Abstract: A force sensing resistor (FSR) sensor with bladder system provides for ingress protection for FSR sensors by using sealed bladder areas, which act as air reservoirs. A sealed bladder area is attached to an air vent of a sensor area. The sensor area includes two conductive layers forming an open circuit in the static state, the two conductive layers separated by an air cavity. When a force is applied to the sensing area, the two conductive layers are forced toward each other to form a short circuit and the air in the air cavity is forced out the air vent into the bladder area. When the applied force is removed, the air in the bladder area returns into the air cavity separating the two conductive layers to form the open circuit. The bladder area provides a sealed environment within the FSR sensor, ensuring more reliable and consistent measurements.

Abstract: A wearable patch for measuring the biochemical composition of a fluid is disclosed. The wearable patch of the present disclosure may comprise a bonding layer configured to adhere to a subject's skin; a microfluidic chip comprising at least one inlet, a plurality of channels and at least one outlet; an electronic chip assembly comprising at least one sensor, the at least one sensor configured to align with the at least one outlet of the microfluidic chip; a wicking layer configured to move the sweat collected in the at least one outlet through the at least one sensor; and a protective layer.

Abstract: A method and apparatus is provided for calculating an estimate of thrust vectors and burn times for an optimal two-burn orbit transfer from an inclined, eccentric initial orbit to a geostationary final orbit. A non-linear root finding algorithm is used to calculate the thrust vectors and burn times for the optimal two-burn orbit transfer. Thrust vectors and burn times are then computed for an optimal multi-segment orbit transfer from the initial orbit to the final orbit.

Abstract: A method is provided for using at least two lunar flyby maneuvers to transfer a satellite from a quasi-geosynchronous transfer orbit having a high inclination to a final geosynchronous orbit having a low inclination. The invention may be used to take the inclination of a final geosynchronous orbit of a satellite to zero, through the use of a first leading-edge lunar flyby and subsequent successive leading or trailing edge lunar flybys resulting in a geostationary orbit.

Abstract: A method is provided for using a lunar flyby maneuver to transfer a satellite from a quasi-geosynchronous transfer orbit having a high inclination to a final geosynchronous orbit having a low inclination. The invention may be used to take the inclination of a final geosynchronous orbit of a satellite to zero, resulting in a geostationary orbit, provided that the satellite is launched in March or September.