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Aspects are directed to a system that includes an outer structure of a thrust reverser, a blocker door, and a plurality of four-bar mechanisms arranged in series with one another that couple the outer structure and the blocker door. Aspects are directed to a system for a thrust reverser of an aircra

Aspects are directed to a system that includes an outer structure of a thrust reverser, a blocker door, and a plurality of four-bar mechanisms arranged in series with one another that couple the outer structure and the blocker door. Aspects are directed to a system for a thrust reverser of an aircraft that includes a blocker door, a kinematic mechanism configured to actuate the blocker door, and a pressure shelf, where the blocker door is configured to reside below the pressure shelf in proximity to a duct of the thrust reverser, and where at least a portion of the kinematic mechanism is configured to reside above the pressure shelf.

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1. A system for a thrust reverser of an aircraft comprising: a blocker door;a kinematic mechanism configured to actuate the blocker door;a pressure shelf,wherein the blocker door is configured to reside below the pressure shelf in proximity to a duct of the thrust reverser, andwherein at least a fir

1. A system for a thrust reverser of an aircraft comprising: a blocker door;a kinematic mechanism configured to actuate the blocker door;a pressure shelf,wherein the blocker door is configured to reside below the pressure shelf in proximity to a duct of the thrust reverser, andwherein at least a first portion of the kinematic mechanism is configured to reside above the pressure shelf; anda seal associated with the pressure shelf is configured to seal around a penetration formed through the pressure shelf through which a second portion of the kinematic mechanism is positioned, the seal maintaining a differential pressure between the duct and an ambient environment located external to the duct. 2. The system of claim 1, wherein the blocker door is configured to be deployed in a substantially radial direction towards a central axis, and wherein the kinematic mechanism is configured to convert a substantially tangential motion associated with the actuation to a substantially radial motion associated with the deployment. 3. The system of claim 1, wherein the kinematic mechanism comprises a gearbox, and wherein the gearbox comprises bevel gears. 4. The system of claim 1, wherein the kinematic mechanism comprises a plurality of four-bar mechanisms arranged in series. 5. The system of claim 1, further comprising: a fixed structure;wherein the kinematic mechanism comprises at least a first crank that pivots in a first plane and a second crank that pivots in a second plane normal to the first plane; andwherein the first crank and the second crank are each configured to move relative to the blocker door. 6. The system of claim 5, wherein the kinematic mechanism comprises a first four-bar mechanism, and the first four-bar mechanism comprises: the fixed structure;a first pushrod coupled to the fixed structure;the first crank coupled to the first pushrod; anda translating sleeve coupled to the first crank and configured to translate along an axis,wherein the first crank is pivotally attached to the translating sleeve. 7. The system of claim 6, further comprising at least one cascade configured to be selectively hidden or exposed based on a degree to which the translating sleeve is translated along the axis. 8. The system of claim 6, wherein the kinematic mechanism further comprises a second four-bar mechanism, the second four-bar mechanism comprising: the first crank;the translating sleeve;a second pushrod coupled to the first crank; andthe second crank coupled to the second pushrod. 9. The system of claim 8, wherein the system is configured to convert a tangential motion associated with the first crank to a radial motion associated with the second crank. 10. The system of claim 8, wherein the kinematic mechanism further comprises a third four-bar mechanism, the third four-bar mechanism comprising: the translating sleeve;the second crank;a third pushrod coupled to the second crank; andthe blocker door coupled to the third pushrod. 11. The system of claim 10, further comprising: wherein at least a portion of the third pushrod is configured to selectively penetrate the pressure shelf based on whether the thrust reverser is operated in a stowed state or a deployed state. 12. The system of claim 5, further comprising a linkage coupled between the second crank and the blocker door, wherein the second crank is pivotally connected to the linkage. 13. A system for an aircraft propulsion system, comprising: a fixed structure of a thrust reverser;a blocker door;a plurality of mechanisms arranged in series with one another to couple the fixed structure and the blocker door, the plurality of mechanisms comprising a first crank and a second crank, the first crank pivotable in a first plane, and the second crank pivotable in a second plane which is normal to the first plane;a pressure shelf configured to translate along an axis of the aircraft propulsion system, wherein the blocker door is configured to reside below the pressure shelf in proximity to a duct of the thrust reverser, and wherein at least a portion of the second crank is configured to reside above the pressure shelf;a translating sleeve configured to translate along the axis; andat least one cascade configured to be selectively covered or uncovered as the translating sleeve translates along the axis;wherein the pressure shelf is connected to and translates with the translating sleeve. 14. The system of claim 13, wherein the first crank and the second crank are each configured to move relative to the blocker door. 15. The system of claim 13, wherein the at least one cascade comprises a plurality of cascades configured to be selectively covered or uncovered as the translating sleeve translates along the axis.