Message transmission assembly

A message transmission assembly for sending a message to emergency responders in an area with limited cellular communication signal, said assembly comprising:

• an unmanned aerial vehicle having flight capabilities wherein said unmanned aerial vehicle is configured to fly at a predetermined altitude, said unmanned aerial vehicle having a fuselage and a plurality of propulsion units each being coupled to said fuselage, said fuselage having a top surface and a perimeter surface, each of said propulsion units being coupled to and extending away from said perimeter surface, said propulsion units being distributed around said fuselage;
• a communication unit being integrated into said unmanned aerial vehicle, said communication unit having signal reception capabilities thereby facilitating said communication unit to receive a communication signal wherein said communication unit is configured to be in wireless communication with an extrinsic communication network when said unmanned aerial vehicle is flown at the predetermined altitude, said communication unit broadcasting an emergency signal when said communication unit receives the communication signal wherein said communication unit is configured to alert emergency responders to an emergency, said communication unit comprising:
• a control circuit being integrated into said fuselage, said control circuit receiving a successful connection input, said control circuit receiving a failed connection input, said control circuit being electrically coupled to each of said propulsion units;
• a first transceiver being integrated into said fuselage for receiving the communication signal from the extrinsic communication network, said control circuit receiving said successful connection input when said first transceiver receives the communication signal, said control circuit receiving said failed connection input when said first transceiver fails to receive the communication signal, said first transceiver broadcasting said emergency signal when said control circuit receives said successful connection input;
• a display being coupled to said top surface of said fuselage wherein said display is configured to be visible to a user, said display being electrically coupled to said control circuit, said display displaying sent indicia when said control circuit receives said successful connection input wherein said display is configured to communicate to the user that the emergency responders have been contacted, said display displaying not sent indicia when said control circuit receives said failed connection input wherein said display is configured to communicate to the user that the emergency responders were not contacted;
• a first light emitter being coupled to said top surface of said fuselage wherein said first light emitter is configured to emit light outwardly therefrom, said first light emitter being electrically coupled to said control circuit, said first light emitter being turned on when said control circuit receives said successful connection input wherein said first light emitter is configured to visually communicate to the user that the emergency responders have been contacted;
• and
• a second light emitter being coupled to said top surface of said fuselage wherein said second light emitter is configured to emit light outwardly therefrom, said second light emitter being electrically coupled to said control circuit, said second light emitter being turned on when said control circuit receives said failed connection input wherein said second light emitter is configured to visually communicate to the user that the emergency responders have not been contacted;
• a location unit being integrated into said unmanned aerial vehicle, said location unit being in wireless communication with a global positioning system wherein said location unit is configured to receive the physical location of said unmanned aerial vehicle when said unmanned aerial vehicle is launched, said location unit communicating the physical location of said unmanned aerial vehicle to said communication unit wherein said communication unit is configured to communicate the physical location of said unmanned aerial vehicle to the emergency responders thereby facilitating the emergency responders to locate the user, said location unit comprising a second transceiver being integrated into said fuselage, said second transceiver being electrically coupled to said control circuit, said second transceiver being in wireless communication with the global positioning system, said second transceiver communicating the physical location of said unmanned aerial vehicle to said control circuit when said control circuit receives said successful connection input thereby facilitating said first transceiver to communicate the physical location to the emergency responders, said control circuit actuating each of said propulsion units to guide said unmanned aerial vehicle in a continually expanding spiral with respect to the physical location of the launch site of said unmanned aerial vehicle until said control circuit receives said successful connection input, said control circuit actuating each of said propulsion units to guide said unmanned aerial vehicle back to the launch site when said control circuit receives said failed connection input after a pre-determined duration of time has passed;
• a launch button being movably integrated into said fuselage, said launch button being electrically coupled to said control circuit, said control circuit actuating each of said propulsion units to fly said unmanned aerial vehicle when said launch button is depressed;
• a strobe light being coupled to said fuselage wherein said strobe light is configured to emit light outwardly therefrom, said strobe light being electrically coupled to said control circuit, said strobe light being turned on when said launch button is depressed wherein said strobe light is configured to enhance visibility of said unmanned aerial vehicle when said unmanned aerial vehicle is in flight;
• and
• a power supply being integrated into said unmanned aerial vehicle, said power supply being electrically coupled to said control circuit, said power supply comprising:
• at least one battery being positioned within said fuselage, said power supply being electrically coupled to said control circuit;
• a solar panel being coupled to said top surface of said fuselage wherein said solar panel is configured to be exposed to sunlight, said solar panel being electrically coupled to said at least one battery for charging said at least one battery;
• a charge indicator being coupled to said fuselage wherein said charge indicator is configured to be visible to the user, said charge indicator being electrically coupled to said at least one battery, said charge indicator indicating a charge of said at least one battery ranging between a minimum charge and a maximum charge;
• a charge port being recessed into said fuselage wherein said charge port is configured to receive a charge cord, said charge port being electrically coupled to said at least one battery for charging said at least one battery;
• and
• a switch being slidably integrated into said fuselage wherein said switch is configured to be manipulated by the user, said switch being electrically coupled to said control circuit for turning said control circuit on and off.