SpaceDev Begins Development Small Launch Vehicle

j05h · Nov 5, 2006

I understand the HL-20's origin. My interest is how much SpaceDev's rebuilding of the vehicle (installing new engines, avionics, etc) will change it's character? Will it only be good for suborbital flights, displaying TPS, interoperability, LES and fairing issues on top of another rocket? I'm not sure. My gut instinct is that they'll copy the mold line and develop a new craft for future versions of Dream Chaser, but the current unit will be suborbital only. Very little info available so far. It looks to be one heck of suborbital launcher. Josh <div class="Discussion_UserSignature"> <div align="center">We need a first generation of pioneers. </div> </div>

Kevin_J_waldroup · May 29, 2008

<div class="storyheadline">SpaceDev Devices Successfully Land on Mars</div> <div id="quigo220NF"><div id="ad-654903" align="center" style="margin:0pt;padding:0pt"> </div></div> SpaceDev, Inc. (OTCBB: SPDV) announced today that it provided a wide array of hardware and instruments for the Phoenix Lander that successfully landed on Mars' north arctic plane Sunday, May 25th at 4:53 pm PDT. SpaceDev mechanical systems on the spacecraft included 16 devices supporting the Microscopy, Electrochemistry and Conductivity Analyzer (MECA) instrument, eight actuators on the Thermal Evolved Gas Analyzer (TEGA) instrument, two actuators deploying the solar arrays, two actuators pointing the Stereo Surface Imager (SSI) camera, and three actuators on the robotic arm. All in all, more than 30 SpaceDev devices are now on the surface of Mars supporting the Phoenix spacecraft. "We congratulate the Phoenix team for a challenging job well done. It is an extraordinary thing to land a spacecraft on another planet," said Mark N. Sirangelo, SpaceDev's Chairman and CEO. "We are honored to play an integral part of this important program. This is the 11th trip to the Red Planet where our products played an important role in the mission and we look forward to a successful effort to search for water and other organic materials on Mars." About SpaceDev SpaceDev, Inc. is a space technology/aerospace company that creates and sells affordable and innovative space products and mission solutions. For more information, visit www.spacedev.com. This news release may contain "forward-looking statements" as defined in the Private Securities Litigation Reform Act of 1995. Such forward-looking statements involve risks that are difficult to predict, are based on the Company's current expectations, and are not guarantees of performance. The Company's actual results could differ materially from its current expectations. Factors that could contribute to such differences include, but are not limited to, risks associated with the Company's ability to effectively manage program, technical, schedule, cost, or customer changes, or cancellation of orders, or obtain additional financing, if needed. The Company also references other factors described in periodic reports filed with the SEC, including its current Annual Report on Form 10-KSB and subsequent Quarterly Reports on Form 10-QSB. These forward-looking statements speak only as of the date of this release. SpaceDev does not intend to update these forward-looking statements.  <div class="Discussion_UserSignature"> </div>

Kevin_J_waldroup · May 29, 2008

SpaceDev Advanced Systems <div align="justify">The entrepreneurial space industry that has been emerging over the past years is changing the course of how space is accessed, explored and utilized. As this paradigm shift occurs, SpaceDev is in a unique position of leading this charge with its broad technology base, its depth of capability, and its entrepreneurial roots. The Advanced Systems group is chartered with developing the advanced systems and technologies that are supporting this sea-change in our industry. A primary current focus of the Advanced Systems group is an overall space transportation system based on the NASA HL-20 lifting body spaceplane. Christened the Dream ChaserTM, it is being designed to carry passengers and cargo in the sub-orbital and orbital flights regimes, including flights to and from the International Space Station. Leveraging the work performed on the NASA HL-20, the Dream ChaserTM will provide a safe and affordable solution for commercial space operations, will launch vertically and land horizontally on conventional runways. </div> SpaceDev Dream ChaserTM Space Transportation System<img src="http://66.116.218.13/uploads/DC_advanced.jpg" border="0" alt="Dream Chaser" title="Dream Chaser" width="485" height="364" />   SpaceDev is currently working in conjunction with NASA Commercial Orbital Transporation Services (COTS) office to develop and configure the system for ISS servicing. In parallel, SpaceDev has signed a memorandum of understanding with United Launch Alliance (ULA) and is evaluating man-rating the Atlas 5 launch vehicle and configuring it for use with Dream ChaserTM to provide a launch configuration based on the exceptional heritage of the Atlas family of launch vehicles. <img src="http://66.116.218.13/uploads/92715744atlas_DC.jpg" border="0" alt="Dream Chaser ULA" title="Dream Chaser ULA" width="250" height="500" />SpaceDev’s Dream ChaserTM Piloted Lifting Body Spaceplane Characteristics <ul><li>Derived from NASA HL-20</li><li>Over 1200 hours of NASA wind tunnel testing</li><li>Builds upon seven years of NASA development</li><li>Low re-entry deceleration Loads (< 1.5 g)</li><li>Large cross range (1600km) → Frequent Landing Opportunities</li><li>Low impact recovery (conventional runway landing)</li><li>Exceptional crew safety: (safe, non-toxic space vehicle propulsion) </li><li>Onboard hybrid propulsion & high lift provide flexible abort options</li><li>Designed for Commercial Orbital Transportation Service: Simple maintenance, quick turnaround</li></ul> SpaceDev’s Dream ChaserTM - Hybrid Propulsion <ul><li>Based on our proven hybrid rocket propulsion technology</li><li>Over 10 years of development</li><li>Over 300 firings</li><li>Based on motors designed for SpaceShipOne (SS1)</li><li>Human flight rated motors</li><li>Hybrid propellants are safe, non-toxic, storable & human flight tested</li><li>Propellants: nitrous oxide (N20) & rubber (HTBP)</li><li>Common Space Vehicle Hybrid Propulsion Modules (SVPMs)</li><li>Modular construction simplifies production and handling</li><li>Throttleable & restartable</li><li>Thrust vectoring control (TVC) by N2O injection; no nozzle gimbals</li><li>Reaction Control System (RCS) uses N2O</li></ul> <div class="Discussion_UserSignature"> </div>

Kevin_J_waldroup · May 29, 2008

SpaceDev Hybrid Propulsion <div align="justify">We are the world leader in safe, hybrid rocket propulsion. This unique technology is based on a combination of two, very safe materials: nitrous oxide (N2O) as the oxidizer, and hydroxy-terminated polybutadiene (HTPB), or synthetic rubber as the fuel. The result is a propulsion technology that blends the simplicity of solid rockets with the restart and throttle ability of liquid-fueled propulsion. The most significant aspect is that hybrid rockets are much safer than other rocket technologies. Vandenberg Air Force Base rates hybrid rockets as having “zero-lb” equivalent explosive energy. The inability of the fuel and oxidizer to mix makes it particularly well suited for human spaceflight and for applications that require a safer propulsion technology that can be, and is, safely, commercially transported and handled. Pioneered by the AMROC Corporation, we acquired the exclusive rights to the AMROC technology in 1998 and have continued its development and application. </div>www.spacedev.com/uploads/Amroc.jpg" border="0" alt="AMROC 250k" title="AMROC 250k" width="283" height="353" />  Capistrano Test FacilitiesThe Capistrano test site is our Space Technology Development Center (STDC), located within the Northrop Grumman Capistrano Test Facility. The site comprises a thrust stand, operations trailer, fire suppression system, fluid storage and delivery system, and data recording system. Initially sized to meet the needs of the HUS program, the facility will eventually be upgraded to accommodate firing hybrid motors with up to 250,000 lb of thrust.  <div align="center"><img src="http://66.116.218.13/uploads/cap1fx.jpg" border="0" alt="Capistrano Test Facility" title="Capistrano Test Facility" width="370" height="283" /></div><hr /> SpaceDev Hybrid Propulsion Programs SpaceShipOne <div align="justify">SpaceDev was chosen as the exclusive provider of critical hybrid propulsion components and integrator of the rocket motor for the revolutionary manned SpaceShipOne. We provided the fuel grains, key operating hardware, and electronics for the hybrid motor. Fourteen motors were provided for the SpaceShipOne program, some providing over 15,000lbs of thrust and running for more than 60 seconds. </div><div align="justify"> Paul Allen’s SpaceShipOne won the worldwide Ansari X-Prize on October 4, 2004, a $10-million purse to be awarded to the first vehicle team to fly a privately-funded sub-orbital spaceship 100 km (62 miles) to space, return safely, and then fly again within two weeks. The piloted spaceship was capable of carrying three individuals. </div> <img src="http://66.116.218.13/uploads/SS1fx.jpg" border="0" alt="ss1" width="315" height="217" /><img src="http://66.116.218.13/uploads/ss1.jpg" border="0" alt="ss1" width="240" height="240" /> <hr />Maneuver and orbital Transfer Vehicle (MoTV)<div align="justify">We have developed a Shuttle-compatible propulsion module for the Air Force Research Lab (AFRL) and a more complete “space tug” using hybrid motors. Our MoTV was designed to provide on-orbit maneuvering and orbit transfers of customer microsatellites and payloads launched from expendable launch vehicles. The throttle-ability and simplicity of the hybrid technology makes it a uniquely capable technology for orbital transfer. </div> <img src="http://66.116.218.13/uploads/MoTVfx.jpg" border="0" alt="MoTV" width="451" height="494" /> <img src="http://66.116.218.13/uploads/HPM%20Firing.jpg" border="0" alt="Hybrid Propulsion Module" title="Hybrid Propulsion Module" width="370" height="277" />  <hr />SpaceDev Dream ChaserTM <div align="justify">The sub-orbital and orbital SpaceDev Dream ChaserTM is derived from an existing NASA HL-20 design and will have a sub-orbital altitude goal of approximately 160 km (about 100 miles), an orbital goal of 420 km (about 200 miles) and will be powered by our hybrid rocket motors. Our Dream ChaserTM hybrid motor will produce approximately 100,000 pounds of thrust—about six times the thrust of the SpaceShipOne motor. </div> <hr />Hybrid Upper Stage <div align="justify">Under the Hybrid Upper Stage, or HUS, program, SpaceDev developed, built, and fired several heavy motor test articles of a small launch vehicle upper stage. Sponsored by AFRL under their Small Launch Vehicle SBIR, five HUS motors were tested at our Space Technology Development Center, located at the Northrop Grumman Capistrano Test Facility. </div> <img src="http://66.116.218.13/uploads/capistrano.jpg" border="0" alt="capistrano_firing" width="467" height="385" /> Additional Information <div class="Discussion_UserSignature"> </div>

keermalec · May 30, 2008

This is probably a dumb question but why are hybrid motors safer than bi-(liquid)propellant motors? If the safety comes from the non-mixing of oxidizer and fuel then aren't they inherently just as safe and not more?   <div class="Discussion_UserSignature"> “An error does not become a mistake until you refuse to correct it.” John F. Kennedy </div>

Swampcat · May 30, 2008

IMO, it is not necessary to copy and paste large parts of a website. That's what a hyperlink is for. <div class="Discussion_UserSignature"> ------------------------------------------------------------------- "I hold it that a little rebellion now and then is a good thing, and as necessary in the political world as storms in the physical. Unsuccessful rebellions, indeed, generally establish the encroachments on the rights of the people which have produced them. An observation of this truth should render honest republican governors so mild in their punishment of rebellions as not to discourage them too much. It is a medicine necessary for the sound health of government."Thomas Jefferson </div>

DrRocket · May 30, 2008

Replying to: <DIV CLASS='Discussion_PostQuote'>This is probably a dumb question but why are hybrid motors safer than bi-(liquid)propellant motors? If the safety comes from the non-mixing of oxidizer and fuel then aren't they inherently just as safe and not more?   Posted by keermalec</DIV>It is because the basic fuel, in this case HTPB is inert.  HTPB is basically rubber.  Commercial grade HTPB is used as backing for carpets.  But if these guys are using the HTPB used in rockets, R45-M or R45-AS, they are going to get to learn an awful lot about the manufacturing process and how to test it to get consistent mechanical properties.  I wonder if they are buying the material from Atochem or from Brazil.Liquids often use materials that are hazardous evern when not mixed -- volatile, inflammable, toxic, etc.  Even kerosene in large quantities can be hazardous.  Obviously, some liquids are more hazardous than others.I am not particularly a fan of hybrids, for a number of reasons. But I will admit that they are safe while in storage. <div class="Discussion_UserSignature"> </div>

keermalec · Jun 1, 2008

Thanx Dr R for explaining that. i searched the net about N2O/Rubber propulsion and found it has an isp of... 250s. That is lower than hydrazine and the same as LOX/LCO! A launcher completely propelled by such a hybrid motor would put about 0.2% of its Gross Lift Off Mass into orbit, against 2-3% for conventional launchers... I love what spacedev does but this hype about their hybrid motor is somewhat misleading: it can at best only be used for reaction control systems and low delta-vs on manned vehicles. Unfortunately nothing to write home about.   <div class="Discussion_UserSignature"> “An error does not become a mistake until you refuse to correct it.” John F. Kennedy </div>

spacy600 · Jun 1, 2008

Replying to: <DIV CLASS='Discussion_PostQuote'>Thanx Dr R for explaining that. i searched the net about N2O/Rubber propulsion and found it has an isp of... 250s. That is lower than hydrazine and the same as LOX/LCO! A launcher completely propelled by such a hybrid motor would put about 0.2% of its Gross Lift Off Mass into orbit, against 2-3% for conventional launchers... I love what spacedev does but this hype about their hybrid motor is somewhat misleading: it can at best only be used for reaction control systems and low delta-vs on manned vehicles. Unfortunately nothing to write home about. Posted by keermalec</DIV> Just wondering did you figure for this?http://tinyurl.com/59oholor the annular hybrid research that NASA is doing?Thanks

keermalec · Jun 2, 2008

Hi Spacy, your link didn't work for me... I got the 250 s isp from the Astronautix entry on SpaceDev's hybrid motor.   <div class="Discussion_UserSignature"> “An error does not become a mistake until you refuse to correct it.” John F. Kennedy </div>

spacy600 · Jun 2, 2008

Hi,Your link was to the SS1 hybrid. That was designed to go suborbital, so to extrapolate  the number fororbital is unfair and misleading. My point is Spacedev is doing R&D into Hybrids like this: AstronautixAnd the link, (worked for me) was to the US patent and tradmark office. I will paste the parts that I find interesting.[0052] Thus, N2O permits a large oxidizer-to-fuel ratio while maintaining a relatively high and uniform specific impulse across a range of ratios. It can be seen from the graph of FIG. 5B that N2O has a lower peak specific impulse than some other oxidizers, such as, for example, LOX (O.sub.2). However, although N2O has a lower peak specific impulse than LOX, N2O has a higher mass fraction than LOX due to the lower mass of the propellant and oxidizer tanks that can be used with N.sub.2O as the oxidizer. As mentioned, a higher mass fraction is desirable for a hybrid rocket system. The higher mass fraction of the N2O system versus the LOX system is at least partly a result of the smaller size of tanks that is required for a N2O system. It has been observed that, for the same amount of total propellant, the N2O tank can be 93% of the size of a LOX tank due to the higher density of N2O. [0053] In a typical hybrid motor, the solid fuel utilization is about 90%. This means that the fuel slivers (which is the residual unburnt fuel) are about 10% of the fuel that is initially loaded in the rocket motor. The use of N2O with a high oxidizer-to-fuel ratio increases the overall propellant utilization to about 99%. [0056] In contrast, a chilled N2O can be used as the oxidizer wherein the N2O is stored at around -95 deg F. This permits a lighter tank for storing the N2O. It has been observed that the tank for storing a cryogenic N2O can be about 62% of the size tank for storing a room temperature N2O. Thus, propellant mass fraction is increased for cryogenic N2O due to the lower inert weight associated with the smaller tank size for the cryogenic N2O.USPTO  NASA SBIR Granted all this is unproven R&D but looks neat and promising, IMO

keermalec · Jun 4, 2008

Replying to: <DIV CLASS='Discussion_PostQuote'>...while maintaining a relatively high and uniform specific impulse ...</DIV>I stand with my statement. "Uniform specific impulse" is only 250 seconds, whereas LOX/Kerosene can go up to 337 seconds and LOX/LH to 462 seconds. Because rocket performance rises exponentially with isp, any hybrid N20/Rubber motor will necessarily have a lower payload to GLOW (Gross Lift Off Weight) ratio than a conventional rocket, even if substantial mass savings can be made by optimizing the propellant tanks.For a single stage to 3.2 km/s target velocity (1 of three in a three-stage rocket to 9.6 km/s): N2O/Rubber ----------Payload mass  1000 kg Fuel mass   656  kg Oxidizer mass   4'589  kg Fuel tank mass   135  kg Oxidizer tank mass   188  kg Pressurant and tank   -    kg Payload adapter   30  kg Engine mass   311  kg Structure   214  kg     Total initial mass   7'123  kg Dry mass without payload   746  kg     Payload to GLOW ratio  14.0%  3-stage ratio  0.28%  Dry mass per payload   44 tons dry mass per ton of payload 1 ton to LEO requires  361 tons GLOW LOX/LH (eg Delta IV) -------------------Payload mass  1000 kg Fuel mass   292  kg Oxidizer mass   1'707  kg Fuel tank mass   225  kg Oxidizer tank mass   186  kg Pressurant and tank   -    kg Payload adapter   30  kg Engine mass   112  kg Structure   93  kg     Total initial mass   3'644  kg Dry mass without payload   576  kg     Payload to GLOW ratio  27.4%  3-stage ratio  2.07%  Dry mass per payload   10.5  tons dry mass per ton of payload 1 ton to LEO requires  48 tons GLOW As you pointed out, tank mass can be highly optimized in an N2O/rubber rocket, but it isn't the tank mass which is the problem, it's the propellant. To get 1 ton to LEO using LN2O/LH would require a 361-ton rocket, with a dry mass of 44 tons. To get 1 ton to LEO using LOX/LH would require a 48-ton rocket, with a dry mass of 11 tons. 11 tons of hardware usually costs less than 44. Unless, in this case, the cost savings induced by the engine's simplicity outweigh the costs induced by its size...(numbers modified once)   <div class="Discussion_UserSignature"> “An error does not become a mistake until you refuse to correct it.” John F. Kennedy </div>

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