A large volume natural gas storage tank comprises rigid tubular walls having closed tubular cross-sections that are interconnected at opposing ends with two other rigid tubular walls such that interiors of the rigid tubular walls define an interior fluid storage chamber. The storage tank also includes bulkheads positioned in the interior fluid storage chamber across intermediate segments of the rigid tubular walls and closure plates connected between exterior surfaces of successive interconnected rigid tubular walls to define sides of the storage tank. Interior surfaces of the closure plates and exterior surfaces of the rigid tubular walls define an auxiliary fluid storage chamber. The storage tank also includes exterior support structures extending through the closure plates and between the exterior surfaces of the rigid tubular walls on some of the sides of the storage tank to reinforce the storage tank against dynamic loading from fluid in the interior fluid storage chamber.

Provided is a pressure tank having a lattice structure, including: a tank body that has a high-pressure fluid accommodated therein and is manufactured to have a prismatic shape; and cell structures that are disposed in the prismatic tank body, are manufactured in a lattice form, arrive from one side wall of the tank body to the other side wall thereof facing it, and are orthogonally arranged regularly.

A securing device for securing a pipe in a housing, which has a cylindrical collar, at least three securing arms, each securing arm containing a proximal arm portion mounted on the cylindrical collar, a distal arm portion bearing a bearing pad, the bearing pad containing a bearing surface facing away from the collar and intended to collaborate with a wall of the housing in which at least one of the securing arms contains a guideway capable of translationally guiding the distal arm portion with respect to the proximal arm portion, an elastic member being coupled to the guideway so as to be able to apply a return force that pushes the distal arm portion away from the proximal arm portion.

Rocket tank liquid level determination, and associated systems and methods. A representative system includes a computer-readable medium having instructions that, when executed, receive an image corresponding to a view of the liquid in the rocket tank, identify an edge between the liquid and a wall of the tank, and, based on at least one of a size, shape, location, or orientation of the edge, estimate a level of the liquid in the tank. In addition to or in lieu of determining the liquid level, the system can determine a characteristic of a sloshing motion of the liquid in the tank, and, based at least on the characteristic of the sloshing motion, direct operation of a forcing element that imparts a force to the rocket to at least partially counteract a force placed on the rocket by the sloshing motion of the liquid in the tank.

Example integrated cryogenic hydrogen tank systems and methods for operating the same are disclosed herein. An example system comprises a first cryogenic tank coupled to a second cryogenic tank via a liquid hydrogen (LH2) transfer flowline and a gaseous hydrogen (GH2) transfer flowline, the LH2 transfer flowline and the GH2 transfer flowline to maintain a fuel level and a vapor pressure across the system, the fuel level corresponding to a cryogenic liquid; an inlet port connected to one of the first cryogenic tank or the second cryogenic tank; an LH2 extraction flowline connected to at least one of the first or second cryogenic tanks to supply the cryogenic liquid to a fuel management system; and a pressure safety system coupled to at least one of the first or second cryogenic tanks via a GH2 extraction flowline.

An LNG carrier which uses natural gas generated by vaporization of LNG as propulsive fuel and including cargo tank, spray apparatus, and carrier communication device; land-based equipment including land-based communication device and processing device; processing device including: first vapor quantity estimating section which estimates total quantity of natural vapor generated from the LNG remaining in the cargo tank in a case where the LNG carrier is traveling on planned ballast course, based on sea weather data; a second vapor quantity estimating section which estimates a total quantity of spray vapor generated by performing spraying operations in a case where the LNG carrier is traveling on planned ballast course, based on the sea weather data; and heel quantity calculating section which calculates required heel quantity, by summing the total quantity of natural vapor and spray vapor, and the land-based communication device transmits the required heel quantity to the carrier communication device.)

A large volume natural gas storage tank comprises rigid tubular walls having closed tubular cross-sections that are interconnected at opposing ends with two other rigid tubular walls such that interiors of the rigid tubular walls define an interior fluid storage chamber. The storage tank includes bulkhead ring webs positioned in the interior fluid storage chamber across intermediate segments of the rigid tubular walls and closure plates connected between exterior surfaces of successive interconnected rigid tubular walls to define sides of the storage tank. Interior surfaces of the closure plates and exterior surfaces of the rigid tubular walls define an auxiliary fluid storage chamber. The storage tank includes exterior support structures extending through the closure plates and between the exterior surfaces of the rigid tubular walls on some of the sides of the storage tank to reinforce the storage tank against dynamic loading from fluid in the interior fluid storage chamber.

An aircraft fuel storage system is disclosed including a fuel tank comprising a chamber for storing fuel, the chamber comprising a first side, a second side, and a base connecting the first side to the second side; a collector; and a first conduit and a second conduit, each of the first and second conduits fluidically coupling the chamber to the collector so that fuel is freely passable from the chamber to the collector via the respective first and second conduits. The first and second conduits open into the chamber at respective first and second conduit openings, the first conduit opening is nearer to the first side than the second conduit opening is to the first side, and the second conduit includes a second conduit lock portion that is nearer to the first side than the second conduit opening is to the first side. Also disclosed is an aircraft including the aircraft fuel storage system.

Various techniques are provided for an energy absorbing fluid bladder. In one example, the fluid bladder includes a bladder body and a perforated baffle structure. The perforated baffle structure can be disposed within the bladder body and configured to mitigate a pulse of fluid (e.g., fuel) moving within the bladder body before the pulse reaches the bladder body. Related methods are also disclosed.

A liquid-stabilizing apparatus for a liquid cargo tank includes a guide structure. The guide structure is provided with a positioning floating body. The positioning floating body is provided with anti-sloshing members. The anti-sloshing members are provided with discontinuous baffles at a fixed angle. By using the liquid-stabilizing apparatus, the liquid cargo tank is no longer required to have a bevel surface structure, thereby increasing load capacity of the liquid cargo tank and preventing the liquid cargo tank in various loading states from being impacted by liquid cargos.