High Speed Target Drone CH-240B
SKU: MD-P00120·UAV Platforms·Sur commande
Vue d'ensemble
2 Overall layout and key parameters The aerodynamic shape adopts the single-wing v-shaped tail, which relies on the aileron and elevator to control the drone by tilting. The fuselage is mainly made of composite and aluminum alloy materials, semi-rigid shell structure. The main parameters are: It adopts CH-240B small turbojet engine developed and produced by ourselves. It adopts digital flight control system and includes flight control computer, IMU, pressure-altitude sensor, airspeed sensor, course sensor, radio transponder, engine controller (ECU, TCU), GPS receiver, detonator actuator, control steering gear and other equipment. It can be preprogrammed to fly autonomously or manually. 5 take-off launching system It adopts ground (or vessels ) zero-length launcher rocket assisted takeoff, assisted rocket will accelerate the drone to 60m/s and then automatically fall off. Assistor s performance is sea level static thrust 3.6kn; Working hours: 1.20s 6 Ground station control system Ground station computer can display the information of drone flight track, course, direction, speed, altitude, distance, attitude, power supply voltage and the working state of the engine through electronic map in real time for the ground operator to control. The drone is equipped with a parachute recovery system, including recovery umbrella, opening device, aseismic airbag, etc., to ensure multiple recovery and use of the drone.
Spécifications techniques
Specifications. Caractéristiques principales : Flight altitude 50-8000m, Max horizontal velocity at sea level 240m/s, Endurance ＞90min, Max range ＞400km, Control radius 100km, Anti-wind ability Level 5, Maneuvering overload 3g, Take-off weight(included assistor) 85kg, Payload 5-10kg, RCS 0.01m², Operating temperature -50--+50 C, overall length 3.2m, FuseDia 0.26m, Wings pan 1.6m, wing area 0.53m², Takeoff thrust 90kg, Continuous thrust 80kg, Max air flow 1.8kg/s, pressure ratio 3.85, Exhaust temperature 780 C, dry weight 8.8kg, Fuel consumption 1.35kg/kg. h, Starting mode Automatic fuel start.
Spécifications techniques — 1 groups
Caractéristiques principales : Flight altitude 50-8000m, Max horizontal velocity at sea level 240m/s, Endurance ＞90min, Max range ＞400km, Control radius 100km, Anti-wind ability Level 5, Maneuvering overload 3g, Take-off weight(included assistor) 85kg, Payload 5-10kg, RCS 0.01m², Operating temperature -50--+50 C, overall length 3.2m, FuseDia 0.26m, Wings pan 1.6m, wing area 0.53m², Takeoff thrust 90kg, Continuous thrust 80kg, Max air flow 1.8kg/s, pressure ratio 3.85, Exhaust temperature 780 C, dry weight 8.8kg, Fuel consumption 1.35kg/kg. h, Starting mode Automatic fuel start.
Spécifications techniques
Specifications
- Flight altitude
- 50-8000m
- Max horizontal velocity at sea level
- 240m/s
- Endurance
- ＞90min
- Max range
- ＞400km
- Control radius
- 100km
- Anti-wind ability
- Level 5
- Maneuvering overload
- 3g
- Take-off weight(included assistor)
- 85kg
- Payload
- 5-10kg
- RCS
- 0.01m²
- Operating temperature
- -50--+50 C
- overall length
- 3.2m
- FuseDia
- 0.26m
- Wings pan
- 1.6m
- wing area
- 0.53m²
- Takeoff thrust
- 90kg
- Continuous thrust
- 80kg
- Max air flow
- 1.8kg/s
- pressure ratio
- 3.85
- Exhaust temperature
- 780 C
- dry weight
- 8.8kg
- Fuel consumption
- 1.35kg/kg. h
- Starting mode
- Automatic fuel start