Abstract: The present invention relates to a novel anti-HLA-A2 antibody, and to a chimeric antigen receptor comprising said HLA-A2 antibody. The present invention further relates to an immune cell expressing said chimeric receptor antigen, and to therapeutic uses thereof, in particular for treating or preventing graft rejection or GVHD.

Abstract: An annular air flow passage for a turbine engine such as a turbojet or a turboprop, crossed by an instrumented rod that includes mechanism(s) for measuring characteristics of a flow potentially traveling along the passage, the rod extending between an outer annular wall and an inner annular wall of the passage. Outer connection(s) fasten(s) an outer end of the instrumented rod to the outer wall in a manner that is rigid in all directions, and inner connection(s) fasten(s) an inner end of the instrumented rod to the inner wall, in a manner that is rigid in the circumferential direction and that has at least one degree of freedom to move in a first direction extending between the inner and outer walls of the passage and having at least a radial component.

Abstract: A buoyancy system (10) for an aircraft (1), the buoyancy system (10) being provided with at least one inflatable float (15). The buoyancy system (10) has at least one inflator (25) and at least one actuator (30) interposed between the inflator (25) and a float (15), the actuator (30) having a cylinder (35) and a rod (40) partially received in the cylinder (35). The rod (40) is secured to a piston (50) defining a first chamber (61) within the cylinder (35) and in fluid flow communication with the inflator (25), and a second chamber (62) within the rod (40) and in fluid flow communication with the float (15), and the piston (50) has a channel (63) to put the first chamber (61) into fluid flow communication with the second chamber (62), the deployment device (20) having a shutter (70) for shutting the channel (63).

Abstract: The invention relates to an annular air flow passage (33) for a turbine engine such as a turbojet or a turboprop, crossed by an instrumented rod (50) that includes means for measuring characteristics of a flow potentially traveling along the passage, said rod extending between an outer annular wall (48) and an inner annular wall (42) of the passage. According to the invention, outer connection means (60, 86) fasten an outer end (58) of the instrumented rod to the outer wall in a manner that is rigid in all directions, and inner connection means (62) fasten an inner end (56) of the instrumented rod to the inner wall, in a manner that is rigid in the circumferential direction and that has at least one degree of freedom to move in a first direction (51) extending between the inner and outer walls (42, 48) of the passage and having at least a radial component.

Abstract: A buoyancy system (10) for an aircraft (1), the buoyancy system (10) being provided with at least one inflatable float (15). The buoyancy system (10) has at least one inflator (25) and at least one actuator (30) interposed between said inflator (25) and a float (15), said actuator (30) having a cylinder (35) and a rod (40) partially received in said cylinder (35). Said rod (40) is secured to a piston (50) defining a first chamber (61) within said cylinder (35) and in fluid flow communication with the inflator (25), and a second chamber (62) within said rod (40) and in fluid flow communication with said float (15), and said piston (50) has a channel (63) to put the first chamber (61) into fluid flow communication with the second chamber (62), said deployment device (20) having a shutter (70) for shutting said channel (63).