Understand Your Drone Technically

ByMDG

Here is the necessary technical information about the drone and its supporting systems. I have extracted this information to make you understand all the technical aspects of Drone (UAS).

Basically, this is guidance by EASA for the collection and presentation of technical relevant information, and this information needs to be sufficient to address the required robustness levels of the mitigations and the Operational Safety Objectives (OSOs) of the SORA.

But as a technical drone user, you should know these key technical points.

Drone Technical Information

Drone (Unmanned Aircraft) Segment

Airframe

Airframe should include the following:

  • A detailed description of the physical characteristics of the drone (mass, centre-of-mass, dimensions, etc.), including photos, diagrams and schematics, if appropriate to support the description of the drone.
    • Dimensions: for fixed-wing drone, the wingspan, fuselage length, body diameter etc.; for a rotorcraft, the length, width and height, propeller diameter, etc.;
    • Mass: all the relevant masses such as the empty mass, MTOM, etc.; and
    • Centre of gravity: the centre of gravity and limits if necessary.
  • Materials: the main materials used and where they are used in the drone, highlighting in particular any new materials (new metal alloys or composites) or combinations of materials (composites ‘tailored’ to designs).
  • Load limits: the capability of the airframe structure to withstand expected flight load limits.
  • Sub-systems: any sub-systems such as a hydraulic system, environmental control system, parachute, brakes, etc.

Drone Performance Characteristics

Drone performance characteristics should include the following:

  • the performance of the drone within the proposed flight envelope, specifically addressing at least the following items:
    • Performance:
      • maximum altitude;
      • maximum endurance;
      • maximum range;
      • maximum rate of climb;
      • maximum rate of descent;
      • maximum bank angle; and
      • turn rate limits.
    • Airspeeds:
      • slowest speed attainable;
      • stall speed (if applicable);
      • nominal cruise speed;
      • max cruise speed; and
      • never-exceed airspeed.
  • Any performance limitations due to environmental and meteorological conditions, specifically addressing the following items:
    • wind speed limitations (headwind, crosswind, gusts);
    • turbulence restrictions;
    • rain, hail, snow, ash resistance or sensitivities;
    • the minimum visibility conditions, if applicable;
    • outside air temperature (OAT) limits; and
    • in-flight icing:
      • whether the proposed operating environment includes operations in icing conditions;
      • whether the system has an icing detection capability, and if so, what indications, if any, the system provides to the remote pilot, and/or how the system responds; and
      • any icing protection capability of the drone, including any test data that demonstrates the performance of the icing protection system.

Propulsion system

A description of the propulsion system and its ability to provide reliable and sufficient power to take off, climb, and maintain flight at the expected mission altitudes.

The propulsion system should include the following:

  • Fuel-powered propulsion systems
    • The type (manufacturer organisation and model) of engine that is used;
    • How many engines are installed;
    • The type and the capacity of fuel that is used;
    • How the engine performance is monitored;
    • The status indicators, alerts (such as warning, caution and advisory), messages that are provided to the remote pilot;
    • A description of the most critical propulsion-related failure modes/conditions and their impact on the operation of the system;
    • How the drone responds, and the safeguards that are in place to mitigate the risk of a loss of engine power for each of the following:
      • fuel starvation;
      • fuel contamination;
      • failed signal input from the remote pilot station (RPS); and
      • engine controller failure;
    • The in-flight restart capabilities of the engine, if applicable, and if so, a description of the manual and/or automatic features of this capability;
    • The fuel system and how it allows for adequate control of the fuel delivery to the engine, and provides for aircrew determination of the fuel remaining. This includes a system level diagram showing the location of the system in the drone and the fuel flow path; and
    • How the fuel system is designed in terms of safety (fire detection and extinguishing, reduction of risk in case of impact, leak prevention, etc.).
  • Electric-powered propulsion systems
    • A high-level description of the electrical distribution architecture, including items such as regulators, switches, buses, and converters, as necessary;
    • The type of motor that is used;
    • The number of motors that are installed;
    • The maximum continuous power output of the motor in watts;
    • The maximum peak power output of the motor in watts;
    • The current range of the motor in amps;
    • Whether the propulsion system has a separate electrical source, and if not, how the power is managed with respect to the other systems of the drone;
    • A description of the electrical system and how it distributes adequate power to meet the requirements of the receiving systems. This should include a system level diagram showing the electrical power distribution throughout the drone;
    • How power is generated on board the drone (for example, generators, alternators, batteries).
    • If a limited life power source such as batteries is used, the useful life of the power source during normal and emergency conditions, and how this was determined;
    • How information on the battery status and the remaining battery capacity is provided to the remote pilot or the watchdog system;
    • If available, a description of the source(s) of backup power for use in the event of a loss of the primary power source. This should include:
      • the systems that are powered during backup power operation;
      • a description of any automatic or manual load shedding; and
      • how much operational time the backup power source provides, including the assumptions used to make this determination;
    • How the performance of the propulsion system is monitored;
    • The status indicators and alert (such as warning, caution and advisory) messages that are provided to the remote pilot;
    • A description of the most critical propulsion-related failure modes/conditions and their impact on system operation;
    • How the drone responds, and the safeguards that are in place to mitigate the risk of a propulsion system loss for each of the following:
      • Low battery charge;
      • A failed signal input from the RPS; and
      • A motor controller failure;
    • If the motor has in-flight reset capabilities, a description of the manual and/or automatic features of this capability.

Flight control surfaces and actuators

This should include the following:

  • A description of the design and operation of the flight control surfaces and servos/actuators, including a diagram showing the location of the control surfaces and the servos/actuators;
  • A description of any potential failure modes and the corresponding mitigations;
  • How the system responds to a servo/actuator failure; and
  • How the remote-pilot or watchdog system is alerted of a servo/actuator malfunction.

Sensors

This section should describe the non-payload sensor equipment on board the drone and its role.

Payloads

This section should describe the payload equipment on board the drone, including all the payload configurations that significantly change the weight and balance, electrical loads, or flight dynamics.

Drone Control Segment

An overall system architecture diagram of the avionics architecture, including the location of all air data sensors, antennas, radios, and navigation equipment. A description of any redundant systems, if available.

This section should include the following:

Navigation

  • How the drone determines its location;
  • How the drone navigates to its intended destination;
  • How the remote pilot responds to instructions from:
    • air traffic control;
    • drone observers or VOs (if applicable); and
    • other crew members (if applicable);
  • The procedures to test the altimeter navigation system (position, altitude);
  • How the system identifies and responds to a loss of the primary means of navigation;
  • A description of any backup means of navigation; and
  • How the system responds to a loss of the secondary means of navigation, if available.

Autopilot

  • How the autopilot system was developed, and the industry or regulatory standards that were used in the development process.
  • If the autopilot is a commercial off-the-shelf (COTS) product, the type/design and the production organisation, with the criteria that were used in selecting the COTS autopilot.
  • The procedures used to install the autopilot and how its correct installation is verified, with references to any documents or procedures provided by the manufacturer’s organisation and/or developed by the drone operator’s organisation.
  • If the autopilot employs input limit parameters to keep the aircraft within defined limits (structural, performance, flight envelope, etc.), a list of those limits and a description of how these limits were defined and validated.
  • The type of testing and validation that was performed (software-in-the-loop (SITL) and hardware-in-the-loop (HITL) simulations).

Flight control system

  • How the control surfaces (if any) respond to commands from the flight control computer/autopilot.
  • A description of the flight modes (i.e. manual, artificial-stability, automatic, autonomous).
  • Flight control computer/autopilot:
    • If there are any auxiliary controls, how the flight control computer interfaces with the auxiliary controls, and how they are protected against unintended activation.
    • A description of the flight control computer interfaces required to determine the flight status and to issue appropriate commands.
    • The operating system on which the flight controls are based.

Remote pilot station (RPS)

  • A description or a diagram of the RPS configuration, including screen captures of the control station displays.
  • How accurately the remote pilot can determine the attitude, altitude (or height) and position of the drone.
  • The accuracy of the transmission of critical parameters to other airspace users/air traffic control (ATC).
  • The critical commands that are safeguarded from inadvertent activation and how that is achieved (for example, is there a two-step process to command ‘switch the engine off’). The kinds of inadvertent input that the remote pilot could enter to cause an undesirable outcome (for example, accidentally hitting the ‘kill engine’ control in flight).
  • Any other programmes that run concurrently on the ground control computer, and if there are any, the precautionary measures that are used to ensure that flight-critical processing will not be adversely affected.
  • The provisions that are made against an RPS display or interface lock-up.
  • The alerts (such as warning, caution and advisory) that the system provides to the remote pilot (e.g. low fuel or battery level, failure of critical systems, or operation out of control).
  • A description of the means to provide power to the RPS, and redundancies, if any.

Detect and avoid (DAA) system

  • Aircraft conflict avoidance
    • A description of the system/equipment that is installed for collaborative conflict avoidance (e.g. SSR, TCAS, ADS-B, FLARM, etc.).
    • If the equipment is qualified, details of the detailed qualification to the respective standard.
    • If the equipment is not qualified, the criteria that were used in selecting the system.
  • Non-collaborative conflict avoidance: A description of the equipment that is installed (e.g. vision-based, PSR data, LIDAR, etc.).
  • Obstacle conflict avoidance A description of the system/equipment that is installed, if any, for obstacle collision avoidance.
  • Avoidance of adverse weather conditions A description of the system/equipment that is installed, if any, for the avoidance of adverse weather conditions.
  • Standard
    • If the equipment is qualified, a list of the detailed qualification to the respective standard.
    • If the equipment is not qualified, the criteria that were used in selecting the system.
  • A description of any interface between the conflict avoidance system and the flight control computer.
  • A description of the principles that govern the installed DAA system
  • A description of the role of the remote pilot or any other remote crew in the DAA system.
  • A description of the known limitations of the DAA system.

Containment system

  • A description of the principles of the system/equipment used to perform containment functions for:
    • avoidance of specific area(s) or volume(s); or
    • confinement in a given area or volume.
  • The system information and, if applicable, supporting evidence that demonstrates the reliability of the containment system.

Ground support equipment (GSE) segment

  • A description of all the support equipment that is used on the ground, such as launch or recovery systems, generators, and power supplies.
  • A description of the standard equipment available, and the backup or emergency equipment.
  • A description of how the drone is transported on the ground.

Command and control (C2) link segment

  • The standard(s) with which the system is compliant.
  • A detailed diagram that shows the system architecture of the C2 link, including informational or data flows and the performance of the subsystem, and values for the data rates and latencies, if known.
  • A description of the control link(s) connecting the UA to the RPS and any other ground systems or infrastructures, if applicable, specifically addressing the following items:
    • The spectrum that will be used for the control link and how the use of this spectrum has been coordinated. If approval of the spectrum is not required, the regulation that was used to authorise the frequency.
    • The type of signal processing and/or link security (i.e. encryption) that is employed.
    • The data link margin in terms of the overall link bandwidth at the maximum anticipated distance from the RPS, and how it was determined.
    • If there is a radio signal strength and/or health indicator or similar display to the remote pilot, how the signal strength and health values were determined, and the threshold values that represent a critically degraded signal.
    • If the system employs redundant and/or independent control links, how different the design is, and the likely common failure modes.
    • For satellite links, an estimate of the latencies associated with using the satellite link for aircraft control and for air traffic control communications.
    • The design characteristics that prevent or mitigate the loss of the data link due to the following:
      • RF or other interference;
      • flight beyond the communications range;
      • antenna masking (during turns and/or at high attitude angles);
      • a loss of functionality of the RPS;
      • a loss of functionality of the UA; and
      • atmospheric attenuation, including precipitation.

C2 link degradation

A description of the system functions in case of a C2 link degradation:

  • Whether the C2 link degradation status is available and in what form (e.g. degraded, critical, automatic messages).
  • How the status of the C2 link degradation is announced to the remote pilot (e.g. visual, haptic, or sound).
  • A description of the associated contingency procedures.

C2 link loss

  • The conditions that could lead to a loss of the C2 link.
  • The measures in case of a loss of the C2 link.
  • A description of the clear and distinct aural and visual alerts to the remote pilot for any case of a lost link.
  • A description of the established lost link strategy presented in the drone operating manual, taking into account the emergency recovery capability.
  • A description of how the geo-awareness or geo-fencing system is used in this case, if available.
  • The lost link strategy, and, if incorporated, the re-acquisition process in order to try to re-establish the link in a reasonably short time.

Safety features

  • A description of the single failure modes and their recovery mode(s), if any.
  • A description of the emergency recovery capability to prevent risks to third-parties. This typically consists of:
    • a flight termination system (FTS), procedure or function that aims to immediately end the flight; or
    • an automatic recovery system (ARS) that is implemented through drone crew command or by the on board systems. This may include an automatic pre-programmed course of action to reach a predefined and unpopulated forced landing area; or
    • any combination of the above, or other methods.
  • The applicant should provide both a functional and physical diagram of the global UA system with a clear depiction of its constituent components, and, where applicable, an indication of its peculiar features (e.g. independent power supplies, redundancies, etc.)