Rocket nozzle assembly with separable nozzle extension
Rocket nozzle assembly having a separable outboard nozzle extension for transitioning from a vacuum-optimized to an atmospheric-optimized configuration. The nozzle assembly includes an inboard divergent nozzle section attached at an interface with a detachable outboard divergent nozzle extension. The nozzle and extension are removably attached via a connector, such as a clamp and strap. An actuator causes the connector to release and thereby allow the extension to separate from the nozzle in flight. The nozzle assembly may be used with a reusable second stage rocket that lands on the ground or an ocean platform. The nozzle extension may be replaced in between flights.
1 . A rocket nozzle assembly comprising:
a nozzle having a frustoconical nozzle body that extends axially between an inboard nozzle end and an outboard nozzle end and defines a nozzle channel;
a nozzle extension having a frustoconical extension body that extends axially from an inboard extension end to an outboard extension end, wherein the inboard extension end is removably coupled to the outboard nozzle end at an interface via a connector extending annularly about the interface, and wherein the frustoconical extension body defines an extension channel that is axially aligned with the nozzle channel;
a first wedge ring and a second wedge ring sandwiching a portion of the nozzle with a portion of the nozzle extension along the interface by the connector; and
an actuator in physical communication with the connector and configured to cause the nozzle extension to detach from the nozzle.
2 . The rocket nozzle assembly of claim 1 , wherein the connector comprises a V-band clamp.
3 . The rocket nozzle assembly of claim 1 , wherein the actuator comprises a pyrotechnic device, an explosive shaped charge, a hydraulic actuator, or an electromechanical actuator.
4 . The rocket nozzle assembly of claim 1 , wherein the nozzle comprises a removable portion configured to be replaced on a landing surface during refurbishment of the nozzle.
5 . The rocket nozzle assembly of claim 1 , wherein the outboard nozzle end comprises a nozzle flange that extends radially outward, and wherein the inboard extension end comprises an extension flange that extends radially outward, the connector comprising at least one clamp coupling the nozzle flange and the extension flange together.
6 . The rocket nozzle assembly of claim 1 , wherein the first wedge ring and the second wedge ring each comprise an angled surface.
7 . The rocket nozzle assembly of claim 1 , wherein the connector comprises one or more clamps and a strap extending circumferentially around at least the portion of the nozzle and the portion of the nozzle extension.
8 . The rocket nozzle assembly of claim 1 , wherein the actuator comprises an explosive bolt, a non-explosive bolt, a clasp, or a reverse pliers mechanism.
9 . The rocket nozzle assembly of claim 1 , wherein the portion of the nozzle comprises a nozzle flange and the portion of the nozzle extension comprises an extension flange.
10 . A rocket system comprising:
a second stage rocket comprising one or more second stage rocket engines having a nozzle assembly configured to transform from a vacuum-optimized configuration to an atmospheric-optimized configuration, wherein the nozzle assembly comprises:
a nozzle having a frustoconical nozzle body that extends axially between an inboard nozzle end and an outboard nozzle end and defines a nozzle channel;
a nozzle extension having a frustoconical extension body that extends axially from an inboard extension end to an outboard extension end, wherein the inboard extension end is removably coupled to the outboard nozzle end at an interface via a connector extending annularly about the interface, and wherein the frustoconical extension body defines an extension channel that is axially aligned with the nozzle channel;
a first wedge ring and a second wedge ring sandwiching a portion of the nozzle with a portion of the nozzle extension along the interface by the connector; and
an actuator in physical communication with the connector and configured to cause the nozzle extension to detach from the nozzle.
11 . The rocket system of claim 10 further comprising a first stage rocket having one or more first stage rocket engines and configured to be coupled with the second stage rocket to launch the rocket system from within an atmosphere.
12 . The rocket system of claim 10 , wherein the actuator comprises a pyrotechnic device, an explosive shaped charge, a hydraulic actuator, or an electromechanical actuator.
13 . The rocket system of claim 10 , wherein the connector comprises one or more clamps and a strap extending circumferentially around at least the portion of the nozzle and the portion of the nozzle extension.
14 . The rocket system of claim 10 , wherein the portion of the nozzle comprises a nozzle flange and the portion of the nozzle extension comprises an extension flange.