A compound carrier vertical take-off cruise missile

Abstract

The application discloses a vertical take-off cruise missile with a composite carrier and unmanned aerial vehicle, and relates to the technical field of cruise missiles, which comprises a carrier and at least one unmanned aerial vehicle; the carrier is used for carrying a first combat unit, and a supporting mechanism is arranged on the carrier and can be supported on a fixed surface when the carrier vertically takes off; the unmanned aerial vehicle is detachably connected to the carrier and is used for carrying a second combat unit; the unmanned aerial vehicle can provide thrust when the carrier vertically takes off and attitude is controlled; and the unmanned aerial vehicle can be separated from the carrier to attack a target. The vertical take-off cruise missile with the composite carrier and unmanned aerial vehicle expands the attack range and multi-target attack capability of the cruise missile and improves take-off conditions and cruising capability.

Description

Technical Field

[0001] This invention relates to the field of loitering munitions, and in particular to a vertical takeoff and landing loitering munition that is a composite carrier for unmanned aerial vehicles. Background Technology

[0002] Loitering munitions are a product of the combination of guided munitions and small unmanned aerial vehicle (UAV) technology, possessing capabilities such as reconnaissance, target location, airborne relay, electronic jamming, and precision strike. Loitering munitions can remain airborne for extended periods, continuously deterring and suppressing mobile targets in "gray areas" with unclear target information over a large area, and conducting coordinated attacks. When equipped with composite seekers and different types of payloads, they can also perform reconnaissance and surveillance, damage assessment, communication relay, and electronic jamming missions. Through data link networking, they can also achieve swarming and coordinated operations among loitering munitions. In recent local wars and conflicts, loitering munitions have also been deployed on the battlefield and used on a large scale. Practice has proven that using loitering munitions to strike armored vehicles, tanks, and radar facilities can achieve good combat results.

[0003] Currently, loitering munitions mainly fall into two categories: small man-portable loitering munitions (MANPADS) and large vehicle-mounted loitering munitions. Small MANPADS can carry small warhead payloads, have short flight times, and short attack ranges, and are primarily launched using small ejection systems. The emphasis on portability limits the weight and size of the warhead payload. These munitions have a limited range, only able to strike nearby personnel and unarmored vehicles. Large loitering munitions, on the other hand, can carry large warhead payloads, have long flight times, and long attack ranges, and are often launched using vehicle-mounted ejection systems or rocket-assisted launches. Large loitering munitions emphasize large payloads and can strike armored targets, but require ejection systems or rocket-assisted launches. The complexity of their launch boosters increases with the aircraft's weight. Large loitering munitions using booster launchers not only place higher structural and stability requirements on the airframe and equipment, but the vehicle-mounted ejection system also limits the number of munitions that can be carried. Summary of the Invention

[0004] The purpose of this invention is to provide a UAV-based composite vertical takeoff and landing loitering munition to solve the problems existing in the prior art, expand the strike range and multi-target strike capability of the loitering munition, and improve takeoff conditions and cruise capability.

[0005] To achieve the above objectives, the present invention provides the following solution:

[0006] This invention provides a UAV-based composite vertical takeoff and landing loitering munition, comprising a carrier aircraft and at least one UAV; the carrier aircraft carries a first warhead and is equipped with a support mechanism that supports the carrier aircraft on a fixed surface during vertical takeoff; the UAV is detachably connected to the carrier aircraft and carries a second warhead; the UAV provides thrust during vertical takeoff and attitude control of the carrier aircraft; and the UAV can detach from the carrier aircraft to engage targets.

[0007] Preferably, the support mechanism includes multiple pods circumferentially distributed at the tail of the carrier aircraft, each pod being parallel to the axial direction of the carrier aircraft, and the outer wall of each pod being streamlined; multiple UAVs are configured, and each pod is detachably equipped with one UAV; the pods are able to be supported on a fixed surface when the carrier aircraft takes off vertically.

[0008] Preferably, each of the pods is provided with a separation mechanism, which is connected to both the pod and the drone. The separation mechanism can limit or release the drone within the pod.

[0009] Preferably, the separation mechanism includes a locking member and a separation drive member; the separation drive member is disposed on the pod and connected to the locking member; the separation drive member can drive the locking member to connect the pod and the drone inside the pod, thereby limiting the drone within the pod, and the separation drive member can also drive the locking member to disconnect the pod and the drone inside the pod, thereby releasing the drone from the limitation within the pod.

[0010] Preferably, the carrier aircraft is a fixed-wing carrier aircraft, including a fuselage, a canard assembly, a wing assembly, and a power assembly; the first warhead is disposed inside the fuselage; the canard assembly is disposed on the front side of the fuselage; the wing assembly is disposed on the rear side of the fuselage, and the support mechanism is disposed on the wing assembly; the power assembly is disposed at the rear end of the fuselage and is used to provide propulsion.

[0011] Preferably, the wing assembly includes four main wings, which are symmetrically arranged about the central section of the fuselage, and the dihedral angle of the main wings on the upper side of the fuselage is the same as that of the main wings on the lower side of the fuselage; each main wing is provided with a pod at its wingtip; and each main wing is provided with a rotatable aileron at its trailing edge.

[0012] Preferably, the canard assembly includes two main canards, which are symmetrically arranged about the center section of the fuselage; and each main canard has a tilting elevator on its trailing edge.

[0013] Preferably, the fuselage is equipped with an electro-optical pod, a first flight controller, and a first power supply unit. The first flight controller is communicatively connected to the power unit, the ailerons, the elevator, the electro-optical pod, the separation mechanism, and the first warhead. The first flight controller is used to communicate with a ground station and can receive command information. The first flight controller can also receive detection information from the electro-optical pod and can control the movement of the power unit, the ailerons, the elevator, the separation mechanism, and the first warhead. The first power supply unit is electrically connected to the electro-optical pod, the first flight controller, the power unit, the ailerons, the elevator, and the separation mechanism, and provides the required electrical energy.

[0014] Preferably, the UAV is configured as a coaxial UAV, including a fuselage, an upper rotor, a lower rotor, a rotation drive assembly, and a rotor torque converter assembly; a second warhead is disposed within the fuselage; the upper rotor, the lower rotor, the rotation drive assembly, and the rotor torque converter assembly are all disposed on the fuselage; the rotation drive assembly is connected to the upper rotor and the lower rotor, and drives the upper rotor and the lower rotor to coaxially rotate in opposite directions; the rotor torque converter assembly is connected to the upper rotor and the lower rotor, and is capable of adjusting the collective pitch and periodic torque of the upper rotor and the lower rotor.

[0015] Preferably, the housing further includes a navigation component, a second flight controller, and a second power supply component. The second flight controller is communicatively connected to the rotary drive assembly, the rotor torque converter assembly, the navigation component, and the first flight controller. The second flight controller can receive command information from the first flight controller and navigation information from the navigation component, and can control the operation of the rotary drive assembly and the rotor torque converter assembly. The second power supply component is electrically connected to the rotary drive assembly, the rotor torque converter assembly, the navigation component, and the second flight controller, and provides the required electrical energy.

[0016] The present invention achieves the following technical effects compared to the prior art:

[0017] The UAV-based composite carrier vertical takeoff and landing loitering munition provided by this invention features a carrier aircraft carrying a UAV, with a support mechanism on the carrier aircraft supporting the ground, enabling the loitering munition to take off vertically. The inclusion of the UAV enhances the vertical takeoff and cruise capabilities of the carrier aircraft, allowing for rapid deployment and launch to perform reconnaissance and strike missions. This eliminates the need for an additional vertical launch mechanism, overcoming the drawbacks of redundant and cumbersome power systems in traditional vertical takeoff and landing aircraft. Furthermore, the carrier aircraft carries a first warhead, while the UAV carries a second warhead, providing multi-target strike capability. The composite layout allows the UAV to engage different targets after separation, working in conjunction with the carrier aircraft. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the structure of a UAV composite carrier vertical takeoff and landing loitering munition provided in an embodiment of the present invention;

[0020] Figure 2 This is a schematic diagram of the internal structure of the carrier provided in an embodiment of the present invention;

[0021] Figure 3 This is a schematic diagram of the internal structure of the main canard provided in an embodiment of the present invention;

[0022] Figure 4 A schematic diagram of the internal structure of the main wing provided in an embodiment of the present invention;

[0023] Figure 5 This is a schematic diagram of the internal structure of the separation mechanism provided in an embodiment of the present invention;

[0024] Figure 6 A schematic diagram showing the arrangement of the UAV provided in an embodiment of the present invention;

[0025] Figure 7 This is a schematic diagram of the internal structure of a drone provided in an embodiment of the present invention;

[0026] Figure 8 This is a flight diagram of a UAV-based composite vertical takeoff and landing loitering munition provided in an embodiment of the present invention.

[0027] In the diagram: 1-Carrier aircraft; 11-First warhead; 12-Fuselage; 13-Canard assembly; 131-Main canard; 132-Elevator; 133-Second servo; 134-Second control stick; 135-Second control angle connector; 14-Wing assembly; 141-Main wing; 142-Aileron; 143-First servo; 144-First control stick; 145-First control angle connector; 15-Electro-optical pod; 16-First flight control system; 17-First power supply unit; 18-Power assembly; 181-Power motor; 182-Propeller; 2-Support mechanism; 21-Hydraulic pod 22-Separation mechanism; 221-Locking component; 222-Separation drive component; 223-Separation ring groove; 3-UAV; 31-Second warhead; 32-Casing; 33-Upper rotor; 34-Lower rotor; 35-Rotation drive assembly; 351-Rotor motor; 36-Rotation pitch control assembly; 361-Upper swashplate; 362-Lower swashplate; 363-Swashplate servo; 364-Lower rotor torque converter; 365-Upper lever; 366-Lower lever; 367-Upper rotor torque converter; 37-Navigation component; 38-Second flight control; 39-Second power supply component. Detailed Implementation

[0028] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] The purpose of this invention is to provide a UAV-based composite vertical takeoff and landing loitering munition to solve the problems existing in the prior art, expand the strike range and multi-target strike capability of the loitering munition, and improve takeoff conditions and cruise capability.

[0030] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0031] Example 1

[0032] This embodiment provides a UAV-based composite vertical takeoff and landing loitering munition. Please refer to [link to previous document]. Figures 1-8 The system includes a carrier aircraft 1 and at least one unmanned aerial vehicle (UAV) 3. The carrier aircraft 1 is used to carry a first warhead 11 and is provided with a support mechanism 2, which can support the carrier aircraft 1 on a fixed surface when it takes off vertically. The UAV 3 is detachably connected to the carrier aircraft 1 and is used to carry a second warhead 31. The UAV 3 can provide thrust when the carrier aircraft 1 takes off vertically and during attitude control. The UAV 3 can detach from the carrier aircraft 1 to strike a target.

[0033] By using a carrier aircraft 1 carrying a drone 3 in a composite configuration, with a support mechanism 2 on the carrier aircraft 1 supporting it on the ground, the loitering munition can be vertically positioned for takeoff. The drone 3 enhances the vertical takeoff and cruise capabilities of the carrier aircraft 1, enabling it to be quickly deployed and launched to perform reconnaissance and strike missions without the need for an additional vertical launch mechanism, thus overcoming the drawbacks of redundant and cumbersome power systems in traditional vertical takeoff and landing aircraft. Furthermore, the carrier aircraft 1 carries a first warhead 11, and the drone 3 carries a second warhead 31, providing multi-target strike capability. The composite configuration allows the drone 3 to engage different targets together with the carrier aircraft 1 after separation.

[0034] In the optional solutions of this embodiment, a more preferred option is described in the following description: Figure 1 The support mechanism 2 includes multiple pods 21 circumferentially distributed at the tail of the carrier aircraft 1. Each pod 21 is parallel to the axis of the carrier aircraft 1, and the outer wall of the pod 21 is streamlined. Multiple drones 3 are configured, and each pod 21 can be detachably installed with a drone 3. The pod 21 can be supported on a fixed surface when the carrier aircraft 1 takes off vertically.

[0035] Multiple pods 21 are circumferentially arranged at the tail of the carrier aircraft 1, which facilitates the UAV 3 to be boosted at the tail of the carrier aircraft 1, thereby improving the overall stability and maneuverability of the loitering munition. In addition, the way the UAV 3 is set in the pods 21 makes it easy to load the UAV 3. The streamlined design of the pods 21 reduces flight drag. Specifically, the front opening of the pods 21 facilitates the installation of the UAV 3, the middle section can be set as a cylindrical section, and the tail end can be set as a conical section. The tail end of the pods 21 extends beyond the carrier aircraft 1 to provide support when placed vertically.

[0036] In the optional solutions of this embodiment, a more preferred option is described in the following description: Figure 5 Each pod 21 is equipped with a separation mechanism 22, which is connected to both the pod 21 and the drone 3. The separation mechanism 22 can limit or release the drone 3 within the pod 21.

[0037] The separation mechanism 22 is designed to limit the UAV 3 as needed during takeoff and cruise phases, or to release the limit when the UAV 3 needs to detach.

[0038] In the optional solutions of this embodiment, a more preferred option is described in the following description: Figure 5 The separation mechanism 22 includes a locking member 221 and a separation drive member 222. The separation drive member 222 is disposed on the pod 21 and connected to the locking member 221. The separation drive member 222 can drive the locking member 221 to connect the pod 21 and the drone 3 inside the pod 21 to limit the drone 3 within the pod 21. The separation drive member 222 can also drive the locking member 221 to disconnect the pod 21 and the drone 3 within the pod 21 to release the drone 3 from the limit within the pod 21.

[0039] The separation mechanism 22 is located inside the wingtip of the main wing 141 and connected to the pod 21. The locking component 221 is a locking half-ring, and the separation drive component 222 is a separation servo connected to one end of the locking half-ring, which can drive the locking half-ring to rotate. Correspondingly, the pod 21 and the shell of the UAV 3 are provided with separation ring grooves 222. When the UAV 3 is assembled in the pod 21, the openings of the separation ring grooves 222 on the shells of the pod 21 and the UAV 3 can be opposite each other. The separation servo can drive the locking half-ring to rotate and extend into the separation ring grooves 222 of the pod 21 and the UAV 3 to connect and limit the connection between the pod 21 and the UAV 3. When it is necessary to release the limit, the separation servo can drive the locking half-ring to rotate in the opposite direction and disengage from the separation ring grooves 222. The number of separation mechanisms 22 can be set to two, which can act synchronously to improve stability.

[0040] In the optional embodiments of this example, more preferably, the carrier aircraft 1 is configured as a fixed-wing carrier aircraft, including a fuselage 12, a canard assembly 13, a wing assembly 14, and a power assembly 18; the first warhead 11 is disposed inside the fuselage 12; the canard assembly 13 is disposed on the front side of the fuselage 12; the wing assembly 14 is disposed on the rear side of the fuselage 12, and the support mechanism 2 is disposed on the wing assembly 14; the power assembly 18 is disposed at the rear end of the fuselage 12 and is used to provide flight power.

[0041] The canard assembly 13 and wing assembly 14 facilitate the adjustment of the fuselage 12's attitude, while the power assembly 18 provides the power required for flight; such as Figure 3 As shown, the fuselage 12 is a streamlined, slender rectangular box along the X-axis of the coordinate system of the carrier aircraft 1. It adopts a beam structure and is mainly composed of a bulkhead, stringers, and skin. The bulkhead and stringers form a frame, and the skin is set outside the frame to cover it to form the fuselage 14. Connecting lugs are provided on the fuselage 14 at the connection parts with the canard assembly 13 and the wing assembly 14 for connecting the canard assembly 13 and the wing assembly 14.

[0042] The power assembly 18 includes a motor 181 and a propeller 182. The motor 181 is an external rotor brushless DC motor, and the propeller 182 is a two-bladed propeller, which provides propulsion for the entire loitering munition. The motor 181 is mounted on the motor mounting plate at the tail end of the fuselage 23 by screws, and the propeller 182 is mounted on the motor 181 by nuts and rotates together with the external rotor of the motor 181 to provide propulsion for the loitering munition. Alternatively, the power assembly 18 can also use other conventional UAV drive mechanisms that can provide propulsion.

[0043] In the optional solutions of this embodiment, a more preferred option is described in the following description: Figure 4 and Figure 6The wing assembly 14 includes four main wings 141, which are symmetrically arranged about the central section of the fuselage 12. The dihedral angle of the main wings 141 on the upper side of the fuselage 12 is the same as that of the main wings 141 on the lower side of the fuselage 12. Each main wing 141 is provided with a pod 21 at its wingtip. Each main wing 141 is provided with a rotatable aileron 142 at its trailing edge.

[0044] The four main wings 141 are symmetrical about the XOZ plane of the carrier aircraft 1 coordinate system. Their projection in the ZOY plane of the carrier aircraft 1 coordinate system is X-shaped. The upper main wing 141 adopts a 25° dihedral angle, and the lower main wing 141 adopts a 25° dihedral angle. The X-wing layout can provide higher lift under limited wingspan conditions and has a stronger payload transport capacity. The UAV 3 is placed at the wingtip of the X-wing, which allows it to take off vertically like a quadcopter, simplifying vertical takeoff control and improving the poor control effect of the control surfaces at low speeds during vertical takeoff of traditional tail-seat aircraft. By setting up rotatable ailerons 142, it is easy to drive the ailerons 142 to produce different deflection patterns, which can achieve different control effects.

[0045] Please see below. Figure 4 Each main wing 141 adopts a beam-type wing surface structure, mainly including beams, ribs and skin. The aileron 142 is driven by a first servo 143 installed in the middle of the main wing 141 near the aileron 142. The first servo 143 is connected to the aileron 142 through a first pull rod 144 and a first rudder angle connector 145. The first servo 143 is communicatively connected to the first flight controller 16. By controlling the first servo 143 to drive the first pull rod 144 to reciprocate, the aileron 142 is deflected through the first rudder angle connector 145.

[0046] In the optional embodiments of this example, more preferably, the canard assembly 13 includes two main canards 131, which are symmetrically arranged about the central section of the fuselage 12; and each of the main canards 131 has a rotating elevator 132 at its trailing edge.

[0047] Among them, the two main canards 131 are symmetrical about the XOZ plane of the carrier aircraft 1 coordinate system and are divided into left and right parts. Their projection in the XOY plane of the carrier aircraft 1 coordinate system is trapezoidal. An elevator 132 is arranged on the trailing edge of the main canards 131. By deflecting it toward the OZ axis of the carrier aircraft 1 coordinate system, a pitching moment about the OZ axis can be obtained, thereby achieving attitude control of the carrier aircraft 1 in the pitch direction.

[0048] Please see below. Figure 3The main canard 131 is a beam-type wing structure with ribs, beams and skin structure. The elevator 132 is driven by a second servo 133 installed in the middle of the main canard 131. The second servo 133 is connected to the elevator 132 through a second rod 134 and a second rudder angle connector 135. The second servo 133 is communicatively connected to the first flight controller 16. By controlling the second servo 133 to drive the second rod 134 to reciprocate, the elevator 132 is deflected through the second rudder angle connector 135.

[0049] In a preferred embodiment, the fuselage 12 is equipped with an electro-optical pod 15, a first flight controller 16, and a first power supply unit 17. The first flight controller 16 is communicatively connected to the power assembly 18, ailerons 142, elevator 132, electro-optical pod 15, separation mechanism 22, and first warhead 11. The first flight controller 16 is used to communicate with the ground station and receive command information. It can also receive detection information from the electro-optical pod 15 and control the separation drive 22 of the power assembly 18, ailerons 142, elevator 132, separation mechanism 22, and the first warhead 11. The first power supply unit 17 is electrically connected to the electro-optical pod 15, the first flight controller 16, the power assembly 18, ailerons 142, elevator 132, and separation mechanism 22, and provides the required electrical energy.

[0050] The power motor 181 of the power assembly 18 is communicatively connected to an electronic speed controller. The signal lines of the electronic speed controller, the optoelectronic pod 21, and all the servo motors on the carrier aircraft 1 are connected to the first flight controller 16 through a data link communication system. Both the electronic speed controller and the data link communication system are located inside the fuselage 12. The first power supply component 17 is a polymer lithium-ion battery, and all electrical components inside the carrier aircraft 1 are powered by the first power supply component 17. The components inside the fuselage 12 can be arranged along the length of the fuselage 12 according to requirements such as weight distribution.

[0051] In the optional embodiments of this example, more preferably, the UAV 3 is configured as a coaxial UAV, including a housing 32, an upper rotor 33, a lower rotor 34, a rotation drive assembly 35, and a rotor torque converter assembly 36; a second warhead 31 is disposed inside the housing 32; the upper rotor 33, the lower rotor 34, the rotation drive assembly 35, and the rotor torque converter assembly 36 are all disposed on the housing 32; the rotation drive assembly 35 is connected to the upper rotor 33 and the lower rotor 34, and drives the upper rotor 33 and the lower rotor 34 to rotate coaxially in reverse; the rotor torque converter assembly 36 is connected to the upper rotor 33 and the lower rotor 34, and can adjust the collective pitch and periodic torque of the upper rotor 33 and the lower rotor 34.

[0052] The fuselage 32 is a beam structure, including a frame, beams, and an outer shell. The frame and beams form a framework, and the outer shell is placed outside the framework for covering. The upper rotor 33 and the lower rotor 34 are coaxially reversed to form a coaxial dual-rotor system. The rotation drive assembly 35 includes two rotor motors 351 with different driving directions. The upper rotor 33 and the lower rotor 34 are connected to the two rotor motors 351 through different rotor main shafts to achieve coaxial reversal of the upper rotor 33 and the lower rotor 34. The yaw control of the coaxial UAV can be achieved by adjusting the speed of the rotor motors 351 through the second flight controller 38. The rotor main shafts adopt a conventional hollow shaft nesting structure.

[0053] The rotor torque converter assembly 36 can adopt a conventional coaxial helicopter torque control mechanism, including an upper swashplate 361, a lower swashplate 362, and a swashplate servo 363. The blades of the upper rotor 33 and the lower rotor 34 are connected to the upper swashplate 361 and the lower swashplate 362 respectively via rotor pitch control rods. The upper swashplate 361 and the lower swashplate 362 are connected by an upper control rod 365. The lower swashplate 362 is connected to the swashplate servo 363 via a lower swashplate control rod 366. When the swashplate servo 363 is activated, it controls the up-down and tilting motion of the lower swashplate 362 via the lower control rod 366. The lower swashplate 362 drives the blades of the lower rotor 34 to produce periodic pitch and collective pitch changes via the lower rotor pitch control rod 364. Meanwhile, the lower swashplate 362 transmits motion to the upper swashplate 361 via the upper lever 365. The upper swashplate 361 then uses the upper rotor pitch control lever 367 to achieve collective pitch and periodic pitch control of the upper rotor 33. In this way, the rotor pitch control system of the swashplate servo 363 can control the collective pitch and periodic pitch of the upper and lower rotors, thereby achieving longitudinal and lateral motion control of the coaxial UAV.

[0054] In a preferred embodiment, the housing 32 further includes a navigation component 37, a second flight controller 38, and a second power supply component 39. The second flight controller 38 is communicatively connected to the rotary drive assembly 35, the rotor torque converter assembly 36, the navigation component 37, and the first flight controller 16. The second flight controller 38 can receive command information from the first flight controller 16 and navigation information from the navigation component 37, and can control the operation of the rotary drive assembly 35 and the rotor torque converter assembly 36. The second power supply component 39 is electrically connected to the rotary drive assembly 35, the rotor torque converter assembly 36, the navigation component 37, and the second flight controller 38, and provides the required electrical energy.

[0055] The rotor motor 351 of the UAV 3 is communicatively connected to an electronic speed controller. The signal lines of the electronic speed controller, the navigation component 37, and all the servo motors on the UAV 3 are connected to the second flight controller 38 via a data link communication system. Both the electronic speed controller and the data link communication system are located inside the housing 32. The second power supply component 39 is a polymer lithium-ion battery, and the navigation component 37 is a strapdown inertial navigation system. All electrical components inside the UAV 3 are powered by the second power supply component 39. The components inside the housing 32 can be arranged along the length of the housing 32 according to requirements such as weight distribution. The data link communication system of the carrier aircraft 1 and the data link communication system of the UAV 3 transmit data wirelessly to achieve communication connection between the first flight controller 16 and the second flight controller 38. During the strike phase, the UAV 3 starts up and separates from the carrier aircraft 1. The carrier aircraft 1 provides guidance commands, which may include the target's position information and target type, etc., and in conjunction with the UAV 3's own inertial navigation system, can guide the UAV 3 to complete the strike on stationary and low-speed moving targets.

[0056] The loitering munition provided in this embodiment has the following navigation mission: Figure 8 As shown: During the vertical takeoff phase, the rotor of UAV 3 and the power unit 18 of carrier aircraft 1 jointly provide lift and control force, and the thrust difference of UAV 3 is used to control attitude; during the vertical-to-horizontal transition phase, the thrust difference of UAV 3 is used to achieve attitude control and gradually transition to the horizontal flight phase; during the horizontal flight phase, i.e., horizontal cruise, the power unit 18 of carrier aircraft 1 provides propulsion for efficient cruise, and carrier aircraft 1 is used for maneuvering and control; during the hovering reconnaissance phase, the electro-optical pod 15 of carrier aircraft 1 detects and identifies targets, and the ground station operator issues the target attack command; during the UAV attack phase, UAV 3 starts up and separates from carrier aircraft 1, i.e., coaxial separation. After separation, carrier aircraft 1 provides guidance commands (such as providing target position information and target type, etc.). In the initial guidance phase, UAV 3 plans its path according to its own navigation control system and the received guidance commands. After reaching the vicinity of the target, the UAV's own navigation control system starts to work, and it guides itself to attack the target; finally, carrier aircraft 1 carries a large first warhead 11 to achieve destructive strike against fast-moving armored targets, i.e., fixed-wing guidance.

[0057] Specifically, during vertical takeoff, the thrust difference of UAV 3 controls the attitude of the loitering munition during takeoff. Increasing the thrust of the two coaxial UAVs in the positive Z direction of the XOY plane of the carrier aircraft 1, or decreasing the thrust of the two coaxial UAVs in the opposite Z direction, allows for pitching control of the entire loitering munition; conversely, pitching control is achieved by decreasing the thrust of the two coaxial UAVs in the positive Y direction of the XOY plane of the carrier aircraft 1, or increasing the thrust of the two coaxial UAVs in the positive Y direction, allows for Z-axis attitude control of the loitering munition; conversely, reverse control is achieved by increasing or decreasing the thrust of the diagonally opposite coaxial UAVs. By controlling the simultaneous increase or decrease of the thrust of the diagonally opposite coaxial UAVs, the X-axis attitude of the loitering munition during vertical takeoff can be controlled. After vertical takeoff, increasing the thrust of the two coaxial UAVs in the opposite Z direction of the XOY plane of the carrier aircraft 1, or decreasing the thrust of the two coaxial UAVs in the positive Z direction, causes the loitering munition to gradually pitch down, transitioning to the horizontal cruise flight phase.

[0058] During the horizontal cruise phase, the coaxial UAV rotor stops rotating, and the carrier aircraft 1 continues to provide propulsion. The elevator 132 of the carrier aircraft 1 controls the pitch axis attitude of the loitering munition. When the elevator 132 deflects downward, it generates a pitching moment, causing the loitering munition to pitch up; conversely, it controls the loitering munition to pitch down. The ailerons 142 of the carrier aircraft 1 control the roll axis attitude of the loitering munition. When the two ailerons 142 in the Y direction of the XOZ plane deflect upward simultaneously, and the two ailerons 142 in the opposite Y direction deflect downward simultaneously, the loitering munition can be rolled around the positive X-axis. Conversely, manipulating them can control the loitering munition to roll in the opposite direction. The ailerons 142 of the carrier aircraft 1 can also control the yaw motion of the loitering munition. When the two ailerons 142 in the positive Y direction of the XOZ plane deflect upward and downward respectively, the loitering munition can be yawed to the right. Conversely, manipulating the aileron 142 in the opposite Y direction can control the loitering munition to yaw to the left.

[0059] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A UAV-based composite vertical takeoff and landing loitering munition, characterized in that: include: The carrier aircraft (1) is used to carry a first warhead (11), and the carrier aircraft (1) is provided with a support mechanism (2). The support mechanism (2) includes a plurality of pods (21) circumferentially distributed at the tail of the carrier aircraft (1). The pods (21) are able to be supported on a fixed surface when the carrier aircraft (1) takes off vertically. and Multiple unmanned aerial vehicles (UAVs) (3) are detachably connected to the carrier aircraft (1). Each UAV (3) carries a second warhead (31). Each of the pods (21) contains one UAV (3). The UAV (3) can provide thrust during vertical takeoff and attitude control of the carrier aircraft (1). The UAV (3) can detach from the carrier aircraft (1) to strike targets. During the vertical takeoff phase, the rotor of the UAV (3) and the power assembly (18) of the carrier aircraft (1) jointly provide lift and control force, and the attitude is controlled by utilizing the thrust difference between multiple UAVs (3); during the vertical-to-horizontal transition phase, the attitude is controlled by utilizing the thrust difference between multiple UAVs (3) and gradually transitions to the horizontal flight phase; during the horizontal flight phase, the power assembly (18) of the carrier aircraft (1) provides propulsion for cruising, and the carrier aircraft (1) is used for maneuvering control; During the reconnaissance phase, the electro-optical pod (15) of the carrier aircraft (1) detects and identifies the target, and the ground station operator issues a strike command; during the strike phase, the UAV (3) starts up and separates from the carrier aircraft (1), the carrier aircraft (1) provides guidance commands, and guides the attack target in conjunction with its own navigation components (37); finally, the carrier aircraft (1) carries the first warhead (11) to carry out a fixed-wing guided strike.

2. The UAV composite carrier vertical takeoff and landing loitering munition according to claim 1, characterized in that: Each of the aforementioned pods (21) is axially parallel to the carrier aircraft (1), and the outer wall of the pod (21) is configured to be streamlined.

3. The UAV composite carrier vertical takeoff and landing loitering munition according to claim 2, characterized in that: Each of the aforementioned pods (21) is provided with a separation mechanism (22), which is connected to both the pod (21) and the drone (3). The separation mechanism (22) can limit or release the drone (3) within the pod (21).

4. The UAV composite carrier vertical takeoff and landing loitering munition according to claim 3, characterized in that: The separation mechanism (22) includes a locking member (221) and a separation drive member (222); the separation drive member (222) is disposed on the pod (21) and connected to the locking member (221); the separation drive member (222) can drive the locking member (221) to connect the pod (21) and the drone (3) inside the pod (21) to limit the drone (3) inside the pod (21), and the separation drive member (222) can also drive the locking member (221) to disconnect the pod (21) and the drone (3) inside the pod (21) to release the drone (3) from the limit inside the pod (21).

5. The UAV composite carrier vertical takeoff and landing loitering munition according to claim 3, characterized in that: The carrier aircraft (1) is configured as a fixed-wing carrier aircraft, including a fuselage (12), a canard assembly (13), a wing assembly (14), and the power assembly (18); the first warhead (11) is disposed inside the fuselage (12); the canard assembly (13) is disposed on the front side of the fuselage (12); the wing assembly (14) is disposed on the rear side of the fuselage (12), and the support mechanism (2) is disposed on the wing assembly (14); the power assembly (18) is disposed at the rear end of the fuselage (12) and is used to provide flight power.

6. The UAV composite carrier vertical takeoff and landing loitering munition according to claim 5, characterized in that: The wing assembly (14) includes four main wings (141), which are symmetrically arranged about the central section of the fuselage (12). The dihedral angle of the main wings (141) on the upper side of the fuselage (12) is the same as that of the main wings (141) on the lower side of the fuselage (12). Each main wing (141) is provided with a pod (21) at its wingtip. Each main wing (141) is provided with a rotatable aileron (142) at its trailing edge.

7. The UAV composite carrier vertical takeoff and landing loitering munition according to claim 6, characterized in that: The canard assembly (13) includes two main canards (131), which are symmetrically arranged about the central section of the fuselage (12); and each of the main canards (131) is provided with a rotating elevator (132) at its trailing edge.

8. The UAV composite carrier vertical takeoff and landing loitering munition according to claim 7, characterized in that: The fuselage (12) is equipped with the electro-optical pod (15), the first flight controller (16), and the first power supply unit (17). The first flight controller (16) is communicatively connected to the power unit (18), the aileron (142), the elevator (132), the electro-optical pod (15), the separation mechanism (22), and the first warhead (11). The first flight controller (16) is used to communicate with the ground station and can receive command information. The first flight controller (16) can also receive the detection information of the electro-optical pod (15) and can control the operation of the power unit (18), the aileron (142), the elevator (132), the separation mechanism (22), and the first warhead (11). The first power supply unit (17) is electrically connected to the electro-optical pod (15), the first flight controller (16), the power unit (18), the aileron (142), the elevator (132), and the separation mechanism (22) and provides the required electrical energy.

9. The UAV composite carrier vertical takeoff and landing loitering munition according to claim 8, characterized in that: The UAV (3) is configured as a coaxial UAV, including a housing (32), an upper rotor (33), a lower rotor (34), a rotation drive assembly (35), and a rotor torque converter assembly (36); a second warhead (31) is provided inside the housing (32); the upper rotor (33), the lower rotor (34), the rotation drive assembly (35), and the rotor torque converter assembly (36) are all disposed on the housing (32); the rotation drive assembly (35) is connected to the upper rotor (33) and the lower rotor (34), and drives the upper rotor (33) and the lower rotor (34) to rotate coaxially; the rotor torque converter assembly (36) is connected to the upper rotor (33) and the lower rotor (34), and can adjust the collective pitch and periodic torque of the upper rotor (33) and the lower rotor (34).

10. The UAV composite carrier vertical takeoff and landing loitering munition according to claim 9, characterized in that: The housing (32) also houses the navigation component (37), the second flight controller (38), and the second power supply component (39). The second flight controller (38) is communicatively connected to the rotary drive assembly (35), the rotor torque converter assembly (36), the navigation component (37), and the first flight controller (16). The second flight controller (38) can receive command information from the first flight controller (16) and navigation information from the navigation component (37), and can control the actions of the rotary drive assembly (35) and the rotor torque converter assembly (36). The second power supply component (39) is electrically connected to the rotary drive assembly (35), the rotor torque converter assembly (36), the navigation component (37), and the second flight controller (38), and provides the required electrical energy.

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