UAS OSC Volume 2

WARNING: This document was generated automatically and may contain errors and/or ommissions. You MUST review the data and satisfy yourself that it is complete and accurate. There is a link to the original source of the data below to help you do that.

Operator ID:

 

UAS Operating Safety Case
Volume 2 - UAS Description:

 

Document reference number:

 

Document version and date:

 

Amendment record

Amendment Number

Date

Amended by

Details of changes

 

 

 

 

CAP722A Table 6


Aircraft and systems description

UAS Model

Phantom 4 RTK

UAS design & manufaturing organisations

DJI

UAS physical characteristics

Empty Mass

Maximum Take-Off Mass (MTOM)

Takeoff Weight:
1391 g

Dimensions for Rotorcraft / Multirotor

Length of aircraft body

Diagonal Distance:
350 mm

Width of aircraft body

Height of aircraft body

Propeller Configuration

Propeller Dimensions

Sound power level

Any other relevant information

CAP722A Table 7

UAS performance characteristics

Maximum airspeed

Max Speed (near sea level, no wind):
31 mph (50 kph)(P-mode)
36 mph (58 kph)(A-mode)

Minimum airspeed to maintain safe flight

Normal/typical operating height

Maximum operating height

Max Service Ceiling Above Sea Level:
19685 ft (6000 m)

Maximum flight time during normal operation

Max Flight Time:
Approx. 30 minutes

Maximum flight time on an ISA day at cruising speed at normal/typical operating height.

Maximum flight range on an ISA day (normal and emergency conditions)

Glide distances

Maximum radio range of the C2 Link

Max Transmission Distance (unobstructed, free of interference):
FCC: 4.3 mi(7 km)；
SRRC / CE / MIC / KCC: 3.1 mi(5 km) (Unobstrcted, free of interference)

Max Transmission Distance:
FCC / NCC: 4.3 mi (7 km);
CE / MIC / KCC / SRRC: 3.1 mi (5 km)
  (Unobstructed, free of interference) 

CAP722A Table 8

UAS environmental limitations

Wind speed limits

Turbulence restrictions

Precipitation limits

OAT limits

Operating Temperature Range:
32 Deg. to 104 Deg. F (0 Deg. to 40 Deg.C)

In-flight icing condition limits

Any other relevant information

CAP722A Table 9

Construction

Type of material

Material characteristics or properties

Any other relevant information

CAP722A Table 10

Electrical power system

Batteries:

Battery type, model and manufacturer

Capacity[1]:
5870 mAh

Battery Type:
LiPo 4S

Quantity

Arrangement

Generator:

Generator type, model and manufacturer

Specification

Electrical loads

Voltage:
15.2 V

Energy:
89.2 Wh

Electrical load shedding functionality

Power supply redundancy

Procedures to charge and discharge batteries.

Safety provisions with regards to hazards inherent to high-voltage storage devices:

Procedures in place for safe handling by any person who may come into contact with high-voltage storage devices

Means of identifying high-voltage storage

Safety provisions for any person discovering the UA following an accident.

Procedures and safety provisions to mitigate the risk of battery thermal runaway.

Procedures for monitoring high-voltage storage devices.

HMI:

Information indicated to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

Charging Temperature Range:
14 Deg. to 104℉(-10 Deg. to 40 Deg.C)

Net Weight:
468 g

CAP722A Table 11

Propulsion system

Propulsion type

Engines:

Type, model and manufacturer

Propeller type, model and manufacturer

Quantity

Arrangement

Power output

Propeller guards

In-flight restart functionality

Performance monitoring

Health monitoring

Safety features and redundancy in the system that allow maintaining flight after a failure or degradation has occurred in the propulsion system.

Fuel-powered propulsion system – Safety features to mitigate the risk of engine loss when the following hazards occur:

Fuel starvation

Fuel contamination

Failed signal input from the control station

Engine controller failure

Indication to the remote pilot

Electric-powered propulsion system:

Power source and supply management with regards to other systems in the UA

Redundant power sources

Maximum continuous power output of the motor

Maximum peak power output of the motor

Electrical distribution architecture

Electrical load shedding functionality

HMI:

Information indicated to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 12

Fuel system

Fuel type

Safety provisions with regards to hazardous substances within the fuel system:

List of hazardous substances and their characteristics.

Procedures in place for safe handling of the UA by any person who may come into contact with the hazardous substances.

Means of identifying the hazardous substances.

Safety provisions for any person discovering the UA following an accident.

HMI:

Information indicated to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 13

Flight Controls system

Design and operation of flight control units, surfaces, actuators, control linkages, etc.

Flight controller:

Type, model and manufacturer

Functions

Flight modes available

Automatic functions:

Take-off and landing

Stabilisation

Autopilot

Return to home

If functions are provided by COTS equipment, provide type, model and manufacturer.

Safety features and redundancy in the system which allow maintaining flight after a failure or degradation of the flight control system, including indication to the remote pilot.

HMI:

Information indicated to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 14

Navigation

Sensors

Type, model and manufacturer

Multi-Frequency Multi-System High-Precision RTK GNSS:
Frequency Used:
GPS: L1/L2；
GLONASS: L1/L2；
BeiDou: B1/B2；
Galileo: E1/E5a

First-Fixed Time: < 50 s

Positioning Accuracy: Vertical 1.5 cm + 1 ppm（RMS) ；
Horizontal 1 cm + 1 ppm（RMS)
1 ppm means the error has a 1mm increase for every 1 km of movement from the aircraft.

Single-Frequency, High-Sensitivity GNSS Module:
GPS+BeiDou+Galileo（Asia)；
GPS+GLONASS+Galileo（other regions)

Quantity

Telemetry links

Method to determine current position.

Method to navigate to intended destination.

Automatic/automated navigation functions

Geo-awareness functions

Containment functions

Safety features and redundancy in the system which allow maintaining flight after a failure or degradation has occurred in the navigation system:

Backup means of navigation

Detection of and response to loss of primary means and secondary means of navigation.

Indication to the remote pilot

HMI:

Information indicated to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 15

Detect and Avoid (DAA) systems

DAA system functions

Devices used

Technology used

Interface between the DAA system and the flight control computer

Limitations of the DAA system

Velocity Range:
<=31 mph(50 kph) at 6.6 ft(2 m) above ground with adequate lighting

Altitude Range:
0-33 ft(0 - 10 m)

Operating Range:
0-33 ft(0 - 10 m)

FOV:
Forward/Rear: 60 Deg. (horizontal), ±27 Deg. (vertical)
Downward: 70 Deg. (front and rear), 50 Deg. (left and right)

Operating Environment:
Surfaces with clear patterns and adequate lighting(＞ 15 lux)

Obstacle Sensing Range:
2-98 ft(0.7-30 m)

Obstacle Sensing Range:
0.6-23 ft(0.2 - 7 m)

Evidence of equipment qualification and approval.

DAA event sequence:

Level of automation

Actions required by the remote pilot

Means to verify normal system operation.

HMI:

Information indicated to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 16

Other avionics systems

 

Command Unit (CU)

Power sources, supply management and redundancy.

Built-in Battery:
6000 mAh LiPo 2S 

Radio signal:

Determination of the signal strength and health value.

Threshold values which represent a critically degraded signal.

Control handover between two CUs

Safety features to mitigate the risk of inadvertent command activation:

List of critical commands

Mitigation means

Safety features to mitigate the risk of display or HMI lock-up.

Safety features to maintain flight-critical processing when multiple programs are running concurrently.

HMI:

Information indicated to the remote pilot.

Radio signal strength and/or health indication to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

Operating Temperature Range:
32 Deg. to 104 Deg. F （0 Deg. to 40 Deg.C)

Operating Temperature:
32 Deg. to 104 Deg. F (0 Deg. to 40 Deg. C)

CAP722A Table 17

Command an Control (C2) link

RLOS

BRLOS

Antennas:

Type, model and manufacturer

Locations on the UAS

Transceivers / Modems:

Power levels

Transmission Power (EIRP):
2.4 GHz
CE (Europe) / MIC (Japan) / KCC (Korea) : < 20 dBm

5.8 GHz
SRRC（China) / FCC（United States) /NCC(Taiwan,China): < 26 dBm

Transmission Power (EIRP):
2.4 GHz
CE / MIC / KCC: < 20 dBm

5.8 GHz
SRRC / FCC: < 26 dBm

EIRP:
2.4 GHz
CE / MIC / KCC: < 20 dBm

5.8 GHz
FCC / SRRC / NCC: < 26 dBm 

Transmission schemes

Operating frequencies

Details of frequency spectrum approvals

Operating Frequency:
2.400 GHz to 2.483 GHz (Europe, Japan, Korea)
5.725 GHz to 5.850 GHz (United States, China)

Operating Frequency:
2.400 GHz-2.483 GHz(Europe,Japan,Korea)
5.725 GHz-5.850 GHz(United States, China)

Operating Frequency:
2.400 GHz to 2.483 GHz (Europe, Japan, Korea)
5.725 GHz to 5.850 GHz (Other countries/regions) 

Maximum power output/range

Type of signal processing

Datalink margin in terms of the overall link bandwidth at the maximum anticipated distance from the CU.

Operational C2 link management:

Frequency switchovers

Contingency situations

Third party link service provider

Radio signal:

Determination of the signal strength and health value

Threshold values which represent a critically degraded signal.

Minimum and average assured data rates

Minimum and average assured latencies

Design features and procedures to maintain availability, continuity, and integrity of the datalink:

RF or other interference

Flight beyond communications range

Antenna masking

Loss of CU functionality

Loss of UA functionality

Atmospheric attenuation

Safety features to mitigate the risk of loss of C2 link:

C2 links redundancy

Automatic triggering of an emergency recovery function

Automatic return to home

Safety features to mitigate the risk of harmful interference.

HMI:

Information indicated to the remote pilot.

Radio signal strength and/or health indication to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 18

Communications

Antennas:

Type, model and manufacturer

Locations on the UAS

Communication method:

VHF

GSM network

Satellite

Safety features to mitigate the loss of communication function:

Primary communication means

Secondary / back-up communication means

HMI:

Information indicated to the remote pilot.

Radio signal strength and/or health indication to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 19

Take-off and landing mechanisms

Wheels, skids, rails, launchers, etc.

If various mechanisms can be fitted:

Primary mechanism

Secondary mechanisms

Operational conditions/requirements for each mechanism.

Any other relevant information

CAP722A Table 20

Emergency recovery and safety systems

Mode of operation

Safety features which mitigate the risk of loss of control or situational awareness.

Means to verify normal system operation.

HMI:

Information indicated to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 21

External lighting

Type, model and manufacturer

Locations on the UA

Colour

Operation

Operating modes

Purpose

HMI:

Information indicated to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 22

Payload

Types

Mass

Interfaces with the UA:

Mechanical interface

Electrical interface

Data interface

Release mechanism

Any other interface

Procedures to install the payload onto the UA.

Effects of the payload on the UA

Sensors

Sensor:
1" CMOS; Effective pixels: 20 M

Safety features to mitigate the risk of the payload affecting the flight of the UA:

Effects on aerodynamics

Effects of electro-magnetic interference.

Effects of electrical power and / or data connection failures on the UAS.

Effects of complete detachment of the payload from the UA (either caused by a failure or through intentional lowering / dropping of the payload).

Effects of partial detachment of the payload from the UA.

Distraction of the remote pilot generated by the payload during flight.

Procedures to verify the attachment points to the UA.

Procedures to verify the UA MTOM and CG location.

Procedures to detect and mitigate any failure of the payload in flight.

Safety provisions with regards to hazards inherent to the payload

Procedures in place for safe handling of the payload.

Means of identifying hazards.

HMI:

Information indicated to the remote pilot.

Alert messages indicated to the remote pilot.

Any other relevant information

CAP722A Table 23

Ground support equipment

UAS launch and recovery systems

Power sources

Transportation equipment

Backup or emergency equipment

Procedures to transport UA, CU, battery/fuel, and other equipment between operation sites and from the loading/off-loading area to the take-off/landing area.

Storage of ground support equipment.

Suitability of the ground support equipment and transportation method with regards to the UAS components’ fragility, sensitivity or inherent hazards.

Ground support equipment standards

Ground support equipment manufacturer's recommendations.

Any other relevant information

CAP722A Table 24

Maintenance

Maintenance manual:

Structure

Maintenance procedures:

Inspections

Overhaul

Repairs

Assurance of repair procedures

Batteries maintenance during storage periods

Origin of each procedure

Maintenance schedules

Procedures to record maintenance that has been carried out.

Storage of maintenance records

Staff qualification and levels of approval.

Procedures to use the manual by the Maintenance staff

Configuration control

Any other relevant information

CAP722A Table 25

Spare parts procurement

Sources of procurement

Process to confirm the suitability of the part.

Any other relevant information

CAP722A Table 26

Change Management and modifications to the system

Hardware, software, and firmware version control

Modification standards

Modification records storage

Safety assessment associated with the modification

Any other relevant information

CAP722A Table 27


Safety features of the UAS

Step 1 – Identify the main functions of the UAS.

 

Step 2 – Identify the sub-functions.

 

Step 3 – Consider the ways each function may fail.

 

Step 4 – Identify the failure conditions.

 

Step 5 – Select those failure conditions that may lead to mid-air collision or harm to uninvolved people on the ground. (Identified Hazard)

 

Step 6 – Assurance

 

Step 7 – Describe the consequence of the failure condition.

 

Step 8 – Describe the failure modes. (Unmitigated Failures)

 

Step 9 – Identify the single points of failure.

 

Step 10 – Describe the risk mitigation means.

 

CAP722A Table 28


ANNEX - Manufacturer supplied data forDJI Phantom 4 RTK

Aircraft

Takeoff Weight1391 g
Diagonal Distance350 mm
Max Service Ceiling Above Sea Level19685 ft (6000 m)
Max Ascent Speed6 m/s (automatic flight); 5 m/s (manual control)
Max Descent Speed3 m/s
Max Speed (near sea level, no wind)31 mph (50 kph)(P-mode)
36 mph (58 kph)(A-mode)
Max Flight TimeApprox. 30 minutes
Operating Temperature Range32 Deg. to 104 Deg. F (0 Deg. to 40 Deg.C)
Operating Frequency2.400 GHz to 2.483 GHz (Europe, Japan, Korea)
5.725 GHz to 5.850 GHz (United States, China)
Transmission Power (EIRP)2.4 GHz
CE (Europe) / MIC (Japan) / KCC (Korea) : < 20 dBm

5.8 GHz
SRRC（China) / FCC（United States) /NCC(Taiwan,China): < 26 dBm
Hover Accuracy RangeRTK enabled and functioning properly:
Vertical: ±0.1 m；Horizontal: ±0.1 m

RTK disabled
Vertical: ±0.1 m（with vision positioning ) ；
±0.5 m（with GNSS positioning)
Horizontal: ±0.3 m（with vision positioning) ;
±1.5 m（with GNSS positioning)
Image Position OffsetThe position of the camera center is relative to the phase center of the onboard D-RTK antenna under the aircraft body's axis:(36, 0, and 192 mm) already applied to the image coordinates in Exif data. The positive x, y, and z axes of the aircraft body point to the forward, rightward, and downward of the aircraft, respectively.

Mapping Functions

Mapping Accuracy **Mapping accuracy meets the requirements of the ASPRS Accuracy Standards for Digital Orthophotos Class Ⅲ
** The actual accuracy depends on surrounding lighting and patterns, aircraft altitude, mapping software used, and other factors when shooting.
Ground Sample Distance (GSD)(H/36.5) cm/pixel，
H means the aircraft altitude relative to shooting scene (unit: m)
Data Acquisition EfficiencyMax operating area of approx. 1 km² for a single flight(at an altitude of 182 m, i.e., GSD is approx. 5 cm/pixel, meeting the requirements of the ASPRS Accuracy Standards for Digital Orthophotos Class Ⅲ

Vision System

Velocity Range<=31 mph(50 kph) at 6.6 ft(2 m) above ground with adequate lighting
Altitude Range0-33 ft(0 - 10 m)
Operating Range0-33 ft(0 - 10 m)
Obstacle Sensing Range2-98 ft(0.7-30 m)
FOVForward/Rear: 60 Deg. (horizontal), ±27 Deg. (vertical)
Downward: 70 Deg. (front and rear), 50 Deg. (left and right)
Measuring FrequencyForward/Rear: 10 Hz;
Downward: 20 Hz
Operating EnvironmentSurfaces with clear patterns and adequate lighting(＞ 15 lux)

Camera

Sensor1" CMOS; Effective pixels: 20 M
LensFOV 84 Deg.；8.8 mm / 24 mm(35 mm format equivalent:24 mm)；
f/2.8 - f/11, auto focus at 1 m - ∞
ISO RangeVideo:100-3200(Auto)
100-6400(Manual)；

Photo:100-3200(Auto)
100-12800(Manual)
Mechanical Shutter Speed8 - 1/2000 s
Electronic Shutter Speed8 - 1/8000 s
Max Image Size4864 x 3648（4:3) ；
5472 x 3648（3:2)
Video Recording ModesH.264，4K: 3840 x 2160 30p
Photo FormatJPEG
Video FormatMOV
Supported File SystemsFAT32（<= 32 GB) ；
exFAT（> 32 GB)
Supported SD CardsMicroSD, Max Capacity: 128 GB. Class 10 or UHS-1 rating required Write speed≥15 MB/s
Operating Temperature Range32 Deg. to 104 Deg. F （0 Deg. to 40 Deg.C)

Intelligent Flight Battery

Capacity[1]5870 mAh
Voltage15.2 V
Battery TypeLiPo 4S
Energy89.2 Wh
Net Weight468 g
Charging Temperature Range14 Deg. to 104℉(-10 Deg. to 40 Deg.C)
Max Charging Power160 W

Intelligent Battery Charing Hub(WCH2)

Input Voltage17.3 - 26.2 V
Output Voltage and Current8.7 V，6 A；5 V，2 A
Operating Temperature41 Deg. to 104℉(5 Deg. to 40 Deg.C)

SDK Remote Controller

Operating Frequency2.400 GHz to 2.483 GHz (Europe, Japan, Korea)
5.725 GHz to 5.850 GHz (Other countries/regions) 
EIRP2.4 GHz
CE / MIC / KCC: < 20 dBm

5.8 GHz
FCC / SRRC / NCC: < 26 dBm 
Max Transmission DistanceFCC / NCC: 4.3 mi (7 km);
CE / MIC / KCC / SRRC: 3.1 mi (5 km)
  (Unobstructed, free of interference) 
Built-in Battery6000 mAh LiPo 2S 
Operating Current / Voltage1.2 A @ 7.4 V
Mobile Device HolderTablets and smartphones 
Operating Temperature32 Deg. to 104 Deg. F (0 Deg. to 40 Deg. C)

GNSS

Single-Frequency, High-Sensitivity GNSS ModuleGPS+BeiDou+Galileo（Asia)；
GPS+GLONASS+Galileo（other regions)
Multi-Frequency Multi-System High-Precision RTK GNSSFrequency Used:
GPS: L1/L2；
GLONASS: L1/L2；
BeiDou: B1/B2；
Galileo: E1/E5a

First-Fixed Time: < 50 s

Positioning Accuracy: Vertical 1.5 cm + 1 ppm（RMS) ；
Horizontal 1 cm + 1 ppm（RMS)
1 ppm means the error has a 1mm increase for every 1 km of movement from the aircraft.

Gimbal

Stabilization3-axis (tilt, roll, yaw)
Pitch-90 Deg. to +30 Deg.
Max Controllable Angular Speed90 Deg./s
Angular Vibration Range±0.02 Deg.

Infrared

Obstacle Sensing Range0.6-23 ft(0.2 - 7 m)
FOV70 Deg.(Horizontal)
±10 Deg.(Vertical)
Measuring Frequency10 Hz
Operating EnvironmentSurface with diffuse reflection material, and reflectivity＞ 8%（such as wall,trees, humans, etc.)

Remote Controller

Operating Frequency2.400 GHz-2.483 GHz(Europe,Japan,Korea)
5.725 GHz-5.850 GHz(United States, China)
Transmission Power (EIRP)2.4 GHz
CE / MIC / KCC: < 20 dBm

5.8 GHz
SRRC / FCC: < 26 dBm
Max Transmission Distance (unobstructed, free of interference)FCC: 4.3 mi(7 km)；
SRRC / CE / MIC / KCC: 3.1 mi(5 km) (Unobstrcted, free of interference)
Power Consumption16 W(typical value)
Display5.5 inch screen, 1920 x 1080, 1000 cd/m², Android System
Memory 4G RAM+16G ROM
Operating Temperature Range32 Deg. to 104 Deg. F （0 Deg. to 40 Deg.C)

Intelligent Flight Battery Charging Hub (PHANTOM 4 CHARGING HUB)

Voltage7.6 V
Operating Temperature Range41 Deg. to 104℉(5 Deg. to 40 Deg.C)
Capacity4920 mAh
Battery TypeLiPo 2S
Energy37.39 Wh
Operating Temperature-4 Deg. to 104℉(-20 Deg. to 40 Deg.C)

AC Power Adapter (PH4C160)

Voltage17.4 V
Rated Power160 W

Data source: https://www.dji.com/phantom-4-rtk/specs

Generated using dronespec.info
Source data acquired 2023-01-23 19:03:42