U.S. patent application number 15/236239 was filed with the patent office on 2017-05-25 for multi-stage space launch systems with reusable thrust augmentation and associated methods.
The applicant listed for this patent is The Boeing Company. Invention is credited to Michael Leslie Hand.
Application Number | 20170144780 15/236239 |
Document ID | / |
Family ID | 54141365 |
Filed Date | 2017-05-25 |
United States Patent
Application |
20170144780 |
Kind Code |
A1 |
Hand; Michael Leslie |
May 25, 2017 |
MULTI-STAGE SPACE LAUNCH SYSTEMS WITH REUSABLE THRUST AUGMENTATION
AND ASSOCIATED METHODS
Abstract
Systems and methods for launching space vehicles into outer
space are disclosed. Method include powering a thrust augmentation
stage of a launch vehicle during an initial portion of a launch
trajectory to provide thrust to the launch vehicle; following the
initial portion of the launch trajectory, separating a first stage
of the launch vehicle from the thrust augmentation stage; powering
the first stage of the launch vehicle during the initial portion
and during a second portion of the launch trajectory following the
initial portion of the launch trajectory to provide thrust to the
launch vehicle; and controlling a controlled descent of the thrust
augmentation stage to Earth following separation of the thrust
augmentation stage from the first stage.
Inventors: |
Hand; Michael Leslie;
(Huntington Beach, CA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
The Boeing Company |
Chicago |
IL |
US |
|
|
Family ID: |
54141365 |
Appl. No.: |
15/236239 |
Filed: |
August 12, 2016 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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14219818 |
Mar 19, 2014 |
9457918 |
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15236239 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64G 1/36 20130101; B64G
5/00 20130101; B64G 1/58 20130101; B64G 1/62 20130101; B64G 1/645
20130101; B64G 1/002 20130101; B64G 1/401 20130101; B64G 1/641
20130101; B64G 1/402 20130101 |
International
Class: |
B64G 1/00 20060101
B64G001/00; B64G 1/64 20060101 B64G001/64; B64G 1/62 20060101
B64G001/62; B64G 1/40 20060101 B64G001/40; B64G 1/36 20060101
B64G001/36 |
Claims
1. A method of launching a space vehicle into outer space, the
method comprising: powering a thrust augmentation stage of a launch
vehicle during an initial portion of a launch trajectory to provide
thrust to the launch vehicle, wherein the initial portion has a
maximum elevation of 10 kilometers; following the initial portion
of the launch trajectory, separating a first stage of the launch
vehicle from the thrust augmentation stage; powering the first
stage during the initial portion and a second portion of the launch
trajectory following the initial portion to provide thrust to the
launch vehicle; and controlling a controlled descent of the thrust
augmentation stage to Earth following separation of the thrust
augmentation stage from the first stage.
2. The method of claim 1, further comprising: separating the space
vehicle from the launch vehicle and placing the space vehicle into
outer space.
3. The method of claim 1, further comprising: retrieving and
reusing the thrust augmentation stage with a distinct first stage
to define a distinct launch vehicle for a subsequent launch of a
distinct space vehicle into outer space.
4. The method of claim 1, wherein the first stage provides thrust
to the launch vehicle during the separating.
5. The method of claim 4, wherein exhaust from the first stage
directly engages the thrust augmentation stage during the
separating.
6. The method of claim 1, wherein the thrust augmentation stage and
the first stage are lit on the ground and both provide thrust for
initial launch of the launch vehicle.
7. The method of claim 1, wherein the controlling the controlled
descent utilizes the same source of thrust used for the powering
the thrust augmentation stage during the initial portion of the
launch trajectory.
8. The method of claim 1, wherein the powering the thrust
augmentation stage comprises powering the thrust augmentation stage
by a liquid fuel.
9. The method of claim 1, wherein the controlling the controlled
descent comprises landing the thrust augmentation stage vertically
on Earth.
10. The method of claim 1, wherein the powering the thrust
augmentation stage is initiated at a launch facility to launch the
launch vehicle; and wherein the controlling the controlled descent
comprises returning the thrust augmentation stage to the launch
facility.
11. The method of claim 1, wherein the controlling the controlled
descent comprises returning the thrust augmentation stage to within
1000 meters from a position from which the launch vehicle was
launched.
12. The method of claim 1, wherein the controlling the controlled
descent comprises landing the thrust augmentation stage vertically
on Earth within 1000 meters from a position from which the launch
vehicle was launched.
13. The method of claim 1, wherein the controlling the controlled
descent comprises automatically landing the thrust augmentation
stage at a predetermined location.
14. The method of claim 1, wherein the controlling the controlled
descent comprises actively controlling the controlled descent by
reacting to conditions sensed by the thrust augmentation stage,
wherein the conditions sensed include wind speed, velocity,
acceleration, and location.
15. The method of claim 1, wherein the controlling the controlled
descent comprises controlling thrust vectors associated with
engines of the thrust augmentation stage.
16. The method of claim 15, wherein the controlling thrust vectors
comprises controlling one or more of (i) gimbals associated with
primary engines of the thrust augmentation stage, (ii) aerodynamic
flaps of the thrust augmentation stage, and (iii) auxiliary engines
of the thrust augmentation stage that are separate from the primary
engines.
17. The method of claim 1, wherein the separating comprises
longitudinally translating at least one rail within at least one
channel.
18. The method of claim 1, wherein the separating comprises
longitudinally translating the first stage out of a central bore of
the thrust augmentation stage.
19. The method of claim 1, wherein the controlling the controlled
descent comprises mating a plurality of shear cones of the thrust
augmentation stage with a plurality of pins of a land-based landing
structure.
20. The method of claim 1, further comprising: following the second
portion of the launch trajectory, separating a second stage of the
launch vehicle from the first stage; and powering the second stage
during a third portion of the launch trajectory following the
initial portion and the second portion of the launch
trajectory.
21. A method of launching a space vehicle into outer space, the
method comprising: powering a thrust augmentation stage of a launch
vehicle during an initial portion of a launch trajectory to provide
thrust to the launch vehicle; following the initial portion of the
launch trajectory, separating a first stage of the launch vehicle
from the thrust augmentation stage; powering the first stage of the
launch vehicle during the initial portion and a second portion of
the launch trajectory following the initial portion of the launch
trajectory to provide thrust to the launch vehicle, wherein the
thrust augmentation stage and the first stage of the launch vehicle
are lit on the ground and both provide thrust for initial launch of
the launch vehicle during the initial portion; and controlling a
controlled descent of the thrust augmentation stage to Earth
following separation of the thrust augmentation stage from the
first stage.
22. The method of claim 21, further comprising: separating the
space vehicle from the launch vehicle and placing the space vehicle
into outer space.
23. The method of claim 21, further comprising: retrieving and
reusing the thrust augmentation stage with a distinct first stage
to define a distinct launch vehicle for a subsequent launch of a
distinct space vehicle into outer space.
24. The method of claim 21, wherein the first stage provides thrust
to the launch vehicle during the separating.
25. The method of claim 24, wherein exhaust from the first stage
directly engages the thrust augmentation stage during the
separating.
26. The method of claim 21, wherein the controlling the controlled
descent utilizes the same source of thrust used for the powering
the thrust augmentation stage during the initial portion of the
launch trajectory.
27. The method of claim 21, wherein the powering the thrust
augmentation stage comprises powering the thrust augmentation stage
by a liquid fuel.
28. The method of claim 21, wherein the controlling the controlled
descent comprises landing the thrust augmentation stage vertically
on Earth.
29. The method of claim 21, wherein the powering the thrust
augmentation stage is initiated at a launch facility to launch the
launch vehicle; and wherein the controlling the controlled descent
comprises returning the thrust augmentation stage to the launch
facility.
30. The method of claim 21, wherein the controlling the controlled
descent comprises returning the thrust augmentation stage to within
1000 meters from a position from which the launch vehicle was
launched.
31. The method of claim 21, wherein the controlling the controlled
descent comprises landing the thrust augmentation stage vertically
on Earth within 1000 meters from a position from which the launch
vehicle was launched.
32. The method of claim 21, wherein the controlling the controlled
descent comprises automatically landing the thrust augmentation
stage at a predetermined location.
33. The method of claim 21, wherein the controlling the controlled
descent comprises actively controlling the controlled descent by
reacting to conditions sensed by the thrust augmentation stage,
wherein the conditions sensed include wind speed, velocity,
acceleration, and location.
34. The method of claim 21, wherein the controlling the controlled
descent comprises controlling thrust vectors associated with
engines of the thrust augmentation stage.
35. The method of claim 34, wherein the controlling thrust vectors
comprises controlling one or more of (i) gimbals associated with
primary engines of the thrust augmentation stage, (ii) aerodynamic
flaps of the thrust augmentation stage, and (iii) auxiliary engines
of the thrust augmentation stage that are separate from the primary
engines.
36. The method of claim 21, wherein the separating comprises
longitudinally translating at least one rail within at least one
channel.
37. The method of claim 21, wherein the separating comprises
longitudinally translating the first stage out of a central bore of
the thrust augmentation stage.
38. The method of claim 21, wherein the controlling the controlled
descent comprises mating a plurality of shear cones of the thrust
augmentation stage with a plurality of pins of a land-based landing
structure.
39. The method of claim 21, further comprising: following the
second portion of the launch trajectory, separating a second stage
of the launch vehicle from the first stage; and powering the second
stage during a third portion of the launch trajectory following the
initial portion and the second portion of the launch trajectory.
Description
RELATED APPLICATION
[0001] The present application is a continuation of and claims
priority to U.S. patent application Ser. No. 14/219,818, filed on
Mar. 19, 2014 and entitled "MULTI-STAGE SPACE LAUNCH SYSTEMS WITH
REUSABLE THRUST AUGMENTATION AND ASSOCIATED METHODS," the complete
disclosure of which is incorporated herein by reference.
FIELD
[0002] The present disclosure relates to multi-stage space launch
systems.
BACKGROUND
[0003] Historically, space launch systems have used varying numbers
of strap-on solid rocket boosters to provide additional thrust to a
multi-stage launch vehicle during an initial portion of a launch
trajectory. Even though it may be possible to reuse solid rocket
boosters in various circumstances, they typically are difficult and
expensive to retrieve and reuse following a launch. Moreover the
cost of such solid rocket boosters often is a significant portion
of the overall cost associated with placing a space vehicle into
outer space.
SUMMARY
[0004] Multi-stage space launch systems and methods for launching
space vehicles into outer space are disclosed herein.
[0005] Systems include a launch vehicle configured to operatively
support a space vehicle for placement in outer space. The launch
vehicle includes at least two stages, including a thrust
augmentation stage configured to provide thrust for launching the
space vehicle during an initial portion of a launch trajectory, and
a first stage configured to be selectively coupled to and decoupled
from the thrust augmentation stage and further configured to
provide thrust for launching the space vehicle during both the
initial portion of the launch trajectory and during a second
portion of the launch trajectory following the initial portion of
the launch trajectory. The thrust augmentation stage is configured
to be selectively decoupled from the first stage during the launch
trajectory and subsequently to be retrieved and reused following a
launch of the launch vehicle. In some systems, the thrust
augmentation stage may be described as a short-range thrust
augmentation stage.
[0006] Methods include powering a thrust augmentation stage of a
launch vehicle during an initial portion of a launch trajectory to
provide thrust to the launch vehicle; following the initial portion
of the launch trajectory, separating a first stage of the launch
vehicle from the thrust augmentation stage; powering the first
stage of the launch vehicle during the initial portion and during a
second portion of the launch trajectory following the initial
portion of the launch trajectory to provide thrust to the launch
vehicle; and controlling a controlled descent of the thrust
augmentation stage to Earth following separation of the thrust
augmentation stage from the first stage. In some methods, the
initial portion of the separating of the first stage from the
thrust augmentation stage may be at a relatively low elevation. In
some methods, the controlling the controlled descent may result in
the thrust augmentation stage landing at the launch facility from
which the launch vehicle initially launched.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] FIG. 1 is a schematic diagram representing multi-stage space
launch systems.
[0008] FIG. 2 is another schematic diagram representing multi-stage
launch systems.
[0009] FIG. 3 is a flowchart schematically representing methods of
launching a space vehicle into outer space.
[0010] FIG. 4 is a perspective view of an illustrative,
non-exclusive example of a launch vehicle of a multi-stage launch
system.
[0011] FIG. 5 is a perspective view of the thrust augmentation
stage of the launch vehicle of FIG. 4.
[0012] FIG. 6 is a perspective view of the assembly of the first,
second, and third stages of the launch vehicle of FIG. 4.
[0013] FIG. 7 is another perspective view of the thrust
augmentation stage of the launch vehicle of FIG. 4.
[0014] FIG. 8 is a perspective view of an illustrative,
non-exclusive example of landing structure for use with the thrust
augmentation stage of the launch vehicle of FIG. 4.
DESCRIPTION
[0015] Multi-stage space launch systems and methods are disclosed
herein. FIGS. 1-2 schematically represent illustrative,
non-exclusive examples of multi-stage space lunch systems 10
according to the present disclosure, and FIG. 3 schematically
represents illustrative, non-exclusive examples of methods 200 for
launching space vehicles into outer space according to the present
disclosure. In general, in FIG. 1, elements that are likely to be
included within an example of a system 10 are illustrated
schematically in solid lines, while elements that may be optional
are illustrated schematically in dashed lines. Moreover, the
methods and steps schematically represented in the flowchart of
FIG. 3 are not limiting and other methods and steps are within the
scope of the present disclosure, including methods having greater
than or fewer than the number of steps illustrated, as understood
from the discussions herein. Additionally, the illustrated steps
are not required to be performed in the order illustrated in all
methods according to the present disclosure. FIGS. 4-8 illustrate,
somewhat less schematically, an illustrative, non-exclusive example
of a multi-stage space launch system according to the present
disclosure.
[0016] Turning first to FIG. 1, as schematically illustrated, a
multi-stage space launch system 10 includes at least a launch
vehicle 12 that is configured to operatively support a space
vehicle 14 for placement in outer space. The launch vehicle
includes at least two stages 16 including a thrust augmentation
stage 18 and a first stage 20 that is configured to be selectively
coupled to and decoupled from the thrust augmentation stage;
however, as schematically and optionally represented in FIG. 1, a
launch vehicle may include more than two stages, including an
optional second stage 22 that is configured to be selectively
coupled to and decoupled from the first stage, and so forth. Any
suitable number of stages may be incorporated into a launch vehicle
12, including more than three stages, for example, depending on the
mass of the space vehicle 14, an orbit in which the space vehicle
is to be placed by a system 10, and/or whether or not the space
vehicle is to remain in an orbit of Earth or be launched beyond
Earth. Illustrative, non-exclusive examples of space vehicles
include man-made satellites, such as communication or other types
of satellites, inter-planet space vehicles, interstellar space
vehicles, including unmanned space vehicles as well as manned space
vehicles.
[0017] With reference to FIG. 2, the thrust augmentation stage 18
of a launch vehicle 12 is configured to augment the thrust of the
first stage 20 for launching the space vehicle during at least an
initial portion 21 of a launch trajectory 24. The first stage 20 of
a launch vehicle 12 is configured to provide thrust for launching
the space vehicle during the initial portion 21 of the launch
trajectory, as well as during a second portion 26 of the launch
trajectory following the initial portion of the launch trajectory.
In other words, the thrust augmentation stage and the first stage
both provide thrust during the initial portion of a launch, and the
first stage continues to provide thrust during the launch
trajectory following the thrust augmentation stage, that is, during
a second portion 26. Stated differently, in examples of launch
vehicles that utilize stages having combustion based engines, or
rockets, the engines associated with both the thrust augmentation
stage and the first stage may be lit on the ground, that is, at the
initiation of a launch, so that both the thrust augmentation stage
and the first stage provide thrust to the launch vehicle during the
initial portion of the launch trajectory.
[0018] Any suitable length of the initial portion 21 of the launch
trajectory 24 is within the scope of the present disclosure. As
discussed herein, some thrust augmentation stages 18 may be
described as short-range thrust augmentation stages, due to their
optional landing within the vicinity of a position from which the
launch vehicle was launched. As illustrative, non-exclusive
examples of short-range thrust augmentation stages, the initial
portion of a launch trajectory may extend to a maximum elevation of
one of 10, 20, 30, 40, or 50 kilometers. Additionally or
alternatively, the initial portion of a launch trajectory may last
for no more than 40, 50, 60, 70, 80, 90, or 100 seconds after
liftoff of the launch vehicle. Additionally or alternatively, an
initial portion of a launch trajectory may last until the launch
vehicle reaches a speed of no more than Mach 2, Mach 3, Mach 4, or
Mach 5.
[0019] As illustrative, non-exclusive examples only, the first
stage 20 and optional second, third, and so forth stages 16 may
correspond to and/or be adapted directly from existing space launch
systems, such as the various Delta and Atlas space launch systems.
That is, the first stage of such existing space launch systems may
be adapted to become the first stage 20 of a system 10 according to
the present disclosure, and thus configured to be used with a
thrust augmentation stage according to the present disclosure.
[0020] Some embodiments of thrust augmentation stage 18 may be
described as being reusable. For example, a thrust augmentation
stage 18 may be configured to be selectively decoupled from the
first stage 20 during the launch trajectory and subsequently
retrieved and reused following a launch of a launch vehicle that
includes the thrust augmentation stage. In some such embodiments,
the thrust augmentation stage 18 may be configured to be
selectively decoupled from the first stage during the launch
trajectory and subsequently retrieved and reused with a distinct
first stage to define a distinct launch vehicle for a subsequent
launch of a distinct space vehicle into outer space. Additionally
or alternatively, a thrust augmentation stage 18 may be configured
to land on Earth following a launch, for example without
significant, if any, damage to the thrust augmentation stage 18.
This optional configuration of a thrust augmentation stage is
schematically illustrated in FIG. 2, with the thrust augmentation
stage 18 separating from the first stage at the transition from the
initial portion 21 to the second portion 26 of the launch
trajectory 24, and with the thrust augmentation stage returning to
and landing on Earth 28.
[0021] In some embodiments, the thrust augmentation stage 18 may be
configured to land on Earth with the same orientation as the thrust
augmentation stage was launched, for example, in a vertical
orientation. In some embodiments, the thrust augmentation stage 18
may be configured to utilize the same source of thrust that is used
during the initial portion 21 of the launch trajectory 24 to return
to and land on Earth. For example, as discussed herein, the thrust
augmentation stage 18 may include one or more engines 54, with at
least a subset of such engines providing thrust both for launching
the launch vehicle during the initial portion of the launch
trajectory and during a controlled descent 29 of the thrust
augmentation stage 18 back to Earth, as schematically and
optionally represented in FIG. 2. The controlled descent 29
additionally or alternatively may be described as a controlled
landing 29. By a controlled descent, or landing, it is meant that
the thrust augmentation stage 18 may land at a predetermined
location, for example, at or near a position from which the launch
vehicle was initially launched, as discussed in more detail herein.
Additionally or alternatively, controlled landing may mean that the
descent and landing of the thrust augmentation stage does not
result in significant damage to the thrust augmentation stage
and/or does not result in significant cost to retrieve and/or reuse
the thrust augmentation stage.
[0022] As illustrative, non-exclusive examples, a thrust
augmentation stage 18 may include four, six, eight, ten, or more
than ten even-numbered engines, with all of the engines being used
during the initial portion of the launch and with only a subset
(e.g., one-half) of the engines being used for the controlled
descent 29. Moreover, the subset of the engines used for the
controlled descent may be evenly spaced around the longitudinal
axis 31 of the thrust augmentation stage, so as to have a thrust
vector that is aligned with the center of mass of the thrust
augmentation stage.
[0023] As schematically illustrated in FIG. 1, some systems 10 also
may include a land-based landing structure 30 that is configured to
selectively mate with the thrust augmentation stage 18 following a
launch, that is, when the thrust augmentation stage returns to
Earth, for example, in systems 10 in which the thrust augmentation
stage is configured to be retrieved and reused following a launch.
Similarly, in such embodiments, the thrust augmentation stage 18 is
configured to mate with the landing structure 30 following a launch
when the thrust augmentation stage returns to Earth. In some
embodiments, the thrust augmentation stage 18 may include a
plurality of shear cones 32 positioned at the aft of the thrust
augmentation stage, and the landing structure 30 may include a
plurality of pins 34 that are configured to mate with the plurality
of shear cones 32, as schematically illustrated in FIG. 1. Other
mating structures also are within the scope of the present
disclosure and may be incorporated into landing structures 30 and
thrust augmentation stages 18.
[0024] In some embodiments, the thrust augmentation stage 18 may
include a body 36 that defines a central bore 38, with the first
stage 20 extending through the central bore when the thrust
augmentation stage and the first stage are operatively coupled
together for launch to define a launch vehicle 12, as schematically
illustrated in FIG. 1. In some such embodiments, the central bore
38 may be coaxial with the longitudinal axis of the launch vehicle
12. Additionally or alternatively, the launch vehicle 12, the
thrust augmentation stage 18, and the first stage 20 may share a
longitudinal axis 31, at least when the thrust augmentation stage
and the first stage are operatively coupled together. Stated
differently, the longitudinal axis of the thrust augmentation stage
may be coaxial with the longitudinal axis of the first stage when
the thrust augmentation stage and the first stage are operatively
coupled together for launch of the launch vehicle and during the
initial portion of a launch trajectory.
[0025] In some embodiments, the central bore 38 may extend
completely through the thrust augmentation stage 18, as
schematically represented in FIG. 1. Accordingly, when the first
stage 20 is operatively coupled to the thrust augmentation stage
18, the first stage 20 may extend through, and, in some
embodiments, completely through, the central bore 38 of the thrust
augmentation stage 18. Additionally or alternatively, the first
stage 20 may be accessible via the central bore from the aft side
of the thrust augmentation stage.
[0026] In some embodiments, and as schematically represented in
FIG. 1, the thrust augmentation stage and the first stage may
collectively define a guide track 40 at an interface between the
thrust augmentation stage 18 and the first stage 20 when they are
operatively coupled together. When present, the guide track 40 may
be configured to operatively constrain movement of the first stage
20 relative to the thrust augmentation stage 18 to longitudinal
translation when the first stage is being coupled to and decoupled
from the thrust augmentation stage. In other words, the guide track
40 may restrict relative rotational movement between the thrust
augmentation stage and the first stage and may provide for a guided
longitudinal coupling of the first stage to the thrust augmentation
stage when they are being coupled together and for a guided
longitudinal uncoupling of the first stage from the thrust
augmentation stage when they are being decoupled.
[0027] Various configurations of optional guide tracks 40 are
within the scope of the present disclosure. As an illustrative,
non-exclusive example, a guide track may include a plurality of
channels 42 and a plurality of corresponding rails 44 that are
configured to longitudinally translate within the plurality of
channels. For example, the thrust augmentation stage may include or
define a plurality of channels, and the first stage may include or
define a plurality of rails corresponding to the plurality of
channels. Additionally or alternatively, the thrust augmentation
stage may include or define a plurality of rails, and the first
stage may include or define a plurality of channels corresponding
to the plurality of rails. In some embodiments, the optional rails
may include rollers 46 configured to longitudinally roll within
corresponding channels. In some such embodiments, the rollers may
be spring biased toward the corresponding channels, for example, to
facilitate desired tolerances of fit between the thrust
augmentation stage and the first stage when they are coupled
together, as well as when they are being coupled together and when
they are being decoupled from each other. As illustrative,
non-exclusive examples, a guide track 40 may include three, four,
or more than four sets of channels 42 and corresponding rails
44.
[0028] Additionally or alternatively, as also schematically
represented in FIG. 1, the launch vehicle 12 may include a coupling
mechanism 48 that is configured to selectively and operatively
couple together the thrust augmentation stage 18 and the first
stage 20 for launch of the launch vehicle and to selectively and
operatively decouple the thrust augmentation stage from the first
stage during launch. In some embodiments, although not required,
the coupling mechanism 48 may be associated with the guide track
40. Illustrative, non-exclusive examples of coupling mechanisms 48
may include explosive bolts and/or separation nuts. The coupling
mechanism 48 also may include a latch mechanism operable to prevent
longitudinal movement of the first stage relative to the thrust
augmentation stage when the first stage is operatively coupled to
the thrust augmentation stage.
[0029] In some embodiments, the thrust augmentation stage 18 may
include interface heat shielding structure 50 at the interface
between the thrust augmentation stage and the first stage 20 when
they are operatively coupled together. When present, this interface
heat shielding structure 50 is configured to protect the thrust
augmentation stage from heat generated by the first stage to which
the thrust augmentation stage may be exposed during separation of
the thrust augmentation stage and the first stage and/or during a
launch. In embodiments in which the thrust augmentation stage
defines a central bore 38, interface heat shielding structure 50
may line the central bore. In some such embodiments, the interface
heat shielding structure may completely line or may substantially
line the central bore. Illustrative, non-exclusive examples of
interface heat shielding structure 50 of a thrust augmentation
stage 18 include (but are not limited to) high-temperature reusable
surface insulation, fibrous refractory composite insulation,
toughened unipiece fibrous insulation, low-temperature reusable
surface insulation, flexible insulation blankets, advanced flexible
reusable insulation, reinforced carbon-carbon, and/or
flame-resistant meta-aramid material.
[0030] In some embodiments, the thrust augmentation stage 18
additionally or alternatively may include aft heat shielding
structure 52. The aft heat shielding structure 52 may be arranged
at an aft portion of the thrust augmentation stage 18. When
present, the aft heat shielding structure 52 may be configured to
protect the thrust augmentation stage from heat generated by the
thrust augmentation stage, such as associated with one or more
combustion based engines of the thrust augmentation stage.
Additionally or alternatively, the aft heat shielding structure 52
may be configured to protect the thrust augmentation stage from
heat generated by the first stage, such as associated with one or
more combustion based engines of the first stage, for example, when
the thrust augmentation stage and the first stage are coupled
together during the initial portion of a launch trajectory. Similar
to interface heat shielding structure 50, the aft heat shielding
structure 52 may include (but is not limited to) high-temperature
reusable surface insulation, fibrous refractory composite
insulation, toughened unipiece fibrous insulation, low-temperature
reusable surface insulation, flexible insulation blankets, advanced
flexible reusable insulation, reinforced carbon-carbon,
flame-resistant meta-aramid material, or combinations thereof.
[0031] In embodiments that include both interface heat shielding
structure 50 and aft heat shielding structure 52, the aft heat
shielding structure 52 may be more robust than the interface heat
shielding structure 50. Additionally or alternatively, the aft heat
shielding structure 52 may be configured to withstand elevated
temperatures for a longer period of time than the interface heat
shielding structure 50. For example, during the initial portion of
a launch trajectory, the aft heat shielding structure 52 may be
exposed to significant elevated temperatures from the thrust
augmentation stage and first stage combustion based engines, while
the interface heat shielding structure 50 may be exposed to
significant elevated temperatures for a short duration, for
example, only during operative separation of the first stage from
the thrust augmentation stage following the initial portion of the
launch trajectory.
[0032] As schematically represented in FIG. 1, a thrust
augmentation stage 18 of a launch vehicle 12 may include one or
more engines 54 that are configured to selectively provide thrust
for at least the initial portion 21 of a launch trajectory 24 and
optionally also during a controlled descent 29 and landing of the
thrust augmentation stage. Any suitable number of engines 54 may be
provided depending on the overall desired configuration of a system
10. As illustrative, non-exclusive examples, a thrust augmentation
stage 18 may include six or more engines evenly spaced around the
aft end of the thrust augmentation stage.
[0033] As also schematically represented in FIG. 1, a first stage
20 of a launch vehicle 12 may include one or more engines 56 that
are configured to provide thrust during both the initial portion 21
and the second portion 26 of the launch trajectory. Any suitable
configuration of engines 54 and engines 56 may be utilized,
including (but not limited to) combustion based engines. As
illustrative, non-exclusive examples, engines 54 and engines 56 may
be powered by a liquid fuel.
[0034] In some embodiments, the thrust augmentation stage 18 may
include a liquid fuel tank 58 for holding a volume of liquid fuel
60, as schematically represented in FIG. 1, with the liquid fuel
tank being operatively coupled to the engine(s) 54. Illustrative,
non-exclusive examples of suitable liquid fuels include Rocket
Propellant-1 (RP-1, kerosene), liquid hydrogen, liquid methane, and
mono-methyl hydrazine; however, any suitable fuel may be used.
Additionally, as also schematically and optionally represented in
FIG. 1, the thrust augmentation stage also may include a liquid
oxygen tank 62 for holding a volume of liquid oxygen 64, with the
liquid oxygen tank also being operatively coupled to the engine(s)
54. Additionally or alternatively, in examples of engines that
utilize mono-methyl hydrazine as a liquid fuel, tank 62 may hold a
volume of nitrogen tetroxide. An illustrative, non-exclusive
example of a suitable engine 54 includes (but is not limited to)
the RS-27A engine used on first stage Delta II rockets.
[0035] In systems 10 that include a thrust augmentation stage 18
that is configured to be retrieved and reused following a launch,
such a system 10 also may include a control system 66 that is
configured, or programmed, to control a controlled descent 29 of
the thrust augmentation stage to Earth following the initial
portion 21 of the launch trajectory 24. In some such embodiments,
the control system 66 may be configured to automatically control
the controlled descent. By automatically control the controlled
descent, it is meant that the control system may be programmed to
automatically control the controlled descent without active and/or
real-time input from a user, such as from a user that pilots, or
otherwise actively steers, directs, and/or controls the controlled
descent via real-time human input. Additionally or alternatively,
the control system may be configured to actively control the
controlled descent 29. By actively control the controlled descent,
it is meant that the control system may be configured to react to
the various conditions sensed and/or detected by the control system
and actively account for such various conditions with instructions
sent to the thrust augmentation stage for controlling the
controlled descent, whether such instructions are or are not the
direct result of real-time human input.
[0036] In some embodiments, the optional control system 66 may
include a land-based communication device 68 and a thrust
augmentation stage communication device 70. The thrust augmentation
stage communication device 70 may be located onboard the thrust
augmentation stage 18. The land-based communication device 68 may
be configured to selectively and/or wirelessly send operational
instructions to the thrust augmentation stage communication device
70 to control the controlled descent of the thrust augmentation
stage.
[0037] In some embodiments, the control system may include one or
more sensors 72 that are configured to sense conditions associated
with the thrust augmentation stage during a controlled descent of
the thrust augmentation stage and to utilize the sensed conditions
to control the controlled descent. The one or more sensors 72 may
be located onboard the thrust augmentation stage 18 and may be
configured to sense such illustrative, non-exclusive conditions as
environmental conditions such as wind speed, as well as positional
conditions such as velocity, acceleration, and location such as
that may be sensed with a global positioning satellite (GPS)
system. The control system may utilize such information to
facilitate a controlled descent of the thrust augmentation
stage.
[0038] Additionally or alternatively, the control system may
include one or more detectors 74 that are configured to detect a
current location of the thrust augmentation stage during a
controlled descent and to utilize the detected location to control
the controlled descent. For example, such detectors 74 may be
land-based and include such systems as radar systems.
[0039] Collectively, one or more of the thrust augmentation stage
communication device 70, the land-based communication device 68,
the sensors 72, and the detectors 74 may be described as an
avionics system 71 of the control system 66. Control systems 66
also may include one or more force control mechanisms, or systems,
75 that operatively provide controlling forces to the thrust
augmentation stage during its controlled descent. For example, the
engines 54 of the thrust augmentation stage may be gimbaled and
controlled to effectuate changes in the thrust vector associated
with the engines during a controlled descent, with this
schematically represented in FIG. 1 with the force control
mechanism 75 illustrated in an overlapping relationship with an
engine 54. Additionally or alternatively, a force control mechanism
75 may include one or more aerodynamic flaps that are operatively
controlled to apply aerodynamic moments on the thrust augmentation
stage. Additionally or alternatively, a force control mechanism 75
may include one or more auxiliary engines that are separate and
apart from the primary thrust engines 54 and that may be controlled
to facilitate the controlled descent of the thrust augmentation
stage. Other configurations and implementation of force control
mechanisms 75 also are within the scope of the present
disclosure.
[0040] In some embodiments, the control system may be configured to
control the controlled descent 29 of the thrust augmentation stage
to Earth following the initial portion 21 of the launch trajectory
24 to within a threshold distance from a position from which the
launch vehicle is launched. Illustrative, non-exclusive examples of
such a threshold include distances of 1000, 500, 100, 10, and 1
meters. In other words, following the initial portion of a launch
trajectory, the thrust augmentation stage may be controlled to
return to the location from which it was initially launched with
the first stage as part of the launch vehicle. In such systems 10,
the thrust augmentation stage may be described as a short-range
thrust augmentation stage, because the thrust augmentation stage
returns to Earth at least within the vicinity of the position from
which the launch vehicle was launched, as opposed to a long-range
system with an augmentation stage returning to Earth a significant
distance from the position from which the launch vehicle was
launched and thus requiring transportation of the augmentation
stage over a significant distance.
[0041] In some such systems 10, a system may be described as
including a launch facility 76, from which the launch vehicle is
launched, and the control system 66 may be configured to control
the controlled descent 29 of the thrust augmentation stage to the
launch facility following the initial portion 21 of the launch
trajectory 24. For example, the launch facility may include a
launch pad 78, from which the launch vehicle is launched, and
optional landing structure 30 may be within a threshold distance of
the launch pad. Illustrative, non-exclusive examples of such a
threshold include distances of 1000, 500, 100, 10, and 1 meters.
Additionally or alternatively, the control system may be configured
to control the controlled descent of the thrust augmentation stage
directly to the launch pad itself. Additionally or alternatively,
in some embodiments, the optional landing structure 30 may be
placed a distance away from the launch pad, such as within one of
the aforementioned threshold distances, for mating with the thrust
augmentation stage when landing, and then following the landing,
the landing structure optionally may be used to support the thrust
augmentation stage for transportation back to the launch pad for
use with a subsequent launch of a launch vehicle.
[0042] FIG. 3 schematically provides a flowchart that represents
illustrative, non-exclusive examples of methods 200 for launching
space vehicles into outer space. Methods 200 may correspond with
one or more examples of systems 10 according to the present
disclosure. Accordingly, the following discussion makes reference
to the various discussed, including optional, components of systems
10; however, not all systems 10 necessarily correspond to a method
200, and methods 200 as discussed herein do not limit systems 10 to
the discussed methods and associated steps.
[0043] With reference also to FIG. 2, methods 200 include powering
a thrust augmentation stage 18 of a launch vehicle 12 during at
least an initial portion 21 of a launch trajectory 24 to provide
thrust to the launch vehicle, as schematically indicated at 202 in
FIG. 3. Methods 200 also include, following the initial portion of
the launch trajectory, separating a first stage 20 from the thrust
augmentation stage 18, as schematically indicated at 204. Methods
200 also include powering the first stage 20 of the launch vehicle
during the initial portion 21 and a second portion 26 of the launch
trajectory to provide thrust to the launch vehicle, as
schematically indicated at 206 in FIG. 3.
[0044] As schematically indicated at 208 in FIG. 3, methods 200
also include separating the space vehicle 14 from the launch
vehicle 12 and placing the space vehicle 14 into outer space.
Depending on the number of stages 16 that a launch vehicle
includes, the space vehicle may be separated from the first stage
20 or from a second or subsequent stage.
[0045] Methods 200 also include controlling a controlled descent 29
of the thrust augmentation stage 18 to Earth 28 following the
initial portion 21 of the launch trajectory 24, as schematically
indicated at 210 in FIG. 3.
[0046] Methods 200 also include retrieving and reusing the thrust
augmentation stage 18 with a distinct first stage 20 to define a
distinct launch vehicle 12 for subsequent launch of a distinct
space vehicle 14 into outer space, as schematically indicated at
212 in FIG. 3. Further optional steps may include recharging or
refueling the thrust augmentation stage 18 for use with another
launch vehicle.
[0047] Turning now to FIGS. 4-8, illustrative non-exclusive
examples of component parts of a system 10 are illustrated. Where
appropriate, the reference numerals from the schematic
illustrations of FIGS. 1-2 are used to designate corresponding
parts of the examples; however, the examples of FIGS. 4-8 are
non-exclusive and do not limit systems 10 to the illustrated
embodiments of FIGS. 4-8. That is, systems 10 are not limited to
the specific embodiments of FIGS. 4-8, and systems 10 may
incorporate any number of the various aspects, configurations,
characteristics, properties, etc. of systems 10 that are
illustrated in and discussed with reference to the schematic
representations of FIGS. 1-2 and/or the embodiments of FIGS. 4-8,
as well as variations thereof, without requiring the inclusion of
all such aspects, configurations, characteristics, properties, etc.
For the purpose of brevity, each previously discussed component,
part, portion, aspect, region, etc. or variants thereof may not be
discussed, illustrated, and/or labeled again with respect to the
examples of FIGS. 4-8; however, it is within the scope of the
present disclosure that the previously discussed features,
variants, etc. may be utilized with these examples.
[0048] FIGS. 4-7 illustrate an example launch vehicle 12, indicated
generally at 112. As illustrated, launch vehicle 112 is an example
of a launch vehicle that includes four stages 16, including a
thrust augmentation stage 18, a first stage 20, a second stage 22,
and a third stage 23 that supports a space vehicle 14. The thrust
augmentation stage of launch vehicle 112 is identified herein as
thrust augmentation stage 118. The first stage, the second stage,
and the third stage of launch vehicle 112 are identified herein as
the main, or primary, stages 116.
[0049] The thrust augmentation stage 118 of launch vehicle 112 is
an example of a thrust augmentation stage 18 that defines a central
bore 38, with the first stage 20 extending through the central bore
when the thrust augmentation stage and the first stage are
operatively coupled together for launch, as illustrated in FIG. 4.
The thrust augmentation stage 118 may include a body 36 which may
be aerodynamically shaped to reduce drag during launch and/or the
initial portion of the launch trajectory. The body 36 may include a
first portion 37 which may define a first fuel tank (e.g., a liquid
fuel tank 58 which may contain a liquid fuel 60, such as RP-1) and
a second portion 39 which may define a second fuel tank (e.g., a
liquid oxygen tank 62, which may contain liquid oxygen 64).
[0050] Moreover, launch vehicle 112 is an example of a launch
vehicle in which the thrust augmentation stage and the first stage
collectively define a guide track 40 at an interface between the
thrust augmentation stage and first stage. In the illustrated
example, the thrust augmentation stage 118 includes three channels
42, as seen in FIG. 5, and the first stage includes three
corresponding rails 44, as seen in FIG. 6.
[0051] The thrust augmentation stage 118 of launch vehicle 112 also
is an example of a thrust augmentation stage that includes a
plurality of shear cones 32 positioned at the aft of the thrust
augmentation stage, as illustrated in FIG. 7. More specifically,
the example thrust augmentation stage includes six shear cones
evenly spaced about the aft of the thrust augmentation stage
interspaced with six engines 54. FIG. 8 illustrates an
illustrative, non-exclusive example of corresponding landing
structure 30 that is configured to mate with the shear cones of the
thrust augmentation stage following a launch of the launch vehicle
112. The example landing structure, identified as landing structure
130, includes six pins 34 that are positioned and sized to mate
with the shear cones. Accordingly, a control system 66 of a system
10 may control a controlled descent of the thrust augmentation
stage 118 so that it lands on and mates with the example landing
structure 130.
[0052] Illustrative, non-exclusive examples of inventive subject
matter according to the present disclosure are described in the
following enumerated paragraphs:
[0053] A. A multi-stage space launch system for launching a space
vehicle into outer space, the system comprising: [0054] a launch
vehicle configured to operatively support a space vehicle for
placement in outer space, wherein the launch vehicle includes at
least two stages including: [0055] a thrust augmentation stage
configured to provide thrust for an initial portion of a launch
trajectory; and [0056] a first stage configured to be selectively
coupled to and decoupled from the thrust augmentation stage and
further configured to provide thrust during the initial portion and
during a second portion of the launch trajectory following the
initial portion of the launch trajectory.
[0057] A1. The system of paragraph A, wherein the thrust
augmentation stage is configured to be selectively decoupled from
the first stage during the launch trajectory and subsequently to be
retrieved and reused following a launch of the launch vehicle.
[0058] A2. The system of any of paragraphs A-A1, wherein the thrust
augmentation stage is configured to be selectively decoupled from
the first stage during the launch trajectory.
[0059] A2.1. The system of paragraph A2, wherein the thrust
augmentation stage is further configured to be subsequently
retrieved and reused with a distinct first stage to define a
distinct launch vehicle for a subsequent launch of a distinct space
vehicle into outer space.
[0060] A2.2. The system of any of paragraphs A2-A2.1, wherein the
thrust augmentation stage is further configured for controlled
landing following separation from the first stage.
[0061] A3. The system of any of paragraphs A-A2.2, wherein the
thrust augmentation stage is configured to land on Earth following
a launch, optionally without significant damage to the thrust
augmentation stage.
[0062] A4. The system of any of paragraphs A-A3, wherein the thrust
augmentation stage is configured to land on Earth with the same
orientation as was launched, optionally vertically, following a
launch.
[0063] A5. The system of any of paragraphs A-A4, wherein the thrust
augmentation stage is configured to utilize the same source of
thrust that is used during the initial portion of the launch
trajectory to return to and land on Earth.
[0064] A6. The system of any of paragraphs A1-A5, further
comprising: [0065] a land-based landing structure configured to
selectively mate with the thrust augmentation stage following a
launch when the thrust augmentation stage returns to Earth; [0066]
wherein the thrust augmentation stage is configured to mate with
the landing structure following a launch when the thrust
augmentation stage returns to Earth.
[0067] A6.1. The system of paragraph A6, [0068] wherein the thrust
augmentation stage includes a plurality of shear cones positioned
at an aft portion of the thrust augmentation stage; and [0069]
wherein the landing structure includes a plurality of pins
configured to mate with the plurality of shear cones.
[0070] A7. The system of any of paragraphs A-A6.1, wherein the
thrust augmentation stage includes a body that defines a central
bore, and wherein the first stage extends through the central bore
for launch.
[0071] A7.1. The system of paragraph A7, wherein the launch vehicle
has a longitudinal axis, and wherein the central bore is coaxial
with the longitudinal axis.
[0072] A7.2. The system of any of paragraphs A7-A7.1, wherein the
central bore extends completely through the thrust augmentation
stage.
[0073] A8. The system of any of paragraphs A-A7.2, wherein the
thrust augmentation stage and the first stage collectively define a
guide track at an interface between the thrust augmentation stage
and the first stage when the thrust augmentation stage and the
first stage are operatively coupled together, wherein the guide
track is configured to operatively constrain longitudinal
translation of the first stage relative to the thrust augmentation
stage when the first stage is being decoupled from the thrust
augmentation stage during launch.
[0074] A8.1. The system of paragraph A8, wherein the guide track
includes at least one channel and at least one rail configured to
longitudinally translate within the at least one channel.
[0075] A8.1.1. The system of paragraph A8.1, wherein one of the
thrust augmentation stage and the first stage includes the at least
one channel and the other of the thrust augmentation stage and the
first stage includes the at least one rail.
[0076] A8.1.2. The system of any of paragraphs A8.1-A8.1.1, wherein
the rail includes rollers configured to longitudinally roll within
the at least one channel.
[0077] A8.1.2.1. The system of paragraph A9.1.2, wherein the
rollers are spring biased toward the at least one channel.
[0078] A9. The system of any of paragraphs A-A8.1.2.1, [0079]
wherein the launch vehicle includes a coupling mechanism configured
to selectively and operatively couple together the thrust
augmentation stage and the first stage for launch of the launch
vehicle, wherein the coupling mechanism is further configured to
selectively and operatively decouple the thrust augmentation stage
from the first stage during the launch trajectory.
[0080] A9.1. The system of paragraph A9, wherein the coupling
mechanism includes explosive bolts.
[0081] A9.2. The system of any of paragraphs A9-A9.1, wherein the
coupling mechanism includes separation nuts.
[0082] A10. The system of any of paragraphs A-A9.2, wherein the
thrust augmentation stage includes interface heat shielding
structure at an interface between the thrust augmentation stage and
the first stage, wherein the interface heat shielding structure is
configured to protect the thrust augmentation stage from heat
associated with the first stage during separation of the thrust
augmentation stage and the first stage during launch of the launch
vehicle.
[0083] A10.1 The system of paragraph A10, wherein the interface
heat shielding structure includes one or more of high-temperature
reusable surface insulation, fibrous refractory composite
insulation, toughened unipiece fibrous insulation, low-temperature
reusable surface insulation, flexible insulation blankets, advanced
flexible reusable insulation, reinforced carbon-carbon, and
flame-resistant meta-aramid material.
[0084] A11. The system of any of paragraphs A-A10.1, wherein the
thrust augmentation stage includes aft heat shielding structure at
the aft of the thrust augmentation stage, wherein the aft heat
shielding structure is configured to protect the thrust
augmentation stage from heat generated by the thrust augmentation
stage and from heat generated by the first stage during launch of
the launch vehicle.
[0085] A11.1. The system of paragraph A11 when depending from
paragraph A10, wherein the aft heat shielding structure is more
robust than the interface heat shielding structure.
[0086] A11.2. The system of any of paragraphs A11-A11.1 when
depending from paragraph A10, wherein the aft heat shielding
structure is configured to withstand elevated temperatures for a
longer period of time than the interface heat shielding
structure.
[0087] A12. The system of any of paragraphs A-A11.2, wherein the
thrust augmentation stage is configured to be powered by a liquid
fuel.
[0088] A13. The system of any of paragraphs A-A12, wherein the
thrust augmentation stage includes a liquid fuel tank, optionally
further comprising liquid fuel in the liquid fuel tank, optionally
wherein the liquid fuel includes Rocket Propellant-1 (RP-1).
[0089] A14. The system of any of paragraphs A-A13, wherein the
thrust augmentation stage includes a liquid oxygen tank, optionally
further comprising liquid oxygen in the liquid oxygen tank.
[0090] A15. The system of any of paragraphs A-A14, wherein the
thrust augmentation stage includes one or more engines configured
to be powered by a liquid fuel and to provide thrust for launching
the space vehicle during at least the initial portion of the launch
trajectory, and optionally during a controlled descent of the
thrust augmentation stage to Earth following the initial portion of
the launch trajectory.
[0091] A16. The system of any of paragraphs A-A15, further
comprising: [0092] a control system configured, or programmed, to
control a controlled descent of the thrust augmentation stage to
Earth following the initial portion of the launch trajectory.
[0093] A16.1. The system of paragraph A16, wherein the control
system is configured to automatically control the controlled
descent.
[0094] A16.2. The system of any of paragraphs A16-A16.1, wherein
the control system is configured to actively control the controlled
descent.
[0095] A16.3. The system of any of paragraphs A16-A16.2, wherein
control system includes a land-based communication device and a
thrust augmentation stage communication device, and wherein the
land-based communication device is configured to selectively send
operational instructions to the thrust augmentation stage
communication device to control the controlled descent of the
thrust augmentation stage.
[0096] A16.4. The system of any of paragraphs A16-A16.3, wherein
the control system includes one or more sensors configured to sense
environmental conditions associated with the thrust augmentation
stage during the controlled descent, and wherein the control system
is configured to utilize the environmental conditions to control
the controlled descent.
[0097] A16.5. The system of any of paragraphs A16-A16.4, wherein
the control system includes one or more detectors configured to
actively detect a detected location of the thrust augmentation
stage during the controlled descent, and wherein the control system
is configured to utilize the detected location of the thrust
augmentation stage to control the controlled descent.
[0098] A16.6. The system of any of paragraphs A16-A16.5, further
comprising: [0099] a launch facility, from which the launch vehicle
is configured to launch; [0100] wherein the control system is
configured to control the controlled descent of the thrust
augmentation stage to the launch facility following the initial
portion of the launch trajectory.
[0101] A16.6.1. The system of paragraph A16.6 when depending from
paragraph A6, wherein the launch facility includes a launch pad,
from which the launch vehicle is configured to launch, and wherein
the landing structure is within 1000 meters, 500 meters, 100
meters, 10 meters, or 1 meter of the launch pad, optionally wherein
the launch pad includes the landing structure.
[0102] A16.7. The system of any of paragraphs A16-A16.6.1, wherein
the control system is configured to control the controlled descent
of the thrust augmentation stage to Earth following the initial
portion of the launch trajectory to within 1000 meters, 500 meters,
100 meters, 10 meters, or 1 meter from a position from which the
launch vehicle is launched.
[0103] A17. The system of any of paragraphs A-A16.7, [0104] wherein
the first stage is configured to be used only once as a component
of a launch vehicle; [0105] wherein the first stage is not
configured to be reused following a launch of the launch vehicle;
and/or [0106] wherein the first stage is configured to not be
reused following a launch of the launch vehicle.
[0107] A18. The system of any of paragraphs A-A17, further
comprising the space vehicle, wherein the space vehicle is
supported by the launch vehicle.
[0108] A19. The system of any of paragraphs A-A18, wherein the
first stage is decoupled from the thrust augmentation stage,
wherein the first stage is along the second portion of the launch
trajectory, and wherein the thrust augmentation stage is being
controlled in a controlled descent to Earth.
[0109] A20. The use the system of any of paragraphs A-A19 to place
a space vehicle into outer space.
[0110] B. A method of launching a space vehicle into outer space,
the method comprising: [0111] powering a thrust augmentation stage
of a launch vehicle during an initial portion of a launch
trajectory to provide thrust to the launch vehicle; [0112]
following the initial portion of the launch trajectory, separating
a first stage of the launch vehicle from the thrust augmentation
stage; [0113] powering the first stage of the launch vehicle during
the initial portion and during a second portion of the launch
trajectory following the initial portion of the launch trajectory
to provide thrust to the launch vehicle; and [0114] controlling a
controlled descent of the thrust augmentation stage to Earth
following separation of the thrust augmentation stage from the
first stage.
[0115] B1. The method of paragraph B, further comprising: [0116]
separating the space vehicle from the launch vehicle and placing
the space vehicle into outer space.
[0117] B2. The method of any of paragraphs B-B1, further
comprising: [0118] retrieving and reusing the thrust augmentation
stage with a distinct first stage to define a distinct launch
vehicle for a subsequent launch of a distinct space vehicle into
outer space.
[0119] B3. The method of any of paragraphs B-B2, wherein the first
stage provides thrust to the launch vehicle during the
separating.
[0120] B3.1. The method of paragraph B3, wherein exhaust from the
first stage directly engages the thrust augmentation stage during
the separating.
[0121] B4. The method of any of paragraphs B-B3.1, wherein the
thrust augmentation stage and the first stage of the launch vehicle
are lit on the ground and both provide thrust for initial launch of
the launch vehicle.
[0122] B5. The method of any of paragraphs B-B4, utilizing the
system of any of paragraphs A-A19.
[0123] As used herein, the terms "selective" and "selectively,"
when modifying an action, movement, configuration, or other
activity of one or more components or characteristics of an
apparatus, mean that the specific action, movement, configuration,
or other activity is intended and/or is a direct or indirect result
of user manipulation of an aspect of, or one or more components of,
the apparatus.
[0124] As used herein, the terms "adapted" and "configured" mean
that the element, component, or other subject matter is designed
and/or intended to perform a given function. Thus, the use of the
terms "adapted" and "configured" should not be construed to mean
that a given element, component, or other subject matter is simply
"capable of" performing a given function but that the element,
component, and/or other subject matter is specifically selected,
created, implemented, utilized, programmed, and/or designed for the
purpose of performing the function. It is also within the scope of
the present disclosure that elements, components, and/or other
recited subject matter that is recited as being adapted to perform
a particular function may additionally or alternatively be
described as being configured to perform that function, and vice
versa. Similarly, subject matter that is recited as being
configured to perform a particular function may additionally or
alternatively be described as being operative to perform that
function.
[0125] The various disclosed elements of apparatuses and steps of
methods disclosed herein are not required to all apparatuses and
methods according to the present disclosure, and the present
disclosure includes all novel and non-obvious combinations and
subcombinations of the various elements and steps disclosed herein.
Moreover, one or more of the various elements and steps disclosed
herein may define independent inventive subject matter that is
separate and apart from the whole of a disclosed apparatus or
method. Accordingly, such inventive subject matter is not required
to be associated with the specific apparatuses and methods that are
expressly disclosed herein, and such inventive subject matter may
find utility in apparatuses and/or methods that are not expressly
disclosed herein.
* * * * *