Payload ejector with shock attenuation device
A system includes a payload ejector configured to contact a payload carried by a flight vehicle and to push the payload away from the flight vehicle. The payload ejector includes a piston configured to extend from the payload ejector and a shock attenuator coupled to the piston, where the shock attenuator is configured to push the payload away from the flight vehicle. The shock attenuator includes a shock attenuator housing and a plunger that is movable within the shock attenuator housing and that extends from the shock attenuator housing. The plunger is configured to be pushed at least partially into the shock attenuator housing in order to damp a shock pulse applied to the payload. The shock attenuator housing may have an interior space, and the shock attenuator may further include a spring, compliant material, or fluid within the interior space.
1. An apparatus comprising:
a shock attenuator configured to be coupled to a piston of a payload ejector, the shock attenuator configured to contact a payload carried by a flight vehicle and to push the payload away from the flight vehicle;
wherein the shock attenuator comprises:
a shock attenuator housing comprising an interior space and a spring or pliant material within the interior space; and
a plunger movable within the interior space of the shock attenuator housing and extending from the shock attenuator housing, the plunger configured to be pushed at least partially into the shock attenuator housing while the plunger pushes against the spring or pliant material within the interior space in order to damp a shock pulse applied to the payload.
2. The apparatus of claim 1 , wherein the shock attenuator further comprises a cap configured to be coupled to the shock attenuator housing in order to secure the plunger within the shock attenuator housing.
3. The apparatus of claim 2 , wherein:
the plunger comprises a recess;
a portion of the cap fits within the recess; and
the spring or pliant material is positioned at least partially around the portion of the cap that fits within the recess.
4. The apparatus of claim 1 , wherein:
the shock attenuator further comprises a fluid within the interior space; and
the plunger comprises at least one orifice configured to allow the fluid to pass through the plunger.
5. The apparatus of claim 1 , wherein the shock attenuator further comprises at least one seal positioned between the plunger and the shock attenuator housing.
6. The apparatus of claim 1 , wherein the shock attenuator housing is configured to be inserted into and secured to an inner piston sleeve that is movable within an outer piston sleeve such that the plunger extends beyond an end of the inner piston sleeve.
7. A system comprising:
a payload ejector configured to contact a payload carried by a flight vehicle and to push the payload away from the flight vehicle, the payload ejector comprising:
a piston configured to extend from the payload ejector; and
a shock attenuator coupled to the piston, the shock attenuator configured to push the payload away from the flight vehicle;
wherein the shock attenuator comprises:
a shock attenuator housing comprising an interior space and a spring or pliant material within the interior space; and
a plunger movable within the interior space of the shock attenuator housing and extending from the shock attenuator housing, the plunger configured to be pushed at least partially into the shock attenuator housing while the plunger pushes against the spring or pliant material within the interior space in order to damp a shock pulse applied to the payload.
8. The system of claim 7 , wherein the shock attenuator further comprises a cap configured to be coupled to the shock attenuator housing in order to secure the plunger within the shock attenuator housing.
9. The system of claim 8 , wherein:
the plunger comprises a recess;
a portion of the cap fits within the recess; and
the spring or pliant material is positioned at least partially around the portion of the cap that fits within the recess.
10. The system of claim 7 , wherein:
the shock attenuator further comprises a fluid within the interior space; and
the plunger comprises at least one orifice configured to allow the fluid to pass through the plunger.
11. The system of claim 7 , wherein the shock attenuator further comprises at least one seal positioned between the plunger and the shock attenuator housing.
12. The system of claim 7 , wherein the piston comprises:
an outer sleeve configured to slide within an ejector housing of the payload ejector; and
an inner sleeve configured to slide within the outer sleeve, the shock attenuator positioned at an end of the inner sleeve.
13. The system of claim 7 , wherein the payload ejector further comprises multiple mounting pads extending from an ejector housing, the mounting pads configured to contact the payload and limit side-to-side movement of the payload.
14. The system of claim 7 , wherein the payload ejector further comprises a piston actuator configured to provide fluid that extends the piston from the payload ejector.
15. The system of claim 7 , wherein the payload ejector comprises multiple pistons and multiple shock attenuators coupled to the pistons.
16. A method comprising:
extending a piston from a payload ejector;
contacting a payload carried by a flight vehicle using a shock attenuator coupled to the piston;
pushing the payload away from the flight vehicle using the shock attenuator and the piston, wherein the shock attenuator comprises:
a shock attenuator housing comprising an interior space and a spring or pliant material within the interior space; and
a plunger movable within the interior space of the shock attenuator housing and extending from the shock attenuator housing, the plunger configured to be pushed at least partially into the shock attenuator housing in order to damp a shock pulse applied to the payload; and
pushing the plunger at least partially into the shock attenuator housing while the plunger pushes against the spring or pliant material within the interior space.
17. The method of claim 16 , wherein:
the shock attenuator housing further comprises a fluid within the interior space;
the plunger comprises at least one orifice; and
the method further comprises pushing the plunger at least partially into the shock attenuator housing while at least some of the fluid passes through the at least one orifice.
18. The method of claim 16 , wherein:
the shock attenuator further comprises a cap coupled to the shock attenuator housing in order to secure the plunger within the shock attenuator housing;
the plunger comprises a recess;
a portion of the cap fits within the recess; and
the spring or pliant material is positioned at least partially around the portion of the cap that fits within the recess.
19. The method of claim 16 , wherein extending the piston from the payload ejector comprises:
extending outer and inner sleeves of the piston from a piston housing; and
extending the inner sleeve from the outer sleeve; and
wherein the plunger extends beyond an end of the inner sleeve.
20. The method of claim 16 , wherein:
the payload ejector further comprises multiple mounting pads extending from an ejector housing; and
the method further comprises contacting the payload with the mounting pads and limiting side-to-side movement of the payload.