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	Matrice 400
UAS design & manufaturing organisations	DJI

UAS physical characteristics

Empty Mass
Maximum Take-Off Mass (MTOM)	Takeoff Weight: Without Batteries: 5020±20 g With Batteries: 9740±40 g The actual product weight may vary due to differences in batch materials and external factors. Max Takeoff Weight: 15.8 kg
Dimensions for Rotorcraft / Multirotor
Length of aircraft body	Dimensions: Unfolded: 980 x 760 x 480 mm (L x W x H) (with landing gear) Folded: 490 x 490 x 480 mm (L x W x H) (with landing gear and gimbal) Maximum dimensions excluding propellers. Aircraft carrying case dimensions: 779 x 363 x 528 mm (L x W x H) Diagonal Wheelbase: 1070 mm
Width of aircraft body
Height of aircraft body
Propeller Configuration	Propeller Model: 2510F
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): 25 m/s
Minimum airspeed to maintain safe flight
Normal/typical operating height	Max Takeoff Altitude: 7000 m
Maximum operating height
Maximum flight time during normal operation	Max Flight Time: 59 minutes Measured with the aircraft flying forward at a constant speed of 10 m/s in a windless environment at sea level, carrying only the H30T (total weight 10,670 g), and from 100% battery level until 0%. Data is for reference only. Actual experience may vary depending on the environment, usage, and firmware version.
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: 49 km Measured by the aircraft flying forward at a constant speed of 17 m/s in a windless environment at sea level, without external payloads, and from 100% battery level until 0%. Actual experience may vary depending on the environment, usage, and firmware version.
Glide distances
Maximum radio range of the C2 Link

CAP722A Table 8

UAS environmental limitations

Wind speed limits	Max Wind Speed Resistance: 12 m/s Max wind speed resistance during takeoff and landing.
Turbulence restrictions
Precipitation limits	Ingress Protection Rating[3]: IP55 The rating is not permanently effective and may decrease due to product wear and tear.
OAT limits	Operating Temperature: -20 Deg. to 50 Deg. C (-4 Deg. to 122 Deg. F) (without solar radiation)
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: 20254 mAh Model: TB100
Quantity
Arrangement
Generator:
Generator type, model and manufacturer
Specification
Electrical loads	Energy: 977 Wh Standard Voltage: 48.23 V
Electrical load shedding functionality	Discharge rate: 4C
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: 5 Deg. to 45 Deg. C (41 Deg. to 113 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 + GLONASS* * GLONASS is supported only when the RTK module is enabled. Equipped with standard airborne ADS-B In receiver and dual antennas, supporting reception up to 20 km.
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: Omnidirectional binocular vision system (surround view provided by full-color fisheye vision sensors) Horizontal rotating LiDAR, upper LiDAR and downward 3D infrared range sensor Six-direction mmWave radar Forward: Measurement Range: 0.4-21 m Detection Range: 0.4-200 m Field of View (FOV): 90 Deg. (horizontal), 90 Deg. (vertical) Backward: Measurement Range: 0.4-21 m Detection Range: 0.4-200 m Field of View (FOV): 90 Deg. (horizontal), 90 Deg. (vertical) Lateral: Measurement Range: 0.6-21 m Detection Range: 0.5-200 m Field of View (FOV): 90 Deg. (horizontal), 90 Deg. (vertical) Downward: Measurement Range: 0.5-19 m The FOV to the front and rear is 160 Deg. and 105 Deg. to the right and left.
Devices used
Technology used
Interface between the DAA system and the flight control computer
Limitations of the DAA system	Operating Environment: Forward, Backward, Left, Right, and Upward: Delicate texture on the surface, adequate light. Downward: The ground has rich textures and sufficient lighting conditions, with a diffuse reflection surface and a reflectivity greater than 20% (such as walls, trees, people, etc.). Sufficient lighting conditions refer to an illuminance not lower than that of a nighttime city light scene.
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
Transmission schemes
Operating frequencies
Details of frequency spectrum approvals
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	Max Payload: 6 kg The 6 kg payload is measured at the third gimbal connector under sea level conditions. Payload capacity decreases as altitude increases. For details, refer to the official user manual.
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
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 Matrice 400

Aircraft
Takeoff Weight	Without Batteries: 5020±20 g With Batteries: 9740±40 g The actual product weight may vary due to differences in batch materials and external factors.
Max Takeoff Weight	15.8 kg
Dimensions	Unfolded: 980 x 760 x 480 mm (L x W x H) (with landing gear) Folded: 490 x 490 x 480 mm (L x W x H) (with landing gear and gimbal) Maximum dimensions excluding propellers. Aircraft carrying case dimensions: 779 x 363 x 528 mm (L x W x H)
Max Payload	6 kg The 6 kg payload is measured at the third gimbal connector under sea level conditions. Payload capacity decreases as altitude increases. For details, refer to the official user manual.
	25 inches
Diagonal Wheelbase	1070 mm
Max Ascent Speed	10 m/s
Max Descent Speed	8 m/s
Max Horizontal Speed (at sea level, no wind)	25 m/s
Max Takeoff Altitude	7000 m
Max Flight Time	59 minutes Measured with the aircraft flying forward at a constant speed of 10 m/s in a windless environment at sea level, carrying only the H30T (total weight 10,670 g), and from 100% battery level until 0%. Data is for reference only. Actual experience may vary depending on the environment, usage, and firmware version.
Max Hover Time (without wind)	53 minutes Measured with the aircraft hovering in a windless environment at sea level, carrying only the H30T (total weight 10,670 g), and from 100% battery level until 0%. Data is for reference only. Actual usage time may vary depending on the flight mode, accessories, and environment.
Max Flight Distance	49 km Measured by the aircraft flying forward at a constant speed of 17 m/s in a windless environment at sea level, without external payloads, and from 100% battery level until 0%. Actual experience may vary depending on the environment, usage, and firmware version.
Max Wind Speed Resistance	12 m/s Max wind speed resistance during takeoff and landing.
	Yaw: 100 Deg./s
Max Pitch Angle	35 Deg.
Operating Temperature	-20 Deg. to 50 Deg. C (-4 Deg. to 122 Deg. F) (without solar radiation)
Global Navigation Satellite System	GPS + Galileo + BeiDou + GLONASS* * GLONASS is supported only when the RTK module is enabled. Equipped with standard airborne ADS-B In receiver and dual antennas, supporting reception up to 20 km.
Hovering Accuracy Range	Vertical: ±0.1 m (with vision positioning) ±0.5 m (with satellite positioning) ±0.1 m (with RTK positioning) Horizontal: ±0.3 m (with vision positioning) ±0.5 m (with satellite positioning) ±0.1 m (with RTK positioning)
	RTK Fix: 1 cm + 1 ppm (horizontal), 1.5 cm + 1 ppm (vertical)
	Supports RTK heading with an accuracy better than 2 Deg.
	Equipped with standard airborne ADS-B In receiver and dual antennas, supporting reception up to 20 km.
Internal Storage	N/A
	USB-C Debug Port x 1: USB 2.0 E-Port V2 x 4: At the lower part of the drone, with 120W single-port power Cellular Dongle 2 Interface x 2: On the underside of the drone
Propeller Model	2510F
Beacon	Built into the aircraft
Ingress Protection Rating[3]	IP55 The rating is not permanently effective and may decrease due to product wear and tear.
Gimbal
	1400 g If exceeds, the gimbal damper lifespan will decrease from 1000 hours to 400 hours.
	950 g
	3 kg for quick-release port, 6 kg for screw lock fastening
Sensing
Sensing Type	Omnidirectional binocular vision system (surround view provided by full-color fisheye vision sensors) Horizontal rotating LiDAR, upper LiDAR and downward 3D infrared range sensor Six-direction mmWave radar
Forward	Measurement Range: 0.4-21 m Detection Range: 0.4-200 m Field of View (FOV): 90 Deg. (horizontal), 90 Deg. (vertical)
Backward	Measurement Range: 0.4-21 m Detection Range: 0.4-200 m Field of View (FOV): 90 Deg. (horizontal), 90 Deg. (vertical)
Lateral	Measurement Range: 0.6-21 m Detection Range: 0.5-200 m Field of View (FOV): 90 Deg. (horizontal), 90 Deg. (vertical)
Downward	Measurement Range: 0.5-19 m The FOV to the front and rear is 160 Deg. and 105 Deg. to the right and left.
Operating Environment	Forward, Backward, Left, Right, and Upward: Delicate texture on the surface, adequate light. Downward: The ground has rich textures and sufficient lighting conditions, with a diffuse reflection surface and a reflectivity greater than 20% (such as walls, trees, people, etc.). Sufficient lighting conditions refer to an illuminance not lower than that of a nighttime city light scene.
	Standard Measurement Range: 0.5-100 m @ 100,000 lux with 10% reflectivity target Measurement Range for Power Line: 35 m @ 30 Deg. @ 10,000 lux for 21.6 mm steel-core aluminum stranded wire with a relative body tilt angle of 30 Deg. to the left and right Field of View (FOV): 360 Deg. (horizontal), 58 Deg. (vertical) Point-Frequency: 520,000 points/second Laser Wavelength: 905 nm Eye Safety Level: Class 1 (IEC60825-1:2014), eye-safe
	0.5-25 m at night (reflectivity > 10%) The FOV to the up and down is 60 Deg. and 60 Deg. to the right and left.
	Measurement Range: 0.3-8 m (reflectivity > 10%) The FOV to the front and rear is 60 Deg. and 60 Deg. to the right and left.
	Measurement Range for Power Line: 36 m for a 12.5mm steel-core aluminum stranded wire 50 m for a 21.6mm steel-core aluminum stranded wire FOV: ± 45 Deg. (horizontal and vertical) The mmWave radar function is unavailable in some countries/regions.
FPV Camera
Resolution	1080p
	DFOV: 150 Deg. HFOV: 139.6 Deg. VFOV: 95.3 Deg.
Frame Rate	30fps
	Starlight Grade
Video Transmission
Video Transmission System	DJI O4 Enterprise Enhanced Video Transmission System
Live View Quality	Remote Controller: 3-channel 1080p/30fps
	902-928 MHz: < 30 dBm (FCC), < 16 dBm (MIC) 1.430-1.444 GHz: < 35 dBm (SRRC) 2.4000-2.4835 GHz: < 33 dBm (FCC), < 20 dBm (CE/SRRC/MIC) 5.150-5.250 GHz: < 23 dBm (FCC/CE) 5.725-5.850 GHz: < 33 dBm (FCC), < 14 dBm (CE), < 30 dBm (SRRC) Operating frequency allowed varies among countries and regions. Refer to local laws and regulations for more information.
Max Transmission Distance (free of interference)	Strong interference (dense buildings, residential areas, etc.): approx. 1.5-6 km Medium interference (suburban counties, city parks, etc.): approx. 6-15 km Weak interference (open spaces, remote areas, etc.): approx. 15-40 km Data is tested under FCC standard in unobstructed environments of typical interference. Only to serve as a reference and provides no guarantee as to the actual flight distance.
Max Download Speed	Standard Mode: 80Mbps Downlink Playback Download: < 25 MBps Single-Channel Bitrate: <= 12 Mbps The above data was measured under conditions where the aircraft and remote controller were in close proximity without interference.
Antenna	WLAN Antenna x 8: 6 vertically polarized antennas and 2 horizontally polarized antennas sub2G Antenna x 2: 2 vertically polarized antennas 4G Antenna x 4 Operating Mode: 2T4R
	Supports Dual Control Mode and 2-channel Cellular Dongle 2
Battery
Model	TB100
Capacity	20254 mAh
Standard Voltage	48.23 V
Max Charging Voltage	54.6 V
	Li-ion 13S
Energy	977 Wh
Weight	4720 ± 20 g
Charging Temperature	5 Deg. to 45 Deg. C (41 Deg. to 113 Deg. F)
	-20 Deg. to 75 Deg. C (-4 Deg. to 122 Deg. F)
	Single Battery: Support Onboard: Support Battery Station: Support
Discharge rate	4C
Max Charging Power	2C
	Supports low-temperature self-heating charging
	400
Intelligent Battery Station
	BS100
Net Weight	11.8 kg
Dimensions	605 x 410 x 250 mm (L x W x H)
	TB100 Intelligent Flight Battery, TB100C Tethered Battery WB37 Battery
Operating Temperature	-20 Deg. to 40 Deg. C (-4 Deg. to 104 Deg. F)
	100-240 V (AC), 50-60 Hz, 10 A
	USB-C: TB100 Battery Interface: 100-110 V: Approx. 1185 W 110-180 V: Approx.1474 W 180-240 V: Approx. 2184 W WB37 Battery Interface: 100-240 V: Approx. 52 W USB-C: 5.0 V 3.0 A, 9.0 V 3.0 A, 12.0 V 3.0 A, 15.0 V 3.0 A, 20.0 V 3.25 A
	Three TB100 and two WB37 batteries
	Ready-to-Fly Mode 90%; Standard Mode 100% Supports Fast Charging Mode and Silent Mode
	TB100/TB100C Battery From 0% to 100%: 220 V: 45 minutes (Fast Charging Mode); 110 minutes (Silent Mode) 110 V: 70 minutes (Fast Charging Mode); 110 minutes (Silent Mode) Charging time is measured in a test environment with a temperature of 25 Deg. C.

	DJI O4 Enterprise Enhanced Video Transmission System
	40 km (FCC) 20 km (CE/SRRC/MIC) Measured in an unobstructed environment free of interference. The above data shows the farthest communication range for one-way, non-return flights under each standard. During your flight, please pay attention to RTH reminder on the DJI Pilot 2 app.
	902-928 MHz: < 30 dBm (FCC), < 16 dBm (MIC) 1.430-1.444 GHz: < 35 dBm (SRRC) 2.400-2.4835 GHz: < 33 dBm (FCC), < 20 dBm (CE/SRRC/MIC) 5.150-5.250 GHz: < 23 dBm (FCC/CE) 5.725-5.850 GHz: < 33 dBm (FCC), < 14 dBm (CE), < 30 dBm (SRRC) Operating frequency allowed varies among countries and regions. Refer to local laws and regulations for more information.
	2T4R, 2.4GHz/5.8GHz multi-beam high-gain antenna sub2G Module: 2T2R
	Supports DJI Cellular Dongle 2
	Wi-Fi Direct, Wireless Display, IEEE 802.11 a/b/n/ac/ax Supports 2 x 2 MIMO Wi-Fi, dual-band simultaneous (DBS) support for dual MAC, with data rates up to 1774.5 Mbps (2 x 2 + 2 x 2 11ax dual-band simultaneous)
	2.4000-2.4835 GHz 5.150-5.250 GHz 5.725-5.850 GHz 5.2 and 5.8GHz frequencies are prohibited in some countries. In some countries, the 5.2GHz frequency is only allowed for use in indoor.
	2.4 GHz: < 26 dBm, < 20 dBm (CE/SRRC/MIC) 5.1 GHz: < 23 dBm (FCC/CE/SRRC/MIC) 5.8 GHz: ＜ 23 dBm (FCC/SRRC), ＜ 14 dBm (CE)
	Bluetooth 5.2
	2.400-2.4835 GHz
	＜ 10 dBm
	1920 x 1200
	7.02 inches
	60fps
	1400 nits
	10-Point Multi-Touch
	2S2P High Energy Density 18650 Lithium-ion Battery (6500 mAh @ 7.2 V) 46.8 Wh
	Optional, WB37 (4920 mAh @ 7.6 V) 37 Wh
	Supports PD fast charging, with a maximum 20V/3.25A USB Type-C charger
	RAM 8G + ROM 128G UFS + expandable storage via microSD card
	2 hours for internal battery; 2 hours for internal plus external batteries. When remote controller is powered off and using a standard DJI charger.
	3.8 hours
	3.2 hours
	HDMI 1.4
	Status LED, battery level LED, connection status LED, tricolor light, brightness adjustable according to ambient light
	Supports buzzer
	Array MIC
	-20 Deg. to 50 Deg. C (-4 Deg. to 122 Deg. F)
	Within one month: -30 Deg. to 45 Deg. C (-22 Deg. to 140 Deg. F) One to three months: -30 Deg. to 35 Deg. C (-22 Deg. to 113 Deg. F) Three months to one year: -30 Deg. to 30 Deg. C (-22 Deg. to 86 Deg. F)
	5 Deg. to 40 Deg. C (41 Deg. to 104 Deg. F)
	Matrice 400
	GPS + Galileo + BeiDou
	268 x 163 x 94.5 mm (L x W x H) Width including external antenna folded, thickness including handle and controller sticks.
	1.15 kg (without external battery)
	TKPL 2
	Android 11
	HDMI 1.4, SD 3.0, USB-C with OTG support, max 65W PD charging, USB-A with USB 2.0 support
	Strap/waist support

	Gimbal Cameras: Zenmuse H30, Zenmuse H30T, Zenmuse L2 and Zenmuse P1 Accessories: Zenmuse S1 (drone spotlight), Zenmuse V1 (drone speaker), Manifold 3, DJI RC Plus 2 sub2G SDR Module, DJI Cellular Dongle 2 RTK Station: D-RTK 3 Multifunctional Station, D-RTK 2 Mobile Station Ecosystem Accessories: DJI X-Port DJI E-Port V2 Development Kit DJI E-Port V2 Coaxial Cable Kit DJI SKYPORT V3 Adapter Set DJI SKYPORT V3 Coaxial Cable Kit

Data source: https://enterprise.dji.com/matrice-400/specs

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Source data acquired 2023-01-23 19:03:43