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	Avata 2
UAS design & manufaturing organisations	DJI

UAS physical characteristics

Empty Mass
Maximum Take-Off Mass (MTOM)	Takeoff Weight: Approx. 377 g
Dimensions for Rotorcraft / Multirotor
Length of aircraft body	Dimensions: 185 x 212 x 64 mm (L x W x H)
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 Horizontal Speed (at sea level, no wind): 8 m/s (Normal mode) ‌16 m/s (Sport mode) 27 m/s (Manual mode)* * No faster than 19 m/s with the Manual mode in the EU regions.
Minimum airspeed to maintain safe flight
Normal/typical operating height	Max Takeoff Altitude: 5000 m Measured in a windless environment when taking off from an altitude of 5000 m and ascending vertically by 500 m, using Sport mode, and from 100% battery level until 20%. Data is for reference only. Always pay attention to reminders on the goggles' screens during your flight.
Maximum operating height
Maximum flight time during normal operation	Max Flight Time: ‌Approx. 23 mins ‌Measured when flying forward at a speed of 21.6 kph in a windless environment at sea level, with camera parameters set to 1080p/30fps, video mode off, and from 100% battery level until 0%. Data is for reference only. Always pay attention to reminders on the goggles' screens during your flight.
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)	Max Flight Distance: 13.0 km‌ ‌Measured when flying forward at a speed of 43.2 kph in a windless environment at sea level, with camera parameters set to 1080p/30fps, video mode off, and from 100% battery level until 0%. Data is for reference only. Always pay attention to reminders on the goggles' screens during your flight.
Glide distances
Maximum radio range of the C2 Link

CAP722A Table 8

UAS environmental limitations

Wind speed limits	Max Wind Speed Resistance: 10.7 m/s (Level 5)
Turbulence restrictions
Precipitation limits
OAT limits	Operating Temperature: -10 Deg. to 40 Deg. C (14 Deg. to 104 Deg. F)
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]: 2150 mAh Battery Type: Li-ion
Quantity
Arrangement
Generator:
Generator type, model and manufacturer
Specification
Electrical loads	Energy: 31.7 Wh@0.5C
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 Time: With Charging Hub (60W max charging power): From 0 to 100%: approx. 45 min‌ From 10 to 90%: approx. 30 min‌‌ Directly Charging the Drone (30 W max charging power):‌ From 0 to 100%: approx. 88 min‌ From 10 to 90%: approx. 60 min‌‌‌‌ Charging Temperature: 5 Deg. to 40 Deg. C (41 Deg. to 104 Deg. F)

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	Global Navigation Satellite System: GPS + Galileo + BeiDou
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	Sensing Type: Downward and backward visual positioning Backward: Measurement Range: 0.5-20 m FOV: Horizontal 78 Deg., Vertical 78 Deg. Downward: ToF Effective Measurement Height: 10 m Precise Hovering Range: 0.3-10 m Measurement Range: 0.3-20 m FOV: Horizontal 78 Deg., Vertical 78 Deg.
Devices used
Technology used
Interface between the DAA system and the flight control computer
Limitations of the DAA system	Operating Environment: Diffuse reflective surfaces with discernible patterns, diffuse reflectivity > 20% (such as concrete pavement) Adequate lighting (lux > 15, normal indoor lighting conditions)
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.
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

CAP722A Table 17

Command an Control (C2) link

RLOS
BRLOS
Antennas:
Type, model and manufacturer
Locations on the UAS
Transceivers / Modems:
Power levels	Transmitter Power (EIRP): 2.4 GHz: <20 dBm (FCC／CE／SRRC／MIC) 5.8 GHz: <20 dBm (FCC／SRRC) < 14 dBm (CE) Transmitter Power (EIRP): <10 dBm
Transmission schemes	Protocol: 802.11a/b/g/n/ac
Operating frequencies
Details of frequency spectrum approvals	Operating Frequency[1]: 2.400-2.4835 GHz 5.725-5.850 GHz Operating Frequency: 2.400-2.4835 GHz
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	Image Sensor: ‌1/1.3-inch image sensor Effective Pixels: 12 MP
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 Avata 2

Aircraft
Takeoff Weight	Approx. 377 g
Dimensions	185 x 212 x 64 mm (L x W x H)
Max Ascent Speed	‌6 m/s (Normal mode) 9 m/s (Sport mode)
Max Descent Speed	‌6 m/s (Normal mode) 9 m/s (Sport mode)
Max Horizontal Speed (at sea level, no wind)	8 m/s (Normal mode) ‌16 m/s (Sport mode) 27 m/s (Manual mode)* * No faster than 19 m/s with the Manual mode in the EU regions.
Max Takeoff Altitude	5000 m Measured in a windless environment when taking off from an altitude of 5000 m and ascending vertically by 500 m, using Sport mode, and from 100% battery level until 20%. Data is for reference only. Always pay attention to reminders on the goggles' screens during your flight.
Max Flight Time	‌Approx. 23 mins ‌Measured when flying forward at a speed of 21.6 kph in a windless environment at sea level, with camera parameters set to 1080p/30fps, video mode off, and from 100% battery level until 0%. Data is for reference only. Always pay attention to reminders on the goggles' screens during your flight.
Max Hovering Time	‌Approx. 21 mins ‌‌Measured when hovering in a windless environment at sea level, with camera parameters set to 1080p/30fps, video mode off, and from 100% battery level until 0%. Data is for reference only. Always pay attention to reminders on the goggles' screens during your flight.‌
Max Flight Distance	13.0 km‌ ‌Measured when flying forward at a speed of 43.2 kph in a windless environment at sea level, with camera parameters set to 1080p/30fps, video mode off, and from 100% battery level until 0%. Data is for reference only. Always pay attention to reminders on the goggles' screens during your flight.
Max Wind Speed Resistance	10.7 m/s (Level 5)
Operating Temperature	-10 Deg. to 40 Deg. C (14 Deg. to 104 Deg. F)
Global Navigation Satellite System	GPS + Galileo + BeiDou
Hovering Accuracy Range	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)
Internal Storage	46 GB
Camera
Image Sensor	‌1/1.3-inch image sensor Effective Pixels: 12 MP
Lens	‌FOV: 155 Deg. Format Equivalent: 12 mm Aperture: f/2.8 Focus: 0.6 m to ∞
ISO Range	100-25600 (Auto) 100-25600 (Manual)
Shutter Speed	Video: 1/8000-1/30 s Photo: 1/8000-1/50 s
Max Image Size	4000 x 2256 (16∶9) 4000 x 3000 (4∶3)
Still Photography Mode	Single shot
Photo Format	JPEG
Video Resolution	4K (4∶3): 3840 x 2880@30/50/60fps 4K (16∶9): 3840 x 2160@30/50/60fps 2.7K (4∶3): 2688 x 2016@30/50/60fps 2.7K (16∶9): 2688 x 1512@30/50/120fps 1080p (4∶3): 1440 x 1080@30/50/120fps 1080p (16∶9): 1920 x 1080@30/50/120fps
Video Format	MP4 (H.264/H.265)
Max Video Bitrate	130 Mbps
Supported File System	exFAT
Color Mode	Standard D-Log M
Camera FOV	Supports normal mode, wide-angle mode, and ultra-wide-angle mode.
EIS	Supports RockSteady 3.0+ and HorizonSteady Can be disabled* * When stabilization is turned off, footage captured with the wide-angle view supports offline stabilization Gyroflow.
Gimbal
Stabilization	Single-axis mechanical gimbal (tilt)
Mechanical Range	Tilt: -95 Deg. to 90 Deg.
Controllable Range	Tilt: -85 Deg. to 80 Deg.
Max Control Speed (tilt)	100 Deg./s
Angular Vibration Range	±0.01 Deg.
Electronic Roll Axis	Real-time screen correction is unavailable during recording, but can be applied to the footage recorded on the drone.
Sensing
Sensing Type	Downward and backward visual positioning
Downward	ToF Effective Measurement Height: 10 m Precise Hovering Range: 0.3-10 m Measurement Range: 0.3-20 m FOV: Horizontal 78 Deg., Vertical 78 Deg.
Backward	Measurement Range: 0.5-20 m FOV: Horizontal 78 Deg., Vertical 78 Deg.
Operating Environment	Diffuse reflective surfaces with discernible patterns, diffuse reflectivity > 20% (such as concrete pavement) Adequate lighting (lux > 15, normal indoor lighting conditions)
Video Transmission
Video Transmission System	O4
Live View Quality	1080p@30/50/60/100fps
Operating Frequency	2.400-2.4835 GHz 5.170-5.250 GHz* 5.725-5.850 GHz* * 5.170-5.250 GHz and 5.725-5.850 GHz can be used only in countries and regions where permitted by local laws and regulations.
Transmitter Power (EIRP)	2.4 GHz: ＜33 dBm (FCC) ＜20 dBm (CE/SRRC/MIC) 5.1 GHz: < 23 dBm (CE) 5.8 GHz: ＜33 dBm (FCC) ＜30 dBm (SRRC) < 14 dBm (CE)
Communication Bandwidth	Max 60 MHz
Max Transmission Distance (free of interference)	Low Interference and Obstructed by Buildings: approx. 0-0.5 km Low Interference and Obstructed by Trees: approx. 0.5-3 km Data tested under FCC standard in environments with typical low interference. Used for reference purposes only and provides no guarantee for actual transmission distance.
Max Download Speed	Wi-Fi: 30 MB/s* * Measured in a laboratory environment with little interference in countries/regions that support both 2.4 GHz and 5.8 GHz. Download speeds may vary depending on the actual conditions.
Lowest Latency	With DJI Goggles 3: 1080p/100fps Video Transmission Quality: 24 ms 1080p/60fps Video Transmission Quality: 40 ms‌
Max Video Bitrate	60Mbps
Antennas	4 antennas, 2T4R
Wi-Fi
Protocol	802.11a/b/g/n/ac
Operating Frequency[1]	2.400-2.4835 GHz 5.725-5.850 GHz
Transmitter Power (EIRP)	2.4 GHz: <20 dBm (FCC／CE／SRRC／MIC) 5.8 GHz: <20 dBm (FCC／SRRC) < 14 dBm (CE)
Bluetooth
Protocol	Bluetooth 5.0
Operating Frequency	2.400-2.4835 GHz
Transmitter Power (EIRP)	<10 dBm
Intelligent Flight Battery
Capacity[1]	2150 mAh
Weight	Approx. 145 g
Standard Voltage	14.76 V
Max Charging Voltage	17 V
Battery Type	Li-ion
Energy	31.7 Wh@0.5C
Charging Temperature	5 Deg. to 40 Deg. C (41 Deg. to 104 Deg. F)
Charging Time	With Charging Hub (60W max charging power): From 0 to 100%: approx. 45 min‌ From 10 to 90%: approx. 30 min‌‌ Directly Charging the Drone (30 W max charging power):‌ From 0 to 100%: approx. 88 min‌ From 10 to 90%: approx. 60 min‌‌‌‌
Charger
Recommended Charger	DJI 65W Portable Charger DJI 65W Car Charger USB Power Delivery charger
Battery Charging Hub
Input	5-20 V, max 3 A
Output	5 V, 2 A
Charging Type	Three batteries charged in sequence.
Compatibility	DJI Avata 2 Intelligent Flight Battery
Storage
Recommended microSD Cards	SanDisk Extreme PRO 32GB U3 A1 V30 microSDHC Lexar Professional 1066x 64GB U3 A2 V30 microSDXC Lexar Professional 1066x 128GB U3 A2 V30 microSDXC Lexar Professional 1066x 256GB U3 A2 V30 microSDXC Lexar Professional 1066x 512GB U3 A2 V30 microSDXC Kingston CANVAS Go! Plus 64GB U3 A2 V30 microSDXC Kingston CANVAS Go! Plus 128GB U3 A2 V30 microSDXC Kingston CANVAS React Plus 64GB U3 A1 V90 microSDXC Kingston CANVAS React Plus 128GB U3 A1 V90 microSDXC Kingston CANVAS React Plus 256GB U3 A1 V90 microSDXC Samsung EVO Plus 512GB U3 A2 V30 microSDXC
DJI FPV Remote Controller 3
Max Operating Time	Approx. 10 hours
Operating Temperature	-10 Deg. to 40 Deg. C (14 Deg. to 104 Deg. F)
Charging Temperature	0 Deg. to 50 Deg. C (32 Deg. to 122 Deg. F)
Charging Time	2 hours
Charging Type	5 V, 2 A
Battery Capacity	2600 mAh
Weight	Approx. 240 g
Dimensions	165 x 119 x 62 mm (L x W x H)
Operating Frequency	2.400-2.4835 GHz
Transmitter Power (EIRP)	2.400 GHz: ＜26 dBm (FCC) ＜20 dBm (CE/SRRC/MIC)
Others
Guaranteed software updates until	2026/12/31

Data source: https://www.dji.com/avata-2/specs

Generated using dronespec.info
Source data acquired 2024-04-26 11:03:42

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.

Amendment record

Aircraft and systems description

UAS physical characteristics

UAS performance characteristics

UAS environmental limitations

Construction

Electrical power system

Propulsion system

Fuel system

Flight Controls system

Navigation

Detect and Avoid (DAA) systems

Other avionics systems

Command Unit (CU)

Command an Control (C2) link

Communications

Take-off and landing mechanisms

Emergency recovery and safety systems

External lighting

Payload

Ground support equipment

Maintenance

Spare parts procurement

Change Management and modifications to the system

Safety features of the UAS

ANNEX - Manufacturer supplied data forDJI Avata 2

Aircraft

Camera

Gimbal

Sensing

Video Transmission

Wi-Fi

Bluetooth

Intelligent Flight Battery

Charger

Battery Charging Hub

Storage

DJI FPV Remote Controller 3

Others