All-weather anti-collision type sentry aircraft

Abstract

The invention discloses an all-weather anti-collision sentry aircraft, which relates to the technical field of aircrafts, and comprises an aircraft and an energy information supply bin, the aircraft is connected with a plurality of side arms, the side arms are provided with rotors, the aircraft is connected with the energy information supply bin through a recovery rope, and a cable is arranged in the recovery rope. The energy information supply bin connected with the aircraft is arranged, so that the aircraft has physical constraint and attribution in the use process, and in practical application, for example, when patrol tasks are carried out on complex terrains such as mountainous areas, forests or urban high-rise standing areas, the aircraft is not prone to being lost due to signal interference, positioning errors and the like.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to an all-weather collision avoidance sentry aircraft. Background Technology

[0002] Sentinel aircraft are very important in the military. However, current sentinel aircraft suffer from problems such as getting lost and having short range. Therefore, it is necessary to design an aircraft structure with a longer range.

[0003] In the prior art, a multi-rotor aerial sentinel drone disclosed in patent publication number CN211001889U includes an aircraft and a connecting base. A support arm is fixed to the side of the aircraft, and a motor is provided at the end of the support arm away from the aircraft. A connecting frame is provided at the bottom of the aircraft, and a clamping plate is connected inside the connecting frame. A fixing plate is provided below the connecting frame. A rotating seat is provided at the edge of the bottom of the aircraft, and one end of a support frame is connected inside the rotating seat. Rollers are installed at both ends of the support frame away from the rotating seat. The connecting seat is respectively provided on the surface of the aircraft and the support frame near the rotating seat. This prior art patent cannot achieve the recovery of the drone, the drone is easy to get lost, and the power supply of the drone cannot be guaranteed. Summary of the Invention

[0004] The purpose of this invention is to solve the problem that existing sentry aircraft are prone to getting lost. This invention is equipped with an energy and information supply compartment, which is connected to the aircraft by a retrieval rope to prevent the aircraft from getting lost and can achieve anti-loss.

[0005] A further objective of this invention is to address the issue of limited endurance in existing aircraft structures. This invention incorporates a cable within the recovery rope to directly drive the entire Sentinel aircraft, thereby achieving a longer endurance.

[0006] To achieve the above objectives, the present invention provides the following technical solution: an all-weather collision avoidance sentry aircraft, comprising an aircraft and an energy and information supply compartment, the aircraft being connected to several side arms, the side arms being equipped with rotors, the aircraft being connected to the energy and information supply compartment by a recovery rope, and cables being arranged inside the recovery rope.

[0007] Preferably, a connector is installed on the top of the aircraft, and a U-shaped fixing plate is fixed below the connector. The U-shaped fixing plate has an inner groove, and a buckle is inserted into the inner groove. The buckle has an insertion port. One end of the recovery rope is connected to the insertion port, and the other end is connected to the energy information supply compartment.

[0008] Preferably, a cutting blade is coaxially mounted above the rotor, a hydrogen layer is provided on the outside of the recovery rope, and a reconnaissance camera and radar are installed below the aircraft.

[0009] Preferably, a connecting harness is provided on one side of the connector, which connects to the receiver to power the drive unit and the reconnaissance camera and radar located below. A connecting flange is provided below the drive unit, which drives the reconnaissance camera and radar below to rotate.

[0010] As a preferred option, the energy information supply compartment is equipped with a motor. One side of the motor is a partition, and the other side of the partition is connected to a shaft. A recovery rope is wound on the shaft, and a circular stop plate is also provided at one end of the shaft near the partition.

[0011] As a preferred option, an elongated chute is also provided on one side of the energy information supply compartment. The elongated chute contains a sliding plate, which is fixed to a U-shaped fixed plate by a connecting column. The U-shaped fixed plate is connected to a pulley, and an anti-winding plate is provided between the pulley and the column. The anti-winding plate separates the pulley from the column, and the recovery rope on the column passes through the pulley and extends out of the energy information supply compartment.

[0012] Preferably, the top of the energy information supply compartment is an upper plate, and a fastening seat is provided on one side of the upper plate. The fastening seat is equipped with a hair. Preferably, a sentry compartment is also provided on one side of the energy information supply compartment. A rope placement notch is provided at the connection between the sentry compartment and the energy information supply compartment. An elastic plate is provided inside the sentry compartment. The sentry compartment has a compartment cover. When the compartment cover is closed, the recovery rope passes through the rope placement notch.

[0013] Preferably, the aircraft has an arc-shaped edge, and the aircraft is also provided with legs on both sides. The legs are connected to ground contact rods, and the ground contact rods have curved sides.

[0014] Preferably, the side arm and the rotor are connected by a fixed base, a support ring is provided above the rotor, a crash plate is connected to one side of the support ring, and a protective net is provided on the support ring.

[0015] Compared with existing technologies, the beneficial effects of this invention are as follows: This invention establishes an energy information supply compartment connected to the aircraft, which provides the aircraft with physical constraints and ownership during use. In practical applications, such as patrol missions in complex terrains like mountains, forests, or urban areas with numerous high-rise buildings, the aircraft is less likely to be lost due to signal interference, positioning errors, or other reasons. This energy information supply compartment acts like a mobile "base," with the aircraft always maintaining a connection to it, greatly enhancing the control and management capabilities of the aircraft, effectively reducing the risk of loss, and improving the safety and reliability of the equipment. For situations where multiple sentry aircraft are operating simultaneously, the presence of the energy information supply compartment facilitates the differentiation and tracking of each aircraft. By setting up markers or positioning systems on the energy information supply compartment, the activity range and status of each aircraft can be monitored, further preventing confusion and loss between aircraft.

[0016] This invention directly powers the entire Sentinel aircraft by incorporating a cable within the retrieval rope, fundamentally altering the way aircraft are powered. Traditional aircraft typically rely on onboard batteries, which have limited capacity and thus short flight times.

[0017] This invention provides continuous power to the aircraft, enabling it to operate stably for extended periods during long-duration border patrols or continuous monitoring of large events without frequent battery replacements or recharging, significantly improving work efficiency. This cable-driven power system may offer higher energy transfer efficiency. Compared to batteries carried by the aircraft itself, cables can transfer electrical energy from ground power sources to the aircraft with minimal energy loss. This not only extends flight time but also reduces the weight burden caused by carrying numerous batteries, thereby improving flight performance such as speed and maneuverability. This makes the Sentinel aircraft more efficient and stable during missions. The invention also incorporates a receiver for microwave power supply. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the aircraft structure of the present invention.

[0019] Figure 2 This is a schematic diagram showing the connection between the aircraft and the energy information supply warehouse of the present invention.

[0020] Figure 3 This is a schematic diagram of the interior of the aircraft of the present invention.

[0021] Figure 4 for Figure 3 Enlarged view of the local structure at point C.

[0022] Figure 5 This is a schematic diagram showing the connection between the energy information supply warehouse and the sentry aircraft warehouse of the present invention.

[0023] Figure 6 This is a schematic diagram of the interior of the energy information supply warehouse of the present invention.

[0024] In the diagram: 1. Aircraft; 11. Arc-shaped section; 2. Support leg; 21. Bent section; 22. Ground contact rod; 3. Side arm; 31. Mounted base; 32. Rotor; 33. Support ring; 34. Protective net; 35. Cutting blade; 4. Connecting harness; 41. Receiver; 42. Drive unit; 43. Connecting flange; 5. Collision plate; 6. Reconnaissance camera; 61. Radar; 7. Connecting seat; 71. U-shaped mounting plate; 72. Inner groove; 73. Buckle; 7 4. Insertion port; 8. Energy information supply compartment; 81. Upper plate; 82. Shaft column; 83. Fastening long seat; 84. Brush; 85. Motor; 86. Partition plate; 87. Stop plate; 88. Anti-winding plate; 9. Retrieval rope; 10. Sliding plate; 101. Connecting column; 102. Long slide groove; 103. U-shaped fixing plate; 104. Pulley; 12. Sentry compartment; 121. Elastic plate; 122. Compartment cover; 123. Rope placement notch; 13. Hydrogen layer. Detailed Implementation

[0025] The technical solution of the present invention will be further described in detail below through specific embodiments and in conjunction with the accompanying drawings. The described embodiments are only some embodiments of the present invention, and not all embodiments.

[0026] Example 1: Refer to Figures 1 to 5 An all-weather collision avoidance sentry aircraft mainly consists of an aircraft 1 and an energy and information supply compartment 8. The aircraft 1 serves as the core body and is connected to several side arms 3, each of which is carefully equipped with rotors 32. This design allows the aircraft 1 to obtain sufficient power support during flight, and the multiple rotors 32 work together to ensure the aircraft's flexible movement in different directions and stable hovering capability. The energy information supply compartment 8 serves as the energy source and information hub for the aircraft. The two are connected by a recovery rope 9, which cleverly incorporates cables. This cable continuously and stably supplies power to the aircraft, ensuring the normal operation of critical components such as the rotor. It also establishes an information transmission channel, facilitating real-time data interaction between the aircraft and the energy information supply compartment. This enables precise monitoring and intelligent control of the flight status. A collision protection plate 5, made of elastic material, is also connected to one side of the support ring. This plate provides cushioning in case of a collision with a hard object. A cutting blade is coaxially mounted above the rotor. When leaves fall above, the blade rotates and cuts them off, preventing damage to the drone. The outer side of the recovery rope has a hydrogen layer, which improves overall performance and reduces weight.

[0027] Further analysis of the internal structure of the aircraft 1 reveals a connecting seat 7 located at its top. Below the connecting seat 7 is a U-shaped fixing plate 71, within which a carefully crafted inner groove 72 allows a buckle 73 to be precisely inserted. The buckle 73 features a cleverly designed insertion port 74, to which one end of the recovery rope 9 is securely connected, while the other end extends to the energy and information supply compartment 8. This connection method not only ensures a stable connection between the aircraft and the energy and information supply compartment but also provides a degree of flexibility, allowing the recovery rope 9 adequate space to move during attitude adjustments and flight operations. This prevents damage to the cable and recovery rope due to excessive pulling, ensuring smooth flight and reliable energy and information transmission.

[0028] Beneath aircraft 1 are mounted a reconnaissance camera 6 and a radar 61. The reconnaissance camera 6 can capture high-definition images in real time, providing comprehensive visual monitoring of the target area. Whether day or night, thanks to advanced imaging technology, it can clearly record surveillance footage, providing the ground command center with an intuitive view of the situation. Radar 61 uses electromagnetic waves to detect the surrounding environment, accurately sensing information such as the distance, relative speed, and orientation between the aircraft and obstacles. It plays a crucial role in environmental perception under complex weather conditions and low visibility. The two working together greatly enhance the aircraft's reconnaissance, monitoring, and collision avoidance capabilities in all weather conditions, ensuring the aircraft can safely and efficiently complete its reconnaissance missions.

[0029] A connecting harness 4 is provided on one side of the connector 7, which connects to a receiver 41. The receiver 41 receives power from the energy information supply compartment 8 and provides stable power to the drive unit 42 and the reconnaissance camera 6 and radar 61 located below. A connecting flange 43 is located below the drive unit 42. The connecting flange 43 securely connects to the reconnaissance camera 6 and radar 61 below, ensuring the stability of the equipment during flight. Furthermore, its design offers high flexibility, allowing for easy replacement of the connected equipment according to different mission requirements. For example, in certain special scenarios, it can be quickly replaced with other functional modules, such as an infrared thermal imager or a gas detector, to adapt to diverse monitoring tasks. Moreover, the drive unit 42 can rotate the reconnaissance camera 6 and radar 61 below, achieving omnidirectional scanning of the surrounding environment, expanding the monitoring range, and improving reconnaissance efficiency and effectiveness.

[0030] Focusing on the internal structure of the energy information supply compartment 8, a motor 85 is installed inside, serving as the core power component to drive the rotation of the shaft 82. One side of the motor 85 is a partition 86, and the other side of the partition 86 is connected to the shaft 82. A recovery rope 9 can be wound around the shaft 82. The rotation of the shaft by the motor allows for control of the recovery rope 9's deployment and retrieval, thereby adjusting the flight altitude and position of the aircraft 1. A circular stop plate 87 is also installed at one end of the shaft 82 near the partition 86. The circular stop plate 87 serves a limiting and stabilizing function, preventing the recovery rope 9 from shifting or loosening during winding, ensuring that the recovery rope 9 is tightly and orderly wound around the shaft 82, and guaranteeing the smoothness and reliability of the aircraft's deployment and retrieval process.

[0031] A long chute 102 is cleverly designed on one side of the energy information supply compartment 8. A sliding plate 10 is built into the long chute 102, and the sliding plate 10 is fixedly connected to a U-shaped fixed plate 103 by a connecting column 101. A pulley 104 is connected inside the U-shaped fixed plate 103. An anti-winding plate 88 is also provided between the pulley 104 and the axle column 82, separating the pulley 104 from the axle column 82. This design effectively prevents the recovery rope 9 from crossing or tangling during winding and release. The recovery rope 9 on the axle column 82 passes through the pulley 104 along a predetermined path and extends out of the energy information supply compartment 8. The pulley 104 acts as a guide and support, making the recovery rope 9 move more smoothly, reducing frictional wear between the recovery rope and the equipment, extending the service life of the recovery rope, and improving the operating efficiency and stability of the entire recovery and release system.

[0032] The top of the energy information supply compartment 8 is a top plate 81, and a fastening seat 83 is provided on one side of the top plate 81. A brush 84 is cleverly installed inside the fastening seat 83. The recovery rope 9 passes through the pulley 104 from the shaft 82, then passes through the brush 84 again, and then connects to the aircraft 1. The brush 84 is of great significance. On the one hand, it can clean the recovery rope 9, removing dust, impurities, etc. from the surface of the recovery rope, preventing impurities from entering the energy information supply compartment and damaging key components such as the motor and shaft. On the other hand, the moderate friction between the brush and the recovery rope can play a certain buffering role, reducing the violent shaking of the recovery rope due to inertia and other factors during the retrieval and release process, and further improving the stability of the aircraft's retrieval and launch process.

[0033] A sentry bay 12 is also located on one side of the energy information supply bay 8. A rope notch 123 is conveniently provided at the connection point between the sentry bay 12 and the energy information supply bay 8. When the aircraft 1 lands back in the sentry bay, the recovery rope 9 can pass through the rope notch 123. An elastic plate 121 is arranged inside the sentry bay 12, which provides a certain degree of cushioning. When the aircraft lands inside the sentry bay, it can effectively reduce the impact force between the aircraft and the bay, protecting the aircraft and the equipment inside the bay from damage and extending the service life of the equipment. The sentry bay 12 also has a bay cover 122. When the bay cover 122 is closed, the recovery rope 9 passes through the rope notch 123. This design facilitates the storage and protection of the aircraft, ensuring it is in a relatively safe and stable storage state when not performing missions. It also facilitates maintenance and inspection of the aircraft, ensuring that the aircraft is always in good working condition and can quickly respond to mission requirements.

[0034] Example 2: Refer to Figures 1 to 5 This is an all-weather collision avoidance sentry aircraft, mainly composed of two core components: the aircraft 1 and the energy and information supply compartment 8. The aircraft 1, as the core of the entire system, undertakes multiple important tasks such as flight, reconnaissance, and data acquisition. To ensure superior flight performance, it is connected to the outside via multiple side arms 3, each of which is meticulously designed and equipped with rotors 32.

[0035] The design of these rotors 32 is not a simple arrangement, but rather the result of extensive wind tunnel testing and fluid dynamics analysis to determine the optimal size, shape, and installation angle. During flight, the multiple rotors 32 generate strong and stable lift, working in tandem to enable the aircraft 1 not only to achieve rapid horizontal movement but also to flexibly perform various attitude adjustments in the air, such as hovering, ascent, descent, and lateral movement. This multi-rotor design greatly improves the aircraft's adaptability and maneuverability in different flight environments, ensuring stable flight whether in open plains, narrow urban areas, or complex mountainous terrain.

[0036] The energy and information supply compartment 8 provides the necessary electrical energy to the aircraft and is also responsible for information transmission and processing. The two are cleverly connected by a recovery rope 9, within which cables are ingeniously arranged. This not only ensures stable energy transmission and guarantees the normal operation of critical components such as rotors and reconnaissance equipment, but also establishes an efficient information transmission channel. Through this channel, the aircraft can transmit various reconnaissance data, such as images and radar signals, back to the energy and information supply compartment in real time. Simultaneously, the ground control center can also send commands to the aircraft through the energy and information supply compartment, enabling precise monitoring and intelligent control of the flight status and ensuring the successful completion of flight missions.

[0037] A U-shaped fixing plate 71 is securely fixed below the connecting seat 7. The U-shaped fixing plate 71 has a carefully crafted inner groove 72. The size and shape of this inner groove 72 perfectly match the buckle 73, allowing the buckle 73 to be inserted precisely. The buckle 73 is designed with an insertion port 74 to firmly fix one end of the recovery rope 9, while the other end of the recovery rope 9 extends to the energy information supply compartment 8.

[0038] Beneath aircraft 1, reconnaissance equipment is a key component of its mission. Equipped with reconnaissance camera 6 and radar 61, the two together constitute the aircraft's powerful environmental awareness system. Reconnaissance camera 6 employs advanced imaging technology, possessing high resolution, high sensitivity, and low-light imaging capabilities. It can capture high-definition images in real time, providing all-around, blind-spot-free visual monitoring of the target area. Whether in bright sunlight or pitch-black darkness, the reconnaissance camera can clearly record the monitoring footage thanks to its excellent performance. This image data can be transmitted to the ground command center in real time, providing decision-makers with intuitive and accurate on-site information, helping them to make rapid judgments and decisions.

[0039] Radar 61 is capable of accurately detecting objects in the surrounding environment. By emitting electromagnetic waves and receiving reflected signals, radar can precisely sense key information such as the distance, relative speed, and orientation between an aircraft and obstacles. In complex weather conditions, such as heavy fog, heavy rain, and snowstorms with low visibility, radar plays a particularly important role. It can promptly detect potential obstacles and hazards, providing reliable early warning information for the aircraft, ensuring safe and stable flight under various weather conditions, and greatly enhancing the aircraft's all-weather reconnaissance, monitoring, and collision avoidance capabilities. The coordinated operation of reconnaissance cameras and radar enables the aircraft to acquire information more efficiently and accurately during reconnaissance missions, ensuring the successful completion of missions and protecting the aircraft's own safety.

[0040] The power supply and drive structure plays a crucial role in ensuring the normal operation of reconnaissance equipment and the flexible adjustment of the aircraft's attitude. A connecting harness 4 is located on one side of the aircraft 1's connecting seat 7. This harness acts as a vital energy and signal transmission link, connecting to the receiver 41. The main function of the receiver 41 is to stably transmit electrical energy from the energy supply compartment 8 and distribute it appropriately to the drive unit 42 and other electrical equipment such as the reconnaissance camera 6 and radar 61 below. This stable power supply mechanism ensures that the reconnaissance equipment can operate continuously and efficiently during flight, without interruption or performance degradation due to insufficient power.

[0041] The drive unit 42 is located above the reconnaissance equipment and is connected to the reconnaissance camera 6 and radar 61 via a connecting flange 43. The design of the connecting flange 43 fully considers the stability and flexibility of the equipment. On the one hand, it securely connects to the reconnaissance equipment below, ensuring stability even during flight, such as encountering turbulence or airflow interference, and guaranteeing clear and accurate transmission of images and radar signals. On the other hand, the connecting flange design is highly flexible, facilitating rapid replacement of the connected equipment according to different mission requirements. For example, in certain special scenarios, such as forest fire monitoring missions, it can be quickly replaced with an infrared thermal imager for more accurate detection of fire sources and monitoring of fire spread; in environmental pollution monitoring missions, a gas detector can be installed to monitor the composition and concentration of harmful gases in the air in real time. This flexible equipment replacement mechanism greatly improves the versatility and adaptability of the aircraft, enabling it to quickly respond to various diverse monitoring mission requirements.

[0042] Furthermore, the drive unit 42 also has the function of rotating the reconnaissance equipment below. Through precise motor control, the drive unit can achieve 360-degree omnidirectional rotation, enabling the reconnaissance cameras and radar to conduct a comprehensive and detailed scan of the surrounding environment. This omnidirectional monitoring capability significantly expands the aircraft's monitoring range, improves reconnaissance efficiency and effectiveness, and allows the aircraft to acquire more comprehensive information in a shorter time, providing richer and more accurate data support for subsequent analysis and decision-making.

[0043] Motor 85 is connected to shaft 82. The rotation of the motor drives the shaft to rotate, thereby controlling the release and retrieval of the recovery rope 9. This release and retrieval control mechanism is key to adjusting the flight altitude and position of the aircraft 1. Operators can precisely control the ascent, descent, and recovery actions of the aircraft by controlling the rotation direction and speed of the motor according to mission requirements and the site environment, ensuring that the aircraft always maintains the optimal flight state and position, and efficiently completes the reconnaissance mission.

[0044] A partition 86 is installed on one side of the motor 85. The partition 86 not only serves as a divider and support but also provides a stable mounting base for the shaft 82. The retrieval rope 9 can be wound around the shaft 82, and under the drive of the motor, the retrieval rope can be wound or released in an orderly manner. A circular stop plate 87 is cleverly installed at one end of the shaft 82 near the partition 86. The circular stop plate 87 plays a crucial role; it effectively prevents the retrieval rope 9 from shifting or loosening during winding, ensuring that the retrieval rope is tightly and neatly wound around the shaft. This not only improves the service life of the retrieval rope but also ensures the stability and reliability of the aircraft's deployment and retrieval process, avoiding safety hazards such as aircraft shaking and loss of control that may result from unstable retrieval rope winding.

[0045] One side of the energy information supply compartment 8 is designed with an elongated chute 102, which provides movement space for the sliding plate 10. The sliding plate 10 is fixedly connected to a U-shaped fixed plate 103 by a connecting post 101, and a pulley 104 is installed inside the U-shaped fixed plate 103. The pulley 104 is a crucial component of the entire retrieval rope guiding system. An anti-winding plate 88 is installed between the pulley 104 and the axle post 82. The anti-winding plate 88 separates the pulley 104 from the axle post 82 by a certain distance, thereby effectively preventing the retrieval rope 9 from crossing or tangling during winding and release. This design greatly improves the reliability and stability of the retrieval rope winding and release system, and reduces the risk of equipment damage and task interruption caused by retrieval rope tangling.

[0046] The retrieval rope 9 on the shaft 82 passes through the pulley 104 along a carefully designed predetermined path and extends into the energy information supply chamber 8. The pulley 104 plays a crucial guiding and supporting role in this process. It allows the retrieval rope 9 to slide more smoothly during movement, reducing frictional wear between the retrieval rope and the equipment. This not only extends the service life of the retrieval rope but also improves the operating efficiency and stability of the entire retrieval system. When the motor drives the shaft to rotate and retrieve the retrieval rope, the pulley ensures that the retrieval rope moves in the correct direction and path, avoiding unnecessary contact and interference between the retrieval rope and other components, thus guaranteeing the efficient and stable operation of the entire system.

[0047] At the top of the energy information supply compartment 8, there is an upper plate 81. A fastening seat 83 is provided on one side of the upper plate 81, and a brush 84 is cleverly installed inside the fastening seat 83. When the recovery rope 9 passes through the pulley 104 from the shaft 82, it passes through the brush 84 again and then connects to the aircraft 1.

[0048] One of the main functions of brush 84 is to clean the recovery rope 9. During the operation of the aircraft, the recovery rope inevitably comes into contact with dust, impurities, and various pollutants in different environments. If these pollutants accumulate on the surface of the recovery rope, they will not only affect the performance of the recovery rope, but may also bring impurities into the energy information supply compartment when the recovery rope is retrieved, causing damage to critical components such as motors and shafts. Brush 84, with its soft and dense bristles, can effectively remove dust and impurities from the surface of the recovery rope as it passes through, providing a good cleaning effect and thus protecting the cleanliness of the energy information supply compartment and the good operating condition of its components.

[0049] Furthermore, the moderate friction between the brush and the retrieval rope provides a certain degree of cushioning. During the retrieval rope's deployment and retrieval, factors such as the rotational inertia of the motor and the aircraft's motion inertia may cause some swaying and impact. The brush's cushioning effect reduces these swaying and impacts, making the retrieval rope more stable during deployment and retrieval. This not only helps extend the retrieval rope's lifespan but also further improves the stability of the aircraft's recovery and launch processes, ensuring the safety and reliability of the aircraft during takeoff and landing, and avoiding problems such as aircraft attitude instability that may result from excessive swaying of the retrieval rope.

[0050] A sentry bay 12 is also designed on one side of the energy information supply bay 8. This sentry bay 12 provides important protection for the storage and protection of the aircraft. A rope placement notch 123 is thoughtfully provided at the connection between the sentry bay 12 and the energy information supply bay 8. This design allows the recovery rope 9 to pass smoothly through the rope placement notch when the aircraft 1 lands, guiding the aircraft smoothly into the bay.

[0051] The Sentinel bay 12 is equipped with a carefully designed elastic plate 121, which possesses excellent elasticity and cushioning properties. When an aircraft lands inside the Sentinel bay, the elastic plate effectively absorbs the impact force generated during landing, thereby protecting the aircraft and the equipment inside the bay from damage. This is crucial for extending the service life of the aircraft and equipment, especially during frequent takeoffs and landings or missions in complex environmental conditions, reducing potential equipment failures and maintenance costs caused by collisions.

[0052] The Sentinel bay 12 is also equipped with a bay cover 122. When the bay cover 122 is closed, the recovery rope 9 can easily pass through the rope placement notch 123. This design not only facilitates the storage and protection of the aircraft, ensuring it is in a relatively safe and stable storage state when not on mission, avoiding the influence of external environmental factors such as wind, rain, and dust, but also facilitates maintenance and inspection by operators. When it is necessary to inspect the aircraft, replace parts, or prepare for a mission, simply opening the bay cover provides easy access to the aircraft, ensuring it is always in good working order, capable of quickly responding to mission requirements, and ready to execute the next reconnaissance mission at any time.

[0053] The aircraft 1 has an arc-shaped section 11 along its edges. This design not only makes the overall shape of the aircraft more streamlined, helping to reduce air resistance and improve the stability and maneuverability of the aircraft during flight, but also disperses the impact force during a collision to a certain extent, enhancing the aircraft's impact resistance. The aircraft 1 also has outriggers 2 on both sides, which are connected to ground contact poles 22. The ground contact poles 22 have curved sections 21 on both sides. The combined structure of the outriggers 2 and the ground contact poles 22 provides stable support for the aircraft, effectively protecting the main body of the aircraft from damage during takeoff and landing. The curved sections 21 further increase the strength and toughness of the ground contact poles, allowing them to better adapt to different terrains and ensuring a smooth landing.

[0054] The side arm 3 and the rotor 32 are connected by a fixed base 31. This connection ensures the stability of the rotor 32 during high-speed rotation. The fixed base 31 is responsible for transmitting power and bearing various forces generated by the rotor. A support ring 33 is provided above the rotor 32, and a protective net 34 is installed on the support ring 33. The support ring 33 provides a stable support structure for the protective net 34, which effectively prevents external objects from impacting and damaging the rotor 32 during flight, ensuring the normal operation of the rotor system. This greatly improves the safety and reliability of the aircraft in complex environments and reduces the risk of malfunctions and accidents caused by accidental collisions.

[0055] For those skilled in the art, the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention.

Claims

1. An all-weather collision avoidance sentry aircraft, characterized in that, It includes an aircraft and an energy and information supply compartment. The aircraft is connected to several side arms, and rotors are installed on the side arms. The aircraft is connected to the energy and information supply compartment by a recovery rope, and cables are arranged inside the recovery rope.

2. The all-weather collision avoidance sentry aircraft according to claim 1, characterized in that, A connector is installed on the top of the aircraft, and a U-shaped fixing plate is fixed below the connector. The U-shaped fixing plate has an inner groove, and a buckle is inserted into the inner groove. The buckle has an insertion port. One end of the recovery rope is connected to the insertion port, and the other end is connected to the energy information supply compartment.

3. The all-weather collision avoidance sentry aircraft according to claim 2, characterized in that, The rotor is coaxially mounted with cutting blades, the outside of the recovery rope is equipped with a layer of hydrogen, and a reconnaissance camera and radar are installed below the aircraft.

4. An all-weather collision avoidance sentry aircraft according to claim 2 or 3, characterized in that, A connecting harness is provided on one side of the connector, which connects to the receiver and supplies power to the drive unit and the reconnaissance camera and radar located below. A connecting flange is provided below the drive unit, which drives the reconnaissance camera and radar below to rotate.

5. An all-weather collision avoidance sentry aircraft according to claim 1 or 3, characterized in that, The energy information supply compartment is equipped with a motor. One side of the motor is a partition, and the other side of the partition is connected to a shaft. A recovery rope is wound on the shaft, and a circular stop plate is also installed at one end of the shaft near the partition.

6. The all-weather collision avoidance sentry aircraft according to claim 5, characterized in that, A long chute is also provided on one side of the energy information supply compartment. A sliding plate is built into the long chute. The sliding plate is fixed to a U-shaped plate by a connecting column. A pulley is connected inside the U-shaped plate. An anti-winding plate is also provided between the pulley and the column. The anti-winding plate separates the pulley from the column. The recovery rope on the column passes through the pulley and extends out of the energy information supply compartment.

7. The all-weather collision avoidance sentry aircraft according to claim 6, characterized in that, The top of the energy information supply compartment is the upper plate, and a fastening seat is set on one side of the upper plate. A brush is installed inside the fastening seat. The recovery rope passes through the pulley from the shaft column and then through the brush, and then connects to the aircraft.

8. An all-weather collision avoidance sentry aircraft according to claim 1 or 7, characterized in that, A sentry cabin is also set up on one side of the energy information supply warehouse. A rope placement gap is set at the connection between the sentry cabin and the energy information supply warehouse. An elastic plate is set inside the sentry cabin. The sentry cabin has a cabin cover. When the cabin cover is closed, the retrieval rope passes through the rope placement gap.

9. An all-weather collision avoidance sentry aircraft according to claim 1 or 7, characterized in that, The aircraft has curved edges, and there are also legs on both sides of the aircraft. The legs are connected to ground contact rods, which have curved sides.

10. An all-weather collision avoidance sentry aircraft according to claim 1 or 7, characterized in that, The side arm and the rotor are connected by a fixed base. A support ring is installed above the rotor. A crash plate is connected to one side of the support ring, and a protective net is installed on the support ring.

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