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

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

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