An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship
An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member having a first end and a second end. The at least one horizontal stabilizing member may define an anhedral configuration. The airship may also include a vertical stabilizing member having a first end pivotally coupled to the airship and a second end oriented to remain below an upper surface of the airship. The vertical stabilizing member may be configured to pivot within a vertical plane, and the first end of the vertical stabilizing member and the first end of the at least one horizontal stabilizing member may be operably coupled to one another.
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1. A flight control system for an airship, the system comprising: one or more operator controls configured to receive operator input;a horizontal control surface associated with a horizontal stabilizing member;a vertical control surface associated with a vertical stabilizing member; andat least five
1. A flight control system for an airship, the system comprising: one or more operator controls configured to receive operator input;a horizontal control surface associated with a horizontal stabilizing member;a vertical control surface associated with a vertical stabilizing member; andat least five propulsion assemblies, wherein: a first of the five propulsion assemblies is operably coupled to a support structure associated with the airship and located at a first location along a periphery associated with the airship;a second of the five propulsion assemblies is operably coupled to the support structure and located along the periphery at approximately 120 degrees with respect to the first propulsion assembly;a third of the five propulsion assemblies is operably coupled to the support structure and located along the periphery at approximately negative 120 degrees with respect to the first propulsion assembly;a fourth propulsion assembly configured to direct a thrust along an axis substantially parallel to a roll axis of the airship and substantially co-located with the second of the five propulsion assemblies; anda fifth propulsion assembly configured to direct a thrust along an axis substantially parallel to the roll axis of the airship and substantially co-located with the third of the five propulsion assemblies; anda processor configured to receive an input signal from the operator controls and generate a signal according to the input signal. 2. The flight control system of claim 1, wherein at least one of the five propulsion assemblies comprises a variable pitch propeller. 3. The flight control system of claim 2, wherein the signal is configured to cause a modification to a pitch associated with a variable pitch propeller. 4. The flight control system of claim 1, further comprising one or more propulsion servo motors operably coupled to any of the five propulsion assemblies. 5. The flight control system of claim 4, further comprising one or more horizontal control surface servo motors operably coupled to the horizontal control surface, and one or more vertical control surface servo motors operably coupled the vertical control surface. 6. The flight control system of claim 5, wherein the signal is provided to any of the one or more propulsion servo motors, one or more horizontal control surface servo motors, and one or more vertical control surface servo motors via a fly-by-wire system. 7. The flight control system of claim 5, wherein the signal is provided to any of the one or more propulsion servo motors, one or more horizontal control surface servo motors, and one or more vertical control surface servo motors via a fly-by-light system. 8. The flight control system of claim 1, wherein the processor is configured to generate signals configured to: navigate the airship within close proximity to a surface of the earth;direct a thrust associated with at least one propulsion assembly in a direction configured to impart a downward force to the airship; andlimit motion of the airship until a securing of the airship to a ground fixture has been substantially completed. 9. The flight control system of claim 8, wherein the signal is configured to modify an operational parameter of at least one of the first propulsion assembly, the second propulsion assembly, the third propulsion assembly, the fourth propulsion assembly, and the fifth propulsion assembly, to cause a reduction of a horizontal velocity associated with the airship and a reduction of an altitude associated with the airship. 10. The flight control system of claim 8, wherein directing thrust is accomplished via modification to a pitch associated with a variable pitch propeller. 11. The flight control system of claim 1, wherein the processor is configured to: receive an input indicative of a take-off type;provide, based on the take-off type, a signal configured to modify operating parameters associated with one or more of the five propulsion assemblies to achieve a desired thrust direction;determine, based on the take-off type, a lift force associated with a lighter-than-air gas provided within a hull of the airship, and aerodynamic forces associated with the hull, a power setting for the five propulsion assemblies; andprovide one or more signals to at least one control surface associated with the airship according to the take-off type. 12. The flight control system of claim 11, wherein the take-off type comprises a substantially vertical take-off. 13. The flight control system of claim 11, wherein the take-off type comprises a taxiing take-off. 14. The flight control system of claim 1, wherein the processor is configured to: determine a horizontal velocity and a pitch associated with the airship;calculate a delta between a predetermined critical speed value and the horizontal velocity associated with the airship; andtransmit a signal based on the delta and the pitch associated with the airship to at least one of the first propulsion assembly, the second propulsion assembly, the third propulsion assembly, the fourth propulsion assembly, and the fifth propulsion assembly. 15. The flight control system of claim 14, wherein the signal is configured to cause a modification in an operating parameter associated with at least one of the first propulsion assembly, the second propulsion assembly, the third propulsion assembly, the fourth propulsion assembly, and the fifth propulsion assembly, such that a force tending to counteract an aerodynamically generated pitching moment is generated. 16. The flight control system of claim 15, wherein the processor is further configured to transmit a second signal to the horizontal control surface based on the delta and the pitch associated with the airship. 17. The flight control system of claim 16, wherein the second signal is configured to manipulate the horizontal control surface to generate an additional force configured to counteract the pitching moment. 18. The flight control system of claim 1, wherein the processor is configured to: receive a signal indicative of a desired pitch associated with the airship;determine at least one of a power setting and a propeller pitch associated with the first propulsion assembly based on the signal indicative of a desired pitch;determine a horizontal control surface setting based on at least one of the power setting, the propeller pitch, and the signal indicative of a desired pitch;transmit a first control signal indicative of the power setting and the propeller pitch; andtransmit a second control signal indicative of the horizontal control surface setting configured to cause the horizontal control surface to respond according to the horizontal control surface setting. 19. The flight control system of claim 18, wherein the signal indicative of a desired pitch is received from an operator of the airship. 20. The flight control system of claim 18, wherein the signal indicative of a desired pitch is calculated by the processor based on a flight plan. 21. The flight control system of claim 1, wherein the processor is configured to: receive a signal indicative of a desired yaw associated with the airship;determine at least one of a power setting and a propeller pitch associated with the fourth propulsion assembly and the fifth propulsion assembly based on the signal indicative of a desired yaw;determine a vertical control surface setting based on at least one of the power setting, the propeller pitch, and the signal indicative of a desired yaw;transmit a first control signal indicative of the power setting and the propeller pitch; andtransmit a second control signal indicative of the vertical control surface setting configured to cause the vertical to respond according to the vertical control surface setting. 22. The flight control system of claim 21, wherein the signal indicative of a desired yaw is received from at least one of an operator of the airship and the processor based on a flight plan. 23. The flight control system of claim 1, wherein the processor is configured to: receive a signal indicative of a desired roll associated with the airship;determine at least one of a power setting and a propeller pitch associated with the second propulsion assembly and the third propulsion assembly based on the signal indicative of a desired roll;determine a horizontal control surface setting based on at least one of the power setting, the propeller pitch, and the signal indicative of a desired roll;transmit a first control signal indicative of the power setting and the propeller pitch; andtransmit a second control signal indicative of the horizontal control surface setting configured to cause the horizontal control surface to respond according to the horizontal control surface setting. 24. The flight control system of claim 23, wherein the signal indicative of a desired roll is received from an operator of the airship. 25. The flight control system of claim 23, wherein the signal indicative of a desired roll is calculated by the processor based on a flight plan.
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