RU2785483C9 - System for connecting the hulls of compartments - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to the field of general mechanical engineering, namely, to systems for detachable connection of the hulls of compartments of an aerial vehicle. The system comprises two or more cylindrical segments with symmetrical internal conical surfaces coupled in the plane of the joint with the outer surface of the frames of a pair of butt-connected compartments, wherein one frame comprises an annular ledge with holes for the threaded connections provided to secure the joint; the joints themselves are at the ends of the segment, with axes thereof passing along the coupling surface perpendicular to the axes of the compartment hulls. The threaded connections provided to secure the joint are made as explosive bolts with an electric detonator, a nut, and a washer; the bolts are installed on the inside of the compartments in the holes of the frame with an annular ledge, recesses are made on the outer surface of the frames in the area of the holes for each bolt perpendicular to the axes thereof, and the cylindrical segments are equipped with threaded sleeves with collars mounted on the segments coaxially to each explosive bolt enabling axial movement thereof and coming in contact with the surface of the frame recesses; wherein the end surface of each sleeve is matched with the separation plane of the bolt, and each washer for a bolt fastening nut is provided with an annular protrusion in the inner diameter of the sleeve.

EFFECT: higher reliability and improved operating characteristics of the system due to the fault-free operation of the explosive bolt and the reduced disturbance to the structural elements of the aircraft.

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Description

The invention relates to the field of general engineering, in particular to the designs of detachable connections of aircraft compartment housings.

Known designs for connecting compartment bodies, for example, patent RU No. 2717930 F16B, published on March 26, 2020, including a pair of butt-connected compartments using two or more cylindrical segments with symmetrical internal conical surfaces mating in the joint plane with the outer surface of the compartment frames, one of which contains an annular ledge with holes for threaded connections, fixing the joint, a pair of threaded connections are placed at the ends of the segment, and their axes pass along the mating surface perpendicular to the axes of the compartment bodies. Taken as a prototype.

The disadvantages of the prototype design include the fact that this design, being a detachable connection, cannot be separated in flight.

The objective of the invention is to create a separable system for connecting compartment bodies, providing increased reliability and improved performance of the system due to the failure-free operation of the explosive bolt and reducing disturbances on the structural elements of the aircraft.

The problem is solved by the fact that a system for connecting compartment bodies is proposed, containing two or more cylindrical segments with symmetrical internal conical surfaces mating in the junction plane with the outer surface of the frames of a pair of butt-connected compartments, one of which contains an annular ledge with holes for threaded connections, fixing joint, the joints themselves are placed at the ends of the segment, and their axes run along the mating surface perpendicular to the axes of the compartment bodies, while the threaded connections fixing the joint are made in the form of explosive bolts with an electric detonator, with a nut and a washer, the bolts are installed from the inside of the compartments into the holes of the frame with an annular ledge , on the outer surface of the frames in the area of the holes for each bolt perpendicular to their axes, recesses are made, and the cylindrical segments are equipped with threaded bushings with flanges installed on the segments coaxially with each explosive bolt with the possibility of axial movement and to contacting with the surface of the recesses of the frames, while the end surface of each sleeve is aligned with the bolt separation plane, and the washers for the nuts of the bolt are provided with an annular protrusion located in the inner diameter of the sleeve.

The invention is illustrated by the figures of the drawing.

On FIG. 1 shows a general view of the compartment connection system (for example, with three cylindrical segments).

On FIG. 2 shows butt-connected compartments in the RB installation area (RB not shown).

On FIG. 3 shows a cross-section of the compartment connection system in the area of the explosive bolt installation.

The connection system consists of: pos. 1 and pos. 2 - compartment housings; pos. 3 - frame compartment 1 with an annular ledge; pos. 4 - frame compartment 2; pos. 5 - explosive bolt (RB); pos. 6 - cylindrical segments; pos. 7 - bolt fastening nut, pos. 8 - sleeve with collar, pos. 9 - washers with an annular protrusion; pos. 10 - electric detonator; pos. 11 - deepening.

The system for connecting the housings of the compartments works as follows. To separate the elements of the aircraft, a command is given to the electric detonator. The electric detonator 10 is triggered and each explosive bolt 5 is destroyed in the plane of separation into two parts. For reliable operation of the bolt, a closed volume is required. This volume is provided by installing a bushing with a shoulder 8 and making a recess 11 on the outer surface of the frames 3 and 4. The bushings are fixed on the segments 6 with the possibility of axial movement due to the recesses in the frames, made together, and the gap between the cylindrical segments and the outer surface of the frames (see Fig. Fig. 3). The end surface of the sleeve is in contact with the surface of the recess in the zone of conical cutting under the RB. In this case, the end surface of the sleeve 8, abutting against the surface of the recess 11 of the frames, is aligned with the separation plane of the bolt 5.

To perform a shatter-free and more reliable separation of the bursting bolt (probability of failure-free operation 0.9999), a uniform gap between the RB and the inner diameter of the sleeve is required. This clearance is provided by the washer pos. 9 with an annular protrusion that fits into the inner diameter of the sleeve.

When actuated, the RB is flared in the area of the bushing holes, filling the cone groove, and the pressure from actuation through the bushing 8 (either along the thread or, when it is sheared, through the shoulder of the bushing) is transmitted to segments 6 and they are discharged together with the bushings and part of the bolts with nuts 7 and washers 9. The second part of the RB, installed in the hole of the frame with an annular ledge 3, departs with the body 1 in which they are installed, and the annular ledge of the frame 3 of compartment 1 itself is the guide of movement when compartments 1 and 2 are separated. 1 and 2, which are joined together by ends made in the form of symmetrical annular frames (see Fig. 2).

The design is made in such a way that the conical groove under the RB pos. 5 is carried out jointly after docking the compartments, the axes of the holes pass in the joint surface, and the holes themselves are made symmetrically in each frame, the compartment bodies are pulled together by two or more cylindrical segments 6, the number of which is determined by the load on the joint, and the bolts are placed at the edges of the segments, which ensures their pressing against the surfaces of frames 3 and 4. The inner surface of the segments 6 is made in the form of two symmetrical conical generatrices corresponding to the conical generatrix of the frames of compartments 3 and 4 and coming into direct contact with them, and the remaining surfaces have guaranteed gaps with compartments 1 and 2. Segments 6, regardless of the number, are made from a single ring-shaped blank by high-performance turning, like the frames of compartments 3 and 4. Explosive bolts are installed in the joint plane perpendicular to the axes of the compartment bodies. The pressure from the operation of the RB acts perpendicular to the axis of the compartments, thereby reducing perturbations on the structural elements of the aircraft during the separation of the compartment bodies.

Thus, the use of the proposed invention makes it possible to create a separable system for connecting compartment bodies, which provides increased reliability and improved performance due to the failure-free operation of the explosive bolt and reduced disturbance to the structural elements of the aircraft.

Claims (2)

1. A system for connecting compartment bodies, containing two or more cylindrical segments with symmetrical internal conical surfaces mating in the interface plane with the outer surface of the frames of a pair of butt-connected compartments, one of which contains an annular ledge with holes for threaded connections that fix the joint, the connections themselves are placed at the ends of the segment, and their axes pass along the mating surface perpendicular to the axes of the compartment bodies, characterized in that the threaded connections that fix the joint are made in the form of explosive bolts with an electric detonator, with a nut and washer, the bolts are installed from the inside of the compartments into the frame holes with an annular ledge, on the outer surface of the frames in the area of the holes for each bolt, recesses are made perpendicular to their axes, and the cylindrical segments are equipped with threaded bushings with flanges installed on the segments coaxially with each explosive bolt with the possibility of axial movement and in contact with the surface of the corner killing frames, while the end surface of each bushing is aligned with the plane of separation of the bolt. 2. The system for connecting compartment bodies according to claim 1, characterized in that each washer for the bolt fastening nut is provided with an annular protrusion located in the inner diameter of the sleeve.

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