An operation method of the blasting system according to the embodiments includes: generating a blasting design including at least one of blasting hole information, explosive information and detonator information based on a base map for a blasting site; forming a plurality of blasting holes based on the blasting design, and complementing the blasting design according to drilling data generated by the drilling device; charging at least one of an explosive and an electronic detonator into the blasting holes based on the blasting design, and complementing the blasting design according to charging data generated by the charging device; and performing a detonator setting on a plurality of electronic detonators corresponding to the blasting holes based on the blasting design, and complementing the blasting design according to setting data generated by the detonator setting device.

An operation method of the blasting system according to the embodiments includes: generating a blasting design including at least one of blasting hole information, explosive information and detonator information based on a base map for a blasting site; forming a plurality of blasting holes based on the blasting design, and complementing the blasting design according to drilling data generated by the drilling device; charging at least one of an explosive and an electronic detonator into the blasting holes based on the blasting design, and complementing the blasting design according to charging data generated by the charging device; and performing a detonator setting on a plurality of electronic detonators corresponding to the blasting holes based on the blasting design, and complementing the blasting design according to setting data generated by the detonator setting device.

Systems and methods for sensor emplacement using unmanned aircraft systems (UASs). In some examples, a UAS includes a propulsion system and a sensor emplacement system including an auger and one or more motors. The UAS includes a control system configuring for controlling the propulsion system to land the UAS at a sensor emplacement site and controlling the one or more motors of the sensor emplacement system to drive the auger into soil at the sensor emplacement site. The control system is configured for measuring one or more augering parameters from the sensor emplacement system; and determining, using an autonomous system trained on soil data and augering data, one or more soil classification values for the soil based on the one or more augering parameters.

Systems and methods for sensor emplacement using unmanned aircraft systems (UASs). In some examples, a UAS includes a propulsion system and a sensor emplacement system including an auger and one or more motors. The UAS includes a control system configuring for controlling the propulsion system to land the UAS at a sensor emplacement site and controlling the one or more motors of the sensor emplacement system to drive the auger into soil at the sensor emplacement site. The control system is configured for measuring one or more augering parameters from the sensor emplacement system; and determining, using an autonomous system trained on soil data and augering data, one or more soil classification values for the soil based on the one or more augering parameters.

Battery modules for unmanned and human piloted electric aircraft comprise two planar substrates with electrochemical cells secured between to form load-bearing structural components from which aircraft with greater endurance can be constructed. The cells can be oriented perpendicular or parallel to the substrates, and in the latter case the substrates can include slots that the cells fit into. The cells can be secured to the substrates by adhesives, welding, soldering and the like, as well as by mechanical tensioners. Battery modules can be formed to the shapes of aircraft parts such as wings. Multirotor aircraft are disclosed in which the arms and other parts of the aircraft are constructed from such battery modules.

Battery modules for unmanned and human piloted electric aircraft comprise two planar substrates with electrochemical cells secured between to form load-bearing structural components from which aircraft with greater endurance can be constructed. The cells can be oriented perpendicular or parallel to the substrates, and in the latter case the substrates can include slots that the cells fit into. The cells can be secured to the substrates by adhesives, welding, soldering and the like, as well as by mechanical tensioners. Battery modules can be formed to the shapes of aircraft parts such as wings. Multirotor aircraft are disclosed in which the arms and other parts of the aircraft are constructed from such battery modules.

Applicant provides a number of embodiments of a sealant, the sealant comprising a polyurethane gel which, in some embodiments, has a thickness of 12 mil or less (uncompressed). Uses of the sealant are shown, including uses between aircraft parts under compression. Sometimes the sealant may have a very thin skeleton. Sometimes the sealant is in the form of a die cut gasket, a tape or a tacky gel sprayable. Methods for making the sealant are also disclosed. The sealants may be used pre-cured or may be sprayed on to the aircraft parts and form in place.

An unmanned aerial vehicle (UAV) including a fuselage frame and a propulsion system coupled to the fuselage frame. The propulsion system includes a first propulsion device and a second propulsion device. The first propulsion device includes a first rotor blade assembly and a first rotor mount assembly, and the second propulsion device includes a second rotor blade assembly and a second rotor mount assembly. The first rotor mount assembly is configured to not allow the second rotor blade assembly to be assembled to the first rotor mount assembly.

An unmanned vehicle including a body and a frame structure extending from the body and supporting a plurality of propeller assemblies, each propeller assembly including at least one propeller and a corresponding motor with the motor housed in a watertight housing or coated and made corrosion resistant. The propellers comprise a first subset of propellers of the propeller assemblies and a second subset of propellers of the propeller assemblies which rotate in a plane positioned below a plane in which the first subset of propellers rotate, wherein said first and second subset of propellers are configured for independent operation of one another as the vehicle transitions from an air medium to a water medium.

An apparatus according to an embodiment includes a receptacle configured to be coupled to an aerial vehicle, a winch configured to be coupled to the receptacle and the aerial vehicle, and a grasper having a multi-bar linkage. The grasper is configured to be coupled to the winch by a tether. The multi-bar linkage of the grasper is configured to be releasably coupled to a package. The grasper is configured to be rotated to a predefined alignment as the winch raises the grasper and the grasper contacts the receptacle.