US 9,845,166 B2 · Pneumatic cubesat payload deployment system utilizing launch vehicle tank pressure

Abstract

A rail-captive sled for deploying payloads into outer space from a space launch vehicle. The sled is driven by a piston, powered by residual tank pressure from a tank native to the space launch vehicle. The rails are arranged parallel and adapted to a cross-sectional shape of a payload, such as small satellites or cubesats. The sled is a box frame sled with an adaptation to receive the piston. The rails may be attached to the residual pressure tank, with the piston in the residual pressure tank and aligned to the rails, or the pressure may be drawn from tank plumbing to a cylinder specific to the piston. The rails have a releasable closure to avoid unplanned egress of the payload, and the closure locks in the open position once released. The piston may be constrained by a direct constraint or by the closure via the payload.

Claims20

Dependent claims

A satellite payload deployment system, comprising:

a. a plurality of parallel rails attachable to extend from a space launch vehicle and arranged to define an interior space adapted to a cross-sectional shape of a payload;
b. a captive sled within said interior space, operable to:
i. slide on said plurality of rails in a direction parallel to said plurality of rails and
ii. support at least one said payload;
c. a piston operable to propel said captive sled and said at least one payload from a proximal end of said plurality of rails to a distal end of said plurality of rails;
and
d. a receiver coupled to said piston and operable to
i. couple to a source of residual tank pressure from a tank native to said space launch vehicle;
and
ii. transfer said residual tank pressure to said piston;
and
e. wherein said receiver comprises said source of residual tank pressure from said tank native to said space launch vehicle, further comprising:
i. a reinforced opening in said tank;
and
ii. a sliding O-ring seal, installed in said opening, surrounding said opening and operable to seal said piston when said tank is pressurized.

12 more elements

A satellite payload deployment system, comprising:

a. a plurality of parallel rails attachable to extend from a space launch vehicle and arranged to define an interior space adapted to a cross-sectional shape of a payload;
b. a captive sled within said interior space, operable to:
i. slide on said plurality of rails in a direction parallel to said plurality of rails;
and
ii. to support at least one said payload;
c. a piston operable to propel said captive sled and said at least one payload from a proximal end of said plurality of rails to a distal end of said plurality of rails;
d. a receiver coupled to said piston and operable to:
i. couple to a source of residual tank pressure from a tank native to said space launch vehicle;
and
ii. transfer said residual tank pressure to said piston;
e. a releasably latchable door operable to releasably close said distal end of said plurality of rails to egress of said payload;
and
f. a constraint to maintain said door in a fully opened configuration after said door latch has been released;
g. wherein said receiver comprises said source of residual tank pressure from said tank native to said space launch vehicle, further comprising:
i. a reinforced opening in said tank;
ii. a sliding O-ring seal, installed in said opening, surrounding said opening and operable to seal said piston when said tank is pressurized.

13 more elements

Dependencies are inferred from the claim text.

Pneumatic cubesat payload deployment system utilizing launch vehicle tank pressure

Life of this patent

Pneumatic cubesat payload deployment system utilizing launch vehicle tank pressure

Life of this patent

Abstract

Claims20