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. An airship comprising: one or more frame members defining a support structure, wherein the support structure supports a hull;the hull comprising at least one envelope configured to retain a volume of a lighter-than-air gas, wherein the envelope is operably coupled to the support structure, and, u
1. An airship comprising: one or more frame members defining a support structure, wherein the support structure supports a hull;the hull comprising at least one envelope configured to retain a volume of a lighter-than-air gas, wherein the envelope is operably coupled to the support structure, and, upon receipt of lighter-than-air gas, defines a substantially oblate spheroid shape; andat least five propulsion assemblies, wherein:a first of the at least five propulsion assemblies is operably coupled to the support structure and located at a foremost portion on a periphery of the hull;a second of the at least five propulsion assemblies is operably coupled to the support structure and located along the periphery at approximately 120 degrees about a central, vertical axis of the hull of the airship with respect to the first propulsion assembly;a third of the at least five propulsion assemblies is operably coupled to the support structure and located along the periphery at approximately negative 120 degrees about the central, vertical axis of the hull of the airship 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 at least five propulsion assemblies along the periphery at approximately 120 degrees about the central, vertical axis of the hull of the airship with respect to the first propulsion assembly; 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 at least five propulsion assemblies along the periphery at approximately negative 120 degrees about the central, vertical axis of the hull of the airship with respect to the first propulsion assembly; andwherein one or both of the second and third propulsion assemblies comprises rotatable directing assemblies for directing a thrust associated with the one or more propulsion assemblies. 2. The airship of claim 1, wherein the at least five propulsion assemblies are configured to provide constant-speed and variable-thrust. 3. The airship of claim 1, wherein the at least five propulsion assemblies include variable pitch propellers. 4. The airship of claim 1, wherein the one or more frame members comprises a substantially carbon-based material. 5. The airship of claim 1, wherein an equatorial diameter associated with the oblate spheroid ranges from about 2.5 to about 3.5 times a polar diameter associated with the oblate spheroid. 6. The airship of claim 1, wherein the airship is configured to perform at least one function associated with lifting objects, elevating a platform, transporting items, displaying items, and transporting humans. 7. The airship of claim 6, wherein operation of the airship to perform the at least one function is related to at least one of assembly of a structure, conducting cellular communications, conducting satellite communications, conducting surveillance, advertising, conducting scientific studies, and providing disaster support services. 8. The airship of claim 1, further comprising: at least one horizontal stabilizing member operably coupled to a lower surface of the airship;a vertical stabilizing member operably coupled to the airship and oriented below an upper surface of the airship; anda gondola assembly operably coupled to a lower side of the support structure and configured to support a person, wherein the gondola assembly includes one or more control devices. 9. The airship of claim 8, wherein the at least one horizontal stabilizing member defines an anhedral configuration. 10. The airship of claim 9, wherein the at least one horizontal stabilizing member is configured to provide support to landing gear associated with the airship. 11. The airship of claim 9, wherein the at least one horizontal stabilizing member comprises one or more landing gear assemblies. 12. The airship of claim 11, wherein the one or more landing gear assemblies comprises at least one of a shock absorber, a wheel, and a pontoon. 13. The airship of claim 8, wherein the vertical stabilizing member is configured to pivot to a position below the lower surface and between at least two of the horizontal stabilizing members. 14. The airship of claim 8, wherein the at least one horizontal stabilizing member comprises at least one control surface. 15. The airship of claim 8, wherein the vertical stabilizing member comprises at least one control surface. 16. The airship of claim 8, wherein the gondola comprises a plurality of members interconnected to form a frame. 17. The airship of claim 8, wherein the one or more control devices includes at least one of a flight stick, a navigation instrument, a pedal, and a throttle. 18. The airship of claim 8, wherein the gondola assembly further comprises at least one forward landing gear assembly. 19. The airship of claim 8, wherein the one or more control devices are operably coupled to one or more of the at least five propulsion assemblies. 20. The airship of claim 19, further including a processor configured to receive input from the one or more control devices. 21. The airship of claim 20, wherein the processor is further configured to transmit signals associated with a desired operation to the one or more propulsion assemblies. 22. The airship of claim 8, further comprising one or more assemblies configured to support at least one crew person. 23. The airship of claim 8, further comprising a cabin assembly operably coupled to the support structure and configured to carry a load. 24. An arrangement for propulsion assemblies associated with an airship, comprising: five propulsion assemblies, wherein:a first of the five propulsion assemblies is operably coupled to a support structure associated with the airship and located on a foremost portion of the hull 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 about a central, vertical axis of the airship 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 about the central, vertical axis of the airship 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 along the periphery at approximately 120 degrees about the central, vertical axis of the hull of the airship with respect to the first propulsion assembly; 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 along the periphery at approximately negative 120 degrees about the central, vertical axis of the hull of the airship with respect to the first propulsion assembly; andwherein one or both of the second and third propulsion assemblies further comprises directing assemblies for enabling vectoring of a thrust associated with the propulsion assembly. 25. The arrangement of claim 24, wherein the first propulsion assembly is configured to cause a pitching motion and a yawing motion associated with the airship depending on a control signal and a thrust vector associated with the first propulsion assembly. 26. The arrangement of claim 24, wherein the five propulsion assemblies are operably connected to a keel hoop associated with the airship via a three-point mount assembly. 27. The arrangement of claim 26, wherein the mount assembly substantially comprises a carbon-based material. 28. The arrangement of claim 24, wherein at least three of the five propulsion assemblies are configured for constant-speed operation. 29. The arrangement of claim 28, wherein at least three of the five propulsion assemblies are configured to provide variable thrust. 30. The arrangement of claim 24, wherein at least three of the five propulsion assemblies are configured to provide variable speed and variable thrust. 31. The arrangement of claim 24, wherein the five propulsion assemblies include variable pitch propellers. 32. The arrangement of claim 31, wherein the variable pitch propellers comprise a substantially carbon-based material. 33. The arrangement of claim 24, wherein the directing assembly comprises a substantially carbon-based material. 34. The arrangement of claim 33, wherein the carbon-based material comprises a honeycomb carbon fiber. 35. The arrangement of claim 34, wherein the directing assembly is rotatable about at least one axis associated with the propulsion assembly. 36. The arrangement of claim 35, wherein the at least one axis is a horizontal axis. 37. The arrangement of claim 24, wherein the propulsion assemblies are powered by at least one of electricity and a fuel. 38. The arrangement of claim 24, wherein the propulsion assemblies are communicatively connected to at least one of a flight stick, a navigation instrument, a pedal, and a throttle. 39. The arrangement of claim 24, wherein the airship is configured to perform at least one function associated with lifting objects, elevating a platform, transporting items, displaying items, and transporting humans. 40. The arrangement of claim 39, wherein operation of the airship to perform the at least one function is related to at least one of assembly of a structure, conducting cellular communications, conducting satellite communications, conducting surveillance, advertising, conducting scientific studies, and providing disaster support services. 41. The arrangement of claim 24, wherein the propulsion assemblies are communicatively connected to a processor configured to send signals indicative of a desired operation to the one or more propulsion assemblies. 42. The arrangement of claim 41, wherein the five propulsion assemblies are configured to receive a control signal. 43. The arrangement of claim 42, wherein the control signal is configured to cause a modification to an operating parameter associated with one or more of the five propulsion assemblies. 44. The arrangement of claim 43, wherein the operating parameter comprises a propeller pitch. 45. The arrangement of claim 43, wherein the operating parameter comprises a thrust vector. 46. The arrangement of claim 43, wherein the control signal is transmitted via a fly-by-wire system. 47. The arrangement of claim 43, wherein the control signal is transmitted via a fly-by-light system.
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