Small fixed-wing unmanned aerial vehicle carrying satellite communication equipment

Abstract

According to the small fixed-wing unmanned aerial vehicle carrying the satellite communication equipment, wings, propellers, motors, a satellite communication system antenna and a battery pack of the unmanned aerial vehicle are connected through quick-release buckles, and quick disassembly and assembly can be achieved. Satellite communication equipment is carried, so that unmanned aerial vehicle communication and control can be performed in real time nationwide; taking-off and landing are flexible, a parachute is carried, and the parachute is automatically opened for emergency landing under the out-of-control or unforeseen circumstances; ground catapulting is adopted for takeoff, and limitation of sites and environments is avoided. Modularized design is adopted, wing empennages can be quickly inserted and pulled, batteries can be quickly assembled and disassembled, disassembly, assembly and maintenance are convenient, and quick deployment is facilitated. A high-performance airborne solid-state lithium battery is used, a high-performance brushless motor and a low-noise carbon fiber propeller are matched, the appearance of the unmanned aerial vehicle is pneumatically optimized, the flight resistance is small, a large number of composite materials are used in the whole unmanned aerial vehicle, the weight is light, and the long-endurance and long-voyage flight performance is achieved.

Description

Technical Field

[0001] This invention relates to unmanned aerial vehicles (UAVs), specifically to the field of aircraft design technology within unmanned aerial vehicles. Background Technology

[0002] Drones first appeared in the 1920s. During World War I, Britain began developing a small aircraft that could be operated by radio without human pilots. In the 1940s, during World War II, unmanned target drones were used to train anti-aircraft gunners.

[0003] Today, with the rapid development of technology, fixed-wing drones have gradually entered people's daily lives and various industries, becoming an important force in promoting social progress and industrial upgrading. From photography and videography to geographic surveying, from agricultural plant protection to disaster relief, drones are used everywhere, demonstrating their enormous potential and value.

[0004] High speed: Fixed-wing drones, by utilizing their fixed-wing design, can achieve high flight speeds in a short time, making them suitable for scenarios requiring rapid response.

[0005] High maneuverability: Fixed-wing UAVs have high maneuverability when flying horizontally, and can quickly change their flight direction and altitude.

[0006] High payload capacity: Due to its structural design and power configuration, fixed-wing UAVs can carry heavy payloads and are suitable for missions requiring large payloads.

[0007] Long battery life: Fixed-wing drones typically have a long battery life, making them suitable for long-duration missions without the need for frequent charging or battery replacements.

[0008] Good stability: Fixed-wing UAVs have high flight stability and can fly stably under various weather conditions.

[0009] Strong wind resistance: Due to its high speed and stable flight characteristics, fixed-wing UAVs perform better when facing strong winds and are suitable for operation in complex weather conditions.

[0010] Agricultural monitoring: Fixed-wing drones can cover large areas of farmland and use onboard multispectral cameras to monitor crop health, helping farmers to manage farmland scientifically.

[0011] Environmental protection: Fixed-wing drones are used to monitor forest, wetland and marine ecosystems, collect critical environmental data, and help environmental organizations develop more effective protection strategies.

[0012] Border patrol: Fixed-wing drones are widely used to enhance border security, provide continuous surveillance, and effectively prevent illegal border crossings and other security issues due to their ability to fly for extended periods and cover a wide area.

[0013] Disaster emergency response: After a natural disaster occurs, fixed-wing UAVs can be rapidly deployed to conduct large-scale disaster assessment and rescue missions, significantly improving the efficiency and effectiveness of emergency response.

[0014] Cargo transportation: In remote areas or areas with poor transportation, fixed-wing drones can effectively transport medical supplies and other emergency items, playing a significant role, especially in post-disaster reconstruction.

[0015] Technological Innovation and Progress: The technological development of fixed-wing UAVs will focus on improving flight performance, enhancing intelligence, and optimizing endurance. Breakthroughs in key technologies, such as autonomous navigation systems, data transmission technology, and energy efficiency improvements, will drive the widespread application of fixed-wing UAVs in both military and civilian fields.

[0016] Market Demand Growth: With the global economic recovery and the development of various industries, the market demand for fixed-wing drones will continue to grow. Application areas will further expand, including but not limited to agricultural plant protection, environmental monitoring, urban planning, and logistics transportation. Particularly in the agricultural sector, the high-efficiency operational capabilities of fixed-wing drones will be increasingly favored, while their role in environmental monitoring and urban planning will also become increasingly important.

[0017] Existing technologies, such as those published in CN 111792023A, CN114735196A, CN117262284A, and CN112141327A, have the following drawbacks:

[0018] Existing small fixed-wing UAVs generally have short flight times, less than 1 hour, and limited payload capacity. Hybrid and fuel-powered UAVs have longer flight times, but they are inconvenient to use and maintain, complex to operate, and generate significant vibrations, which can affect the measurement results of mission payloads. In addition, most existing long-endurance UAVs use runway takeoff, which requires a dedicated runway and places high demands on the runway width, length, and surrounding environment, making them unsuitable for portable management and flexible deployment.

[0019] Existing small fixed-wing UAVs have short endurance and range, making long-distance communication impossible. They rely on wireless communication, which is prone to signal interruption in complex long-distance flight environments, severely impacting their operational capabilities and efficiency. Fuel-powered UAVs require complex maintenance, and generate significant vibration and noise during flight, affecting the measurement accuracy of payload sensors. Furthermore, existing fixed-wing UAVs typically use wheeled landing gear for takeoff and landing, making them highly dependent on runways and hindering flexible deployment. The wing-fuselage connections of existing fixed-wing UAVs are usually bolted together, requiring specialized tools and involving complex operations, which cannot meet the demands of increasingly complex flight missions. Summary of the Invention

[0020] This invention provides a small fixed-wing unmanned aerial vehicle (UAV) equipped with satellite communication equipment, the technical solution of which is as follows:

[0021] A small fixed-wing unmanned aerial vehicle (UAV) equipped with satellite communication equipment mainly includes wings, motors and propellers, a fuselage, a vertical tail, a horizontal tail, a satellite communication system antenna, a front equipment compartment, a belly equipment compartment, a parachute compartment, a power battery, an airborne satellite communication system host, and a pneumatic catapult. The connections between the UAV's wings, propellers, motors, satellite communication system antenna, and battery pack are made using quick-release clips for rapid assembly and disassembly. The wings are mounted on the left and right sides of the fuselage, connected and fixed to the fuselage via quick-release clips a. A vertical tail and a horizontal tail are located at the rear of the fuselage; the vertical tail is connected and fixed to the fuselage via quick-release clips b, and the horizontal tail is connected and fixed to the fuselage via quick-release clips c. The motors and propellers are located at the leading edges of the wings near the root.

[0022] Beneficial effects

[0023] Compared to conventional fixed-wing drones, this invention's small fixed-wing UAV is equipped with satellite communication equipment, enabling real-time communication and control nationwide. It offers flexible takeoff and landing, featuring a parachute for autonomous emergency landing in case of loss of control or accidents. Takeoff is via ground ejection, unrestricted by location or environment. Its modular design allows for quick insertion and removal of wings and tail fins, and rapid battery installation and removal, facilitating maintenance and rapid deployment. Utilizing a high-performance onboard solid-state lithium battery, coupled with a high-performance brushless motor and low-noise carbon fiber propeller, the UAV's aerodynamic shape minimizes drag. Extensive use of composite materials results in lightweight design and long endurance and range. Attached Figure Description

[0024] Figure 1 The overall three-dimensional structure of the small fixed-wing UAV of the present invention Figure I ;

[0025] Figure 2This is a three-dimensional diagram of the overall structure of the small fixed-wing UAV of the present invention (II).

[0026] Figure 3 This is a schematic diagram of the antenna protrusion on the back of the fuselage of the small fixed-wing UAV of the present invention;

[0027] Figure 4 This is a schematic diagram of the front equipment compartment of the fuselage of the small fixed-wing UAV of the present invention;

[0028] Figure 5 This is a front view of a schematic diagram of the battery installation on a small fixed-wing UAV according to the present invention.

[0029] Figure 6 Schematic diagram of battery installation for the small fixed-wing UAV of the present invention. Figure 3 Vito;

[0030] Figure 7 This is a schematic diagram showing the battery installation completed for the small fixed-wing UAV of the present invention.

[0031] Figure 8 This is a schematic diagram of the wing connection of the small fixed-wing UAV of the present invention;

[0032] Figure 9 This is a schematic diagram of the vertical tail connection of the small fixed-wing UAV of the present invention;

[0033] Figure 10 This is a schematic diagram of the horizontal tail connection of the small fixed-wing UAV of the present invention;

[0034] Figure 11 This is a schematic diagram of the quick-release buckle connection for the small fixed-wing UAV of the present invention. Figure I ;

[0035] Figure 12 This is a schematic diagram of the quick-release buckle connection for the small fixed-wing UAV of the present invention. Figure II ;

[0036] Figure 13 This is a schematic diagram of the parachute recovery of the small fixed-wing UAV of the present invention;

[0037] Figure 14 This is a three-dimensional diagram of the aerodynamic catapult mount for the small fixed-wing UAV of the present invention;

[0038] Figure 15 This is a schematic diagram of the catapult launch of the small fixed-wing UAV of the present invention;

[0039] In the diagram: 1. Wing, 2. Motor and propeller, 3. Fuselage, 4. Vertical tail, 5. Horizontal tail, 6. Satellite communication system antenna, 7. Forward equipment compartment, 8. Belly equipment compartment, 9. Parachute compartment, 10. Battery recess, 11. Power battery, 13. Catapult rail, 14. Front support, 15. Rear support, 16. Tractor, 17. Quick release buckle, 18. Separation surface. Detailed Implementation

[0040] Example 1

[0041] The embodiments of the present invention are illustrated below through examples:

[0042] This invention provides a small fixed-wing unmanned aerial vehicle (UAV) equipped with satellite communication equipment. It adopts a conventional layout and mainly includes a wing 1, a motor and propeller 2, a fuselage 3, a vertical tail 4, a horizontal tail 5, a satellite communication system antenna 6, a front equipment compartment 7, a belly equipment compartment 8, a parachute compartment 9, a power battery 11, a satellite communication system onboard unit, and a pneumatic catapult. The connections between the UAV's wings, propellers, motor, satellite communication system antenna, and battery pack are made using quick-release clips 17, allowing for rapid assembly and disassembly. The electrical system interfaces are rationally designed and effectively integrated, facilitating UAV maintenance and replacement, and effectively improving UAV deployment efficiency.

[0043] The wings 1 are installed on the left and right sides of the fuselage 3 to provide the lift required for flight. The wings are connected and fixed to the fuselage by quick-release buckles 17a. A vertical tail and a horizontal tail are provided at the rear of the fuselage. The vertical tail is connected and fixed to the fuselage by quick-release buckles 17b, and the horizontal tail is connected and fixed to the fuselage by quick-release buckles 17c.

[0044] The quick-release buckle 17 includes an elastic pressure plate 19a, a first base 19b, a second base 19c, a rotating shaft 19d, and a baffle 19e. The first base and the second base are respectively installed on the fuselage and wing to be connected. The separation surface between the two parts is 18. By moving the elastic pressure plate 19a, it passes through the hole in the baffle 19e. The baffle 19e rotates around the rotating shaft 19d, which completes the connection or disconnection of the two parts.

[0045] The motor and propeller 2 are located on the leading edge of the wings near the root on both sides, providing power for the drone to move forward.

[0046] The fuselage is equipped with three large-capacity equipment bays, including a forward equipment bay 7, a ventral equipment bay 8, and a parachute bay 9, located at the front, ventral, and rear of the fuselage, respectively. Each of the forward equipment bay 7, ventral equipment bay 8, and parachute bay 9 is equipped with a canopy. A horizontal protrusion 6a is provided on the back of the fuselage for mounting the satellite communication system antenna 6. The horizontal protrusion has been aerodynamically designed and analyzed to be aligned with the shape of the satellite communication system antenna, resulting in low aerodynamic drag. This helps to improve the positioning accuracy of the satellite communication system antenna and ensures that the attitude feedback of the satellite communication system antenna is consistent with that of the fuselage.

[0047] The satellite communication system antenna 6 is mounted on a horizontal protrusion 6a on the back of the fuselage. This antenna supports nationwide data transmission and remote control, making it suitable for areas inaccessible to traditional communication networks, such as remote regions, oceans, and mountainous areas. Through the satellite communication system antenna, operators can communicate between the drone, the onboard satellite communication terminal, the satellite, the ground receiving terminal, and the ground station to monitor the drone's status, transmit mission data, and send remote commands, ensuring successful mission execution. Communication is also possible in network-free environments such as mountainous areas, deserts, or seas, making it particularly suitable for drones performing remote monitoring, disaster relief, and environmental detection missions.

[0048] The front equipment compartment 7 is equipped with a battery recess 10, and a battery installation guide groove 10a is provided on the side of the battery recess. The upper part of the outer shell of the battery pack 11 is equipped with a rope handle 11a, and the side is equipped with a side guide groove 11b. The bottom of the battery pack is equipped with a battery electrical connector. By lifting the battery pack 11 and placing the prepared fully charged battery pack into the battery recess 10 at the front of the compartment, the battery replacement and electrical connector connection can be completed without the need for the battery pack to be fixed and the wiring connected again, which significantly reduces the time interval between operations and effectively improves efficiency.

[0049] The specific steps for battery installation are as follows:

[0050] Lift the smart battery strap handle 11a by hand and align the sliding groove of the side guide groove 11b of the battery pack with the battery installation guide groove 10a of the groove 10. Then, place the battery pack 11 vertically downward. During the downward movement of the battery pack 11, the battery electrical connector will contact the connector inside the body. When the battery is installed to the bottom, release the strap handle 11a by hand, and the electrical connector will complete the connection.

[0051] The forward equipment bay is also used to install the airborne satellite communication host, which is located at the rear of the forward equipment bay, behind the battery pack.

[0052] The parachute compartment 9 is used to install the parachute pack. In the event of a drone malfunction or an accident, the parachute pack will automatically deploy for an emergency landing. Depending on the size of the recovery site, the drone can either glide to the ground or use a parachute for a landing.

[0053] The small fixed-wing UAV also includes a pneumatic catapult, which uses high-pressure gas to drive the UAV to take off, eliminating the dependence on runways. The pneumatic catapult includes a catapult rail 13, a front support 14, a rear support 15, and a trolley 16. The catapult rail 13 can be divided into three sections: front, middle, and rear. After disassembly, the longest section is no more than 1.5m. The three sections are connected by a quick-release structure, making disassembly and assembly simple and reliable. The front support 14 and the rear support 15 are foldable, making the entire catapult easy to transport and deploy with the UAV.

[0054] Small fixed-wing UAVs are equipped with a special pneumatic catapult for takeoff, which allows the UAVs to take off in various terrains without the need for a runway.

[0055] The catapult launch process is as follows: The UAV is installed on the trolley 16 of the pneumatic catapult. After the catapult is inflated, it is activated. The trolley pulls the UAV together and moves towards the front catapult rail 13. When the UAV moves with the trolley 16 to the end of the catapult rail 13, the trolley 16 stops and releases the UAV. The UAV completes the launch and continues to fly forward.

[0056] This invention relates to a small fixed-wing UAV that utilizes lightweight composite materials, reducing the aircraft's structural weight and significantly improving its fatigue and impact resistance while lowering flight energy consumption. The UAV's airframe and wing skin are made of honeycomb composite materials; the main structural beams and frames utilize carbon fiber foam sandwich composite materials and carbon fiber tubes; and the propeller is made of carbon fiber.

[0057] It uses a high-performance onboard solid-state lithium battery, paired with a high-performance brushless motor and a low-noise carbon fiber propeller, which has high energy utilization efficiency and is energy-saving and environmentally friendly.

[0058] Example 2

[0059] The small fixed-wing UAV equipped with satellite communication equipment described in Embodiment 1 of the present invention uses a phased array panel for radio transmission and reception in its satellite communication system antenna. By controlling the feed phase of the radiating elements in the array antenna to change the shape of the radiation pattern, and by changing the direction of the maximum value of the antenna radiation pattern, the beam scanning can be aligned with the satellite. It has a fast response speed, does not require a mechanical transmission device compared to a parabolic antenna, has a low antenna height, significantly reduced size and weight, and low power consumption.

[0060] Operating mechanism: Nationwide, the satellite communication module can provide a stable transmission connection. The UAV operates autonomously during flight. When the flight distance exceeds the coverage of the conventional communication network, it automatically switches to satellite communication mode to ensure that flight status parameters can be transmitted to the ground station in a timely manner for monitoring and operation.

[0061] Information confirmation and retransmission mechanism: After each data transmission, the system waits for confirmation from the ground station. If confirmation is not received within a set time, the airborne terminal automatically retransmits the data. After multiple retransmission failures, the system can automatically activate redundant links to further improve the reliability of data transmission.

[0062] When the wireless network coverage area is at the edge or when high stability is required, the satellite communication system can be activated simultaneously to transmit flight data via dual channels to ensure real-time transmission.

[0063] Example 3

[0064] The small fixed-wing UAV equipped with satellite communication equipment described in Embodiment 1 of the present invention includes an encoding / decoding unit, a buffer unit, and a transmitting unit as its onboard satellite communication unit.

[0065] The encoding and decoding unit encodes the parameters output by the UAV flight control system into a format suitable for satellite communication transmission, and decodes the received information to input it into the flight control system, ensuring accurate data transmission.

[0066] Buffer unit: Employs advanced compression algorithms to temporarily store data to be transmitted, reducing data volume, managing data priority and transmission order, and lowering satellite communication transmission latency.

[0067] Transmitting unit: transmits data to antenna 6 of the satellite communication system and transmits it through the satellite link, optimizing the transmission power and transmission path, and improving the stability of the communication link.

[0068] Example 4

[0069] The small fixed-wing UAV equipped with satellite communication equipment described in Embodiment 1 of the present invention further includes a satellite communication ground receiving terminal and a UAV ground station. The satellite communication ground receiving terminal consists of a ground antenna and satellite communication software. The ground antenna receives signals transmitted by the UAV via satellite, and the satellite communication software restores the encoded data in the signal into UAV flight parameters and forwards them to the ground station. The UAV ground station receives the UAV flight parameters and displays real-time information, and ground personnel can issue relevant control commands based on the information.

[0070] This invention discloses a small fixed-wing UAV equipped with satellite communication equipment. It integrates a self-developed lightweight small satellite communication module, enabling global data transmission and remote control. This module is suitable for areas inaccessible to traditional communication networks, such as remote areas, oceans, and mountainous regions. Through this module, operators can monitor the UAV's status, transmit mission data, and send remote commands to ensure successful mission execution.

[0071] 4) Long-endurance and long-range flight performance

[0072] By employing aerodynamic optimization methods combined with scaled-down model wind tunnel testing, the aircraft's drag during flight was reduced, improving its endurance. The wheeled landing gear was eliminated, and the fuselage adopted a streamlined shape, significantly reducing frictional drag caused by the irregular shape during flight. Computer simulation analysis was used to analyze the aerodynamic shape of the entire UAV, and flow field analysis was employed to simulate the airflow state of the UAV at various flight stages. Flow field data around the aircraft was obtained, the aircraft's shape was modified, and flight drag was reassessed. This process was repeated, and a scaled-down verification model was created for wind tunnel testing to verify the effectiveness of the drag reduction. Finally, the optimized aerodynamic shape was obtained, resulting in a UAV with lower drag during flight.

[0073] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed invention. The scope of protection claimed by the appended claims and their equivalents is defined.

Claims

1. A small fixed-wing unmanned aerial vehicle (UAV) equipped with satellite communication equipment, mainly comprising wings, motors and propellers, fuselage, vertical tail, horizontal tail, satellite communication system antenna, front equipment compartment, belly equipment compartment, parachute compartment, power battery, onboard host of the satellite communication system, and pneumatic catapult; the connections between the UAV's wings, propellers, motors, satellite communication system antenna, and battery pack are made using quick-release clips, allowing for rapid assembly and disassembly, characterized in that: The wings (1) are installed on the left and right sides of the fuselage (3). The wings are connected and fixed to the fuselage by quick-release buckles a. A vertical tail and a horizontal tail are provided at the rear of the fuselage. The vertical tail is connected and fixed to the fuselage by quick-release buckles b, and the horizontal tail is connected and fixed to the fuselage by quick-release buckles c. The motor and propeller (2) are located at the leading edge of the wings near the root on both sides.

2. A small fixed-wing UAV equipped with satellite communication equipment according to claim 1, characterized in that: the quick-release buckle includes an elastic pressure plate (19a), a first base (19b), a second base (19c), a rotating shaft (19d), and a baffle (19e), wherein the first base and the second base are respectively installed on the fuselage and the wing to be connected, and the separation surface between the two parts is (18). By moving the elastic pressure plate so that it passes through the hole of the baffle, the baffle rotates around the rotating shaft, and the connection or disconnection of the two parts can be completed.

3. A small fixed-wing UAV carrying satellite communication equipment according to claim 1, characterized in that: the fuselage is provided with three large-capacity equipment compartments, including a front equipment compartment (7), an abdominal equipment compartment (8) and a parachute compartment (9), which are respectively located at the front, abdomen and rear of the fuselage, and the front equipment compartment, the abdominal equipment compartment and the parachute compartment are respectively provided with canopies; a horizontal boss (6a) is provided on the back of the fuselage for installing the satellite communication system antenna (6), and the horizontal boss is aligned with the shape of the satellite communication system antenna.

4. A small fixed-wing UAV equipped with satellite communication equipment according to claim 3, characterized in that: the satellite communication system antenna uses a phased array panel for radio transmission and reception, and the radiation pattern shape is changed by controlling the feed phase of the radiating element in the array antenna, and the beam scanning is aligned with the satellite by changing the direction of the maximum value of the antenna radiation pattern.

5. A small fixed-wing unmanned aerial vehicle equipped with satellite communication equipment as described in claim 3. Its features are as follows: a battery recess (10) is provided in the front equipment compartment, a battery installation guide groove (10a) is provided on the side of the battery recess, a rope handle (11a) is provided on the upper part of the outer shell of the battery pack (11), a side guide groove (11b) is provided on the side, and a battery electrical connector is provided at the bottom of the battery pack; by taking out the battery pack (11) and placing the prepared fully charged battery pack into the battery recess (10) in the front section of the front equipment compartment, the battery replacement and electrical connector connection can be completed. The forward equipment bay is also used to install the airborne satellite communication host, which is located at the rear of the forward equipment bay, behind the battery pack. The interior of the parachute compartment (9) is used to install parachute packs.

6. A small fixed-wing unmanned aerial vehicle equipped with satellite communication equipment as described in claim 5. Its characteristic is that the satellite communication airborne host includes an encoding / decoding unit, a buffer unit, and a transmission unit; The encoding and decoding unit encodes the parameters output by the UAV flight control system into a format suitable for satellite communication transmission, and decodes the received information and inputs it into the flight control system to ensure accurate data transmission. The buffer unit uses an advanced compression algorithm to temporarily store data to be transmitted, reducing data size, managing data priority and transmission order, and reducing satellite communication transmission latency. The transmitting unit transmits data to the satellite communication system antenna and then transmits it via the satellite link, optimizing the transmission power and path, and improving the stability of the communication link.

7. A small fixed-wing UAV carrying satellite communication equipment according to claim 1, characterized in that: it further includes a pneumatic catapult, the pneumatic catapult includes a catapult slide rail (13), a front support (14), a rear support (15) and a trolley (16), the catapult slide rail (13) can be divided into three sections: front, middle and rear, and the longest length after disassembly is no more than 1.5m, the front, middle and rear sections of the slide rail are connected by a quick-release structure; the front support (14) and the rear support (15) are foldable.

8. The small fixed-wing UAV equipped with satellite communication equipment according to claim 7, wherein the catapult takeoff process is as follows: the UAV is installed on the trolley of the pneumatic catapult, the catapult is inflated and started, the trolley moves the UAV together with the front catapult rail, and when the UAV moves with the trolley to the end of the catapult rail, the trolley stops and releases the UAV, and the UAV completes the launch and continues to fly forward.

9. A small fixed-wing UAV equipped with satellite communication equipment according to claim 1, characterized in that: It also includes a ground receiving terminal and a UAV ground station. The ground receiving terminal receives the encoded data sent by the UAV via satellite and restores it into UAV flight parameters, which are then forwarded to the ground station. The UAV ground station receives the UAV flight parameters and displays real-time information, which ground personnel can use to issue relevant control commands.

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