A payload joint for detachably attaching to each other two adjacent construction elements in a spacecraft and/or launch vehicle, wherein the payload joint comprises a clamp , comprising an inner clamp portion and an outer clamp portion facing the inner clamp portion , wherein the inner clamp portion comprises a first and second inner clamp flange (12a1, 12a2) and an inner mid portion between the first and second inner flanges (12a1, 12a2), wherein the outer clamp portion comprises a first and second outer clamp flange (12b1, 12b2) and an outer mid portion between the first and second outer flanges (12b1, 12b2), wherein the payload joint comprises a first construction element end portion of a first construction element comprising a first end section and a second construction element end portion (25") of a second construction element (2") comprising a second end section (9"), and wherein the first end section comprises a first outer construction element flange (14b1) and a first inner construction element flange (14a1), wherein the second end section (9") comprises a second outer construction element flange (14b2) and a second inner construction element flange (14a2), wherein the first end section comprises a first contact surface formed by a portion of an outer surface of the first outer construction element flange (14b1) and by a portion of an outer surface of the first inner construction element flange (14a1), and wherein the second end section (9") comprises a second contact surface formed by a portion of an outer surface (30") of the second outer construction element flange (14b2) and by a portion of an outer surface (30") of the second inner construction element flange (14a2), wherein the first and second contact surfaces (31', 31") are abutting each other in the payload joint forming a reference plane (RP), wherein a first inner clamp locking surface (20a1) of the first inner clamp flange (12a1) is arranged at a first angle (A1) to the reference plane (RP), wherein a first outer clamp locking surface (20b1) of the first outer clamp flange (12b1) is arranged at a second angle (A2) to the reference plane (RP), wherein a second inner clamp locking surface (20a2) of the second inner clamp flange (12a2) is arranged at a third angle (A3) to the reference plane (RP), wherein a second outer clamp locking surface (20b2) of the second outer clamp flange (12b2) is arranged at a fourth angle (A4) to the reference plane (RP), wherein a first inner construction element locking surface (21a1) of the first inner construction element flange (14a1) is arranged at a fifth angle (A5) to the reference plane (RP), wherein a first outer construction element locking surface (21b1) of the first outer construction element flange (14b1) is arranged at a sixth angle (A6) to the reference plane (RP), wherein a second inner construction element locking surface (21a2) of the second inner construction element flange (14a2) is arranged at a seventh angle (A7) to the reference plane (RP), wherein a second outer construction element locking surface (21b2) of the second outer construction element flange (14b2) is arranged at an eight angle (A8) to the reference plane (RP), characterised in that each clamp portion comprises a through opening , wherein the payload joint comprises a bolt , configured to be arranged in the through openings , and in that the payload joint comprises a bolt cutter comprising a cutting device arranged at a cutting angle (CA) towards the bolt and a driving device arranged in connection to the cutting device and arranged to drive the cutting device towards the bolt with a shear force that breaks and separates the bolt into two or more pieces, wherein the cutting angle (CA) is defined with reference to a normal to a length extension of the bolt and being zero degrees or close to zero degrees. <EOS>