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Flight Unsuccessful

Absolutely banish the remaining

November 12, 13, 15, and 16 (busy week!) meeting notes

 

Flight Unsuccessful

 

We prepared for and conducted our first remote flight test at the Oklahoma Spaceport facility in Burns Flat this week.  Several lessons were learned.

 

We built a checklist for our flight operations, which was a very good idea.  Going through it before setting off caught several things we almost forgot.

 

The five hour drive from Dallas to Burns Flat was rougher on the equipment than expected.  The tarp we put over everything to keep people from staring was damaged by the wind in several places, and the wooden cradle we transport the vehicle on actually broke one of its 2x4 support bars.  We are probably going to arrange some hoops for the trailer so we can tarp it like a covered wagon in the future.  I may consider an enclosed trailer with a suspension in the future.

 

Everyone was extremely helpful in Oklahoma, and we set up in the middle of a service road well off from the main airport runway.  Our expected altitude with only five gallons of peroxide was under 1500’, and our parachute drift range with 13 mph winds was only about 2000’, so we had plenty of room.  Bill Kourie from OSIDA stayed with us to communicate with the air traffic control tower during our launch activities.

 

Our setup was a bit slower than we expected, but everything got done fairly smoothly.  The VOX on the radios we brought was more trouble than it was worth, often triggering with wind noise, but this was our first time using radio communication.

 

We did a full water test, then loaded up five gallons of peroxide.  The engines all warmed quickly, and ran perfectly clear, even though it was in the mid 50s.

 

When we were cleared for our launch, I smoothly throttled up the engine over a two second period.  The vehicle tilted a little bit on liftoff, but seemed to straighten out, but it then continued tipping, eventually tipping all the way over and flipping into the ground from a hundred or so feet up.

 

There was still peroxide left in the vehicle tank, but all the pressure had drained out by the time we reached it.  We tipped it up to allow the remaining peroxide to drain down into the main engine and slowly catalyze away, then we carried the vehicle back to the road to run some low pressure water through it to clean it up.

 

http://media.armadilloaerospace.com/2002_11_16/flightUnsuccessful.mpg

 

We drove the remains to our bunker to strip off the good parts, and left the main body there.

 

http://media.armadilloaerospace.com/2002_11_16/bunker.mpg

 

 

Analysis

 

The telemetry cut off only four seconds after throttle-up, indicating that the computer died, but there was very valuable data.

 

Immediately after liftoff, there was a +Z angle rate kick, probably caused by the funny takeoff aerodynamics underneath the tail flare.  The piece of aluminum sheet metal we put under the rocket for ground protection was folded in half and crumpled up after liftoff, which was completely unexpected.  You can briefly see that in one of the liftoff video frames.  The rate peaked at 22 deg/s, with the opposite attitude engine full on, then it started coming back down. The liftoff test last week did not show this behavior, but the feet were changed, and the surface was different this time.  It is also possible that the main engine mount was slightly distorted by the travel. 

 

The Crossbow stopped updating 1.25 seconds before telemetry ceased.

 

The vertical acceleration was right at one G when the Crossbow stopped updating, and very smooth.  This was slightly higher than expected, indicating about 600 pounds of thrust from the engine at 280 psi takeoff tank pressure.  The plumbing on the test stand was definitely limiting performance compared to the straight shot on the vehicle.  The welded catalyst pack continues to perform very well.

 

The battery voltage started dropping rapidly at this point, but the computer continued operating for another 1.25 seconds, until the battery voltage reached 9v, at which point telemetry ceased.  The 15v power converter for the Crossbow probably suffered a voltage drop before the 5v power converter for the main computer.  The main engine feedback potentiometer reading fell off as the 5v supply dropped below 5v, and the engine pressure transducer started falling off faster than it should as the supply voltage dropped below 10v.  All of this points to a general power system failure, rather than just a computer power failure (which has triple redundant connections to the main power supply from the manned lander work).

 

During the last 1.25 seconds of operation, the computer continued using the last valid Crossbow data, which caused it to hold the same two attitude engines on, which built up momentum on all three axis.  Presumably the attitude solenoids all closed when the computer died and stopped sending an active signal to the solid state relay boards, but quite a bit of momentum could be built up in that time.  The main engine would remain in the full-open position.  As the vehicle did its flip, you could see it slowing down while it was pointed upwards.

 

The flight control code has in the past had stop-all-engines behavior when the crossbow stops updating, but on this flight there was no cutoff checks, which was a mistake.  If there had been, the rocket would have just dropped from about 20’ in the air, and suffered much less damage.  The exact timing for deciding the crossbow isn’t working is a tough judgment call, but a quarter second should certainly be enough time to decide that the attitude engines should cut off.  The decision to cut the main engine is harder, because the vehicle should be able to continue flying as an unguided, aerodynamically stabilized vehicle if it is going fast enough, but right-off-the-pad, it could turn into a land shark.

 

There was one GPS update after liftoff, showing it at three meters above the ground, but with only a small vertical velocity.  The processing latency on GPS velocity and position may be different.

 

My initial thought was that something had shorted, perhaps in the motor drive feedback or pressure transducer, which have power running to them from the main bus.  When we opened the electronics box, the cable to the battery positive terminal was not connected.  The battery still had full voltage in it, so we believe that the terminal came off during the flight, causing the voltage drop that led to the failure, rather than during the crash.  It is unfortunate that it seemed to work during the water test and warm-ups, but the drive from Texas probably loosened the connection to the point that it was barely hanging on.  The batteries have slip-on connectors, which have bothered me for quite a while, but screw terminal batteries are not available until much larger sizes.  We are going to drill our own screw terminals in the lugs of future batteries, and possibly solder them as well.

 

 

The Damage

 

The important thing is that the Crossbow IMU survived, because that costs more than everything else put together, and can have an 8 week lead time.  I am going to buy a backup, in case we aren’t so lucky next time.  Crossbow is now offering (but not shipping yet) an improved fiber optic gyro IMU with half the drift rate, but they jacked up the price a few thousand dollars.

 

The main tank actually seems to be ok, but we are not going to trust pressurizing it again.

 

The fiberglass nose and tail cones were both broken.

 

The engines casings for the parachute tower still look OK, I guess they bent away before the body hit them.

 

The tower was mangled, of course.

 

The pressure transducer at the top of the tank was broken.

 

Our aluminum engine frame at the base was bent a fair amount.

 

One attitude engine broke the jet holder fitting off inside, but we can probably remove it.

 

The main engine servo valve had the half inch pipe fitting permanently bent in it, but we were able to swap that section of the valve with scrap from a valve broken in a different way, so it seems to have been saved, but we haven’t leak checked it yet.  The plastic connectors on the valve were very brittle from the cooking they took on our hover tests that stuck to the ground, and broke when disassembled.  We are going to run Tefzel wire all the way to the valve motors in the future, instead of using the supplied pigtail connectors.

 

All the plumbing survived, except for the two fittings that jammed in engines.

 

All the engines look ok, but we will have to carefully check that the main engine hasn’t bent its inlet connector.

 

The WinSystems SBC computer seems dead.  The memory SIMM was ripped out of the socket, which also partially detached, and even after reseating everything, it won’t boot.  The flash drive still works fine in another system, which saves me the effort of building a new linux system from my last backup.

 

The antenna connector on the Esteem wireless unit is broken, but the unit looks OK.  Taking the case apart showed that we can save a large amount of electronics area and several pounds by just mounting the guts and ditching the case.

 

Both batteries have cracked cases, although neither one spilled any acid gel in the box.

 

The fan over the power supplies was wrecked.

 

The A/D breakout board was smashed by the batteries.

 

 

New Vehicle Work

 

We are going to proceed with the next vehicle design, as if this test had succeeded, rather than rebuilding an identical vehicle.  The major change is to move to four large engines that are differentially throttled, instead of the single large engine and four solenoid controlled attitude engines.  This goes back to the control style of our very first lander, and is motivated by the fact that we are bumping up against vehicle size limits for being controlled by the thrust we can get from solenoid based attitude engines.

 

The vehicle will pay much more attention to streamlining, with the intention of being capable of supersonic flight.  The nose will be 10 or 15 degrees, and we will be using a honeycomb composite constructed box fin arrangement for stability instead of the tail flare.  There will be no external protrusions or loose cables along the sides.  We are going to try a rear parachute ejection system, with an intentionally crushable top nose section

 

The propulsion system will have a master cutoff valve, run by a separate watchdog computer.  We have talked about this for ages, but not yet implemented it.  If implemented on the last vehicle, it would have dropped it from a much lower altitude.

 

We are going to make many changes in the electronics to improve reliability.

 

There will be a backup 9600 baud telemetry radio, in addition to the Esteem 802.11b.

 

No more solid core wire for DB connectors, move to 22 ga stranded Tefzel wire.  All 18 gauge wire is already Tefzel, but I had been using solid wire for soldering serial cables, which is a known poor practice.  I am moving to mil-spec double-crimp terminals for all flight hardware, instead of the single-crimp industrial terminals we have been using.

 

Mount all the electronics, except for the inertial unit, on a vibration isolated board.

 

New A/D breakout board

 

The breakout board that WinSystems sells for their A/D board takes up a lot more space than necessary, and uses bare wire screw terminals for input, so we are going to replace it with a custom board that is smaller and takes ring terminals.

 

16 signal inputs with #6 ring terminals, one ground is common to all signals measured.

 

The range is +/- 10V, so we need to cut the main battery voltage in half before sampling.  It is a toss up if this should be done on the A/D breakout board, or on the power supply board.  There should be a grid of holes for soldering in random resistors or capacitors to modify signals.

 

The grounds are common to all the signals, so I think all we need is a single ground ring terminal that we will run back to the power supply.

 

The connector going to the A/D board is a 26 pin ribbon cable with the following pinout:

1: ch0   2: ch8

3: ch1   4: ch9

5: gnd   6: gnd

7: ch2   8: ch10

9: gnd   10: gnd

11: ch3 12: ch11

13: gnd 14: gnd

15: ch4 16: ch12

17: gnd 18: gnd

19: ch5 20: ch13

21: gnd 22: gnd

23: ch6 24: ch14

25: ch7 26: ch15

 

 

Watchdog Board

 

Trivial microcontroller that watches a continuous signal from the main computer, and uses a private motor drive to open the master cutoff valve only when the main computer is healthy.

 

Input:

One optically isolated digital line from the main computer

Private +12v / GND

 

Output:

Two #6 ring terminals to control the master cutoff servo valve (the main computer will still read the pot feedback of that valve)

 

Power supply board

 

Multiple, diode isolated batteries for redundancy, with an additional port for running on external power

 

External charging ports for each battery, so the electronics don’t need to be taken out of the vehicle for charging.

 

Short run from batteries to boards, no in-line power switch.  Use the power pin on the DC/DC power converters for switch-on.  Use redundant switches to prevent a switch glitch under vibration from turning everything off.

 

Run nothing from the unregulated power supply, except for the A/D line for current voltage level.  We previously ran a couple things from the unregulated 12v supply, like the Esteem wireless unit, and the pressure transducer.  It is possible we were losing telemetry momentarily earlier than the computer died, depending on the details of their power use.

 

Instead of running wires from the power supply board to jumpered barrier strips for distribution as we previously did, build plenty of terminals directly onto the power supply board.  At a minimum:

 

Lots of grounds.

 

Unregulated +12v: Battery A/D line

+5v: computer (two lines)

+5v: 6 motor drive potentiometer feedbacks

+5v: several spares

+6v: laser altimeter

+12v: pressure transducer

+12v: GPS

+12v: Panel-PC LCD display

+12v: Several spares

-12v: Panel-PC LCD display

+15v: Crossbow IMU

We might want to use a higher voltage for the IMU, as the range is 15v-30v, and we have been warned by someone about running avionics at their minimum recommended voltages.  Today’s result seem to corroborate that it is closer to going out than the rest of the systems.

 

 

Current draw signal for telemetry?  If we ever have a short somewhere, this would be helpful in diagnostics.

 

Isolated voltage signals for each battery?  If we don’t have that, telling when a battery has failed will be difficult.

 

 

Actuator Boards

 

Our current solid state relay board still has bare wire terminals (although they are high quality ones that haven’t yet given problems), it still has the old power supply on it that we don’t use, and one bit on the input connector is flaky, so it needs to be replaced.

 

Isolated voltage signal for A/D telemetry?

 

Isolated continuity checks for each actuator?  The motor valves can be self-tested by watching the potentiometer feedback, but solenoids and pyro would need a low-current test signal.  The actuator battery needs to be completely isolated from the main battery to avoid noise problems, so a continuity sensor would need to be isolated as well.

 

We have known needs for up to six solid state relays and six motor drives, so building for eight and eight is probably good planning.

 

 

 





 






 
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