An aerial craft and sealed force vectoring flight system is disclosed. The aerial craft includes a main body hull, lift jets, a generator, an electrical re-introduction circuit, a hydraulic pump, air flow compressors, an RPM sensor, a max speed limiter hydraulic draft by-pass valve, and a battery. The electrical re-introduction circuit throttles the generator into high-velocity rotation and yields excess electrical current to then be applied to the lift jets. The hydraulic pump pulls pressurized hydraulic fluid across a preceding hydraulic drive impellor such that the pressurized hydraulic fluid returns to confinement under pneumatic pressure faster than a discharge of hydraulic fluid. The air flow compressors generate electricity that is re-introduced into the lift electric motors. The RPM sensor and max speed limiter hydraulic draft by-pass valve speed regulate the generator. The battery initially powers the generator.

An equipment monitoring system includes an unmanned vehicle, an alarm circuit remote from the unmanned vehicle, and a vehicle control circuit remote from the unmanned vehicle. The unmanned vehicle can include a communications circuit and a flight controller. The alarm circuit detects a failure condition of a building component and outputs an indication of the failure condition. The vehicle control circuit receives the indication of the failure condition from the alarm circuit; generates, based on the indication of the failure condition, an equipment verification signal that includes an identifier of the building component, a position of the building component, and a test of the building component to be executed; and transmits the equipment verification signal to the flight controller of the unmanned vehicle via the communications circuit of the unmanned vehicle to cause the unmanned vehicle to execute the test of the building component.

An equipment monitoring system includes an unmanned vehicle, an alarm circuit remote from the unmanned vehicle, and a vehicle control circuit remote from the unmanned vehicle. The unmanned vehicle can include a communications circuit and a flight controller. The alarm circuit detects a failure condition of a building component and outputs an indication of the failure condition. The vehicle control circuit receives the indication of the failure condition from the alarm circuit; generates, based on the indication of the failure condition, an equipment verification signal that includes an identifier of the building component, a position of the building component, and a test of the building component to be executed; and transmits the equipment verification signal to the flight controller of the unmanned vehicle via the communications circuit of the unmanned vehicle to cause the unmanned vehicle to execute the test of the building component.

Systems and methods for calculating launch sites for a satellite constellation are provided. A carrier aircraft may be configured to launch a first satellite into the first orbit and a second satellite into the second orbit. In some embodiments, information about an accessible range of the aircraft may be received. Based on the received information, a geographical area that the aircraft can access without landing may be calculated. Using received information and the orbit parameters of the first orbit and the second orbit, a first launch site for launching the first satellite and a second launch site for launching the second satellite may be calculated. The first launch site may comprise a first geographical position and a first launch time, and the second launch site may comprise a second geographical position and a second launch time. Both launch sites may be within the calculated geographical area.

There is provided a leading edge system for an aerospace vehicle. The leading edge system has at least one structural member. The leading edge system further has a plurality of removable modules removably attached to the at least one structural member. Each removable module has a hollow box substructure and at least one flange portion disposed along a first end of the hollow box substructure. The leading edge system further has a plurality of first attachment elements configured for attaching the at least one flange portion of the removable module to a first end portion of the at least one structural member. The leading edge system further has a plurality of second attachment elements configured for attaching a second end of the hollow box substructure opposite the flange portion, to a second end portion of the at least one structural member opposite the first end portion.

A plurality of space vehicles forming a satellite constellation, each space vehicle comprising a housing having a first side and an opposite side, and an axis; a first elongated, rectangular sheet including an array of transducer devices including multijunction solar cells mounted on, and extending from a surface of the first side of the housing, and a second elongated rectangular sheet including an array of transducer devices including multijunction solar cells mounted on and extending from a surface of the second side of the housing in a direction opposite to that of the first elongated rectangular sheet, wherein the selection of the composition of the subcells and their band gap of the multijunction solar cells maximizes the efficiency of the solar cell at the end-of-life EOL in the application of one of (i) a low earth orbit (LEO) satellite that typically experiences radiation equivalent to 510.sup.14 electron fluence per square centimeter (e/cm.sup.2) over a five year EOL, or (ii) a geosynchronous earth orbit (GEO) satellite that typically experiences radiation in the range of 510.sup.14 e/cm.sup.2 to 110.sup.15 e/cm.sup.2 over a fifteen year EOL, with the efficiency of the multijunction solar cells being less at the beginning-of-life (BOL) than the end-of-life (EOL).

The disclosed embodiments describe an integrated aerial exploration system for deployment on a planetary surface, the system including: a rotorcraft configured for flight in a low-density atmosphere and adapted to carry a scientific payload; an enclosure housing the rotorcraft during launch, transit, and landing, the enclosure including a mounting interface for attachment to a host vehicle and a cover movable to provide an opening for deployment of the rotorcraft; and a deployment mechanism configured, upon activation, to move the rotorcraft from within the enclosure to a position outside the enclosure through said opening; where activation of the deployment mechanism automatically releases the rotorcraft from the enclosure and deploys one or more stowed components of the rotorcraft into a flight-ready configuration for aerial operation.