Abstract: Crystalline molecular framework:small molecule compounds. The molecular framework is formed from guanidinium cations and organosulfonate anions and the guanidinium cations and organosulfonate anions are associated via one or more hydrogen bond. The small molecule(s) is/are encapsulated by the molecular framework. Methods for making crystalline molecular framework:small molecule compounds may include combining guanidinium cations, organosulfonate anions, and small molecules in a single step. The crystalline molecular framework:small molecule compounds can be used to determine the structure of the small molecule(s).

Abstract: Crystalline molecular framework:small molecule compounds. The molecular framework is formed from guanidinium cations and organosulfonate anions and the guanidinium cations and organosulfonate anions are associated via one or more hydrogen bond. The small molecule(s) is/are encapsulated by the molecular framework. Methods for making crystalline molecular framework:small molecule compounds may include combining guanidinium cations, organosulfonate anions, and small molecules in a single step. The crystalline molecular framework:small molecule compounds can be used to determine the structure of the small molecule(s).

Abstract: An aircraft fuel tank assembly includes a tank for holding fuel, a canister and a fuel pump assembly. The fuel pump assembly includes: an electric motor, a pump and an electronics unit. The electronics unit and canister are arranged so that, in use, a dry bay is defined between the electronics unit and the canister.

Abstract: A valve system both controls fuel flow by means of a valve and senses the condition of the valve. The valve is actuated by an actuator via a rotatable shaft. Light is transmitted by a laser diode, via a polarising filter (which is mounted to rotate with the shaft), down the shaft, and is reflected by a mirror which directs the light back up the shaft via the filter to a receiver, which is able to detect different directions of polarisation of the light received. The polarisation of the light received by the receiver indicates whether the valve is open or shut. If no light is received a fault is deemed present. Thus, the condition of the valve is checked directly by means of an apparatus remote from the valve and the fuel.

Abstract: On failure, a burst rotor of a wing-mounted engine (13, 23) can penetrate fuel tank walls in the wing of a conventional aircraft. There exists a zone that is at risk of such damage. Thus, the layout of fuel tanks (3, 11C, 21C) in the wing of an aircraft in accordance with embodiments includes port and starboard inner fuel tanks (11C, 21C) that are positioned adjacent to a central fuel tank (3) in the central wing section, but outside of the at-risk zone. Each of the port and starboard inner fuel tanks (11C, 21C) is defined in part by a respective inner boundary member (5RP, 5RS) that when viewed in plan extends, at least in part, in a direction at an angle of less than 20° to the adjacent vertical plane (A-A) defining the at-risk zone. Thus the amount of fuel stored in fuel tanks (11C, 21C) in the wing assembly that cover a region outside of the at-risk zone and that do not extend into the at-risk zone may be increased.

Abstract: On failure, a burst rotor of a wing-mounted engine (13, 23) can penetrate fuel tank walls in the wing of a conventional aircraft. There exists a zone that is at risk of such damage. Thus, the layout of fuel tanks (3, 11C, 21C) in the wing of an aircraft in accordance with embodiments includes port and starboard inner fuel tanks (11C, 21C) that are positioned adjacent to a central fuel tank (3) in the central wing section, but outside of the at-risk zone. Each of the port and starboard inner fuel tanks (11C, 21C) is defined in part by a respective inner boundary member (5RP, 5RS) that when viewed in plan extends, at least in part, in a direction at an angle of less than 20° to the adjacent vertical plane (A-A) defining the at-risk zone. Thus the amount of fuel stored in fuel tanks (11C, 21C) in the wing assembly that cover a region outside of the at-risk zone and that do not extend into the at-risk zone may be increased.

Abstract: An aircraft fuel tank assembly includes a tank for holding fuel, a canister and a fuel pump assembly. The fuel pump assembly includes: an electric motor, a pump and an electronics unit. The electronics unit and canister are arranged so that, in use, a dry bay is defined between the electronics unit and the canister.

Abstract: A method is provided for detecting an analyte in a liquid sample, the method using light energy propagational properties of an analyte-responsive polymer. The analyte-responsive polymer is interfaced with a means to detect changes in the light propagation of the analyte-responsive polymer and the changes are correlated to the amount of analyte in the liquid sample.

Abstract: A composition is provided which is a transducing polymer having from 1 to 20 crosslinks per polymer molecule and selected from the group consisting of amphoteric co- or ter-polymers of pI between 6.2 to 8.0 of acrylic acid, alkyl methacrylate, and N,N-dimethly-aminoethyl methacrylate, the amphoteric co- or ter-polymer immobilized on a surface. Also provided is a method for the preparation of an analyte-responsive polymer immobilized on a surface in which the steps are a. mixing a solution of a crosslinker and the claimed transducing polymer, b. applying the solution of step a to a surface, and c. then curing the polymer to a ratio of from 1 to 20 crosslinks per transducing polymer molecule. Acoustic and optical methods for detecting analtyes are also provided which use an analyte-responsive polymer.

Abstract: A biosensor detector method for detecting biological targets, using specific binding, or hybridization techniques coupled with enzymatic amplification and the mass sensing capability of a piezoelectric oscillator. An optical biosensor is also contemplated.