35results about How to "Ensure safe landing" patented technology

The invention discloses a method for autonomous site selection and landing of an unmanned aerial vehicle integrating LIDAR point cloud and image data. The method includes generating a color point cloud image based on the fusion of lidar point cloud data stream and image data stream; calculating at least one smooth area in the color point cloud image, taking the smooth area closest to the UAV as the initial landing point, and controlling the UAV Move to the initial landing point; in the process of moving to the initial landing point, perform visual analysis on the semantic information corresponding to all smooth areas, and filter to obtain at least one safe smooth area; determine the safe smooth area closest to the current position of the drone as The final landing point, control the drone to land to the final landing point. The invention realizes that without relying on unreliable sensor information such as GPS and IMU, the optimal landing point in the area is independently selected for landing over various terrains, and the landing point with potential safety hazard can be quickly and effectively screened.

The invention provides an inertial anti-skid braking system and a control condition determination method. The inertial anti-skid braking system provided by the invention adopts the structure that a floor switch is added to an inertial anti-skid braking system in the prior art, the positive pole of an electric apparatus contact of the floor switch is connected with the positive pole of an electric apparatus contact of an inertial sensor, and the negative pole of the electric apparatus contact of the floor switch is connected with the negative pole of the electric apparatus contact of the inertial sensor. The floor switch on an airplane undercarriage is logically synthesized with accessories of the braking system, and the braking pressure is locked in the air, so that before touch-down of an airplane or when the braking airplane wheel does not rotate fully although the airplane touches down, the inertial anti-skid braking system cannot apply braking pressure to the braking airplane wheel; and after ground protection fails, the anti-skid braking system conducts normal braking on the braking airplane wheel.

A soft landing obstacle avoidance simulation test system comprises a six-freedom-degree motion simulation device, a high-simulation lunar surface simulation sand board screen, a GNC simulation computer, a sensor and executing mechanism simulation interface box, a dynamic emulation computer and a ground test general control computer. Three-axis rotation and three-dimensional translational motion relative to the lunar surface of a prober are simulated through the six-freedom-degree motion simulation device. The landform of the lunar surface for the prober to land on and the characteristics of lunar surface reflection to a sensor are simulated through the high-simulation lunar surface simulation sand board screen. Guidance, navigation and control calculation is performed by the GNC simulation computer according to the output of the sensor and executing mechanism simulation interface box and measured information of the landing navigation sensor to acquire executing mechanism control instructions, the executing mechanism control instructions are sent to the dynamic emulation computer for orbit and posture dynamic calculation and parameter update, and six-freedom-degree motion parameters are generated to be used for driving the six-freedom-degree motion simulation device. The ground test general control computer is responsible for control over the whole test system and data management.

A method for scan-selecting safety landing region of moon craft at hovering stage includes obtaining 3-D information of moon surface by utilizing sensor of moon surface-imaging defining region occupied by moon craft-landing as unit area being defined as landing center, moving said landing center as per fixed distance from inside to outside to judge whether each landing region on landing center issatisfied with landing condition or not and moving said landing center continuously to make judgment if it is not or otherwise moving moon craft to relevant position for landing.

The invention provides a power reduction initial point parameter optimization method based on terrain of moon surface, The method particularly comprises the following steps: a first step, setting a moon latitude and a selenocentric distance of a power reduction initial point, wherein RL is an average moon radius in a certain local area where range finding is introduced; a second step, in a period between near-moon braking and around-moon rail reducing, optimizing the moon latitude and the selenocentric distance of the power reduction initial point, and introducing the optimized result into a third step; and the third step, in the period between around-moon rail reducing and power reduction, if a fact that the selenocentric distance error or / and moon latitude deviation are larger than allowable envelope in design, optimizing the moon latitude and the selenocentric distance of the power reduction initial point according to the manner of the second step until the moon latitude and the selenocentric distance of the power reduction initial point are set in the allowable envelope in design, and hereon utilizing the optimized moon latitude and the selenocentric distance of the power reduction initial point as initial parameter of a power reduction period. The initial parameter determined by the method can ensure a detector to safely fall into a preset target area in soft landing process.