An aircraft includes at least one sensor, an altitude actuator, a memory device, and an electronic controller. The at least one sensor is configured to detect altitude of the aircraft, current position of the aircraft and speed of the aircraft. The altitude actuator is configured to change the altitude of the aircraft. The memory device is configured to store predetermined terrain data of an area. The electronic controller is configured to estimate a future position of the aircraft based on a detected current position of the aircraft and a detected speed of the aircraft. The electronic controller is further configured to control the altitude actuator based on the future position, a detected altitude of the aircraft and the predetermined terrain data.

An unmanned aerial vehicle (UAV) includes a casing including a first end portion and a second end portion away from the first end portion. An accommodation chamber is formed at the second end portion. The UAV further includes a support plate arranged in the casing. The accommodation chamber is recessed relative to the support plate. The UAV also includes a circuit board assembly housed in the casing and a load provided at the first end portion of the casing. The circuit board assembly includes a circuit board connected to the support plate and an inertial measurement assembly provided at the circuit board and accommodated in the accommodation chamber.

A drive unit for air vehicle, which allows building the vertical take-off and landing vehicles, intended for use, for instance, in the production of flying taxis, as well as in the model-making branch and in the toy industry.

The drive unit is composed of the air channel, in the form of a straight segment of a tube with circular section, which has fans with engines fixed on its both ends. The vertical draft force outlet-inlet nozzle opening is located between fixed fans of the drive unit.

Provided is a vertical take-off/landing aircraft controlling a tilt angle of a main rotor, based on a vertical posture control signal during low-speed flight, wherein, when an aircraft steering signal including a vertical posture control signal for changing the pitch posture angle of the vertical take-off/landing aircraft by a first pitch posture angle is obtained, a flight controller determines a tilt angle of the main rotor with reference to the first pitch posture angle and generates a tilt angle control signal for the main rotor based on the determined tilt angle.

A thruster controller is used in a flying device that has at least two thrusters and a main controller that outputs an instruction value to the thruster for controlling a thrust of the thruster. The thruster controller includes an instruction value obtainer and an instruction value generator. The instruction value obtainer obtains an instruction value that is output from the main controller to the thruster based on an assumption that a propeller pitch is fixed. The instruction value generator outputs, to a pitch changing mechanism of the thruster, a propeller pitch instruction value generated from the obtained instruction value for setting the propeller pitch, and outputs, to a motor, a corrected rotation number instruction value for setting a rotation number of the motor by correcting the instruction value based on the propeller pitch instruction value.

A method for detecting a mounting error of an accelerometer includes acquiring actual output data of the accelerometer mounted to an unmanned aerial vehicle (UAV) while the UAV is in a hover state. The method also includes determining a mounting error angle of the accelerometer based on the actual output data.

An unmanned aerial vehicle (UAV) includes a radar configured to perform ranging on a ground during rotation and a terrain prediction device communicatively connected to the radar. The terrain prediction device includes a memory storing a computer program and a processor configured to execute the computer program to acquire N pieces of ranging data each being obtained by the radar when a rotation angle of the radar is within a preset angle interval, and determining a terrain parameter of the ground according to the N pieces of ranging data. N is an integer greater than 1. The terrain parameter includes at least one of a gradient or a flatness.

Provided is a crash detection device, a method of detecting a crash of a flying object, a parachute or paraglider deployment device, and an airbag device that can improve the reliability in terms of safety. A device detecting a crash of a flying object includes a detection part capable of detecting a flying state of the flying object, a calculation section capable of determining whether the flying state of the flying object is abnormal based on data on the flying state of the flying object acquired by the detection part, and an abnormal signal output section capable of outputting an abnormal signal to the outside when the calculation section determines that the flying state of the flying object is abnormal. The calculation section acquires data from the detection part at a sampling frequency of 1 kHz or more, determines whether the data is data indicating that the flying state of the flying object is abnormal or noise that is unnecessary data when the data is equal to or greater than a predetermined threshold value, determines that the flying state of the flying object is abnormal when the data is determined to be the data indicating that the flying state of the flying object is abnormal.

The present disclosure provides a motion sensor assembly applied to an unmanned vehicle. The motion sensor assembly includes a mounting bracket, a sensor assembly body, and a shock absorption mechanism disposed between the mounting bracket and the sensor assembly body. The sensor assembly body includes a protective casing and a sensor module disposed in the protective casing. The shock absorption mechanism including a plurality of elastic members, which are disposed between the mounting bracket and the protective casing for absorbing the shock of the sensor module in the protective casing.

The present disclosure relates to the technical field of unmanned aerial vehicles, and in particular, to an unmanned aerial vehicle. The unmanned aerial vehicle includes at least a first dual-polarized antenna and a second dual-polarized antenna, wherein the first dual-polarized antenna is provided in a horizontal direction of the unmanned aerial vehicle, and the second dual-polarized antenna is provided in a vertical direction of the unmanned aerial vehicle. As the antenna designed in this structure is applied to the unmanned aerial vehicle of the present application, a weak signal in a vertical polarization direction is compensated by a strong electromagnetic signal in a horizontal polarization direction, and therefore an image transmission height of the unmanned aerial vehicle is increased in the vertical direction.