Thrusting rails for launch vehicles, and associated systems and methods
The present technology is directed to thrusting rails for launch vehicles, and associated systems and methods. Certain embodiments of the thrusting rails can include a first rail housing portion having a cavity and a second rail housing portion having a projection positioned at least partially within the cavity. The rails can include a bellows positioned within the cavity and an elongated tube positioned within the bellows. The elongated tube can include a vent opening in a lateral wall of the elongated tube. A shield can be positioned between the vent opening at the bellows and a sleeve can be positioned within the elongated tube. The sleeve can be constructed from a fibrous material and positioned to retain an ordnance within the elongated tube.
1 . A thrusting rail assembly comprising:
a rail housing portion having a first wall, a second wall, and a cavity between the first wall and the second wall;
a bellows positioned within the cavity;
a manifold comprising a clamping ring on a first side to enable clamping of at least one end of the bellows and comprising an opening on a second side which is opposite the first side, wherein the opening is for an adapter, a detonator, or an ordnance, and wherein the opening is associated with a seal ring to contact the clamping ring and to support sealing of the opening;
an elongated tube positioned within the bellows and comprising a vent opening in a lateral wall thereof; and
a sleeve positioned within the elongated tube to retain the ordnance therein.
2 . The thrusting rail assembly of claim 1 , wherein the thrusting rail assembly comprises a shape associated with a joint to be separated, in part, by detonation of the ordnance.
3 . The thrusting rail assembly of claim 1 , wherein the thrusting rail assembly is to be associated to a fairing at one or more joints to enable the fairing to be separated into one or more portions, and wherein the separation of the fairing enables delivery of a payload comprised within the fairing.
4 . The thrusting rail assembly of claim 1 , further comprising:
a further rail housing portion having a further first wall and a further second wall, the further first wall and a further second wall in a direction which is away from the first wall and the second wall of the rail housing portion, and wherein the thrusting rail assembly is associated to a fairing with a first portion of the fairing associated with the rail housing portion and a second portion of the fairing associated with the further rail housing portion.
5 . The thrusting rail assembly of claim 1 , further comprising:
a further rail housing portion having a further first wall and a further second wall, and a piston portion, the piston portion to support the bellows positioned within the cavity of the rail housing portion.
6 . The thrusting rail assembly of claim 1 , further comprising:
a further rail housing portion having a further first wall and a further second wall, and in a direction which is away from the first wall and the second wall of the rail housing portion; and
a plurality of holes in the rail housing portion or the further rail housing portion, the plurality of holes based in part on one or more of a weight intended for thrusting rail assembly, the rail housing portion, or the further rail housing portion, a force required to separate the rail housing portion from the further rail housing portion, or a breathing frequency of a fairing to be separated into portions, in part, by detonation of the ordnance.
7 . The thrusting rail assembly of claim 1 , wherein the elongated tube is positioned within the cavity, and wherein the sleeve is constructed from a material which is adapted to fracture, disintegrate, or otherwise deconstruct without producing shrapnel in response to detonation of the ordnance retained therein.
8 . The thrusting rail assembly of claim 1 , wherein the bellows has a cylindrical shape before assembly of the thrusting rail assembly, and wherein the bellows has a folded or U-shaped configuration within the cavity, based in part on a piston portion of a further rail housing portion providing part of the cavity with the rail housing portion.
9 . The thrusting rail assembly of claim 1 , wherein the sleeve is constructed from a fibrous material comprising one or more of kraft paper or foam.
10 . A thrusting rail assembly comprising:
a rail housing portion having a first wall, a second wall, and a cavity between the first wall and the second wall;
a manifold comprising a clamping ring on a first side to enable clamping of at least one end of a bellows which extends into the cavity and comprising an opening on a second side which is opposite the first side, wherein the opening is for an adapter, a detonator, or an ordnance, and wherein the opening is associated with a seal ring to contact the clamping ring and to support sealing of the opening; and
a sleeve to be associated within the bellows, the sleeve adapted to fracture, disintegrate, or otherwise deconstruct without producing shrapnel in response to detonation of the ordnance retained therein.
11 . The thrusting rail assembly of claim 10 , wherein the sleeve comprises a radial thickness to fill or at least substantially fill a radial space between the ordnance and an elongated tube positioned within the bellows.
12 . The thrusting rail assembly of claim 10 , wherein the sleeve comprises a radial thickness to maintain the ordnance at least substantially at a predetermined position within an elongated tube positioned within the bellows.
13 . The thrusting rail assembly of claim 10 , wherein the sleeve is to maintain the ordnance at least substantially at a predetermined position within an elongated tube positioned within the bellows, the predetermined position to direct blast forces from the ordnance toward predetermined locations.
14 . A method for space vehicle portions, the method comprising:
providing, for at least one of the space vehicle portions, a rail housing portion having a first wall, a second wall, and a cavity between the first wall and the second wall;
positioning a bellows within the cavity;
providing a manifold comprising a clamping ring on a first side and comprising an opening on a second side which is opposite the first side;
enabling clamping of at least one end of the bellows to the clamping ring;
receiving an adapter, a detonator, or an ordnance through the opening;
enabling a seal ring associated with the opening to contact the clamping ring and to support sealing of the opening; and
positioning an elongated tube within the bellows, the elongated tube comprising a vent opening in a lateral wall thereof; and
positioning a sleeve within the elongated tube to retain the ordnance therein.
15 . The method of claim 14 , further comprising:
providing a further rail housing portion having a further first wall and a further second wall, the further first wall and a further second wall in a direction which is away from the first wall and the second wall of the rail housing portion, wherein the cavity is enabled in part by a piston portion of the further rail housing portion.
16 . The method of claim 14 , further comprising:
providing a fairing in a plurality of portions forming the space vehicle portions, the fairing to comprise a payload;
associating at least a first one of the plurality of portions of the fairing to the rail housing portion; and
associating at least a second one of the plurality of portions of the fairing to a further rail housing portion which in a direction which is away from the first wall and the second wall of the rail housing portion.
17 . A method for a fairing comprising:
providing the fairing to comprise space vehicle portions to be separated, wherein at least one of the space vehicle portions comprises a rail housing portion having a first wall, a second wall, and a cavity between the first wall and the second wall for a bellows, comprises an elongated tube positioned within the bellows and having a vent opening in a lateral wall thereof, comprising a sleeve positioned within the elongated tube to retain an ordnance therein, and comprises a manifold having a clamping ring on a first side to enable clamping of at least one end of the bellows and having an opening on a second side which is opposite the first side for an adapter, a detonator, or the ordnance, wherein the opening associated with a seal ring to contact the clamping ring and to support sealing of the opening; and
associating a payload with the fairing; and
enabling detonation of the ordnance for disassociation of the space vehicle portions, wherein the payload is enabled to be delivered based in part on the disassociation of the space vehicle portions.
18 . The method of claim 17 , further comprising:
configuring one or more aspects of the ordnance so that the space vehicle portions are to separate and move away from a rocket associated with the fairing.
19 . The method of claim 18 , wherein the one or more aspects comprises one of positioning of the ordnance at a predetermined position within the elongated tube or enabling blast forces from the ordnance toward predetermined locations.
20 . The method of claim 17 , further comprising:
issuing a command to the at least one of the space vehicle portions to initiate the separation, wherein the command is from a terrestrial source or from a source local to a launch vehicle associated with the fairing.