Module Separation Mechanism, In Particular For Rockets

Abstract

A module separation mechanism, in particular for rockets, includes a cylindrical first body, a cylindrical second body, and a ring connecting the two bodies, The ring comprises at least one tension lock together with a cover. The first body comprises at least one radially mounted actuator that is adapted to eject the tension lock together with the cover from the ring in a manner to disengage the ring. The first body further comprises at least one ejecting member adapted to eject the second body from the first body. The outer surface of the ring together with the cover is faced with the outer surface of the first body and the second body.

Claims

1. A module separation mechanism, in particular for rockets, comprising: a cylindrical first body; a cylindrical second body; and a ring connecting the first body and the second body, wherein: the ring comprises a tension lock together with a cover, the first body comprises at least one radially mounted actuator that is adapted to eject the tension lock together with the cover from the ring in a manner as to disengage the ring, the first body comprises at least one ejecting member adapted to eject the second body from the first body, and an outer surface of the ring together with the cover faces outer surfaces of the first body and the second body.

2. The module separation mechanism according to claim 1, comprising: two independent modules connected by the ring, wherein the tension lock comprises two tension locks.

3. The module separation mechanism according to claim 1, wherein: the first body comprises two independent, radially mounted actuators adapted to eject the tension lock out of the ring in a manner to disengage the ring when only one of the actuators is operated.

4. The module separation mechanism according to claim 1, wherein, in a connected state, modules are sealed at their connection point by a gasket.

5. The module separation mechanism according to claim 1, wherein, in a connected state, modules are positioned by at least two positioning pins that take away freedom in a direction perpendicular to an axis of the modules.

6. The module separation mechanism according to claim 1, wherein the actuator is at least one of electrically driven, pneumatically driven, or pyrotechnically driven.

7. The module separation mechanism according to claim 1, wherein: the cover faces the outer surfaces of the first body and the second body, and the cover has a projection that prevents screws of the tension lock from being unscrewed.

8. The module separation mechanism according to claim 1, comprising: a pushing member comprising a spring.

9. The module separation mechanism according to claim 8, wherein the spring is a pushing gas spring.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The present invention is explained in an embodiment illustrated in the drawing figures.

[0022] FIG. 1 shows a schematic diagram of the mechanism in various cross-sections.

[0023] FIG. 2 shows an enlarged cross-sectional section of the body connection mechanism.

[0024] FIG. 3 shows an exploded view of the mechanism.

DETAILED DESCRIPTION

[0025] As shown in FIGS. 1-3, the module separation mechanism according to an embodiment comprises two cylindrical bodies, a first body 1 and a second body 2, a ring 3 connecting the two bodies, electrical connectors with fittings 7, two tension locks 6, and two actuators 5 and pushing members 4 in the form of two gas springs.

[0026] The bodies 1 and 2 are connected in a friction-shaped manner through a ring 3 having two articulated joints 3c located in a plane perpendicular to the tension locks 6. The ring 3 consists of two sets of parts—the first arm of the ring 3a, the second arm of the ring 3b, and the articulated joint 3c of the ring 3. The two sets of parts of the ring 3, superimposed on the connected first and second bodies, are connected by a tension lock 6 secured against unscrewing by a cover 9.

[0027] The bodies 1 and 2 have interfaces to connect the module to other components of the rocket or other separable object. Depending on the need, it is possible to adapt them to the standard used within the solution (e.g., RADAX, flange connection, axial connection). The plane of separation is between the two modules, in the plane of symmetry of the ring 3. The axial interconnection of the modules has allowed them to be sealed in their connected state at the point where they are connected by an O-ring type gasket 8, thus ensuring full tightness of the mechanism. This type is referred to as the radial build type, external (piston) sealing.

[0028] The disconnection of the modules is effected by the initiation of one of the two actuators 5, which push the tensioning lock 6 opposite them, holding the ring 3 halves. The ring 3 thus released no longer provides any resistance to the two modules. As a result of the action of the gas springs, the two modules are free to separate, ejecting the ring halves 3 outwards. Due to the use of spherical washers 6d under the bolt heads 6a, 6b of the tension lock 6, only one of the two actuators 5 needs to be actuated for correct separation to occur.

[0029] It is possible for the module separation mechanism to contain only one actuator 5 and only one tension lock 6. In this case, the ring 3 consists of four ring arms, three articulation joints 3c, and one tension lock 6 secured by a cover 9. Two of the three articulation joints are positioned analogously to the use of two actuators, while the third articulation joint is located in place of the second tension lock 6. The first body 1 has only one socket intended to accommodate the actuator 5, and the second body 2 has only one opening for the actuator piston.

[0030] In some embodiments, a pyrotechnic propulsion system is used to propel the actuators 5, wherein the charge used has a low mass but high energy density. The use of a low mass charge ensures that the explosion is small, controlled and does not cause stress on the rocket structure. The detonation of the charge in these embodiments is only intended to create sufficient pressure in the actuator to open the tensioning lock 6.

[0031] In certain embodiments, the mechanism according to this disclosure is housed in a rocket of small diameter, preferably in a rocket whose combined modules have an outer diameter in the range of 100-150 mm.

[0032] In the context of the present disclosure, the facing of the outer surface of the ring 3 including the cover 9 of the tension lock 6 with the outer surface of the first body 1 and the second body 2 should be understood as a complete overlapping of their outer surfaces.

[0033] The present disclosure allows maximization of the internal through diameter inside one of the separated modules. Thus, after separation, it may be possible, for example, to realize an observation of the sky from inside one of the sections and to trigger a parachute system located in the axis of the upper of the separated modules. The invention also reduces the forces generated at the moment of separation, also thanks to the use of gas springs (instead of devices based on explosive charges).

[0034] The invention can be used to separate cargo compartments from the main part of the structure, thus facilitating the execution of tests and the subsequent recovery process.

[0035] The use of two actuators increases the reliability of the system, as only one allows separation to take place. The mechanism allows the use of a different number of gas springs with different characteristics, making it highly scalable and applicable to both small and large diameter objects.

[0036] The geometry used allows high forces and moments to be transferred in all directions.

[0037] The following is a list of reference numbers used in this description and the drawings.

1 First body
2 Second body

3 Ring

[0038] 3a First arm of the ring
3b Second arm of the ring
3c Articulation joint of the ring
4 Pushing member

5 Actuator

[0039] 6 Tension lock
6a, 6b Tension lock screws
6c Tension lock nut
6d Spherical washer
7 Electrical connectors with fittings

8 Gasket

9 Cover

10 Positioning pin