AP 10.1

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

OVERVIEW

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.

FLEXIBILITY & SCALABILITY

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).

COMPATIBILITY

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

SPECIFICATIONS

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 SMA

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:

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	Cell
1.9	Angle of Sideslip Transmitter	AST	UV01.431329.05	180
1.10	Power distribution, switch unit	PSU	UV01.431329.07	Cell
1.11	Flight recorder	FR	UV01.431329.15-01	Cell
1.12	Emergency rescue system controller	ERSC	UV01.431329.06	Cell
1.13	Onboard antenna	OA	UV01.431329.100.315	Cell
2	Optional airborne equipment
2.1	Antivibration mounting for CPU (for UAVs MTOW more than 200 kg)	Cell	UV.431329.90.330-10.00	4600
2.2	Laser Altimeter (0-100 m altitude)	Cell	Cell	Cell
2.3	Radio Altimeter (0.3-400 m altitude)	Cell	Cell	Cell
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