May 062016
 

A NASA illustration of an advanced solid rocket motor concept, dated 1963. The most obvious difference between the “present” and “advanced” design was the buried nozzle. By properly shaping the solid propellant grain, the motor would perform normally but with a minimum of unused internal volume; this allowed the motor to be substantially shorter than the conventional design. This would make the associated interstage section equivalently shorter, lighter and cheaper. And by shortening and lightening the interstage, the launch vehicle would be shorter, lighter and stronger, with slightly sturdier structural dynamics.

advanced motor

The advantages of a more compact motor like this are pretty obvious. The disadvantages, maybe less so. The most apparent disadvantage is the *need* for far more advanced materials. That buried rocket nozzle is shown to be quite thin, thinner than the “present” design, yet it would be subjected to horrifying heating rates on *both* sides. There are few materials that could withstand that and retain any sort of structural strength.

Additionally: the desire is shown for thrust vectoring. Numerous options for that are available for the conventional nozzle… but it would be much harder with a buried nozzle. It might be easiest to simply gimbal the entire motor. Stop/restart capability has been achieved with solid rockets, but neither design show here provides for that. It is a non-trivial feature.

The igniter is show to be a small rocket motor suspended within the nozzle, directing it’s exhaust forward into the bore volume of the main motor. Variations on this sort of igniter are quite common for relatively short and stubby upper stage motors such as these.

 Posted by at 11:06 pm
May 022016
 

A photo of a NASA wind tunnel model of a hypersonic aircraft configuration. The circa 1960 NASA brochure (promoting the organization to college students) that included this provided no further information, but I’m reasonably sure I’ve seen the wind tunnel test report on this, calling it a reusable booster or reusable launch vehicle. If that’s the case, the upper stages and payload were *probably* going to be carried on the things back.

RLV

 Posted by at 8:58 am
May 012016
 

I admit that the USBP series looks kinda… bland. It’s text and line drawings; not a whole lot can be done to jazz that up. Especially since I have no head for graphics design whatsoever apart from layout diagrams.

Still, one reader sent me a mockup of a revised cover of USBP #18:

USBP18blue

Things are moved around a little bit, but the obvious change is the addition of color. The suggestion was also made to consider color-coding each title in the USXP series. Just off the top of my head, I came up with:

Bombers: Olive Drab

Spacecraft: Black

Launch Vehicles: Blue on bottom, transitioning to black at the top

Fighters: slightly bluish gray (like the F-15 or F-22)

Transports: ??

VTOL: ??

The USBP#18 cover was re-done to reflect this, thusly:

USBP18green

Thoughts? Is this more appealing?How about color-coding… good idea or not? And if so, what colors?

I tried something vaguely like this once before, with USBP#05.

 Posted by at 9:43 am
May 012016
 

Or $750/lb. SpaceX pricing for the Falcon 9 and Falcon 9 heavy:

http://www.spacex.com/about/capabilities

capabilities_services_4.29.16_5

For comparison, the Delta IV Heavy costs $375,000,000 with a LEO payload of 28,790 kg/63,470 lbs, or $13,025/kg or $5920/lb.

SpaceX stands a decent chance of monopolizing the launch market in the US. And while the price does not include a Dragon capsule, the US is currently paying the Russians $70 per astronaut to fly on a Soyuz. That’s more than the price of an entire Falcon 9 launch which, with a Dragon V2 capsule, should carry 7 astronauts.

 

 Posted by at 9:17 am
Apr 272016
 

Elon Musk has announced that SpaceX is planning on using a Falcon 9 Heavy to launch a modified and unmanned Dragon 2 space capsule to Mars. In 2018.

 

 

 

Seems the Dragon 2 has been designed to be an all-round planetary lander, supposedly good for “anywhere in the solar system” (oh, yeah, smart guy? Like, the sun? Jupiter? Detroit?). That’s certainly handy, but they’ll need an ascent vehicle if they want to send (and recover) humans.

 Posted by at 5:02 pm
Apr 232016
 

I’ve never really been much of a fan of the space elevator concept. Not so much that it relies upon nearly magical levels of structural strength (though some new materials are strong enough – at least at small scale – to make the concept feasible), but because it is something of a snail for getting payloads into orbit. If your elevator can climb at a brisk 100 km/hour, and that would be a massive challenge, it will take the elevator about 358 hours to climb to geosynchronous… slightly over two weeks. That’s a couple days in the van Allen belts, so your elevator had better be highly shielded… which means the ratio of payload to climber will be minimal. And then your climber has to either be jettisoned, or it has to make the climb all the way back down. That will be probably several days, during which time you can’t send another climber back up. So you’re probably looking at a turnaround time of around three weeks per “flight.”

Turnaround time can be improved by not going all the way to GEO. Instead, go several thousand miles up, then throw the payload overboard. The higher up you go, the more tangential velocity you’ve have, and the closer to a circular orbit you’ll have. To get into an actual circular orbit, you’ll need to have an onboard propulsion system; the lower your ejection altitude, the more propulsive capability you’ll need. But while this’d speed up the elevator system, it’ll reduce effective payload by *a* *lot.*

Jettisoning a payload puts it into an elliptical orbit with the jettison point being apogee. Perigee rises as the elevator rises; at some point you’ll have an orbit where the perigee is something convenient like 400 km. So all you’ll need is enough propulsive capability to circularize at perigee. But since I can’t be bothered to do the actual math, it seems to me the apogee altitude will be quite high for the elevator, so it might only shave a relatively small fraction off the elevator trip time compared to going all the way to GEO.

Then there’s the problem of actually climbing. How? The cable might be a flat ribbon, millimeters thick by centimeters wide, or it might be actually cable-shaped. But the materials under consideration, graphene and diamond fiber and such, have a little problem: they are virtually frictionless. Run wheels on them all you like, you probably won’t get much traction. Adding a ribbed surface for traction, or adding magnetic materials so a maglev system can haul up the elevator, will add vast amounts of weight to the system.

This video points out some of the engineering issues with the concept:

 Posted by at 7:33 pm
Apr 172016
 

Now available: two new US Aerospace Projects titles.

US Bomber Projects #18

US Bomber Projects #18 is now available (see HERE for the entire series). Issue #18 includes:

  • Boeing Model 726-13: A nuclear powered bomber with the cockpit in the tail
  • Martin Model 164: A pre-war high altitude twin-tailed bomber
  • North American WS-110A: An early concept for what became the B-70, with “floating wingtips”
  • Convair MX-1593: An Early, large five-engined Atlas ICBM concept
  • Boeing Model 701-299-1: The final XB-59 supersonic bomber design
  • Boeing Model 464-72: A B-52 with pusher turboprops
  • Boeing F-15GSE Global Strike Eagle: An unmanned F-15 with a giant missile on its back General Dynamics – Light Weight Attack Configuration 29: An advanced ground attacker with vectored thrust

usbp18ad2 usbp18ad1

USBP #18 can be downloaded as a PDF file for only $4:

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US Transport Projects #6

US Transport Projects #06 is now available (see HERE for the entire series). Issue #06 includes:

  • Lockheed CL-408-15: An early Mach 3 SST
  • Lockheed L-155-4: A very early 8-engine jetliner
  • Boeing Model 754-4V: A very-wide-bodied cargo hauler for Husky
  • Gates Learjet PD1502A: A four-seater with a turbofan
  • Convair Comet Seaplane: An American idea for turning a British jetliner into Flying Boat
  • Lockheed Twin C-5 Shuttle Carrier Aircraft: Two C-5’s mated together to carry a Shuttle between them
  • Boeing Model 765-096 Rev A “SUGAR Volt”: A hybrid jetliner
  • CRC HOT EAGLE – Super Global Troop Transport: Finally, hard data on a rocket transport for Special Forces and Marines

ustp06ad2 ustp06ad1

USTP #06 can be downloaded as a PDF file for only $4:

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And don’t forget…

US Fighter Projects #1 and US VTOL Projects #1 are still new and still available!

 Posted by at 9:44 pm
Apr 162016
 

A sadly tiny illustration of a “Saturn Space Laboratory” from a circa 1960 NASA brochure (promoting the organization to college students). This looks like something halfway between MOL and Skylab; three pressurized modules in a “wet lab” space station. Diameter looks to be 10 feet, same as the Titan booster; early concepts for the Saturn called for the use of the Titan first stage to be the second stage of the Saturn I, with the second stage of the Titan being the third stage of the Saturn. This may well represent a Titan I or II first stage/Saturn I second stage as a space lab.

Given the entertainingly toxic nature of the Titan II propellants, I’d guess this was an earlier Titan I-based concept.

satur space lab

 Posted by at 10:36 pm
Apr 122016
 

A Visionary Project Aims for Alpha Centauri, a Star 4.37 Light-Years Away

A just-announced proposal for a $10 billion program to develop laser-propelled interstellar probes. The idea is to have a mile-wide ground-based array of lasers generate a whopping 100 gigawatts for two minutes to push tiny solar sails with a payload massing about a gram (comparable to the innards of an Iphone). In those two minutes the probe would be accelerated to 20% lightspeed, shooting past Alpha Centauri in about 20 years. It is estimated that Starshot would take 20 years to get going, so, when you factor in the time it takes for the message to get back to Earth, the first photos of A. Cent. from close-up won’t be available until 2060 or so.

The basic idea is not new. Lasers and microwaves have been suggested as “pushers” for sails for decades. Starting in  the 1980s, engineers and scientists such as Robert L. Forward have suggested that advances in computer technology were such that probes could be made trivially small, meaning that it was possible to start considering power systems capable of sending probes to stars at good fractions of lightspeed.

The real trick would be developing a molecule-thick sail that won’t promptly vaporize when hit with a 100 gigawatt laser. This, to me, seems the most difficult part of the project. Next up would making a one-gram payload transmit useful data across the lightyears.

While not mentioned in the article, it seems to me that this vast laser array could, when not shooting microprobes to the stars, be used to power vastly larger launch vehicles into orbit, or perhaps “solar thermal” rockets leaving Earth orbit for, say, Mars.

So far no decent technical details, but the website for the project will supposedly eventually have tech reports.

 Posted by at 10:03 am