A drop-type early warning drone

Abstract

The present invention provides a delivery-type early warning UAV, which is installed at the wing tip position of the wings on both sides of the mother aircraft through a centrifugal force locking device; the delivery-type early warning UAV includes a core component, a flight control computer, a fuselage and a control rudder; the fuselage is a triangular wing-body fusion body layout, and its tail is a dovetail structure; the control rudder is respectively arranged on the dovetails on both sides of the rear of the fuselage; the flight control computer is arranged at the head of the fuselage and embedded in the fuselage; the core component includes a detection radar and a turbojet engine, and a fuel tank for providing fuel for the turbojet engine is also arranged inside the fuselage; the centrifugal force locking device is arranged in the core component. The present invention has a novel structure and a reasonable design. Before performing a dangerous task, it is separated from the mother aircraft to first detect and judge the danger level, which can effectively improve the battlefield survivability and help to better complete the flight mission.

Description

Technical Field

[0001] The present invention relates to the technical field related to unmanned aerial vehicles (UAVs), and in particular to a delivery-type early warning UAV. Background Art

[0002] Unmanned early warning aircraft usually undertake multiple tasks during the mission, such as reconnaissance, communication, evaluation, etc., and in order to improve its long endurance, the unmanned early warning aircraft usually flies at a slow speed and is easily attacked by the enemy. Therefore, in some dangerous battlefield environments, it is necessary to improve the survivability of unmanned early warning aircraft and reduce the number of times it performs dangerous tasks. At this time, there is an urgent need for a flexible and consumable early warning detection method to replace the early warning drone to go out of the dangerous area for reconnaissance. If there is a drop-type early warning drone that can be carried on the unmanned early warning aircraft mother aircraft, before performing dangerous tasks, it can be separated from the mother aircraft to first investigate and judge the danger level, then it can effectively improve the survivability of the unmanned early warning aircraft mother aircraft in the battlefield, which will help to better complete the flight mission. Summary of the invention

[0003] The purpose of the present invention is to solve the shortcomings of the prior art and to propose a delivery-type early warning drone.

[0004] To achieve the above-mentioned purpose, the present invention provides a delivery-type early warning UAV, which is installed at the wingtips of the wings on both sides of a mother aircraft through a centrifugal force locking device; the delivery-type early warning UAV includes a core component, a flight control computer, a fuselage and control rudders; the fuselage is a triangular wing-body fusion layout, and its tail is a dovetail structure; the control rudders are respectively arranged on the dovetails on both sides of the rear part of the fuselage; the flight control computer is arranged at the head of the fuselage and buried inside the fuselage; the core component includes a detection radar and a turbojet engine, and a fuel tank for providing fuel for the turbojet engine is also arranged inside the fuselage; the centrifugal force locking device is arranged in the core component.

[0005] As a preferred configuration of the present invention, the core component also includes an outer shell, wherein the detection radar is arranged at the upper part of the outer shell of the core component, the turbojet engine is arranged at the lower part of the outer shell of the core component, and the centrifugal force locking device is arranged in the outer shell.

[0006] As a preferred setting of the present invention, the centrifugal force locking device includes a centrifugal spring and a centrifugal pressure tongue arranged at the top of the outer shell, and an insertion groove corresponding to the centrifugal pressure tongue is opened in the outer shell; lateral compression springs and lateral compression plates respectively connected to the two lateral compression springs are respectively arranged on both sides of the outer shell; grooves are arranged at the wing tip positions on both sides of the mother aircraft for accommodating the core assembly, and grooves corresponding to the two lateral compression plates are arranged on both sides of the groove; when the centrifugal pressure tongue is in the inserted state, the lateral compression plates are respectively inserted into the corresponding grooves.

[0007] As a preferred configuration of the present invention, the two lateral compression plates are provided with corresponding inclined surfaces at one end close to the centrifugal pressing tongue. After the centrifugal pressing tongue is separated from the insertion groove, the two lateral compression plates move toward each other under the action of the lateral compression spring until the two corresponding inclined surfaces are completely fitted.

[0008] As a preferred configuration of the present invention, when the centrifugal tongue is in an inserted state, the centrifugal spring is in an initial state, and the two lateral compression springs are in a compressed state.

[0009] As a preferred configuration of the present invention, an electromagnet is embedded in the groove, and the lateral compression plate is adsorbed by the electromagnet when inserted into the groove; the electromagnet is powered by a power supply in the mother machine, and the power switch is provided in the cockpit of the mother machine.

[0010] As a preferred configuration of the present invention, the detection radar is a rectangular structure, and radar array surfaces are respectively arranged on the left and right sides.

[0011] The beneficial effects of the present invention are:

[0012] The present invention provides a drop-type early warning UAV. When it is not separated from the mother aircraft, the electromagnet in the slot firmly sucks the two side compression plates, and the mother-child aircraft is in a locked state. It can be used as the wingtip winglets on both sides of the wings of the mother aircraft to improve the aerodynamic performance of the aircraft wings. When entering a dangerous area and needing to conduct reconnaissance, the electromagnet is powered off, the mother aircraft performs a rolling maneuver, the centrifugal spring is compressed by centrifugal force, the centrifugal tongue is separated from the insertion slot under the action of the centrifugal spring and the centrifugal force, the lateral compression plate is retracted under the action of the lateral compression spring, the mother-child aircraft is disconnected, separated from the mother aircraft, and performs the reconnaissance mission by itself. The present invention has a novel structure and a reasonable design. In an emergency, it can be separated from the mother aircraft and perform the reconnaissance mission by itself, which can effectively improve the efficiency of the action and help to better complete the flight mission. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of the structure of the present invention when it is not separated from the mother machine.

[0014] Figure 2 It is a structural schematic diagram of the present invention.

[0015] Figure 3 It is a structural schematic diagram of the core components of the present invention;

[0016] Figure 4 It is a schematic structural diagram of the centrifugal force locking device of the present invention. DETAILED DESCRIPTION

[0017] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0018] It should be noted that when a component is referred to as being "fixed to" another component, it may be directly on the other component or there may also be a component centered. When a component is considered to be "connected to" another component, it may be directly connected to the other component or there may also be a component centered. When a component is considered to be "set on" another component, it may be directly set on the other component or there may also be a component centered. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only.

[0019] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art of the present invention. The terms used herein in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more related listed items.

[0020] Reference Figures 1 to 3 The present invention provides a delivery-type early warning UAV, wherein the delivery-type early warning UAV 1 is installed at the wing tips 3 of the wings on both sides of a mother aircraft 2 through a centrifugal force locking device; the delivery-type early warning UAV 1 comprises a core component 7, a flight control computer 5, a fuselage 4 and a control rudder 6; the fuselage 4 is a triangular wing-body fusion layout, and its tail is a dovetail structure; the control rudder 6 is respectively arranged on the dovetails on both sides of the rear part of the fuselage 4; the flight control computer 5 is arranged at the head of the fuselage 4 and embedded in the fuselage 4; the core component 7 comprises a detection radar 8 and a turbojet engine 9, and a fuel tank for providing fuel for the turbojet engine 9 is also arranged inside the fuselage 4; the centrifugal force locking device is arranged in the core component 7.

[0021] As a preferred setting of an embodiment of the present invention, further, the core component 7 also includes an outer shell 10, wherein the detection radar 8 is arranged at the upper part of the outer shell 10 of the core component 7, the turbojet engine 9 is arranged at the lower part of the outer shell 10 of the core component 7, and the centrifugal force locking device is arranged in the outer shell 10.

[0022] As a preferred setting of an embodiment of the present invention, further, the centrifugal force locking device includes a centrifugal spring 11 and a centrifugal pressure tongue 12 arranged at the top of the outer shell 10, and an insertion groove corresponding to the centrifugal pressure tongue 12 is opened in the outer shell 10; lateral compression springs 13 and lateral compression plates 14 respectively connected to the two lateral compression springs 13 are respectively arranged on both sides of the outer shell 10; grooves are arranged at the wing tip positions on both sides of the mother machine 2 for accommodating the core assembly 7, and grooves corresponding to the two lateral compression plates 14 are arranged on both sides of the groove; when the centrifugal pressure tongue 12 is in the inserted state, the lateral compression plates 14 are respectively inserted into the corresponding grooves.

[0023] As a preferred setting of an embodiment of the present invention, further, the two lateral compression plates 14 are provided with corresponding inclined surfaces 15 at one end close to the centrifugal pressing tongue 12. After the centrifugal pressing tongue 12 is separated from the insertion groove, the two lateral compression plates 14 move toward each other under the action of the lateral compression spring 13 until the two corresponding inclined surfaces 15 are completely fitted together.

[0024] As a preferred configuration of the embodiment of the present invention, further, when the centrifugal tongue 12 is in the inserted state, the centrifugal spring 11 is in the initial state, and the two lateral compression springs 13 are in the compressed state.

[0025] As a preferred setting of an embodiment of the present invention, further, an electromagnet is embedded in the groove, and the lateral compression plate 14 is adsorbed by the electromagnet when inserted into the groove; the electromagnet is powered by a power supply in the mother machine 2, and the power switch is provided in the cockpit of the mother machine 2.

[0026] As a preferred configuration of the embodiment of the present invention, further, the detection radar 8 is a rectangular structure, and radar array surfaces are respectively arranged on the left and right sides.

[0027] Example 1

[0028] An embodiment of the present invention provides a delivery-type early warning UAV, wherein the delivery-type early warning UAV 1 is composed of a core component 7, a flight control computer 5, a fuselage 4, and a control rudder 6. The fuselage 4 is a triangular wing-body fusion layout, wherein its tail is a dovetail structure to prevent the engine gas from eroding the fuselage. The fuselage 4 has a wingspan of L2 and a height of H2, and serves as a winglet at the wingtip 3 of the mother aircraft 2 to improve the aerodynamic performance of the aircraft wing. The control rudder 6 is located on the dovetails on both sides of the rear part of the fuselage 4 of the delivery-type early warning UAV 1, and is composed of two parts. The flight control computer 5 is located at the head of the fuselage 4 and is embedded in the fuselage 4, with no protrusions in the structure. The fuel of the delivery-type early warning UAV 1 is stored inside the fuselage 4.

[0029] The core component 7 is composed of a detection radar 8 and a turbojet engine 9. The detection radar 8 is located at the upper part of the core component 7, and the turbojet engine 9 is located at the lower part of the core component 7. The power required for the detection radar 8, the flight control computer 5 and the control rudder 6 during operation is provided by the turbojet engine 9. The detection radar 8 is a rectangular structure, and the detection radar 8 is provided with two left and right radar arrays, and the number of turbojet engines is 1. After the drop-type early warning drone 1 is separated from the mother aircraft, its detection radar 8 immediately starts working and sends data to the mother aircraft in real time.

[0030] A centrifugal locking device is provided in the outer shell of the core component 7. The centrifugal locking device includes a centrifugal spring 11 and a centrifugal tongue 12 provided at the top of the outer shell 10, and an insertion groove corresponding to the centrifugal tongue 12 is provided in the outer shell 10; lateral compression springs 13 and lateral compression plates 14 respectively connected to the two lateral compression springs 13 are provided on both sides of the outer shell 10; grooves are provided at the wing tip positions on both sides of the mother machine 2 for accommodating the core component 7, and grooves corresponding to the two lateral compression plates 14 are provided on both sides of the groove; when the centrifugal tongue 12 is in the inserted state, the lateral compression plates 14 are respectively inserted into the corresponding grooves. The two lateral compression plates 14 are provided with corresponding inclined surfaces 15 at one end close to the centrifugal tongue 12. After the centrifugal tongue 12 is separated from the insertion groove, the two lateral compression plates 14 move toward each other under the action of the lateral compression springs 13 until the two corresponding inclined surfaces 15 are completely fitted. When the centrifugal tongue 12 is in the inserted state, the centrifugal spring 11 is in the initial state, and the two lateral compression springs 13 are in the compressed state. Furthermore, an electromagnet is embedded in the groove, and the lateral compression plate 14 is attracted by the electromagnet when inserted into the groove; the electromagnet is powered by the power supply in the mother machine 2, and the power switch is provided in the cockpit of the mother machine 2.

[0031] The wingspan L1 of the mother machine 2 is 34 meters. The height of the core component 7 is 0.4 meters. The wingspan L2 of the drop-type early warning drone 1 is 1.5 meters, and the length H2 is 2 meters.

[0032] When not separated from the mother aircraft, the electromagnet in the groove firmly sucks the two side compression plates 14, and the mother-child aircraft is in a locked state, which can be used as winglets on the wings on both sides of the mother aircraft 2 to improve the aerodynamic performance of the aircraft wings; when entering a dangerous area for reconnaissance, the electromagnet is powered off, the mother aircraft performs a rolling maneuver, and the centrifugal spring 11 is compressed by centrifugal force. The centrifugal pressure tongue 12 is separated from the insertion groove under the action of the centrifugal spring 11 and the centrifugal force, and the lateral compression plate 14 is retracted under the action of the lateral compression spring 13. The mother-child aircraft is disconnected, separated from the mother aircraft, and performs the reconnaissance task on its own.

[0033] Example 2

[0034] An embodiment of the present invention provides a delivery-type early warning UAV, wherein the delivery-type early warning UAV 1 is composed of a core component 7, a flight control computer 5, a fuselage 4, and a control rudder 6. The fuselage 4 is a triangular wing-body fusion layout, wherein its tail is a dovetail structure to prevent the engine gas from eroding the fuselage. The fuselage 4 has a wingspan of L2 and a height of H2, and serves as a winglet at the wingtip 3 of the mother aircraft 2 to improve the aerodynamic performance of the aircraft wing. The control rudder 6 is located on the dovetails on both sides of the rear part of the fuselage 4 of the delivery-type early warning UAV 1, and is composed of two parts. The flight control computer 5 is located at the head of the fuselage 4 and is embedded in the fuselage 4, with no protrusions in the structure. The fuel of the delivery-type early warning UAV 1 is stored inside the fuselage 4.

[0035] The core component 7 is composed of a detection radar 8 and a turbojet engine 9. The detection radar 8 is located at the upper part of the core component 7, and the turbojet engine 9 is located at the lower part of the core component 7. The power required for the detection radar 8, the flight control computer 5 and the control rudder 6 during operation is provided by the turbojet engine 9. The detection radar 8 is a rectangular structure, and the detection radar 8 is provided with two left and right radar arrays, and the number of turbojet engines is 1. After the drop-type early warning drone 1 is separated from the mother aircraft, its detection radar 8 immediately starts working and sends data to the mother aircraft in real time.

[0036] A centrifugal locking device is provided in the outer shell of the core component 7. The centrifugal locking device includes a centrifugal spring 11 and a centrifugal tongue 12 provided at the top of the outer shell 10, and an insertion groove corresponding to the centrifugal tongue 12 is provided in the outer shell 10; lateral compression springs 13 and lateral compression plates 14 respectively connected to the two lateral compression springs 13 are provided on both sides of the outer shell 10; grooves are provided at the wing tip positions on both sides of the mother machine 2 for accommodating the core component 7, and grooves corresponding to the two lateral compression plates 14 are provided on both sides of the groove; when the centrifugal tongue 12 is in the inserted state, the lateral compression plates 14 are respectively inserted into the corresponding grooves. The two lateral compression plates 14 are provided with corresponding inclined surfaces 15 at one end close to the centrifugal tongue 12. After the centrifugal tongue 12 is separated from the insertion groove, the two lateral compression plates 14 move toward each other under the action of the lateral compression springs 13 until the two corresponding inclined surfaces 15 are completely fitted. When the centrifugal tongue 12 is in the inserted state, the centrifugal spring 11 is in the initial state, and the two lateral compression springs 13 are in the compressed state. Furthermore, an electromagnet is embedded in the groove, and the lateral compression plate 14 is attracted by the electromagnet when inserted into the groove; the electromagnet is powered by the power supply in the mother machine 2, and the power switch is provided in the cockpit of the mother machine 2.

[0037] The wingspan L1 of the mother machine 2 is 10 meters. The height of the core component 7 is 0.2 meters. The wingspan L2 of the drop-type early warning drone 1 is 0.8 meters, and the length H2 is 1 meter.

[0038] When not separated from the mother aircraft, the electromagnet in the groove firmly sucks the two side compression plates 14, and the mother-child aircraft is in a locked state, which can be used as winglets on the wings on both sides of the mother aircraft 2 to improve the aerodynamic performance of the aircraft wings; when entering a dangerous area for reconnaissance, the electromagnet is powered off, the mother aircraft performs a rolling maneuver, and the centrifugal spring 11 is compressed by centrifugal force. The centrifugal pressure tongue 12 is separated from the insertion groove under the action of the centrifugal spring 11 and the centrifugal force, and the lateral compression plate 14 is retracted under the action of the lateral compression spring 13. The mother-child aircraft is disconnected, separated from the mother aircraft, and performs the reconnaissance task on its own.

[0039] To sum up, the present invention has a novel structure and a reasonable design. It can be carried on an unmanned early warning aircraft mother aircraft. Before performing a dangerous mission, it can be separated from the mother aircraft to conduct reconnaissance and assessment of the danger level. This can effectively improve the survivability of the unmanned early warning aircraft mother aircraft on the battlefield and help to better complete the flight mission.

[0040] In addition, those skilled in the art will appreciate that, although some embodiments described herein include certain features included in other embodiments but not other features, the combination of features of different embodiments is meant to be within the scope of the present invention and to form different embodiments. For example, in the above claims, any one of the claimed embodiments may be used in any combination. The information disclosed in this background technology section is intended only to deepen the understanding of the overall background technology of the present invention and should not be regarded as an admission or in any form of implication that the information constitutes prior art known to those skilled in the art.

Claims

1. A delivery-type early warning drone, characterized in that: The delivery-type early warning UAV is installed at the wingtips of the wings on both sides of the mother aircraft through a centrifugal locking device; the delivery-type early warning UAV includes a core component, a flight control computer, a fuselage, and a control rudder surface; the fuselage is a triangular wing-body fusion layout, and its tail is a dovetail structure; the control rudder surface is respectively arranged on the dovetails on both sides of the rear of the fuselage; the flight control computer is arranged at the head of the fuselage and embedded inside the fuselage; the core component includes a detection radar and a turbojet engine, and a fuel tank for providing fuel for the turbojet engine is also arranged inside the fuselage; the centrifugal locking device is arranged in the core component; The core component also includes an outer shell, wherein the detection radar is arranged at the upper part of the outer shell of the core component, the turbojet engine is arranged at the lower part of the outer shell of the core component, and the centrifugal force locking device is arranged in the outer shell; The centrifugal force locking device includes a centrifugal spring and a centrifugal pressure tongue arranged at the top of the outer shell, and an insertion groove corresponding to the centrifugal pressure tongue is opened in the outer shell; lateral compression springs and lateral compression plates respectively connected to the two lateral compression springs are respectively arranged on both sides of the outer shell; grooves are arranged at the wing tip positions on both sides of the mother machine for accommodating the core assembly, and grooves corresponding to the two lateral compression plates are arranged on both sides of the groove; when the centrifugal pressure tongue is in the inserted state, the lateral compression plates are respectively inserted into the corresponding grooves.

2. The delivery-type early warning UAV according to claim 1, characterized in that: The two lateral compression plates are provided with corresponding inclined surfaces at one end close to the centrifugal pressing tongue. After the centrifugal pressing tongue is separated from the insertion groove, the two lateral compression plates move toward each other under the action of the lateral compression spring until the two corresponding inclined surfaces are completely fitted.

3. The delivery-type early warning UAV according to claim 1, characterized in that: When the centrifugal tongue is in the inserted state, the centrifugal spring is in the initial state, and the two lateral compression springs are in the compressed state.

4. The delivery-type early warning UAV according to claim 1, characterized in that: An electromagnet is embedded in the groove, and the lateral compression plate is adsorbed by the electromagnet when inserted into the groove; the electromagnet is powered by a power supply in the mother machine, and a power switch is arranged in the cockpit of the mother machine.

5. The delivery-type early warning UAV according to claim 1, characterized in that: The detection radar is a rectangular structure, and radar array surfaces are respectively arranged on the left and right sides.

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