Platform and launch initiation system for secondary spacecraft for launch vehicle

Abstract

A platform and launch initiation control system for secondary spacecraft for a launch vehicle includes an aluminum honeycomb core sandwiched between top and bottom structural aluminum skins and strengthened by a spider-like stiffener. Spool inserts for engaging the secondary spacecraft are arranged on the platform. A computer processor based auxiliary payload support unit (APSU) is provided on the platform and receives power and enable signals through a single cable from the LV to permit the APSU to control the release of the secondary spacecraft transparently to the LV without impacting LV operations.

1 . Assembly for supporting one or more auxiliary payloads (AP) in a launch vehicle (LV) delivering the AP into space, comprising:
 a core sandwiched between top and bottom structural skins;   a stiffener coupled to the core and formed with plural stiffening arms oriented radially relative to the core; and   engagement inserts configured to releasably engage a separation device of the AP arranged on the core.   
     
     
         2 . The assembly of  claim 1 , wherein the core is made of aluminum honeycomb and is disk-shaped. 
     
     
         3 . The assembly of  claim 1 , wherein the core is made of aluminum honeycomb and is parabolic shaped. 
     
     
         4 . The assembly of  claim 1 , wherein the core is made of aluminum honeycomb and is elliptically shaped. 
     
     
         5 . The assembly of  claim 1 , wherein the core is made of aluminum honeycomb and is shaped as a triangular arch. 
     
     
         6 . The assembly of  claim 1 , wherein the core is made of aluminum honeycomb and is shaped as a segmented arch. 
     
     
         7 . The assembly of  claim 1 , wherein the core is made of aluminum honeycomb and is shaped as a right circular frustum. 
     
     
         8 . The assembly of  claim 1 , wherein the core is made of aluminum honeycomb and is a free form shape designed to support a specific AP. 
     
     
         9 . The assembly of  claim 2 , wherein the aluminum honeycomb core defines a honeycomb ribbon direction and the honeycomb ribbon direction is radial. 
     
     
         10 . The assembly of  claim 1 , wherein the stiffener fits snugly within slots formed in the core, the slots being shaped complementarily to the stiffener, a surface of the stiffener being flush with a surface of the core. 
     
     
         11 . The assembly of  claim 10 , wherein the stiffener has a central opening that is coaxial with the core and that is circumscribed by a central enclosed hollow ring, at least some of the stiffening arms extending radially outwardly from the central enclosed hollow ring. 
     
     
         12 . The assembly of  claim 1 , wherein the engagement inserts are received in registered sets of insert holes in the skins, stiffener, and core, the engagement inserts being arranged in one or more circles. 
     
     
         13 . The assembly of  claim 1 , further comprising LV interface fittings arranged along the outer periphery of the core, respective fasteners extending through respective fastener holes in at least one of the skins, into a respective fitting, and being engaged with structure on the LV to securely hold the assembly to the LV. 
     
     
         14 . The assembly of  claim 1 , wherein the skins, stiffener, and core are bonded together by an adhesive injected as a fluid before it hardens thereby filling in interior spaces in the core. 
     
     
         15 . The assembly of  claim 1 , wherein the stiffener and core are made integrally with each other. 
     
     
         16 . A auxiliary payload support unit (APSU) for coordinating release of at least one auxiliary payload (AP) from an AP support assembly of the APSU, the APSU being engageable with a launch vehicle (LV), the APSU comprising:
 at least one circuit at least indicating at least a portion of a launch sequence of a particular AP on the APSU;   at least one communications interface between the circuit and LV;   at least one computer readable data storage medium accessible to the circuit; wherein   the APSU is configured to communicate with the LV through at least one cable, the circuit being configured for receiving, post-launch of the LV, an enable signal from the LV prior to which the circuit does not cause power to be sent to any AP such that the LV controls when the APSU begins executing AP release, the circuit being configured for, responsive to receiving the enable signal, causing power to be supplied to at least one AP on the APSU to begin execution of a launch sequence for the at least one AP on the APSU such that the LV need not, after sending the enable signal to the APSU, thereafter command or communicate anything to the APSU regarding AP release, relieving the LV of the burden of controlling launch of the AP, the APSU being configured for receiving a separation signal indicating the AP is separated from the APSU.   
     
     
         17 . The APSU of  claim 16 , wherein the circuit, responsive to the enable signal, enables power switching to the AP such that a separation device of the AP is energized as appropriate to ensure AP launch on schedule. 
     
     
         18 . The APSU of  claim 16 , wherein the circuit is configured to receive from the AP a separation signal indicating AP separation from the APSU. 
     
     
         19 . The APSU of  claim 18 , wherein the circuit is configured for, responsive to receiving the separation signal, determining whether another AP awaits release from the APSU and if so, enabling release of the AP. 
     
     
         20 . The APSU of  claim 18 , wherein the circuit is configured to, responsive to receiving the separation signal, determine whether another AP awaits release from the APSU and if not, deenergize itself. 
     
     
         21 . Auxiliary payload (AP) support assembly comprising:
 disk-shaped core configured for holding one or more APs;   plural fittings arranged along the periphery of the core and configured for engaging structure of a launch vehicle (LV) to secure the core to the LVs; and   controller assembly coupled to the core and configured for electrically communicating with the LV to receive power therefrom, the controller assembly also configured to receive, post-launch of the LV, an enable signal from the LV prior to which the controller assembly cannot begin executing a launch sequence for any AP such that the LV controls when the controller assembly begins executing AP release from the LV but does not thereafter command or communicate anything to the controller assembly regarding AP release.   
     
     
         22 . The assembly of  claim 21 , wherein the assembly communicates with the LV through one and only one cable. 
     
     
         23 . The assembly of  claim 21 , wherein the core is sandwiched between top and bottom structural skins and a stiffener is coupled to the core and formed with plural stiffening arms oriented radially relative to the core. 
     
     
         24 . The assembly of  claim 23 , further comprising engagement inserts configured to releasably engage a separation device of the AP arranged on the core. 
     
     
         25 . The assembly of  claim 23 , wherein the stiffener fits snugly within slots formed in the core, the slots being shaped complementarily to the stiffener, a surface of the stiffener being flush with a surface of the core. 
     
     
         26 . The assembly of  claim 23 , wherein the stiffener has a central opening that is coaxial with the core and that is circumscribed by a central enclosed hollow ring, at least some of the stiffening arms extending radially outwardly from the central enclosed hollow ring, the engagement inserts being received in registered sets of insert holes in the skins, stiffener, and core, the engagement inserts being arranged in one or more circles.