Fixed-wing Attack Drone with 2000km Range And Large Payload of 50kg Loitering Munition UAV—SPEED 2500

Fixed-wing Attack Drone with 2000km Range And  Large Payload of 50kg Loitering Munition UAV

Analysis of Technical Requirements, Performance Indicators, and Application Scenarios for Loitering Munitions (UAVs):

1.Low cost, compact size, and rapid deployment of UAVs.   

2.Capable of rapid payload modification and replacement;;

3.Typical operating point: H=1000m, V=180km/h;

4.Maximum payload: 50kg;

5.Endurance: 12 hours;

6.Takeoff method: Rocket-assisted takeoff;

Design Concept:

1)Adopting a delta wing layout to effectively improve the UAV's cruising speed and reduce its size;

2)Adopting a blended wing-body design to reduce overall drag, achieving a compact structure and easy portability;

3) Adopting an integrated wing-fuselage fuel tank design to effectively increase the UAV's fuel tank volume, reduce the fuselage cross-sectional area, thereby reducing flight drag and increasing endurance;

4) Adopting a tail-thrust propulsion arrangement to effectively improve propeller efficiency..

5）Overall Layout Scheme: Adopting a delta wing overall layout with a cylindrical fuselage for easy installation of the seeker head and warhead. The drone has a compact overall structure, making it easy to transport.

Table 1 Take off weight:

Power System:

Since catapult launch is used, there are no special requirements for takeoff run. Considering the typical power-to-weight ratio of 0.1~0.15 for propeller-driven UAVs, a typical value of 0.12 is chosen. The maximum engine power should not be less than 21.6 kW. Considering the UAV's high-altitude performance and acceleration, a 35 kW engine is selected.

Wing Loading Design:

Design Basis: To better utilize the high lift-to-drag ratio for cruise, the cruise lift coefficient is designed to be around 0.55, and the initial wing surface parameters are determined to be 2.5 square meters.

Table 2 Full machine size:

Overall System Composition 1) UAV Airframe:

1.Wing Structure Design: The wing adopts an integrated carbon tube three-spar design, combined with carbon fiber ribs and carbon fiber skin, forming an integrated wing structure through adhesive bonding. The skin also becomes one of the main load-bearing components, fully utilizing the high tensile strength of carbon fiber to form a high-strength, high-rigidity, high-aspect-ratio wing   

2.Fuselage Structure Scheme: The fuselage structure is formed by a carbon fiber integral frame beam plus carbon fiber skeleton plates and carbon fiber skin. It features lightweight, high strength, and minimal deformation.

3.TStructural strength analysis software is used to perform numerical analysis on the entire structure, obtaining its stress and strain distribution, and obtaining the deformation of the wingtips under specified loads. This is used as a reference for local reinforcement of the wing.

4.Integrated Aerodynamic Structure Optimization Design: For the wing, aerodynamic requirements dictate that the thinner the wing, the better, as this helps improve the lift-to-drag ratio.  However, structural designers require the wing to be as thick as possible, as a thicker wing makes it easier to meet stiffness and strength requirements while controlling weight.  Therefore, aerodynamic and structural design have opposite requirements for wing shape. To reconcile these conflicting disciplines, we developed an integrated aerodynamic-structural optimization design. This involves optimizing aerodynamic and structural parameters to achieve maximum flight time, while keeping the total weight constant and using flight time as the optimization objective.

2) Professional-Grade Flight Control System

1.The flight control system employs a self-developed high-precision GPS/SINS/AHRS navigation algorithm with a 400Hz update frequency.

2.The flight control system utilizes a self-developed multi-processor architecture, possessing powerful matrix computing capabilities and featuring high reliability and low power consumption.

3.The flight control system integrates high-precision, high-reliability professional-grade inertial sensors, exhibiting strong vibration resistance, good stability, and high attitude accuracy.

4.The flight control system integrates a high-precision differential satellite receiver, achieving centimeter-level positioning accuracy.

5.The flight control system has undergone temperature calibration within the range of -40ºC to +70ºC.

6.The flight control system supports multiple flight modes: remote control mode, stability augmentation mode, and autonomous mode, supporting one-button fully autonomous takeoff and landing..

7.The flight control system supports multiple protection measures: link anomaly protection, positioning anomaly protection, low voltage protection, attitude anomaly protection, altitude anomaly protection, electronic fence protection, and remote control loss protection. The flight control system supports data forwarding, providing critical flight control status data to third-party devices (such as pod devices) via the flight control payload interface to meet their application requirements.

8.The ground station software includes comprehensive takeoff check functions and a guided takeoff check process, helping users perform thorough checks before each flight to ensure error-free operation, significantly reducing the probability of human-caused accidents and ensuring safe flight.

Piston Engine:

1. Employs a 550cc piston engine;

2.The engine is a four-cylinder, horizontally opposed, air-cooled, two-stroke design;

3. The engine uses solid-state magneto ignition, ensuring stability and reliability;

4.The engine uses air-fuel mixture lubrication, facilitating maintenance and reducing costs;

5.Rated power is 37kW, meeting the design requirements of the UAV's power system;

6.The cylinder block is made of cast aluminum alloy with a nickel-silicon hardened plating on the inner wall, ensuring durability;

7.Fuel is 97# unleaded gasoline with a 1:50 ratio of two-stroke fully synthetic lubricating oil.

Data Link System

Model: P142A-B02P-02

Operating Frequency: 1.37-1.45 GHz (1.4 GHz band)

Channel Bandwidth: Uplink (Tx): 10 MHz Downlink (Rx): 10 MHz

Transmit Power: 30 dBm (1 W)

Modulation: OFDM (Orthogonal Frequency Division Multiplexing)

Constellation Mode: BPSK, QPSK, 16QAM

Forward Error Correction (FEC): LDPC (Low-Density Parity-Check Code), Code Rate 1/2, 2/3, 3/4, 5/6

Duplex Mode: TDD (Time Division Duplex)

Throughput: Downlink: 2-8 Mbps Uplink: 600 kbps

Serial Port Parameters:

Baud Rate: 9600/57600/115200 bps

Interface: 2×TTL (Transistor-to-Transistor Logic)

Network Interface: 1×Ethernet Port

S.BUS Interface: 2×S.BUS (Multi-control Protocol)

Power Parameters:

Connector: XT30U-M (Gold-plated High-Current Connector)

Power Consumption:Air Unit (Tx): 7 W

Ground Unit (Rx): 6 W

Operating Temperature: -40℃ to +65℃

Ground Station System

The UAV ground station intelligent monitoring system is the primary human-machine interface for UAV control.

1. It can display UAV flight data in real time and features professional functions such as automatic route planning, 3D electronic fence setting, multi-UAV control from a single station, and log playback.

2. Handheld design for easy portability.

3. It effectively integrates UAV payload data, achieving a new integrated control experience for both UAV flight and payload operation.

4. Durable all-aluminum alloy CNC shell with custom silicone rubber corner protectors for impact and shock absorption.

5. Uses imported Panasonic batteries and is equipped with a military-grade power management board, featuring accurate coulomb meter power display,supporting up to 4 hours of continuous flight.