Headlines > News > Armadillo Aerospace News: Spheres, Development, Engines, Ablatives, Liftoffs

Armadillo Aerospace News: Spheres, Development, Engines, Ablatives, Liftoffs

Published by Sigurd De Keyser on Thu Sep 8, 2005 11:13 pm
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Spherical tanks

We have tested two new spherical tank sets – 18” diameter, 3/16” pre-spun thickness, and 36” diameter, ¼” thickness in 5086 aluminum. Unlike the previous ones, we took these with “as-spun” finish instead of the pretty brushed finish that probably contributed to stress risers. The small ones were $198 per hemisphere, and the big ones were $650 from www.amsind.com .

The weld bevels weren’t as deep as we would have liked, but the thicker hemispheres did line up better than the 1/8” thick 36” diameter spheres we tested last month. A good thing, because our method of welding tabs on the inside to force the hemispheres to better alignment didn’t work out at all on the thicker spheres.

The small tank welded very easily, and exceeded our burst pressure expectations. It had a dry weight of 16 pounds, and a full-of-water (before any yielding) weight of 125 pounds for a mass ratio of 7.8.

Burst pressure was 1250 psi, and it failed in the section of maximum thinning from the spinning process, not at the weld or in the heat effected zone.

The 36″ diameter, 1/8″ thick tank we previously tested ruptured at 340 psi, which would scale to 1040 psi for this size. We believe the extra 210 psi of strength was from the surface finish, but it might also be from the better alignment of the thicker hemispheres.

The ¼” thick 36” hemispheres are just about at the limit of our in-house welding capabilities. With the relatively shallow weld bevel provided, we need to put a lot of power into it to get full penetration, and our air-cooled torches get hot fast. We had AMS send some cut off scraps of the metal so that James could do a lot of test welds to work out best practices, which turned out to be pretty important.

The 36” sphere was 81 pounds dry and 950 pounds full of water, for a mass ratio of 11.7. The first hydrotest resulted in a small leak at the weld seam at 720 psi. This was a bit surprising, because usually once any crack starts, the entire thing unzips. James identified this as one of his weld stop points. After re-welding that area, the tank made it up to 760 psi before completely coming apart along the weld / heat affected zone on one side. Examination showed that we didn’t have 100% penetration at that point, but this is still good enough for our purposes.

We will probably do a bit better on the two production tanks now that we know what the problem areas are. James is starting the prep work on the two 36” tanks for the next big vehicle.

Development Work

We had been having some annoying troubles with our Esteem wireless communication system not connecting at startup. I would go through a voodoo dance of rebooting one or both systems a couple times until it would eventually link properly. When I finally got sick of it and connected directly to the units and dumped the log files, it turned out that the wireless chipset on the flight computer unit was failing to init on boot most of the time. That unit was in the last peroxide vehicle that had the fall that snapped the catch tether, so it was probably slightly damaged. Replacing the unit cleared the problems up.

For several weeks we had engine test results that were completely baffling us. It turned out to have an amusing cause – our fuel flow meter hadn’t been connected since it had been removed to weld the flow straightening pipes directly to the meter (we had chronic fuel leakage from the 1” NPT threads). The fuel flow A/D channel happened to be read right after the chamber pressure transducer, so the floating line still had the voltage from the previous channel, only slightly decayed. By sheer happenstance, the signal ranges of the two sensors were close enough to each other that the fuel flow values looked somewhat plausible. Chamber pressure and fuel flow are usually proportional… Plugging it in properly cleared everything up, but we went through a few design changes with bad data.

In the process of investigating some odd behavior with the lox pressurization on the test stand, we replaced another check valve on the test stand that was behaving poorly. We have seen several problems with check valves over the years, and this is probably the final straw in my decision to use completely independent pressurization tanks and regulators on the next vehicle, so we don’t need any check valves. There is some benefit to having a single pressurization system – we lost one regen engine early on because the fuel pressure was accidentally much lower than the lox pressure, and it would be more mass efficient to have a unified system. Dual systems does completely remove a failure mode, and we might take advantage of the ability to slightly tweak mixture ratios with different pressures.

Even with the check valve fixed, the lox pressurization still behaved a bit strangely. When we start pressurizing, the lox pressure goes up a bit, then stays almost constant for a while as the fuel pressure rises, then finally hits a point where it jumps up rapidly to the same level as the fuel, then they continue in sync to the final pressurization level. We thought that it was probably the nitrogen dissolving into the lox, and / or cooling down significantly, so we tried pressurizing with helium.

With helium, the lox pressure exactly tracks the fuel pressure, so it was definitely nitrogen dissolving instead of simply cooling. A given regulator flows almost three times the volume of helium as it does nitrogen, so our pressure rises are much faster now, and the regulator droop on engine start is much lower. Our engine performance has also gone up, because we aren’t sending “fluffy” lox with dissolved nitrogen into them.

We are going to use helium exclusively from now on. At some point in the distant future, the cost of helium will become important relative to all of our other operating costs, but we are paying $390 / six pack of helium, which doesn’t seem too bad. I understand it is much more expensive for the guys out at Mojave.

The one downside to helium is that the roll control thrusters on the vehicle dump a lot more volume for a given impulse, and purges drop the pressure very fast.

Partly because of the aforementioned baffling problems with the fuel flow meter, I purchased a couple cavitating venturis.from Fox Valve for our test stand, calibrated to flow exactly 3 pounds per second of propellant at 350 psi. I always feel ripped off paying so much for these, and this time I paid extra for expediting because we are in a bit of a hurry due to the X-Prize Cup. These have been helpful, and if I didn’t have them, the flow meter issue might have gone unnoticed even longer.

One smart thing we did on the vehicle recently was to permanently mount a compass for vehicle alignment on the top of the heat shield. To use GPS based position hold the vehicle needs to know which way north is. For our previous vehicles we have just painted an arrow on the ground at our two test sites, but since we are going to be flying at a new location for the XPC, we would have to remember to bring a compass with us. Just gluing the half ounce compass to the vehicle made a lot of sense.

Related to that theme of “try to engineer around needing to remember something”, we are going to be bolting extension handles onto our lox filling hose so we don’t need to carry a big pipe wrench around for popping it off. The (pretty damned expensive) cryo connector is supposed to just pop off with a twist of the handle, but it doesn’t always cooperate. Our lox supplier said they have to hit them with hammers sometimes to break them free, but we found that just some extra leverage does the job better.

I finally got around to tracking down a supplier for AN sealing caps. I had seen these mentioned in Caroll Smith’s auto racing tech books years ago, but I never tracked down a supplier. Aircraft Spruce caries them. They are basically soft metal foil caps that you put over a male AN fitting before tightening the female fitting down on top of them. We have had several -16 fittings that always dripped a bit, and these fixed them right up.

Engine Development

We burned through a number of tube engines, including one that I really don’t think should have. I am suspecting that the looser fit cooling jacket that we moved to after having one of the chambers buckle inwards is probably a mistake, giving us too low of coolant velocity.

I’m having good success at drilling accurate impinging injectors on our tube engines. Our original injectors were all just straight towards the center from the outside of the tube, but by drilling down from a point offset from the center of the tube you can make different stream angles that result in impingement close to the outer edge of the tube instead of the middle, giving good spray fans. By using unlike angles, you can make spray patterns that swirl around the tube. To drill accurate holes on the slope of a tube, I first mill down a flat with an end mill by slowly plunging in and milling half a diameter along the length of the tube (I found a while ago that just plunging with an end mill leaves a slight bump in the center, which throws off small drills), then spot the hole with a 1/8” spotting drill, then finally drill through with a 3/64” carbide mini-drill.

I want to repeat the test again, but early results show that swirled fuel and non-swirled lox works well, while counter-swirled fuel and lox ran fairly rough. This back-to-back test was with somewhat too-large injection holes (1/16”), so the counter-swirl may still work well with a higher injector drop.

We made one test engine based on the theory that it would be good to let the lox completely vaporize before it gets to the fuel injection point. To try to do this, we put the lox injectors six inches above the fuel injector. From our experience with the old preburner based engines, we expected the temperature of the lox with just the igniter spray nozzle to be a bit too high for aluminum, so we made cooling channels in that section of the chamber for the lox to flow through.

Because there was so little combustion, I didn’t think that we would have problems with the lox vaporizing, but that turned out not to be the case. Lox flow rates always plummeted immediately after throttle up, indicating boiling in the channels. We normally leave the igniter spray nozzle running continuously during engine runs, but I tried turning it off after ignition so the lox channels wouldn’t be getting directly heated.

With the spray nozzle shut off quickly after ignition, the lox flow rate would slowly creep back up as the top of the chamber cooled back down, but it was going to take forever. I tried letting the lox flow longer before starting the igniter to pre-chill the chamber, which helped a bit.

Then we made a bad decision – we tried opening the lox flow up a lot more before ignition to reduce the heat that went into the chamber during startup. We had a couple failed ignitions, then we had an igniter hard start that peeled the top of the engine like a banana. It is worth noting that all the fuel for the bang came from a 0.030” spray nozzle. A hard start from main engine fuel flow is a much more serious issue.

This, of course, killed the load cell on the test stand.

We are about to test a regen engine with an extra set of film cooling injectors half way down the tube.

Ablative Engines

We were starting to really stress out about not having a definitely good engine for the X-Prize Cup demo flights, so we decided to try making an ablative engine that should be more predictable and for-sure wouldn’t have any issues with throttling.

Initial tests with a 2” ID, 3” OD grade LE Garolite (phenolic – linen) rod from McMaster was promising. We externally threaded the phenolic with an 8 tpi thread and made an injector head with a matching female thread and a face seal o-ring. After a 20 second burn it had just started to burn through the threaded area.

For the second test, we tried extending the aluminum injector for ¾” and internally threading the phenolic tube, hoping that the swirled fuel would film cool the aluminum enough to protect it and the phenolic threads, so it could have the full thickness to ablate through. Didn’t work. The aluminum extension melted off very quickly, making our test stand blast-deflector into a phenolic chamber-deflector.

For the third test, we went to a solid 4” diameter by 12” long rod of phenolic that we bored out to 2” ID and added a 3” ID exit cone. To retain this, we used a bottom plate and 8 threaded studs, so it didn’t require any thread machining. This worked well, and we made several good runs with it.

For the fourth test, we made a new injector head with larger injector holes to get some more thrust, because we were a little marginal for flight. We changed the chamber retention scheme to use a pipe with threads and a metal threaded closure so it could just be unscrewed and another chamber put in. This was a bust – we made the threads too tight, so after a firing when it was heated up, they couldn’t be turned off. The bigger injector holes also hurt, only slightly improving thrust, at the expense of a lot of Isp.

For the fifth test, we used a counter-swirling injector head in hopes of bringing the Isp back up with the higher flowing injectors, and we also bored the chamber out a bit so that it had a real chamber / throat / expansion like a conventional engine instead of being throatless. We intended to try a looser thread on the retainer, but the metal for the end didn’t come in, so we used the same retainer as the previous run. This was also when we switched over to helium pressurization.

On ignition of the first firing of this engine, the bottom retainer blew off the engine and shot the chamber into the blast deflector (killing another load cell…). We found the chamber split in two lengthwise like a piece of cordwood. This is a significant drawback of the solid rods of phenolic – they are cut out of thick laminated plates, so there are no reinforcing fibers along one diameter direction. The phenolic tubes are wound up as you would expect.

At first we through that this was just a result of adding the bored out chamber area resulting in more down pressure on the retainer, which we had only tack welded on because the throatless engines really done have any significant down force. Later testing would show that what probably happened was that the chamber split first, then the retainer blew off.

Our ignitions have always started with a bit of a bang, so we tried adding a 0.020” reducing jet in front of the 0.030” fuel spray nozzle. This has made the ignitions much, much softer.

The next test run did not split the chamber on startup, but it was running rather rough. We don’t know for sure if it was because of the counter-swirled injector or the bored out chamber ahead of the throat.

For the next test, we went back to the #3 engine with the 3/64” injectors, fuel swirled, lox non-swirled. We were out of new phenolic rods, so we took one of the older chambers that we had already burned, bored it out to match the previous test, and ran it. Performance was good, so we rule out the chamber and the helium as causes of the roughness in the previous engine, leaving the large counter-swirled injector as the culprit.

When we got more phenolic in, we repeated the run and had the chamber split again a few seconds after startup. We decided to stop boring the chambers out, going back to a throatless design that should have less stress, but lower Isp. We will probably be better off using the thinner wound tubes instead of the thicker laminated rods, even if it limits us to 15 second flights, because they won’t crack.

We went ahead and added gimbal attach points and mounted the engine under the vehicle for flight testing.

Ablative engines are not what we want to use, but this is a prudent step to hit our XPC flight obligations. A side benefit is that the ablative engines give a much more visible exhaust plume, with the bright burning phenolic and cotton to go with the clean burning ethanol.

Liftoffs

A few weeks ago we did an initial test with the vehicle and one of our regeneratively cooled engines. We modified our blow-out stands to support the vehicle 4’ off the ground, and used four climbing ropes on two eye-bolts to suspend the vehicle about 20’ under the lift. After snapping the tether on the last peroxide vehicle, we wanted more redundancy in supporting the vehicle.

A software error related to the auto-hover control and the new pulse width modulated valve speed control caused the engine to only throttle up to 50% and basically stay there. This was not enough thrust to lift off, and the low fuel flow caused the engine to burn through.

Because of this, I finally got around to updating my simulator for the gimbaled engine configuration, and got the auto-hover and boosted hop logic working properly with all the new changes.

Last night, we finally got the vehicle up in the air (briefly) on an ablative engine.

On the first test, I briefly lifted off with manual throttle just to see if we had enough thrust. We did. However, the attitude data was a noisy mess. It turned out that when the flight computer was moved over from the test stand, it wasn’t bolted down securely, so it basically rattled around on top of the vehicle.

For the second test, I disabled GPS position hold so it would only try to do angle hold without velocity / position gains added in, which makes some analysis easier. I lifted off with auto-hover, and it worked fine. The vehicle isn’t balanced very well, so the angle hold had a constant tilt to it, but it corrected back and forth properly until I shut it off.

I turned on position hold for the next test, which we expected to work perfectly, but when we were checking the vehicle out we noticed that a short crack had begun in the chamber at the nozzle end. We went ahead and swapped the chamber out, but when we fired everything back up we were surprised to find that the vehicle was no longer making sufficient chamber pressure to lift off. It just nudged off the supports and swung on the tether with the engine burning full throttle.

It took a little while to figure out what had happened, but I am 90% sure that the problem was decreased lox density. It was 45 minutes from the time we loaded the lox to the time of the third liftoff attempt, and it was under pressure the entire time.

At the boiling point at 15 psi, lox is at 92k and has a density of 1.13. When lox starts boiling at 400 psi, it is at 140k and has a density of 0.81.

Lox at atmospheric pressure is almost 40% denser than saturated 400 psi lox! The flow through the plumbing goes up a little for the lower density, but it is still probably 30% less lox mass going into the engine, which is going to be 20% less total mass, and a much richer mixture ratio. This can easily account for the lower thrust on the last run.

We are implementing many little changes in hardware and software based on the experiences, and will be testing extensively in the coming weeks.

Combined telemetry graphs for the engine-active portions of all three tests:
http://media.armadilloaerospace.com/2005_09_08/liftoff_combined.GIF

Video of the three tests:
http://media.armadilloaerospace.com/2005_09_08/liftoffs.mpg

A bunch of images from the last month:

http://media.armadilloaerospace.com/2005_09_08/2005_08_06_a.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_06_b.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_06_c.jpg

http://media.armadilloaerospace.com/2005_09_08/2005_08_09_a.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_09_b.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_09_c.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_09_d.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_09_e.jpg

( Matt was doing training for his pilot instrument rating for a week )

http://media.armadilloaerospace.com/2005_09_08/2005_08_20_a.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_20_b.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_20_c.jpg

http://media.armadilloaerospace.com/2005_09_08/2005_08_23_a.jpg
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http://media.armadilloaerospace.com/2005_09_08/2005_08_23_c.jpg

http://media.armadilloaerospace.com/2005_09_08/2005_08_27_a.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_27_b.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_27_c.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_27_d.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_27_e.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_27_f.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_08_27_g.jpg

http://media.armadilloaerospace.com/2005_09_08/2005_09_03_a.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_09_03_b.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_09_03_c.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_09_03_d.jpg
http://media.armadilloaerospace.com/2005_09_08/2005_09_03_e.jpg

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