The object of the invention is a multichamber structural element manufacturing method which for forming a multichamber structural element with chamber profiles (1) extending radially from the center defined by the connection of the chamber profiles (1) comprises the following steps: at least three chamber profile preforms (2) are provided, wherein each chamber profile preform (2) comprises two walls (3) made of a sheet of metal material and arranged with respect to each other in substantially parallel planes with a gap retained between them, wherein the edges of the individual walls (3) converge, and wherein a valve element (6) is arranged on at least one wall (3); the unconnected wall (3) edges of each of the chamber profile preforms (2) are sealed with a seal (5) for forming a closed hermetic empty inner space of the chamber profile preform (2); a fluid under pressure is introduced through the valve element (6) into the inner space of the chamber profile preform (2) for forming a deformed chamber profile (1), at least three chamber profile preforms (2) or chamber profiles (1) are connected in the area of the corresponding inner edges of the chamber profile preform (2) or the chamber profile (1), proximal with respect to the connection axis (4), along at least part of the inner edges. The object of the invention is also a multichamber structural element.

The invention relates to a form element (1), an arrangement comprising such a form element (1) and a method for forming at least part of a formwork for a concrete part using this form element (1), wherein the form element (1) is flexibly three-dimensionally deformable in its first state, and wherein the form element (1) is stiffened and solidified in its second state, in particular in a deformed position of the form element (1), wherein the form element (1) comprises at least two flexible layers (2), which are arranged superimposed in a planar manner, and wherein the layers (2) are connected to each other, in particular reversibly, in the second state to solidify the form element (1).

The present invention relates to a pneumatic structure (10) comprising an inextensible body (12) defining at least a network of internal cavities (14), each cavity having a closed contour in at least one section of the cavity

Each cavity being suitable for being pressurized so as to change the inextensible body from a rest configuration to at least one pressurized configuration,

Inextensible body having, in each pressurized configuration, a macroscopic metric different from its macroscopic metric in the rest configuration,

Each cavity being formed of at least two substantially rectilinear channels, each channel being fluidly connected to at least one of the other channels, the two said channels forming a heading change angle,

Each cavity comprising at least one non-zero heading change angle, in particular at least three non-zero heading change angles.

A transverse span for an airform membrane is disclosed that can include a material having a perimeter defined at least in part by a longitudinal edge having opposite ends that terminate at a base edge further defining the perimeter. The longitudinal edge can be configured to couple to a longitudinal edge of an adjacent transverse span of the airform membrane. The base edge can at least partially define a base perimeter of the airform membrane for coupling with a base support structure. The transverse span can also include a load compensated region with a length dimension and/or a width dimension reduced from an intended final dimension to compensate for stretch of the material when the airform membrane is inflated. In addition, the transverse span can include a flare region between the load compensated region and the base edge. The flare region can transition in the length dimension and/or the width dimension between the load compensated region and the base edge.

Disclosed are devices, systems, and methods for self-constructing structures. In particular, a mold for forming a structure includes an inflatable inner balloon, a non-inflatable outer shell coupled to the inner balloon about a base circumference, the outer shell having an apex and an opening disposed at the apex, and a pump in fluid communication with the opening of the outer shell; wherein, when the inner balloon is inflated, a gap is formed between the inner balloon and the outer shell for containing a building material, and the outer shell comprises a dome shape.

The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.

The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.

The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.

The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.

The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.