AP 10.1

Automatic Control System for UAV with a takeoff weight of 100 kg up to 4000 kg


The Automatic Control System (AP) provides the hardware and vehicle control abstraction layer for the host platform enabling fully autonomous operation. All flight systems including take-off, landing, navigation and mission execution can be instigated with a single keystroke. All diagnostics, flight mission planning and remote control can be achieved wirelessly.

A notable feature of the AP is its distributed architecture. Each component of the system has a dedicated microcontroller providing data and communication with other components within the CAN bus. This decentralized configuration helps to manage central processor loading by distributing routine management tasks across all system components. Additionally, there are no restrictions on the number of same-type modules connected to one system, enabling multiple redundancy on all levels. With nearly all payloads or ready-made third-party modules, entire systems can be connected to the AP.


Thanks to the AP’s distributed architecture, the system can be used in a wide variety of vehicles ranging from small quadcopter to full size converted piloted aircraft. The redundant layering provides basic functionality while ground control software is multi-platform and functions across multiple workstations in a both a wide or local area network configuration. Specific payloads/sensors can be integrated by scripting custom protocols through onboard Virtual Machines (VMs).


The AP is compatible with almost any vehicle configuration (VTOLs, USVs, UGVs, etc.), including non-traditional aircraft concepts. The flight control algorithm relies on Total Energy Control System (TECS) for improved reliability and response to malfunction including automatic landing with engine failure, auto-rotation for helicopters and parachute deployment. The AP is resilient against jamming and features precise dead-reckoning navigation in absence of a GNSS signal.

Payload of almost any type can be connected and controlled using the interfaces:
  • 1-Wire
  • RS-232
  • RS-485
  • UART
  • CAN

Key features

  • control of actuating mechanisms
  • engine control
  • semi-automatic control with automatic stabilization of the vehicles
  • manual control using the main 928MHz communication channel
  • from ground control station (GCU)
  • control of the vehicles object in emergency mode
  • payload control
  • payload feedback
  • control of rotating platforms in gyro-stabilization mode using AP10.1
  • receipt and transfer of telemetric data between GCU and the vehicles
  • simulation mode
  • flight simulator
  • onboard power control
  • power stabilization
  • conversion
  • power distribution, including emergency power supply mode
  • onboard power monitoring


Available Interfaces:

  • up to 15 x servo drives (PWM control)
  • 2x inputs for RPM sensor (Hall-effect sensors)
  • 1-Wire interface
  • TTL UART interface
  • RS-485 interface
  • Controller area network - CAN
  • RS-232 interface
  • Low-side power output (3.7A, @ 20V, 68MOhm)
  • 3x digital inputs (timing, level)
  • 5x general purpose inputs-outputs (remappable on MCU)

Technical specifications:

Operating temperature IP rating Housing material Connector
-40°C to +60°C IP67 Aluminium alloy Amphenol PT02E12-10P
Amphenol PT02E8-4P
Amphenol PT02E18-32P
Power supply Protection
7-27 V All digital logic inputs and outputs are protected ESD protection Power supply reverse-polarity protection


Application cases

Fixed Wing UAS

VTOL Drone

Unmanned Surface Vessel (USV)

AP 10.1 system configuration for airplanes example:

Autopilot Configuration

AP10.1 Kit

# Item Designation Part number Weight, g
 1 AP 10.1 Kit
 1.1 Onboard Telemetry Unit  OTU  UV01.431329.100.310  170
 1.2 Interfaces Controller  IFC  UV01.431329.100.332  100
 1.3 Onboard Antenna  OA  UV01.431329.100.315  300
 1.4 GPS Receiver  GPS  UV01.431329.100.346  67
 1.5 Central Processing Unit
 CPU  UV01.431329.102.330.00  160
 1.6 Pitot Tube  PT  UV01.468339.80.341  62
 1.7 Data Processing Unit of Pitot Tube  DPU-PT  UV01.431329.100.320  230
 1.8 CAN-HUB  CAN-HUB  UV01.468353.01  
 1.9 Angle of Sideslip Transmitter  AST  UV01.431329.05  180
 1.10 Power distribution, switch unit  PSU  UV01.431329.07  
 1.11 Flight recorder  FR  UV01.431329.15-01  
 1.12 Emergency rescue system controller  ERSC  UV01.431329.06  
 1.13 Onboard antenna  OA  UV01.431329.100.315  
 2 Optional airborne equipment   
Antivibration mounting for CPU (for UAVs MTOW more than 200 kg)
   UV.431329.90.330-10.00  4600
 2.2 Laser Altimeter (0-100 m altitude)      
 2.3 Radio Altimeter (0.3-400 m altitude)      
 All housings are hermetic.
 3 Ground control unit   
 3.1 GCU  ground telemetry unit  GCU-GTU  UV01.431329.100.211  110
 3.2 GCU  antenna  GCU-A  UV01.431329.80.215  400
 3.3 Portable ground control station *  PGCS  UV01.468323.01  19500

* Exploitation of Uavos PGCS is optional. Required software (GCU) can be installed on any computer under Linux OS control

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