U.S. patent application number 14/088722 was filed with the patent office on 2014-05-15 for platform and launch initiation system for secondary spacecraft for launch vehicle.
This patent application is currently assigned to HKM Enterprises Inc.. The applicant listed for this patent is HKM Enterprises Inc.. Invention is credited to Michael Darmody, James England, Jack Rubidoux, Philip Smith.
Application Number | 20140131522 14/088722 |
Document ID | / |
Family ID | 47005718 |
Filed Date | 2014-05-15 |
United States Patent
Application |
20140131522 |
Kind Code |
A1 |
Smith; Philip ; et
al. |
May 15, 2014 |
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.
Inventors: |
Smith; Philip; (San Diego,
CA) ; England; James; (Highlands Ranch, CO) ;
Darmody; Michael; (San Diego, CA) ; Rubidoux;
Jack; (La Mesa, CA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
HKM Enterprises Inc. |
Denver |
CO |
US |
|
|
Assignee: |
HKM Enterprises Inc.
Denver
CO
|
Family ID: |
47005718 |
Appl. No.: |
14/088722 |
Filed: |
November 25, 2013 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
13066471 |
Apr 15, 2011 |
8608114 |
|
|
14088722 |
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Current U.S.
Class: |
244/173.3 ;
244/173.1 |
Current CPC
Class: |
B64G 1/428 20130101;
B64G 2001/643 20130101; B64G 1/641 20130101; B64G 1/002 20130101;
B64G 1/64 20130101; B64G 1/645 20130101 |
Class at
Publication: |
244/173.3 ;
244/173.1 |
International
Class: |
B64G 1/64 20060101
B64G001/64 |
Claims
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.
Description
FIELD OF THE INVENTION
[0001] The present application relates generally to platforms and
launch initiation systems for secondary spacecraft for launch
vehicles (LV).
BACKGROUND OF THE INVENTION
[0002] As satellites become increasingly miniaturized along with
electronics in general, it has become possible and economically
desirable to use excess volume and weight capacity in launch
vehicles (LV) to carry auxiliary payloads (AP), essentially small
secondary space vehicles (SV) incorporating satellites of various
uses and capabilities. Depending on their weight, such small
satellites may be classified as pico spacecraft, nano spacecraft,
micro spacecraft, or mini spacecraft. By piggybacking APs onto LVs
having an otherwise independent mission, the costs for placing a
small satellite into space are greatly reduced, making space-based
resources available to a much larger market.
[0003] As understood herein, it is desirable that Ms be technically
and programmatically transparent to the primary spacecraft and that
APs impose no technical or contractual risk, including the risk of
delaying launch schedules, to the primary spacecraft and its
mission. It is further desirable that more than one AP be
accommodated when appropriate, e.g., when multiple picos, nanos,
micros or minis can be included as APs on a launch vehicle, without
undue technical complexity in arranging the AP in the available
area of the LV and without requiring undue coordination between
individual manufacturers of APs.
SUMMARY OF THE INVENTION
[0004] Accordingly, an assembly for supporting one or more
auxiliary payloads (AP) in a launch vehicle (LV) delivering the AP
into space includes a deck comprised of a core sandwiched between
top and bottom structural skins and a stiffener coupled to the core
and formed with plural stiffening arms oriented radially relative
to the core. Engagement inserts configured to releasably engage a
separation device of the AP are arranged on the deck.
[0005] If desired, the core may be made of aluminum honeycomb and
can be disk-shaped. The aluminum honeycomb core defines a honeycomb
ribbon direction and the honeycomb ribbon direction preferably is
radial. The stiffener may fit snugly within slots formed in the
core. The slots can be shaped complementarily to the stiffener,
with a surface of the stiffener being flush with a surface of the
core.
[0006] If desired the core and the combined structural skins may
formed into a frustum of a right circular cone. Alternatively the
combined core and skins may form a dome having an elliptical arch,
parabolic arch, triangular arch or segmental arch vertical cross
section when viewed through the apex of the doom. Alternatively the
combined core and skins may be free formed into a shape to support
APs at one or more points on the structural form.
[0007] In example embodiments 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
extend radially outwardly from the central enclosed hollow ring.
The engagement inserts can be received in registered sets of insert
holes in the skins, stiffener, and core in one or more circles.
[0008] Additionally, LV interface fittings may be arranged along
the outer periphery of the core. Respective fasteners can extend
through respective fastener holes in at least one of the skins,
into a respective fitting, and can be engaged with structure on the
LV to securely hold the assembly to the LV. The skins, stiffener,
and core may be bonded together by an adhesive injected as a fluid
before it hardens thereby filling in interior spaces in the core.
Or, the stiffener and core can be made integrally with each
other.
[0009] In another aspect, a auxiliary payload support unit (APSU)
for coordinating release of at least one auxiliary payload (AP)
from an AP support assembly in a launch vehicle (LV) includes a
processor, a communications interface between APSU and the LV , and
a computer readable data storage medium accessible to the
processor. The APSU communicates with the LV through one and only
one cable and receiving commands and power therethrough. The APSU
also receives, post-launch of the LV, an enable signal from the LV
prior to which the APSU cannot begin executing a launch sequence
for any AP such that the LV controls when the APSU begins executing
AP release but does not thereafter have to command or communicate
anything to the APSU regarding AP release, relieving the LV of the
burden of controlling launch of the AP.
[0010] In this aspect, if desired the processor, 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. The processor may receive from the AP a
separation signal indicating AP separation from the AP support
assembly. The processor, responsive to receiving the separation
signal, can determine whether another AP awaits release from the AP
support assembly and if so, the processor enables release of the
AP. Otherwise, the APSU deenergizes itself.
[0011] In another aspect, an auxiliary payload (AP) support
assembly includes a disk-shaped core configured for holding one or
more APs and 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 LV. A controller assembly is coupled to
the core and is configured for electrically communicating with the
LV to receive power therefrom. The controller assembly is 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.
[0012] The details of the present invention, both as to its
structure and operation, can best be understood in reference to the
accompanying drawings, in which like reference numerals refer to
like parts, and in which:
BRIEF DESCRIPTION OF THE DRAWINGS
[0013] FIG. 1 is an exploded perspective view of a launch vehicle
(LV) showing an example platform and launch initiation system, with
the primary spacecraft omitted for clarity;
[0014] FIG. 2 is a more detailed perspective view of the LV shown
in FIG. 1 including the primary spacecraft;
[0015] FIG. 3 is a perspective view of the platform and launch
initiation system of FIG. 1;
[0016] FIG. 4 is a side view detail taken at 4-4 in FIG. 3;
[0017] FIG. 5 is an exploded perspective view of an example
platform configured for three secondary spacecraft, with the
secondary spacecraft partially broken away;
[0018] FIG. 6 is a perspective view of the platform shown in FIG.
5, with the spool inserts removed for clarity;
[0019] FIG. 7 is an exploded perspective view of an example
platform configured for a single secondary spacecraft, with the
secondary spacecraft partially broken away;
[0020] FIG. 8 is a perspective view of the platform shown in FIG.
7, with the spool inserts removed for clarity;
[0021] FIG. 9 is a perspective view of an example spool insert;
[0022] FIG. 10 is a perspective view of one of a pair of LV
interface fittings;
[0023] FIG. 11 is a perspective of part of an example platform with
LV connectors shown in an exploded relationship;
[0024] FIG. 12 is a perspective view of an alternate platform for
three secondary spacecraft in which the strengthening web is made
integrally with the structural skin;
[0025] FIG. 13 is a perspective view of an alternate platform for a
single secondary spacecraft in which the strengthening web is made
integrally with the structural skin;
[0026] FIG. 14 is a functional block diagram of an example control
module, referred to herein as an auxiliary payload support unit
(APSU);
[0027] FIG. 15 is a functional flow diagram with additional detail
and interfaces of the APSU shown in FIG. 14;
[0028] FIG. 16 is a flow chart for a typical mission of example
logic including launch initiation logic that the APSU may execute
in accordance with present principles; and
[0029] FIGS. 17-21 are side elevational views of alternate shapes
that the may be used for the honeycomb core, with FIG. 21 showing a
core in relation to a launch vehicle.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
[0030] Referring initially to FIGS. 1-4, a launch vehicle 10 such
as but not limited to an Atlas V rocket or a Delta IV rocket can
have multiple booster stages 12 for carrying into space a primary
spacecraft 14 (FIG. 2), typically enclosed within separable
fairings 16 that part from each other once in space to permit
release of the primary spacecraft 14. A cylindrical ring-shaped
primary spacecraft adapter 18 may be provided between the uppermost
booster stage 12 and primary spacecraft 14 for engaging the
below-described AP platform system which supports one or more APs
20. As best shown in FIG. 4, the primary spacecraft adapter 18 can
be circumscribed around its upper edge with an inner annular flange
22 formed with bolt holes (not shown in FIG. 4), e.g., 121 bolt
holes, to which the below-described AP platform system including,
in example embodiments, an aluminum honeycomb cylindrical core 24
sandwiched between top and bottom structural aluminum skins 26, 28
is fastened.
[0031] FIGS. 5 and 6 illustrate an embodiment of the AP platform
system which supports three APs 30, it being understood that the AP
platform can be configured to support greater or fewer APs in
accordance with principles set forth herein. As shown, the core 24,
which in one implementation is made of aluminum honeycomb, is
cylindrical with opposed substantially continuous plane circular
faces. In the example shown, as schematically indicated by the
arrows 32 the honeycomb ribbon direction preferably is radial,
i.e., the direction of the ribbons of the honeycomb lie along
radials of the core 24. In example non-limiting embodiments the
core 24 may be composed of three equally-sized pie-shaped portions
that are bonded to each other using an adhesive such as but not
limited to FM410 adhesive. The core 24 may be made of Hexcel
1/8-5052-.002-8.1 pcf and may be 3.624 inches thick, although these
characteristics are not limiting. The core 24 may further be
machined to provide clearance for the below-described stiffener and
inserts.
[0032] With more specificity, a web-like stiffener 34 may be
provided to stiffen the structure and in particular reduce or
eliminate as many vibrations below frequencies of fifty Hertz as
possible. The stiffener 34 preferably fits snugly within slots 36
machined in to the core 24 and the slots 36 are shaped
complementarily to the stiffener 34 as shown. When so engaged the
top surface of the stiffener 34 is flush with the top surface of
the core 24 as can be appreciated in references to FIGS. 5 and 6.
The stiffener 34 may be made of aluminum such as quarter inch thick
6061-T6 aluminum and holes are machined into the stiffener 34 as
shown to accommodate the below-described inserts and fittings. The
choice of materials is not limiting.
[0033] In the example non-limiting embodiment shown, the stiffener
34 has a central opening that is coaxial with the core 24 and that
is circumscribed by a central enclosed hollow ring 38. Projecting
radially outwardly from the central enclosed hollow ring 38
substantially to the outer periphery of the core 24 are plural
azimuthally-spaced flat elongated stiffener arms 40. Completely
enclosed AP openings 42, one for each AP 30, are formed between
pairs of immediately adjacent long arms 40 and are radially outward
of the central enclosed hollow ring 38 and partially defined
thereby. Each AP opening 42 thus is defined in part by the central
enclosed hollow ring 38, the two long arms 40 that bound the
opening 42, and a respective outer peripheral segment 44,
protruding radially outwardly from which substantially to the outer
periphery of the core 24 is a respective stub arm 46. Accordingly,
for each AP opening 42 there is a respective pair of
radially-oriented long arms 40 and a respective radially-oriented
stub arm 46, with the AP openings 42 being uniformly distributed in
the azimuthal dimension defined by the core 24.
[0034] The top and bottom skins 26, 28 may be substantially
continuous disks except for holes as shown to accommodate the
below-described inserts and fittings. Specifically, in the three-AP
embodiment shown in FIGS. 5 and 6 each skin 26, 28 is formed with
three sets of twenty four insert holes 48, which each set being
arranged in a circle and the circles being uniformly distributed in
the azimuthal dimension defined by the core 24. It is to be
understood however that the number of inserts (and thus insert
holes 48) and their locations are established to match the AP 30
attachment system footprint.
[0035] Around their outer edges the skins 26, 28 are formed with
fitting fastener holes 50 arranged in sets for four, with the
circles of insert holes 48 being registered with respective AP
openings 42 of the stiffener 34 and with respective circles of
insert holes of the other skin. Likewise, the fitting fastener
holes 50 are registered with like holes in the opposite skin and
with fastener holes 52 in respective fittings 54 which are embedded
in fitting receptacles 56 of the core 24 as more fully disclosed
below. Like the below-described spool inserts for engaging the AN
30, the fittings 54, which engage the LV (specifically, which are
bolted to the flange 22 shown in FIG. 4) may be potted into the
core 24 using, e.g., EA9396.6MD potting compound. The skins 26, 28
may be made of aluminum such as 3/16 inch thick AL 6061-T6
aluminum.
[0036] Spool-like inserts 58 are received in registered sets of
insert holes 48 in the skins 26, 28, stiffener 34, and core 24
(insert holes in core 24 not shown). As intimated above, each set
of circularly-arranged inserts 58 engages a release mechanism of a
respective AP 30 to releasably couple the AP 30 to the core
24/stiffener 34/skins 26, 28 assembly. Referring briefly to FIG. 9,
each insert 58 may have a radially large central cylinder 60
terminating at opposed coaxial radially smaller end cylinders 62,
each of which may be formed with a respective central opening
64.
[0037] Turning to the fittings 54, an example of which is shown in
FIG. 10, the fittings 54 are arranged in pairs along the outer
periphery of the core 24 as shown and when engaged with the fitting
receptacles 56 of the core 24 are substantially flush with the top
and bottom surfaces of the core 24. Briefly referring to FIG. 10,
each fitting 54 is substantially parallel piped-shaped with opposed
parallel hollow fastener receptacles 66, so that a pair of fittings
54 has four receptacles 66 that are registered with respective
fastener holes 50 in the skins 26, 28. The ends of the receptacles
66 extend through the above-mentioned holes in the stiffener 34.
Accordingly, as shown in brief reference to FIG. 11, respective
fasteners 68 can extend through respective washers 70, fastener
holes 50 in the top skin 26, and fastener receptacles 66 of a
fitting 54 to securely hold the above-described assembly together
and to the flange 22 shown in FIG. 4. Bottom fasteners (not shown)
similarly can extend through the bottom skin 26 into bottoms of the
receptacles 66. In any case, the inserts 58 and receptacles 54 may
be made of the above-disclosed aluminum.
[0038] In some embodiments the skins, stiffener, and core are
bonded together (using, e.g., FM300-2U adhesive) and bolted
together using the above fasteners which may be "wet installed"
using an appropriate adhesive such as EA9394. The adhesive can be
injected as a fluid before it hardens thereby filling in the
honeycomb core directly surrounding the fastener. This infilling
increases the cores ability to "hold on to" the fastener by
increasing the shear surface the fastener can interact with.
[0039] Completing the description of FIGS. 5 and 6, an auxiliary
payload support unit (APSU) 72 is mounted on the top skin 26 for
reasons to be shortly disclosed.
[0040] FIGS. 7 and 8 show an assembly which is in all essential
respects identical to that shown in FIGS. 5 and 6, except that the
assembly shown in FIGS. 7 and 8 is configured to support a single
AP 30. Accordingly, a core 124 strengthened by a stiffener 134 is
sandwiched between upper and lower skins 126, 128. The stiffener
134 has a central opening that is coaxial with the core 124 and
that is circumscribed by a central enclosed hollow ring 138.
Projecting radially outwardly from the central enclosed hollow ring
138 and extending substantially to the outer periphery of the core
124 are plural azimuthally-spaced flat elongated stiffener arms
140. Unlike the assembly shown in FIGS. 5 and 6, in FIGS. 7 and 8
the central hollow ring 138 is configured to engage the AP 30 and
no other openings are formed in the stiffener, so that all the arms
140 are of the same length. Both the ring 138 and skins 126, 128
are formed with a single set of insert holes 148 arranged in a
circle and the circles of the stiffener and skins being registered
with each other to receive inserts 158 therein.
[0041] FIGS. 12 and 13 respectively three AP and single AP
assemblies in which stiffeners 234 are machined as single parts
with respective cores 224. The unitary cores/stiffeners shown in
FIGS. 12 and 13 may be used in lieu of their counterparts in FIGS.
5 and 7, respectively.
[0042] FIG. 14 shows a block diagram of an example APSU. A
processor 250 communicates with power circuitry 252 that in turn
receives, over a single electrical cable 254, power and enable
signals from a source 256 including a power source, typically 28
VDC, in the LV 10. The APSU 72 and the remainder of the AP 30
support assembly do not require any other electrical connections
with the LV 10. The processor 250 also accesses computer readable
data storage 258 such as disk-based and/or solid state storage for
purposes to be shortly disclosed. The processor 250 may also access
a wired or wireless communication interface 260; a telemetry module
262 and a video module (263) that may include an interface to,
among other components, instruments or a video camera.
[0043] FIG. 15 shows a combined functional flow and hardware block
diagram to illustrate additional features of the APSU 72. A power
management function 264 may be undertaken by the processor 250
and/or power circuitry 252 to supply power to the various
components of the APSU 72 and to the various Ms 30 (three shown in
FIG. 15). Mission sequences, e.g., AP 30 launch sequences, may be
stored in the storage 258 for access by a programmable deployment
sequencer function 266 that may be implemented by the processor 250
in accordance with logic set forth further below.
[0044] The power management function 264 may communicate with a
power switching function 268, also implemented or controlled by the
processor 250, which receives deploy signals from the programmable
deployment sequencer 266 indicating when a particular AP 30 should
begin to receive power from the power management function 264, with
the power switching function 268 sending power to the AP 30
indicated by the deploy signal. An AP 30 typically includes a
separation device 270 that engages the inserts described above and
a separation switch 272 that sends an separation signal to the
programmable deployment sequencer 266, to inform of successful
separation event. As was the case with the sole cable connection
254 between the APSU 72 and LV 10, a sole respective cable 274
connects the APSU 72 to each AP 30.
[0045] FIG. 15 shows that the APSU 72 communicates through the
communications interface 260 with the communication network 276 of
the LV 10 and thence to a ground station 278. Also, the telemetry
module 262 may receive input from various instrumentation 280 on
the LV 10 and may sense separation of an AP 30 as shown, to
activate a telemetry function to commence, e.g., generating video
of an AP as it releases from the LV. The telemetry module 262 may
also be controlled by or actuated by the programmable deployment
sequencer function 266 as shown. A system monitor function 282 may
be provided as part of the APSU 72 (and executed by, e.g., the
processor 250) to monitor APSU functions and components for
housekeeping and watchdog functions or provide updates thereon to
the ground station 278.
[0046] FIG. 16 shows example logic that may be implemented in
accordance with present principles. The first four steps are ground
operations and are presented for completeness. At step 284 the AP
30 deployment sequence is built or created, including which AP 30
will be launched from the LV 10 when during the flight of the LV
10. The sequence may be tested at step 286 in accordance with test
principles known in the art and then copied in software form onto,
e.g., the storage 258 at step 288. At step 290, once the launch
sequence has been received and other ancillary commands programmed
into it, the APSU 72 transitions to a dormant mode for launch, in
which it consumes little or no power.
[0047] Launch and transition to orbital operations begins at step
292, after which, at step 294, the LV 10 commences sending power to
the APSU 72, which powers up and commences executing its logic at
step 296. Proceeding to step 298 the APSU 72 receives an enable
signal from the LV 10 prior to which the APSU 72 cannot begin
executing a launch sequence for any AP 30. In this way, a safety
interlock is provided to the LV 10, which controls when the APSU
can begin executing AP 30 release but which does not thereafter
have to command or communicate anything to the APSU, relieving the
LV 10 of the burden of controlling launch of the AP 30.
[0048] Responsive to the enable signal at step 298, the APSU
proceeds to step 300 to load the launch sequence from, e.g.,
storage 258 to working memory of the processor 250. At step 302 the
APSU 72 enables power switching (from the power switching function
268 to the APs 30) so that as the APSU 72 executes the launch
sequence logic at step 304, the separation device(s) 270 of the
AP(s) 30 can be energized at step 306 on time as appropriate to
ensure AP launch on schedule. At step 308, separation device 270 is
activated to deploy the AP into space, leaving the LV 10.
Simultaneously at step 308, separation switch 272 is activated to
signal separation to the APSU 72. Responsive to receiving the
separation signal, at decision diamond 310 the APSU 72 determines
whether another AP 30 awaits release and if so, loops back to step
304 to execute the release of the other AP 30; otherwise, in the
event that the last AP 30 has been deployed, the APSU 72
deenergizes itself at state 312 to return to dormant mode as in
step 290.
[0049] FIGS. 17-21 illustrate that the above-described honeycomb
core which is sandwiched between structural skins may have shapes
other than disk-shaped. For example, as shown in FIG. 17 a core 400
may be shaped in side elevational view as a parabola, whereas FIG.
18 shows a core that may be shaped as an ellipse. FIG. 19
illustrates a core 404 shaped as a triangular arch while FIG. 20
shows a core 406 shaped as a segmental arch. Yet again, as shown in
FIG. 21 as core 408 may be shaped as a right circular frustum.
Respective structural skins may be provided on the upper and lower
(or inner and outer) surfaces of the cores shown in FIGS. 17-21 in
accordance with disclosure above. The core that is made of aluminum
honeycomb may be shaped using a free form tool to support one or
more APs.
[0050] While the particular PLATFORM AND LAUNCH INITIATION SYSTEM
FOR SECONDARY SPACECRAFT FOR LAUNCH VEHICLE is herein shown and
described in detail, it is to be understood that the subject matter
which is encompassed by the present invention is limited only by
the claims.
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