LM-30 UAV System: Innovative Folding Design from Leading China Suppliers and Factory
Product composition
LM-30 UAV system includes flight platform, command and control system, launching system and integrated support system. The flight system comprises a LM30 platform, an airborne datalink end and a gimbal camera.etc, the command and control system include a ground control station and a ground datalink; the launching system include a launcher device, a launching ignition system and a booster; The integrated support system includes packaging equipment and operation and maintenance equipment.
Figure3 UAV system composition architecture
Energy Power System
1. Battery
The UAV is equipped with two rechargeable lithium-ion batteries as the energy source of the whole aircraft.
Table3 Parameters of lithium ion battery
| Item | Description | Specification |
|---|---|---|
| 1 | Type of battery | 14s lithium ion battery |
| 2 | Nominal capacity | 36Ah |
| 3 | Charge and discharge cut-off voltage | 35V～58.8V |
| 4 | Storage voltage | 49.7V～53.2V |
| 5 | Weight | 5.85kg |
| 6 | size | 215mm×152mm×88mm |
| 7 | Output connector | AS120-F |
| 8 | Rechargeable temperature | -10℃～50℃ |
| 9 | Operating ambient temperature | -20℃～55℃ |
| 10 | Storage temperature | -20℃～35℃ |
| 11 | Charging current | 28A |
2. Power system
The UAV power system consists of a motor with a maximum power of 7.5KW, an electric regulator with a maximum continuous working current of 120 A (good heat dissipation) and a two-blade propeller with a size of 23 inches. The performance parameters of the power system are shown in the table below.
Table4 Parameters of power system
| Category | Description | Parameter |
|---|---|---|
| Propeller | Propeller diameter | 23in |
| Use the altitude | 0-5000m | |
| Material | Carbon fiber composite | |
| Electric machinery | Size | φ90mm×80.8mm |
| Weight | 1115g | |
| Power | 10S-14S | |
| Maximum power | 7500W | |
| Electric Tune | Size | 116mm×56mm×31.5mm |
| Weight | 405g | |
| Power | 6S-14S | |
| Current specification | 200A |
Electrical system
The power distribution system is composed of relay box, distribution box and cable assembly to complete the functions of UAV power access, secondary power conversion and power transmission. The relay box has the functions of power supply access, pre-charging and power-on, power-on self- locking and power-off. The distribution box has the function of secondary power supply conversion. The cable transmits the electric energy to each electrical equipment, as shown in the following figure.
The belly has a pull-out breakaway connector with the following functions:
a. Charge and discharge the battery on the machine;
b. Ground power access;
c. Maintenance interface of flight control computer (network port and mode switching interface);
d. Upper and lower electrical interfaces of UAV;
e. Rocket launch interlock interface.
The belly has a pull-out breakaway connector with the following functions:
a. Charge and discharge the battery on the machine;
b. Ground power access;
c. Maintenance interface of flight control computer (network port and mode switching interface);
d. Upper and lower electrical interfaces of UAV;
e. Rocket launch interlock interface.
Figure4 Power distribution system diagram
Airborne data link
Airborne datalink is a bidirectional data link for UAV applications, which can transmit video data and measurement and control data at the same time. The airborne datalink uses a single antenna time-sharing multiplexing mode, which greatly reduces the total weight of the equipment, has simple connection, is convenient to install and integrate, and can be quickly deployed for work; Intelligent design is adopted to adjust the working frequency point, bandwidth and output power on site.
Table5 Airborne datalink parameter
| Item | Description | Parameter |
|---|---|---|
| 1 | size | Airborne data terminal: 98.99x63.1x22.2mm |
| 2 | Weight | Airborne data terminal: 180g ± 5g |
| 3 | Operating temperature | -20 ~ 65℃ |
| 4 | Storage temperature | -40 ~ 85℃ |
| 5 | Operating voltage | Airborne data terminal: DC 9 ~ 32 V |
| 6 | RF power | 2W（33dBm±1dBm） |
| 7 | RF bandwidth | 15MHz |
| 8 | Power consumption of the whole machine | Airborne data terminal: 30W |
| 9 | Operating frequency band | 1432MHz |
| 10 | Effective code rate | Uplink: 200kbps, Downlink: 8Mbps, 4Mbps, 2Mbps, 250kbps (dynamically configurable) |
| 11 | Receive sensitivity | -99dBm@15MHz |
| 12 | Airborne antenna gain | Greater than 1 dBi |
| 13 | Ground Omnidirectional Antenna Gain | Greater than 1 dBi |
| 14 | Ground Directional Antenna Gain | Greater than 15 dBi |
| 15 | Doppler shift | Up to 300Km/H relative motion speed |
| 16 | End-to-end delay | Video delay: ≯ 200ms (excluding video acquisition delay), Data delay: ≯ 40ms |
Figure5 Airborne Datalink
Gimbal camera
The gimbal camera adopts a two-axis stabilized platform, installs a conductive slip ring to achieve 360 ° continuous rotation, and is equipped with a 30x high-definition visible light camera, a long-wave uncooled infrared imaging component, and a laser rangefinder. It is mainly used for ground imaging detection, identification, tracking, ranging and positioning, and meets the needs of aerial mapping, monitoring, survey, etc. Its important functional performance indicators are as follows.
A. Visible zoom camera
i. Working waveband: 0.4 μm ~ 0.9 μm;
ii. Resolution: 1920 × 1080;
iii. Focal length: 4.3mm ~ 129mm, optical 30x continuous zoom, 12x digital zoom;
iv. Optical zoom hFOV 63.7º ~ 2.3º;
v. Video output: Ethernet, 1080P, 30 Hz;
i. Working waveband: 0.4 μm ~ 0.9 μm;
ii. Resolution: 1920 × 1080;
iii. Focal length: 4.3mm ~ 129mm, optical 30x continuous zoom, 12x digital zoom;
iv. Optical zoom hFOV 63.7º ~ 2.3º;
v. Video output: Ethernet, 1080P, 30 Hz;
| Target | Target Size (m) | Detection (Km) | Recognition (Km) |
|---|---|---|---|
| PEOPLE | 0.5x1.8 | 6 | 2 |
| VEHICLE | 3x6 | 15 | 8 |
B. Uncooled LWIR
i. Operating band: 8 μm ~ 14 μm;
ii. Detector pixel number: 640 × 512;
iii. Pixel size: 12 um;
iv. NETD：50mk；
v. Focal length: 35mm/F1.0;
vi. Field angle: 12.5º × 10º;
vii. Video output: Ethernet, 1080P, 30 Hz.
i. Operating band: 8 μm ~ 14 μm;
ii. Detector pixel number: 640 × 512;
iii. Pixel size: 12 um;
iv. NETD：50mk；
v. Focal length: 35mm/F1.0;
vi. Field angle: 12.5º × 10º;
vii. Video output: Ethernet, 1080P, 30 Hz.
| Target | Target Size (m) | Detection (Km) | Recognition (Km) |
|---|---|---|---|
| PEOPLE | 0.5x1.8 | 1 | 0.25 |
| VEHICLE | 3x6 | 6 | 1.5 |
C. Laser Rangefinder
i. Working wavelength: 1535nm;
ii. Ranging accuracy: ± 1 m;
iii. Ranging frequency: 5Hz;
iv. Laser ranging distance: 50-3000m
i. Working wavelength: 1535nm;
ii. Ranging accuracy: ± 1 m;
iii. Ranging frequency: 5Hz;
iv. Laser ranging distance: 50-3000m
D. Servo System
i. Swing range
Azimuth axis: n × 360 ° continuous rotation
Pitch axis: -110 ° ~ + 10 ° (horizontal direction is 0 °, upward is positive)
ii. Angle measurement accuracy: ≤ 2mrad;
iii. Stabilization accuracy: ≤ 100µrad (1σ) (2 °/1Hz, 1 °/2Hz swing);
iv. Maximum angular velocity: ≥ 50 °/s;
v. Maximum angular acceleration: ≥ 90 °/s 2 .
i. Swing range
Azimuth axis: n × 360 ° continuous rotation
Pitch axis: -110 ° ~ + 10 ° (horizontal direction is 0 °, upward is positive)
ii. Angle measurement accuracy: ≤ 2mrad;
iii. Stabilization accuracy: ≤ 100µrad (1σ) (2 °/1Hz, 1 °/2Hz swing);
iv. Maximum angular velocity: ≥ 50 °/s;
v. Maximum angular acceleration: ≥ 90 °/s 2 .
E. Tracking Functions
i. Pixel deviation update rate: 50hz;
ii. Tracking speed: 30 pixels/frame;
iii. Minimum target contrast: 8%;
iv. Minimum target imaging size: 4 × 3 pixels;
v. In the case of rolling, rapid reduction or enlargement of target imaging, it has the ability of tracking without slippage and loss.
It has the ability to automatically recapture the target after the short-term occlusion of clouds and ground scenes is eliminated.
i. Pixel deviation update rate: 50hz;
ii. Tracking speed: 30 pixels/frame;
iii. Minimum target contrast: 8%;
iv. Minimum target imaging size: 4 × 3 pixels;
v. In the case of rolling, rapid reduction or enlargement of target imaging, it has the ability of tracking without slippage and loss.
It has the ability to automatically recapture the target after the short-term occlusion of clouds and ground scenes is eliminated.
Ground Control Station
The UAV system can be easily controlled from a portable computer, such as a laptop. In addition, the user can select the command module to improve the working conditions of the command and system operators. For the command module, the ground data link and power supply unit can also be integrated to make the system more convenient to use.
Figure7 Portable Ground Control Station
Ground Datalink
The ground datalink adopts a light PTZ, and the ground processing equipment is integrated inside the turntable, which is a completely integrated design. Appearance and dimensions of the ground datalink are shown in the figure below:
Table6 Ground Datalink Parameters
| Item | Description | Parameter |
|---|---|---|
| 1 | Size | Ground data terminal: 675x386.6 x156.9 mm |
| 2 | Weight | Ground data terminal: 9500 G ± 100 G |
| 3 | Power consumption of | Ground data terminal: 20W (rotary table |
| the whole machine | stationary), 40W (rotary table rotating) | |
| 4 | Operating voltage | Ground data terminal: DC 24V |
| 5 | Rotation speed | Level 0.01 ° ~ 30 °/s; Pitch 0.01 ° ~ 12 °/s |
| (continuously variable speed) | ||
| 6 | Rotation angle | Horizontal: 0 ~ 360 ° continuous rotation |
| Elevation: + 20 ° ~ -20 ° | ||
| 7 | Angular resolution | 0.5° |
| 8 | Power consumption of | ≤30W |
| the whole machine | ||
| 9 | Quiescent power | 5W |
| consumption | ||
| 10 | Operating | -20 ℃ ~ + 55 ℃ , 90% ± 3%, non- |
| temperature | condensing | |
| 11 | Storage temperature | -40℃～+65℃ |
Figure8 Ground Datalink
Launcher
Dimension of single launch tube: 300mm × 250mm × 2600mm, material: glass fiber + partial metal structure, weight: about 50kg
Figure9 Schematic diagram of vehicle-mounted launcher
Launch ignition system
The launch ignition control system consists of an adapter box, a control box, a 6S rocket ignition battery and a cable, which can realize the functions of UAV power on and off, on-board battery charging, launch interlock control, rocket ignition, etc.
Figure10 Electrical Block Diagram of Launch Ignition System
a) The adapter box and the control box are used to realize the functions of aircraft power on and off and rocket ignition control, wherein the adapter box is fixed on the launcher, and the control box is placed in the ignition safety area:
1) The arrangement of the panel of the switching box is described as follows:
A. Voltage display: used to display the aircraft battery voltage;
B. Safety: used to protect the ignition battery;
C. Charging and discharging interface: used to maintain the aircraft battery without disassembling the aircraft battery;
D. Ignition battery interface: used to connect the ignition battery and provide power for the adapter box and control box;
E. X1 connector: a 16-core waterproof connector is used to connect the aircraft through the adapter cable. The red dot on the plug of the adapter cable is aligned with the red dot on the X1 connector for plugging. The connection is completed after the locking sound is heard.
F. X2 connector: 2-core waterproof connector is used to connect the booster rocket;
G. X3 connector: a 12-core waterproof connector is used to connect the control box through the adapter cable.
1) The arrangement of the panel of the switching box is described as follows:
A. Voltage display: used to display the aircraft battery voltage;
B. Safety: used to protect the ignition battery;
C. Charging and discharging interface: used to maintain the aircraft battery without disassembling the aircraft battery;
D. Ignition battery interface: used to connect the ignition battery and provide power for the adapter box and control box;
E. X1 connector: a 16-core waterproof connector is used to connect the aircraft through the adapter cable. The red dot on the plug of the adapter cable is aligned with the red dot on the X1 connector for plugging. The connection is completed after the locking sound is heard.
F. X2 connector: 2-core waterproof connector is used to connect the booster rocket;
G. X3 connector: a 12-core waterproof connector is used to connect the control box through the adapter cable.
Figure11 Physical drawing of the adapter box
2) The layout of the control box panel is described as follows:
A. Power-on switch: a self-reset switch is used to power on the aircraft, and it needs to be pressed for 3s.
B. Power-off switch: a self-reset switch is used to power off the aircraft, and it needs to be pressed for 3s.
C. Ignition switch: It is a self-reset knob switch. When the arrow isupward, it is closed. It can be opened by rotating clockwise to ignite the rocket booster. When igniting, it is held for 1 second after rotating clockwise.
D. Power-on indicator: used to indicate the power-on condition of the aircraft;
E. Disarming indicator: used to indicate the unlocking condition of the ground station software;
F. Ignition indicator: It is used to indicate the energization of pin 2 of the X2 connector of the junction box. When the ignition indicator is on, the X2 connector is energized and the rocket booster is ignited.
A. Power-on switch: a self-reset switch is used to power on the aircraft, and it needs to be pressed for 3s.
B. Power-off switch: a self-reset switch is used to power off the aircraft, and it needs to be pressed for 3s.
C. Ignition switch: It is a self-reset knob switch. When the arrow isupward, it is closed. It can be opened by rotating clockwise to ignite the rocket booster. When igniting, it is held for 1 second after rotating clockwise.
D. Power-on indicator: used to indicate the power-on condition of the aircraft;
E. Disarming indicator: used to indicate the unlocking condition of the ground station software;
F. Ignition indicator: It is used to indicate the energization of pin 2 of the X2 connector of the junction box. When the ignition indicator is on, the X2 connector is energized and the rocket booster is ignited.
Figure12 Physical drawing of control box
b) The ignition battery is used to provide energy for the control drive and booster rocket in the adapter box. The parameters of the battery are described in the following table.
Table7 Main parameters of single lithium polymer battery
| Access mode | 6S1P |
| Nominal capacity | 4000mAh @ 2C Discharge |
| Nominal voltage | 22.8V（Cell 3.80V） |
| Size | MAX（T*W*L）:170×50×38mm |
| Weight | 620g |
Booster
Rocket Booster: Provide the overall thrust of the UAV during launch to ensure that the aircraft can reach the initial flight speed and altitude. The booster is installed at the tail of the aircraft and is detached after operation. The rocket booster and its installation are shown in the figure below.
Table8 Booster parameters
| Description | Parameter indicators |
|---|---|
| Weight/kg | 3.2 |
| Diameter/mm | 82 |
| Length/mm | 335 |
| Total stroke/N • s | 2600 |
| Average thrust/N | 1857 |
| Working time/s | 1.4 |
Figure13 Schematic diagram of the rocket booster
Frequently Asked Questions (FAQ)
What components make up the LM-30 UAV system?
The system consists of the LM30 flight platform (including the airborne datalink end and gimbal camera), the command and control system (ground control station and ground datalink), the launching system (launcher device, launching ignition system, and booster), and the integrated support system.
What are the battery and power system specifications for the LM-30 UAV?
The flight platform is powered by two 14s lithium-ion batteries with a nominal capacity of 36Ah. The propulsion system uses a motor with a maximum power of 7500W, a 200A electric regulator, and a 23-inch carbon fiber composite propeller.
What are the key technical features of the airborne and ground datalinks?
The airborne datalink operates at 1432MHz with a 15MHz bandwidth, supporting dynamic downlink code rates up to 8Mbps. The ground datalink features a lightweight PTZ structure with 360° continuous horizontal rotation, an elevation range of +20° to -20°, and operates on DC 24V.
What camera payloads does the gimbal camera integrate?
The gimbal integrates a 30x optical zoom visible light camera (1920x1080 resolution), an uncooled long-wave infrared (LWIR) component (640x512 resolution), and a 1535nm laser rangefinder with a ranging distance of 50m to 3000m.
How does the launch ignition system function?
The launch ignition control system utilizes an adapter box on the launcher and a remote control box in the safety area. Powered by a 22.8V 6S1P lithium polymer battery, it manages power status, charging, launch interlocking, and rocket booster ignition.
What are the parameters of the rocket booster used for launch?
The rocket booster weighs 3.2kg with a diameter of 82mm and length of 335mm. It provides an average thrust of 1857N and a total stroke of 2600 N·s over a working time of 1.4 seconds to accelerate the UAV to its initial flight speed.