초록 ▼

Vibration isolation devices and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage having a first fuselage section and a second fuselage section adjacent to and at least approximately longitudinally aligned with the first

Vibration isolation devices and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage having a first fuselage section and a second fuselage section adjacent to and at least approximately longitudinally aligned with the first fuselage section. The aircraft can also include at least one vibration isolation device coupling the first fuselage section to the second fuselage section. The vibration isolation device is translationally stiffer along a longitudinal axis than it is along a lateral and a vertical axis, and rotationally stiffer about a pitch and a yaw axis than it is about a roll axis.

대표청구항 ▼

1. An unmanned aircraft system, comprising: a fuselage having a first fuselage section and a second fuselage section adjacent to and at least approximately longitudinally aligned with the first fuselage section; andat least one vibration isolation device coupling the first fuselage section to the se

1. An unmanned aircraft system, comprising: a fuselage having a first fuselage section and a second fuselage section adjacent to and at least approximately longitudinally aligned with the first fuselage section; andat least one vibration isolation device coupling the first fuselage section to the second fuselage section, wherein the vibration isolation device is— translationally stiffer along a longitudinal axis than it is along a lateral axis and a vertical axis; androtationally stiffer about a pitch axis and a yaw axis than it is about a roll axis. 2. The unmanned aircraft system of claim 1 wherein the individual vibration isolation devices comprise: a first member attached to the first fuselage section with a first fastener;a second member attached to the second fuselage section with a second fastener; anda tensioning member connected to and extending between the first member and the second member. 3. The unmanned aircraft system of claim 2 wherein: the tensioning member includes a first wire and a second wire;the first member includes a first clamping plate engaged with a first end portion of each of the first and second wires; andthe second member includes a second clamping plate engaged with a second end portion of each of the first and second wires. 4. The unmanned aircraft system of claim 2 wherein: the first member includes a non-linear first mating surface facing the second member; andthe second member includes a non-linear second mating surface configured to mate with the first mating surface, and wherein the first and second mating surfaces define, at least in part, one interlocking finger. 5. The unmanned aircraft system of claim 1, further comprising a rubber shear spring between the first and second fuselage sections, and wherein the individual vibration isolation devices comprises: a first member attached to the first fuselage section, the first member including a first ball joint;a second member attached to the second fuselage section, the second member including a second ball joint; anda ball link connected to and extending between the first member and the second member. 6. The unmanned aircraft of claim 1 wherein the at least one vibration isolation device comprises: two or more compressible layers in contact with and between the first and second fuselage sections, wherein the compressible layers are composed of a generally compressible material; anda constraining layer between the individual compressible layers, wherein the constraining layer is composed of a generally rigid material. 7. The unmanned aircraft system of claim 1 wherein the first fuselage section is spaced apart from the second fuselage section by a gap, and wherein the vibration isolation device further comprises a generally compressible material between and in contact with the first fuselage section and the second fuselage section. 8. The unmanned aircraft system of claim 1 wherein multiple vibration isolation devices are arranged generally symmetrically about an outer circumference of the fuselage and positioned to couple the first fuselage section to the second fuselage section. 9. The unmanned aircraft system of claim 1 wherein: the first fuselage section is a nose portion of the aircraft including a turret assembly and a surveillance payload carried by a gimbal system; andthe second fuselage section is immediately aft of the first fuselage section. 10. The unmanned aircraft system of claim 1, further comprising a rope deflection assembly carried by one or more vibration isolation devices. 11. The unmanned aircraft system of claim 1 wherein the aircraft is a piston-powered aircraft. 12. An aircraft system, comprising: an unmanned aircraft having a fuselage and a pair of wings extending from the fuselage;a first component carried by the aircraft;a second component carried by the aircraft and positioned adjacent to the first component; anda vibration isolation assembly coupling the first component to the second component, wherein the vibration isolation assembly is configured to (a) resist relative movement between the first and second components with respect to one translational degree of freedom and two rotational degrees of freedom, and (b) allow relative movement between the first and second components with respect to two translational degrees of freedom and one rotational degree of freedom. 13. The aircraft system of claim 12 wherein the vibration isolation assembly is configured to: resist relative movement between the first and second components with respect to the longitudinal axis, the pitch axis, and the yaw axis; andallow relative movement between the first and second components with respect to the lateral axis, the vertical axis, and the roll axis. 14. The aircraft system of claim 12 wherein the vibration isolation assembly comprises: a first member attached to the first component;a second member attached to the second component; anda tensioning member connected to and extending between the first member and the second member. 15. The aircraft system of claim 14 wherein: the first member includes a first base having a non-linear first mating surface, a first channel positioned to receive a portion of the tensioning member, and a first clamping plate positioned to engage the tensioning member, and wherein the non-linear first mating surface faces the second member; andthe second member includes a second base having a non-linear second mating surface configured to mate with the first mating surface, a second channel positioned to receive another portion of the tensioning member, and a second clamping plate positioned to engage the tensioning member, and wherein the first and second mating surfaces define, at least in part, one interlocking finger. 16. The aircraft system of claim 14 wherein: the tensioning member includes a first wire and a second wire;the first member includes a first clamping plate engaged with a first end portion of each of the first and second wires; andthe second member includes a second clamping plate engaged with a second end portion of each of the first and second wires. 17. The aircraft system of claim 12 wherein: the first component is an engine carried by the aircraft; andthe second component is a fuselage section immediately adjacent to the engine. 18. The aircraft system of claim 12 wherein: the first component is a payload carried by the aircraft; andthe second component is a portion of the aircraft immediately adjacent to the payload. 19. The aircraft system of claim 12 wherein the vibration isolation assembly is a removable feature configured to be releasably attached to the respective first and second components. 20. The aircraft system of claim 12 wherein the vibration isolation assembly is a generally non-removable feature fixedly attached to the respective first and second components. 21. The aircraft system of claim 12 wherein first component is spaced apart from the second component by a gap, and wherein the vibration isolation assembly further comprises a generally compressible material between and in contact with the first and second components. 22. An aircraft system, comprising: an unmanned aircraft including a fuselage having (a) a first fuselage section including a nose portion with a turret assembly and a surveillance payload carried by a gimbal system, and (b) a second fuselage section immediately aft of and at least approximately longitudinally aligned with the first fuselage section; anda plurality of vibration isolation devices arranged generally symmetrically about an outer circumference of the fuselage and positioned to couple the first fuselage section to the second fuselage section, wherein each vibration isolation device is— translationally stiffer along a longitudinal axis than it is along a lateral axis and a vertical axes; androtationally stiffer about a pitch axis and a yaw axis than it is about a roll axis; andwherein the individual vibration isolation devices include— a tensioning member connected to and extending between a first member attached to the first fuselage section and a second member attached to the second fuselage section, wherein the tensioning member includes a first wire and a second wire,wherein the first member including a first base having a non-linear first mating surface, a first channel, and a first clamping plate engaged with a first end portion of each of the first and second wires, and wherein the non-linear first mating surface faces the second member, andwherein the second member includes a second base having a non-linear second mating surface configured to mate with the first mating surface, a second channel positioned to receive another portion of the tensioning member, and a second clamping plate engaged with a second end portion of each of the first and second wires, and wherein the first and second mating surfaces define, at least in part, one interlocking finger. 23. The aircraft system of claim 22 wherein the vibration isolation devices are removable features configured to be releasably attached to the respective first and second fuselage sections and positioned to mate the two sections together. 24. The aircraft system of claim 22 wherein the vibration isolation devices are generally non-removable features secured to the respective first and second components and positioned to mate the two sections together.