Air Data Computers
Our Air Data Computers (ADC) are available in a number of configurations for a variety of applications, including UAV applications. Since its market introduction our family of ADCs has proven to provide outstanding performance, high accuracy and very long term stability.
Introduced in 2001, Air Data’s line of ADCs has been selected for a number of important programs. For example, Air Data’s ADCs are an integral part of one of the world’s largest production UAV program and have been selected for an important European UAV program. Other customers for the ADC include helicopter manufacturers, systems integrators and modification centers.
Air Data’s line of ADCs are designed to measure and compute navigation parameters in transport aircraft, high speed military trainers, helicopters and unmanned vehicles (UAV). Parameters such as pressure altitude, baro-corrected altitude, altitude rate of change, computed and true airspeeds, Mach number and static air temperature are computed. A comprehensive built-in test (BIT) function that provides high-reliability fault detection and isolation capability is also one of their features. The unit packaging is extremely robust and provides standard pitot and static tubing interface.
- Easily tailored to any flight application.
- Very high accuracy, +/- 5 feet typical at sea level.
- Long term stability.
- Interface to most OAT or TAT probes.
- Powerful CPU with expansion capability.
- Severe indirect lightning protection and 150 V/m HIRF.
- Optional discrete I/O’s.
- Many models already TSO certified.
Introduced in 2006, Air Data Pitot probes have been selected for a number of important programs. Air Data’s Pitot Static Probes are heated, measure dynamic and static pressures and can be tailored to various application requirements. This small Pitot Static Probe (PSP) is heated and measures dynamic and static pressures.
It is lightweight and compact and can be tailored to various commercial application requirements. In addition, this rugged Pitot Static Probe (PSP) has a built in temperature regulator that reduces aircraft power requirement.
- Easily adaptable to various types of UAV and FAR Part 23 aircraft
- Lightweight and compact (0.630 inch diameter)
- Low power consumption (150W max)
- Integrated boom holder
- Input Voltage
- Built in Overvoltage Protection
- Anti-Icing and De-Icing Capability
- Internal Control module regulating deicing power requirements
- Probe cover protection
- No scheduled maintenance required
Air Data has developed the skills, tools and know-how to work as a highly valued partner with OEM manufacturers, from the preliminary study to the manufacturing phase of tailor-made avionics systems. Air Data also has a laboratory for environmental testing and qualification of its products.
Air Data’s innovations find their application in various systems aboard aircraft and helicopters:
- Fuel Gauging and Management
- Data Communications
- Sensors and Detectors
- Cockpit Display Instruments
- Flight Control Equipment
- Electromagnetic Actuators
- Microwave Landing Systems
Air Data has developed several lines of ground equipment for its aeronautical clientele that includes the MLS (Microwave Landing System) series. The most recent developments address the needs of maintenance facilities for airlines and airport authorities seeking versatile test equipment allowing them to decrease the time and cost of maintaining critical parts for their fleet of aircraft and airport infrastructure.
BEP Description (+28VDC Bus Equipment Protection)
- The BEP protects avionic equipment from severe transient that may occur on the aircraft electrical bus.
- The unit is installed between the aircraft +28 VDC bus (input) and the avionic equipment to be protected at its input (output).
- The BEP automatically clamps the threat voltages transients to 60 V maximum while diverting the return current, up to of 1000 A peak under 10/1000 us waveform.
- The BEP has a single MIL-38999 series connector with four 16-AWG pins.
- The connector is nickel plated for corrosion resistance.
- Pin A (input) connects to the +28 VDC aircraft bus.
- Pin B connects to the aircraft chassis ground.
- Pin C connects to the +28 VDC input of avionic equipment.
Note 10:1000 Means 10us for a waveform to reach the peak value, and 1000us means the diminution of 50% from the peak in 1000us
The GLS CP is a component of a stand-alone GPS Landing System using Space Based Augmentation System (SBAS) or Ground Based Augmentation System (GBAS) in order to provide precision approach ILS look-alike guidance along the Final Approach Segment (FAS).
The Cabin Sensor Unit is a proprietary component embedded in the Liebherr Humispace unit; this product purpose is to increase humidity in the aircraft cabin.
The Duct Sensor Unit is a proprietary component embedded in the Liebheer Humispace unit; this product purpose is to increase humidity factor in the aircraft cabin.
Air Data has developed and qualified a communication module named the CIU (Communication Interface Unit).
The CIU is used as an interface module to be installed between two avionics equipment operating using different communication protocols and speeds. The unit performs data conversion between ARINC-429 and ARINC-561 busses and vice versa. All the channels are processed in real-time simultaneously.
The CIU is based on FPGAs (Field Programmable Gate Array) that can be easily reprogrammed for new applications. A weatherproof aluminum casing contains the whole circuitry.
The first released CIU version allows BAE Systems Canada to install its popular CMA-900 Flight Management System on Boeing 747-300 aircraft equipped with 6-wire ARINC-561 navigation equipment.
The CIU firmware has been designed according to RTCA/DO-178B, level C and to the new RTCA/DO-254 standard. The unit meets the environmental qualification requirements of RTCA/DO-160D.
- 4 ARINC 429 input busses
- 7 ARINC 429 output busse
- 3 ARINC 561 input busses
- 4 ARINC 561 output busses
- 7 configuration pins
- MTBF 50 000 hrs at 35° C
- Accepts 200 ms power interruption
An OAT Sensor (temperature sensor) is selected to measure air temperature. The OAT probe is corrected as a function of the computed Mach number and the corresponding recovery factor of the probe.
The Printer Converter is a network appliance whose function is to accept print jobs from a parallel port and to transport them to a network printer. It is particularly useful with computer that cannot be modified to work on Ethernet networks.
Air Data designs and manufactures a Pedal Restrictor Control Unit for commercial helicopters. The Pedal Restrictor Control Unit is a solid state air data sensing Electronic Control Unit that provides an output to the solenoid that mechanically restricts the pedal movement when the indicated airspeed reaches a predetermined airspeed.
Air Data’s Fuel Transfer Control Unit is an Electronic Control Unit that controls the fuel transfer between the various fuel tanks in the helicopter to keep the Center of Gravity within allowable limits. Used in conjonction with an Integrated Instrument Display Systems (IIDS), the FTCU provides fuel transfer monitoring and caution indication to the flight crew in case of system failure. The FTCU is used on the Bell Helicopter 427 aircraft.
The RPM Sensor is an electronic tachometer used on helicopters. It monitors an electrical signal which varies directly with the rotational speed of the main rotor.
Contrary to former analog technologies, the electrical signal is digitally analyzed by software. The characteristics measured are compared to predetermined levels to generate alarm signals for the pilot, if necessary.
The RPM Sensor was designed in compliance with software standard RTCA/DO-178B, level B, and environment standard RTCA/DO-160C. The unit is a standard installation on the Bell-407.
Using the latest technologies in microcontrollers, the RPM Sensor is a light, compact unit whose design ensures excellent protection against electromagnetic interferences and reliable operation in extreme-temperature conditions.
- Airtight aluminum casing
- Compact (2″ X 2 1/2″ X 1 1/2″)
- Light (260 g)
- Wide power range (18 – 50 VDC)
- Clear transitions with hysteresis
- Digital reference clock stable at 100 ppm