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POLYMATH







THURSDAY, MAY 2, 2024


RADIAN AEROSPACE SPACEPLANE.



 Copyright 2024 Robert Clark




 I was interested to see this interview with Livingston Holder, co-founder of
Radian Aerospace:












 As well as the video lecture Mr. Holder did for Valispace:














 I noted Radian is following the approach of winged horizontal launch for their
near-SSTO. It’s a near-SSTO because it uses sled launch to reduce the propulsion
requirements of the craft.















 I wonder if Radian could do the trades instead for a vertical launch approach
that would be a true SSTO. Former Air Force officer Major Mitchell Burnside
Clapp who did stints both with the DC-X and X-33 programs did an analysis
showing both hydrogen and kerosene fueled true SSTO’s are possible by vertical
launch:




A LO2/Kerosene SSTO Rocket Design.

https://web.archive.org/web/20211001062714/https://erps.org/archives/321




 Vertical launch has the advantage that the wings only have to support the dry
mass of the craft during return, thus requiring much reduced wing weight. In
horizontal launch on the other hand the wings have to support the entire weight
of the fully-fueled craft, thus needing a much heavier wing weight.




 As Mr. Holder described in the Valispace lecture though the horizontal launch
approach has the advantage it can use a sled to provide some of the propulsion
and also horizontal flight can reduce the gravity loss.




 Still, those large heavy wings for horizontal launch induce a significant dry
mass hit which is why I would like to see a trade analysis on both approaches.




 In support of the feasibility of vertical launch where the wings only have to
support dry mass on return, we can look at the Air Force’s X-37B spacecraft.
This is certainly not a SSTO, but I’m referencing the short, stubby wings that
enable winged return from orbit. 




 The small wings will correspond to a relatively small wing weight. Indeed, we
could use the X-37B’s plan as a model, scaled-up, for what a vertical launch
SSTO might look like. There are actually several aircraft/spacecraft with short
stubby wings we could model the basic plan on.





Robert Clark

@RGregoryClark

Use short, stubby wings for lightweight. Use spiral path to return 1st stage to
launch site.


1:13 PM · Mar 17, 2021




 In Mr. Holder’s video discussion he mentioned that during the famous X-33
development and competition back in the 90’s to develop a SSTO, he decided with
Boeing to pull out of the competition on financial viability reasons.




 But two very important reasons suggest why that conclusion needs to be
reconsidered, and why quite likely it is no longer valid.




 First, an overwhelmingly important fact is SpaceX has shown space vehicles as
privately financed can cut 90%(!) off the development cost compared to the usual
government financed approach. And secondly, the large number of satellite
launches required with several megaconstellation satellite systems soon coming
online, requiring tens of thousands of satellites each, make reusable launchers
imperative.




 So the two factors of low development cost plus a definite market for the
needed launches suggest a reusable SSTO may now be financially feasible.




 Still, an operational SSTO has not been done before so there is still some
financial and technical risk involved. Then I advise first doing a small scale
vehicle that, most importantly, is based on a design of existing expendable
rocket stages.




 The importance of basing it on existing rocket stages is we can look at the
most efficiently weight-optimized stages and then make estimates of the added
weight needed for reusability systems.




 Then there are two existing rocket stages I think might be useful in this
regard: the kerosene fueled Falcon 9 upper stage and the hydrogen fueled Centaur
upper stage. Again we want to use small stages at the beginning to limit the
financial risk.




 The F9 second stage has a quite impressive mass ratio:




Type

Falcon 9 FT Stage 2

Length

12.6m (Separated Length)

Diameter

3.66 m

Inert Mass

4,000 kg (est.)

Propellant Mass

107,500 kg (est.)

Fuel

Rocket Propellant 1

Oxidizer

Liquid Oxygen

LOX Mass

75,200 kg (est.)

RP-1 Mass

32,300 kg (est.)

LOX Tank

Monocoque

RP-1 Tank

Monocoque

Material

Aluminum-Lithium

Guidance

Inertial

Tank Pressurization

Heated Helium

Propulsion

1 x Merlin 1D Vac

Engine Type

Gas Generator

Propellant Feed

Turbopump

Thrust

934kN

Engine Dry Weight

~490kg

Burn Time

397 s

Specific Impulse

348s

Chamber Pressure

>9.7MPa (M1D Standard)

Expansion Ratio

165

Throttle Capability

Yes

Restart Capability

Yes

Ignition

TEA-TEB, Redundant

Pitch, Yaw Control

Gimbaled Engine

Roll Control

Reaction Control System

Shutdown

Commanded Shutdown

Reaction Control S.

Cold-Gas Nitrogen Thruster

https://spaceflight101.com/spacerockets/falcon-9-ft/




An est. 4 tons of dry mass and est. 107.5 tons propellant mass. 




 Its single Merlin could not launch it from the ground however, since, as an
upper stage, the engine does not need thrust/weight ratio above 1.




 Two solutions for that that also speak to the vertical vs. horizontal launch
question: 1.) we can add a second Merlin, and 2.)we can add sufficient wings for
ground launch.




 For the 1st approach we would only use small, stubby wings a la the X-37B as we
are using vertical launch and the wings only have to support the dry mass on
return.




 For the 2nd approach note for horizontal launch the engines do not have to have
a T/W above 1 because aerodynamic lift is being used to loft the vehicle. But
because the wings have to support the fully-fueled weight they need to be
heavier, eventhough you don’t have the added weight of an additional engine.




 The trades need to be done to see which approach is optimal. It may be both
approaches would close to allow an operational SSTO.




  As a first level estimate of wing weight, they are typically 5% to 10% of the
lifted weight of an aircraft. But with composites we might be able to make it
half to that at 2% to 5% of the lifted weight. Now for the case of adding a
second Merlin to the F9 upper stage for vertical launch, that would be an
additional 470 kg for the extra engine. Then if wing weight is as low as 2% of
dry mass that would only be an additional 90 kg added to the dry mass.




 On the other hand, if you have to use wings to loft the entire fully-fueled
weight that’s 2% to 5% added on to the 108 ton gross weight. That’s 2 to 5 tons
added onto the vehicle dry mass in wings alone.




 That makes it difficult for this approach to close without the addition of sled
launch. Sled launch though adds more to the capital cost of development.




 By the way, Holder also discusses in his interview that the engines would use
altitude compensation to achieve high vacuum Isp from engines that can launch
from ground. There are many ways of accomplishing this. One way that would
involve the least technical risk because it is a technique that has been in use
already for decades is to use extendible nozzles. 







Robert Clark

@RGregoryClark




1st image shows how the extendable nozzle on the RL10 looks; 2nd shows it can
even work for multiple engine stages; 3rd image shows how an inflatable nozzle
would look.
GIF



5:16 PM · Oct 16, 2022

 Note that while the suggestion is of basing the SSTO core on the Falcon 9 upper
stage it is not necessary to use the actual stage or even the Merlin engine. The
tech involved in developing the Falcon 9 was not particularly advanced. Indeed
the performance of the Merlin is no more advanced than the kerolox engines
already available in the 60's. Then probably we could use just surplus engines
lying around such as the RS-27 engines. Quite key is the increased performance
needed will come from the altitude compensation nozzles applied to them, able to
increase both thrust at sea level and Isp at vacuum.

 

 That’s the discussion for the Falcon 9 upper stage case. For the
hydrogen-fueled Centaur case there is again the question of adding additional
engines vs. large wings for horizontal launch. For the Centaur to use vertical
launch though using the RL10 engine an important consideration is how much the
thrust is reduced for the sea level version, to ca. 6 ton force. Then you would
likely need 4 to 5 engines instead of the one or two used on the Centaur.  This
would add in the range of 1 ton to the original 2 ton dry mass just in added
engine weight. 




 But for the wings for the horizontal launch, if it is 2% added weight that
would be 2% of the 23 ton gross mass or 460 kg. But if the added wing weight is
at 5% that would be 1,150 kg added weight. This is about the same as the added
engine weight case. 




 So it is possible here horizontal launch is more competitive to the vertical
launch case.




  Robert Clark


at May 02, 2024 No comments:
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Labels: altitude compensation, Centaur, Falcon 8, Livingston Holder, Merlin
engine, Radian Aerospace, RL10 engine, RS-27 engine, SSTO

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 Copyright 2024 Robert Clark  I was interested to see this interview with
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hospitalization hospitalizations hover hoverboards hovering Hubble telescope
Hubble tension Hubble-class human spaceflight humanoid robot humidity hybrid
engine hybrids hydrogen hydrolox hydrothermal hydroxychloroquine hypergolic
hypergolic storable propellant hypersonic waverider hypersonic waveriders
IceCube Neutrino Observatory ideal delta-v ideal velocity idle mode IFT-2 ILC
Dover illusion impulse pressure Inc. India InfiniLED inflatable fairings
Integrated Apogee Boost interferon interferon alpha Interplanetary Transport
System interstellar asteroid interstellar visitor intertank intubated intubation
intubations intuition inversion layer ion drive ionic wind ionocraft Isaac
Asimov isentropic efficiency isotruss ISRO ISRU ISS Italy ITAR Ithacus ITS
ivermectin IXV J-2 Jan Woerner JAVE JAXA Jeff Bezos Jerome Pearson jet engines
jet stream jetpacks John C. Whitehead John Glenn John Schilling Jordin Kare
Jupiter Jupiter rocket JWST Kaguya Kestrel Kestrel engine kilotons kinetic
energy Kuiper Satellite system L2 Lagrange points laminar flow Lancet landing
landing site laser laser missile defense launch abort system(LAS) launch abort
test launch market ArianeSpace Launch Performance Calculator Launch Vehicle
Calculator Launch Vehicle Performance Calculator LaunchPoint LCROSS LE-5 LEO
Liberty rocket lift/drag ratio lifters liquid water Livingston Holder Lockheed
Lofstrom launch loop luminal boom lunar lunar base Lunar Catalyst lunar crew
module lunar Gateway lunar habitat lunar lander lunar mining lunar missions
lunar south pole LVM3 M. Moleman Magic Dragon magnesium MaiaSpace malaria
Malaysian Airlines Flight 370 manned manned launch manned launcher manned
launcher. SpaceX manned launchers manned spaceflight Mars Mars Climate Orbiter
Mars Curiosity Mars Express Mars missions Mars Odyssey Mars Pathfinder Mars
Sample Return Mars satellites mass fraction mass ratio Masten Masten Space
Systems Masten XEUS Masten XEUS lander maternal fevers medications
megaconstellation melting MER rovers Mercury Merlin Merlin 1A Merlin 1D Merlin 2
Merlin engine Merlin Vacuum Messenger metamaterials Methane methane engine
methane engines methylprednisolone microburst microfluid channels microLED mini
Starship mini-Starship missile defense Mitchell Burnside Clapp Mk 1 Moderna Moon
Moon base Moon Direct Moon Express Moon flight Moon mission Moonrise Morpheus
Morpheus lander mortality MOXIE Multi-Role Recovery Capsule N-1 rocket
nanoflares nanoscale piping nanowires NASA NASA Cygnus negative refractive index
Nemesis neon lights neural tube defects New Horizons New Shepard New Space next
generation shuttle NK-33 noctilucent clouds Noctis Labyrinthis nosecone nozzle
extension nozzle extensions nozzles NRHO NRO nuclear reactor nuclear thermal
rocket(NTR) Odyssey sea platform Office of the Inspector General OldSpace OMS
pods OneWeb Orbital Sciences orbital velocity ORBITEC Orion Orion capsule
OSIRIS-REx oxygen parabolic trough mirror paradigm shift partitioned tanks
passenger passive radar Pathfinder payload payload fraction Pegasus Peter
Diamandis Pfizer Phil Bono Philip Bono Phillip Bono Phobos Phoenix capsule
PICA-X planetary protection Planetary Resources Planetary Resources Inc. plasma
drive plasma propulsion platinum plug nozzle plumes point-to-point Polar
Stratospheric Clouds Port Isabel positron pressure ratio pressure-fed
pressurized fluid private development private space Pro150 Project M Project
Morpheus Prometheus engine propellant depots propellant generation propensity
score matching prophylaxis Psyche PubMed pumping water Quantum tunneling Radian
Aerospace radiation hardened electronics radiators radio astronomy ram pump
random number generator randomized controlled trial Raptor Raptor engine RCT
RD-0242 RD-171 RD-180 REACH ice-penetrating radar real world experience RECOVERY
trial Red Dragon redshift reentry relights remdesivir RETALT2 reusability
reusable reusable first stage reusable launchers reusable spaceplane Richard
Feynman RL-10 RL-10B-2 engine RL10 RL10 B-2 RL10 engine RL10-A5 engine RLV
Robert Zubrin Robonaut Rocket Propulsion Analysis rocket SSTO Rocketdyne Rogallo
wing rogue or nomad planets rollerons routine spaceflight Royal Aeronautical
Society RP-1 RS-27 engine RS-27A RS-68 Russia RWE S-IC S-II S-II stage Sabatier
reaction safety sample return SASSTO satellite phones satellite radio satellite
servicing Satellite TV Saturn II Saturn V Scaled Composites Scanning tunneling
microscope(STM) Scharnhorst Schilling calculator Scifer steel wire scifer wire
Sea Launch service module SEV shadowed craters Ship 26 shockwave shuttle ET
Shuttle External Tank shuttle OMS Sierra Nevada Sierra Nevada Dream Chaser
significance level Silverbird Astronautics Simberg Skylon SLS SN10 SN11 SN4 snow
machine sodium solar cells solar concentrator solar concentrators solar corona
heating problem solar furnace solar irradiance solar sails solar thermal power
solid rockets South Korea South Padre Island South Pole Aitken impact basin
Soyuz space access space colonization space elevator space hotel Space Launch
System space mining space shuttle space shuttle tiles Space Solar Power Space
Station Alpha space tankers space telescope costs Space tourism space tower
space tugs Space-based Solar Power Spaceflight Industries spaceplane spaceship
SpaceShipTwo SpaceX SpaceX Dragon abort test SpaceX HLS spatial intelligence
specific power SpinLaunch SRB's SRB’s SS2 SSME SSME's SSP SSTO stability Star 17
Star 17 solid rocket motor Star 24 Star 37 Star 37X Star 48 Star 48B Starhopper
StarLink Starship Starship V1 Starship. tanker statistical significance steel
Stonehenge stonewalled storable propellant strokes sublimation suborbital
suborbital flight Sunjammer Sunjammer solar sail Super Heavy super heavy lift
superconductivity supercooling SuperDraco Superdraco thrusters SuperHeavy
superhydrophobicity superluminal sustainable resources swirl SWORDS tachyon TAN
tank tanker tapered rods Tara Haelle Target Asteroids temperature terminal
velocity test hop Thales Alenia Space The Martian thermobaric thin plate
deflection throttle throttleability throttled down throttling thrust augmented
nozzle thrust augmented nozzle(TAN) thymosin-α1 tiger stripes Titan Titan II
titanium alloy titanium hydride TLI TMI tocilizumab topological insulator
Transhab translunar injection transparent batteries transparent nanotube sheets
transparent solar cells triple-cored TSSD TSTO TUFI turbine turbomachinery
turbopump turbopumps turbulence pumping water Turkey Tyche U.S. Army Ukraine ULA
Ultra Low-Cost Access to Space unzipping carbon nanotubes upper stage uranium
V-22 Osprey V2 vaccines Valkyrie Vandenberg VASIMR Vector Space Vega Vega-C
ventilator ventilators vents VentureStar Venturi effect Venus Vietnam Vikas
Vikas 2 engine Viking Vinci Vinci engine VIPER rover Virgin Galactic vortex
engine VTHL VTVL Vulcain Vulcain engine Vulcain II water water scarcity WHO wild
fires wind power wind shear wings WISE telescope X-33 X-37 X-37B XCOR Xeus XS-1
Youtube financing zinc zipping up graphene nanoribbons




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