (701), and a plurality of exhaust holes provided on the body part (2), the exhaust holes being along the central axis direction of the body part (2), and the plurality of exhaust holes being connected to the multi-way air guide tube, and one end of the air guide channel 1 (804) and the air guide channel 2 (805) being located on the support slide bar (701) near the fixed connecting plate (711). At the position of, the two spliced mounting frames (806) are respectively connected to the air guide channel 1 (804) and the air guide channel 2 (805), the two one-way valve bodies (807) are distributed in opposite directions, the other end of the air guide channel 2 (805) is located on the conical head (702), the other end of the air guide channel 1 (804) is connected to the multi-way air guide tube, the one-way valve body (807) adapted to the air guide channel 1 (804) is used to limit the gas in the sealed air storage chamber to only flow into the air guide channel 1 (804), and the one-way valve body (807) adapted to the air guide channel 2 (805) is used to limit the gas in the air guide channel 2 (805) to only flow into the sealed air storage chamber; The one-way valve body (807) comprises a central shell (8070), a ventilation ring plate (8071) connected to the exhaust end of the central shell (8070), a second spring (8073) connected to the ventilation ring plate (8071), a hollow stepped shaft (8072) connected to the outer wall of the central shell (8070), and a sealing ring (8074) connected to the outer wall of the central shell (8070). The hollow stepped shaft (8072) is used to seal the air inlet end of the central shell (8070).

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