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 extending from a first inboard end to a first outboard end having a larger diameter than the first inboard end;
a nozzle extension releasably coupled to the nozzle at an interface, the nozzle extension extending from a second inboard end to a second outboard end, the second outboard end having a larger diameter than the second inboard end, wherein the second inboard end and the first outboard end are releasably coupled at the interface;
a connector extending annularly about the interface to secure the nozzle with the nozzle extension; and
an actuator comprising a clasp system configured to actuate to release the connector from the interface to allow the second inboard end of the nozzle extension to release from the first outboard end of the nozzle.
2 . The rocket nozzle assembly of claim 1 , wherein the clasp system comprises:
a dynamic element coupled to a first end of the connector, the dynamic element configured to transition between a secured position and an unsecured position;
a static element coupled to a second end of the connector, and
a rod comprising a first end coupled to the dynamic element and a second end coupled to the static element.
3 . The rocket nozzle assembly of claim 2 , wherein the connector comprises a strap, and wherein the dynamic element is coupled to a first end of the strap, and the static element is coupled to a second end of the strap.
4 . The rocket nozzle assembly of claim 2 , wherein the dynamic element comprises:
a base member coupled to the connector; and
a rotational member rotationally secured with the base member about a pivot point and configured to rotate about the pivot point to transition the dynamic element between the secured position and the unsecured position.
5 . The rocket nozzle assembly of claim 4 , wherein the rotational member comprises a first end and a second end opposite the first end, the first end facing the static element and coupled about the pivot point, wherein the rod is coupled to the second end of the rotational member.
6 . The rocket nozzle assembly of claim 4 , wherein the dynamic element further comprises a latch actuator extending from the rotational member.
7 . The rocket nozzle assembly of claim 6 , wherein the latch actuator is configured to move linearly to initiate rotation of the rotational member from the secured position to the unsecured position.
8 . The rocket nozzle assembly of claim 6 , wherein the latch actuator comprises a spring.
9 . The rocket nozzle assembly of claim 2 , wherein the static element comprises a slot and an actuation mechanism, wherein the actuation mechanism comprises a sliding latch and a securing element, wherein the sliding latch is linearly movable within the slot, and wherein the securing element is configured to engage the sliding latch.
10 . The rocket nozzle assembly of claim 9 , wherein the securing element is a solenoid, and wherein the sliding latch is a magnet.
11 . 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 extending from a first inboard end to a first outboard end having a larger diameter than the first inboard end;
a nozzle extension releasably coupled to the nozzle at an interface, the nozzle extension extending from a second inboard end to a second outboard end, the second outboard end having a larger diameter than the second inboard end, wherein the interface is positioned between the second inboard end and the first outboard end;
a connector extending along the nozzle and the nozzle extension at the interface, the connector comprising a first end and a second end; and
a clasp system configured to allow the second inboard end of the nozzle extension to release from the first outboard end of the nozzle at the interface, the clasp system comprising:
a dynamic element coupled to the first end of the connector, the dynamic element configured to transition between a secured position and an unsecured position;
a static element coupled to the second end of the connector, and
a rod comprising a first end coupled to the dynamic element and a second end coupled to the static element.
12 . The rocket system of claim 11 , wherein the dynamic element is configured to rotate about a pivot point to transition between the secured position and the unsecured position.
13 . The rocket system of claim 11 , wherein the clasp system maintains a tension of the connector in the secured position and the clasp system does not maintain the tension of the connector in the unsecured position.
14 . The rocket system of claim 11 , wherein the dynamic element comprises:
a base member coupled to the connector; and
a rotational member rotationally secured with the base member about a pivot point and configured to rotate about the pivot point to transition the dynamic element between the secured position and the unsecured position.
15 . The rocket system of claim 14 , wherein the rotational member comprises a first end and a second end opposite the first end, the first end facing the static element and coupled about the pivot point, wherein the rod is coupled to the second end of the rotational member.
16 . The rocket system of claim 14 , wherein the dynamic element comprises a latch actuator configured to move linearly to initiate rotation of the rotational member from the secured position to the unsecured position.
17 . A method comprising:
operating a rocket engine of a rocket in a vacuum thrust mode, wherein the rocket engine comprises at least one nozzle assembly having a nozzle with an outboard end and a nozzle extension having an inboard end releasably attached to the outboard end of the nozzle along an interface;
actuating a clasp system to release a connector extending annularly about the interface;
releasing the inboard end of the nozzle extension from the outboard end of the nozzle; and
operating the rocket engine in an atmospheric thrust mode using the nozzle without the nozzle extension.
18 . The method of claim 17 , wherein actuating the clasp system comprises rotating a dynamic element about a pivot.
19 . The method of claim 17 , wherein actuating the clasp system comprises rotating a rod of the clasp system relative to a static element and a dynamic element.
20 . The method of claim 17 , wherein actuating the clasp system comprises actuating a latch actuator to rotate a dynamic element of the clasp system.