The invention discloses a hovercraft using single ducted fan with vectoring propulsion, including a hull and a single ducted fan arranged on the hull, wherein the single ducted fan comprises barrel shaped shell and oar-blade component arranged in chamber of the shell, a first air outlet is disposed on one side of shell towards the tail end of the hull, diversion rudders enabling to block the first air outlet are disposed on the shell, two first air guide all connected with chamber of the shell is disposed on both sides of the shell, a second air outlet towards external of the single ducted fan is disposed on the first air guide, and the second air outlet and the first air outlet are arranged in reverse or with an included angle greater than 0 degree.

A hovercraft includes a lift air supply source having a dynamic air flow area in communication with a central lift air chamber to provide continuous air flow to the central lift air chamber and a static air flow area in communication with an inflatable skirt extending around a periphery of the hovercraft. Air flow from the static air flow area enters the skirt to replenish air leaking from the skirt. The static air flow area has less air flow than the dynamic air flow area. The static air flow area is located at a higher position than the dynamic air flow area to reduce the likelihood of water entering the inflatable skirt when the hovercraft is operated on water.

A hovercraft including imaginary longitudinal, transverse and vertical axes; a propulsion system (12), configured to generate airflow; a base (50) and, a skirt (13) wherein the skirt (13) further including air permeable regions (130) and at least two set of outflow nozzles (220); wherein the air permeable regions (130) and the set of outflow nozzles (20, 21) are in fluid communication; wherein each set of nozzles (20, 21) comprises, at least, one outflow nozzle (22), said outflow nozzle (22) including two opposing ends, a first end (221) and a second end (222); the hovercraft further including actuating means (30) suitable to control the opening of at least one end (221 or 222) of the nozzles (22) managing the passage of airflow through the end (221 or 222). The technical features and functionalities described herein are applicable to the field of hovercrafts. More particularly, to controllable outflow nozzles and controlling systems for hovercrafts.

In one aspect there is provided an air caster comprising a platform to support a load above a surface, a skirt, wherein said skirt cooperates with said platform to define an interior volume, at least one air inlet to allow air to enter said interior volume, at least one air exit to allow air to exit said interior volume, and a skirt stabilizer operable to create a substantially airtight seal between the skirt and the surface, said airtight seal being formed circumferentially around said at least one air exit when the air caster is in a resting state.

A hovercraft including imaginary longitudinal, transverse and vertical axes; a propulsion system (12), configured to generate airflow; a base (50) and, a skirt (13) wherein the skirt (13) further including air permeable regions (130) and at least two set of outflow nozzles (220); wherein the air permeable regions (130) and the set of outflow nozzles (20, 21) are in fluid communication; wherein each set of nozzles (20, 21) comprises, at least, one outflow nozzle (22), said outflow nozzle (22) including two opposing ends, a first end (221) and a second end (222); the hovercraft further including actuating means (30) suitable to control the opening of at least one end (221 or 222) of the nozzles (22) managing the passage of airflow through the end (221 or 222). The technical features and functionalities described herein are applicable to the field of hovercrafts. More particularly, to controllable outflow nozzles and controlling systems for hovercrafts.

A pneumatic device may be configured and used to provide multiple movement related functions, such as in an automated assembly system. The pneumatic device may comprise a chamber; a sealing element configurable to contact a surface, to enable creating a seal around the chamber by application of pneumatic suction into the chamber; a biasing element configurable to push the sealing element away from the surface; and a pneumatic cushion configurable to expand by application of pneumatic inflow, thus urging the pneumatic device away from the surface.

A hovercraft includes a lift air supply source having a dynamic air flow area in communication with a central lift air chamber to provide continuous air flow to the central lift air chamber and a static air flow area in communication with an inflatable skirt extending around a periphery of the hovercraft. Air flow from the static air flow area enters the skirt to replenish air leaking from the skirt. The static air flow area has less air flow than the dynamic air flow area. The static air flow area is located at a higher position than the dynamic air flow area to reduce the likelihood of water entering the inflatable skirt when the hovercraft is operated on water.

Devices, systems, and related methods for balancing two or more pieces of independently rotating (e.g., not synchrophased) machinery are provided. In some aspects, the devices, systems, and methods can provide improved balancing techniques and can include providing a controller configured to simultaneously measure/receive vibration data and control balancers, one balancer at a time. In some aspects, the controller can calculate a beating cycle or a beating period using vibration data received from multiple rotating machines. In some aspects, a balance correction command can be derived in part from either one of: (a) an interpolation of an average vibration of the first rotating machine from a complex vibration of the multiple rotating machines or (b) an average vibration derived from one or more rules applied based upon the duration of the beating period or the beating cycle.

The invention discloses a hovercraft using single ducted fan with vectoring propulsion, including a hull and a single ducted fan arranged on the hull, wherein the single ducted fan comprises barrel shaped shell and oar-blade component arranged in chamber of the shell, a first air outlet is disposed on one side of shell towards the tail end of the hull, diversion rudders enabling to block the first air outlet are disposed on the shell, two first air guide all connected with chamber of the shell is disposed on both sides of the shell, a second air outlet towards external of the single ducted fan is disposed on the first air guide, and the second air outlet and the first air outlet are arranged in reverse or with an included angle greater than 0 degree.

An air cushioned landing system for an air vehicle comprises an inflatable and deflatable skirt (113) in the form of a tube having inner (101) and outer (100) walls. The inner wall defines a central plenum (116) within the skirt, the skirt including gas pockets (130) arranged to stiffen one or more regions of at least one of the inner (101) and outer (100) sidewalls during deflation of the skirt. A gas pocket fan inflates the gas pockets prior to and during deflation of the skirt, wherein the gas pockets are constrained to move from a mutually spaced apart position when the skirt is inflated, to a mutually closely adjacent position when the skirt is fully deflated.