Relief valve for being arranged on an opening of a fuselage shell of an aircraft, fuselage part with such a relief valve and aircraft fuselage

Abstract

The invention pertains to a relief valve ( 10 ) for being arranged on an opening ( 10 ) of a fuselage shell of an aircraft, wherein the opening ( 10 ) has a front opening edge ( 9 a ) and a rear opening edge ( 9 a ), and wherein the relief valve ( 10 ) features: a cover ( 13 ) that is arranged on the fuselage shell by means of an opening and closing device in order to open and close the opening ( 10 ) of the fuselage shell, and a prestressing device for prestressing the cover ( 13 ) into an initial position, wherein a guide plate ( 23 ) is arranged on the cover ( 13 ) by means of a mounting device ( 20 ), wherein the guide plate is spaced apart from the cover ( 13 ) and extends along the cover ( 13 ), and wherein the invention furthermore pertains to a fuselage part with such a relief valve ( 10 ) for being installed into an aircraft fuselage with a fuselage shell and a plurality of fuselage frames arranged on the inside of the fuselage shell, as well as to an aircraft fuselage with such a fuselage part.

1 . A relief valve ( 10 ) for being arranged on an opening ( 10 ) of a pressurized fuselage part of an aircraft, wherein the opening ( 9 ) has a front opening edge ( 9   a ) and a rear opening edge ( 9   b ), and wherein the relief valve ( 10 ) features:
 a cover ( 13 ) that is arranged on the fuselage part by means of a hinge joint ( 11 ) in order to open and close the opening ( 9 ) of the fuselage part, and   a pre-stressing device for pre-stressing the cover ( 13 ) into an initial position,   a guide plate ( 23 ) being arranged on the cover ( 13 ) by means of a support device ( 20 ), wherein said guide plate is spaced apart from the cover ( 13 ) and extends along the cover ( 13 ), and wherein the support device ( 20 ) is realized permeable in a main direction (H) extending from the cover edge with the hinge joint ( 11 ) to the cover edge situated opposite thereof,   
       wherein the cover ( 13 ) and the guide plate ( 23 ) are formed such that the distance between the cover ( 13 ) and the guide plate ( 23 ) decreases along the main direction (H) so that the air flowing between the cover ( 13 ) and the guide plate ( 23 ) is accelerated along the main direction (H) and a resulting negative pressure is generated acting in the opening direction of the cover ( 13 ). 
     
     
         2 . The relief valve ( 10 ) according to  claim 1 , wherein the cross-section of the guide plate ( 23 ) running along the main direction (H) has a profile form which has a decreasing cross-section in a section of the guide plate ( 23 ) along the main direction (H). 
     
     
         3 . The relief valve ( 10 ) according to  claim 1 , wherein the support device comprises at least one support rod ( 25 ,  26 ) that extends between the cover ( 13 ) and the guide plate ( 23 ) so as to connect the cover ( 13 ) and the guide plate ( 23 ). 
     
     
         4 . The relief valve ( 10 ) according to  claim 3 , wherein the support device ( 20 ) comprises at least one front support rod ( 25 ) and at least one rear support rod ( 26 ) with regard to the main direction (H). 
     
     
         5 . The relief valve ( 10 ) according to  claim 4 , wherein the front support rod ( 25 ) is mounted on a rotating part of the hinge joint ( 11 ). 
     
     
         6 . The relief valve ( 10 ) according to  claim 4 , wherein the surface ( 25   a ) of the front support rod ( 25 ) which is facing the main direction (H) is inclined in the direction of the main direction (H) to support the opening of the cover ( 13 ) by the air flow (S). 
     
     
         7 . A relief valve ( 10 ) for being arranged on an opening ( 10 ) of a pressurized fuselage part of an aircraft, wherein the opening ( 9 ) comprises a front opening edge ( 9   a ) and a rear opening edge ( 9   b ), and wherein the relief valve ( 10 ) features:
 a cover ( 13 ) that is arranged on the fuselage part by means of a hinge joint ( 11 ) in order to open and close the opening ( 9 ) of the fuselage part, and   a pre-stressing device for pre-stressing the cover ( 13 ) into an initial position,   a guide plate ( 23 ) being arranged on the cover ( 13 ) by means of a support device ( 20 ), wherein said guide plate is spaced apart from the cover ( 13 ) and extends along the cover ( 13 ), and wherein the support device ( 20 ) is realized permeable in a main direction (H) extending from the cover edge with the hinge joint ( 11 ) to the cover edge situated opposite thereof,   wherein the support device ( 20 ) comprises at least one front support rod ( 25 ) and at least one rear support rod ( 25 ) with regard to the main direction (H) wherein the front support rod ( 25 ) is mounted on a rotating part of the hinge joint ( 11 ), wherein each of the support rods ( 25 ,  26 ) is coupled in an articulated fashion to the cover ( 13 ) and to the guide plate ( 23 ) such that the distance between the guide plate ( 23 ) and the cover ( 13 ) can be adjusted by rotating the rods,   wherein the support rods ( 25 ,  26 ) are pre-stressed into an initial position, in which the cover ( 13 ) and the guide plate ( 23 ) have the smallest distance from one another within the adjustable distance range, and   wherein the cover ( 13 ) the pre-stressing of the support rods ( 25 ,  26 ) is adjusted such that in the state in which the guide plate ( 23 ) is blown by the air (S) in the main direction (H), during an initial opening movement of the cover ( 13 ), the cover ( 13 ) is moved in an open position while the distance between the guide plate ( 23 ) and the cover ( 13 ) increases.   
     
     
         8 . The relief valve ( 10 ) according to  claim 7 , wherein the cover ( 13 ) and the guide plate ( 23 ) are formed such that the distance between the cover ( 13 ) and the guide plate ( 23 ) decreases along the main direction (H) so that the air flowing between the cover ( 13 ) and the guide plate ( 23 ) is accelerated along the main direction (H) and a resulting negative pressure is generated acting in the opening direction of the cover ( 13 ). 
     
     
         9 . The relief valve ( 10 ) according to  claim 8 , wherein the cross-section of the guide plate ( 23 ) running along the main direction (H) has a profile form which is decreasing in a section of the guide plate ( 23 ) along the main direction (H). 
     
     
         10 . A pressurized fuselage part of an aircraft fuselage, wherein said fuselage part has a longitudinal direction (X 1 ) that extends in the direction of the longitudinal aircraft axis (X) when it is installed into an aircraft fuselage and features an opening ( 9 ) that is arranged between two fuselage frames, as well as a relief valve device with a relief valve ( 10 ) according to  claim 1 , wherein the rotational axis of the hinge joint ( 11 ) is running across the longitudinal aircraft axis.