craft

Craft (version from trans-GSO-> direct lunar flight) The same craft with paload adapter

payload adapers for different configuration of the cafts (that adapter takes 18 month delay for adaptation satellite to launch vehicle)

Main impulse (for flight from trans-GSO -direct lunar flight) frame adapter for main impulse engine

Mar 6, 2013 Now, after communication system design done, it is the time to place everything together

ON APRIL 20, 2013 11:46 PM Overview of mission control

Last week's changes

on - http://www.adobri.com/SatCtrlR.aspx

ON MARCH 26, 2013 04:18 PM Radiation according horoscope.

Thanks Boris - crystal diffraction of heavy particles can make some "pockets" with low probability of radiation. And also thanks for another idea - stamped, laminated surface of gold leaf in the form of reflective concave mirror can achieve the same. In that case radiation protection for electronics can be done inexpensively - Holes under microchips (anyway done for soldering ground plates) needs to be filled by indium-lead alloy around 2/3 thickness of PCB. The surface tension of the molten alloy forms a concave surface. All that remains - wash off the solder paste in alcohol and apply gold leaf to the surface. According Alan Turing in his Systems of Logic based on Ordinals http://fregimus.livejournal.com/212682.html - our intuition needs to be proved before it becomes ingenuity. Of course we are not MIT to check all this in the lab - but the idea is beautiful.
1993, Moscow, friend's house, "space" talks in a kitchen - -
- R-7 rocket's engine was... mainframe computers are… and was invented....gyrocompass …..
Little, 6 years old girl, patiently listening to a scientific talk, then suddenly asked:
- Uncle Alex, in what year you were born?
- ?! 1959.
- Uncle Alex! You are the pig! According east’s gyroscope!
Nice article http://haritonoff.livejournal.com/210442.html can be implemented on Xbox (in Russian. Not sure about appropriate/correct translation to other languages)

MARCH 15, 2013 12:51 PM "Communication session" DB.

Thanks, Serg, MySQL is not really my, but yours. To my pleasure language is different from another SQL. StorProcs are different, has a problems with integration to VS2010 and etc. All are hard to learn in one day. Pros- for MYSQL - according Victor - available MS product has limitation - on size - for big DB needs to pay in 3 zeroes, another plus for MySQL- according Boris MySQL perfectly can holds gigabytes, especially on SSD. Cons- According to Victor - time to be spend will the same as pay for commercial product in same 3 zeros.
All what needs from you are - to store from a “ground- station- control- computer” via web interface (i.e. page Post.aspx) record into a table in "Communication session" database with fields (a) session identifier (b) type of record ("uplink"/"downlink"/"downlink-was-with-error) (c) packet number (d) station identifier/backup channel (e) variable data size and two times (f) time of WebControl (g) time of send/receive via ground stations. Simple and non fancy. Also need to have one BD per one table.

I'll take care of”listening" software on a ground station computer. It is includes control for a ground station antenna / rover, and transmitter/receiver.

For you- via web interface (you can see "mockup" page GroundStation.aspx) will be set addresses and another parameters for station control computer. Then on a page
CraftCubeSat.aspx will be formed commands to be sent to a craft/Cubesats. Click on "send" button initiates transfer of uplink data to IP connected GrStn computer (that will be my headache to post/get data from one web server to GrStn software). GrStn software accepts command and send it to uplink (or to Azimuth / altitude controls, GrStn diagnostics) and posts back to website one records with a new session number, "uplink" / "GrStn_control" / "diag" type, GrStn number, "real" send time, and with packet's number is 0. As a result in DB will be exactly what send to uplink was. Then response (downlink) received on a 2.4Ghz communication will be posted as a second record into DB. Difference is a received time, packet number, and type. One "uplink" can creates many "downlinks". If packed can not be restored by algorithms inside communication system's microprocessor, then record will be with type of "downlink-broken-record". New uplink reset packet number to 0 and assign new session number. Another page to view (list) is a SessionData.aspx on it will be possible to visually check data.

That approach makes initial data to be stored as its. Any derivatives like retriving video or pictures or telemetry can be done separatly from a process of communication and control. Broken packages (impossible to restore in real time) can be restored later (using hash algorithm's matching). In that case additional record (of a restored packet) will be inserted additionally to a original broken packet. All addons can be done separatly, independently, and from different distributed processing computers.

I need for tonight: (a) Post.aspx page (needs to strip site.master's copy, long responce from IIS is not nessesary) (b)another page (for testing and manual entry) SesionPost.aspx (c) C# code for MyrSQL data insertion (d) visualization DB page Sessiondata.aspx (e) StorProc to get new Session number (table do not have "uniqe key" field or whatever terminology used in YourSQL).
SatCtrl web server available from link on a page http://www.adobri.com/ProjectGsC.aspx. If it is not working then ether – I am debugging, or give me a call I’ll reset server.
--------------------------
thnks Serg. Well done. Just to small remind - I need StoreProc. Friday - Are you coming to Korean БАНЯ? I have beer. I have to pick up next portion of just printed lunar money and then we can go.

Sep 30, 2012. Open letter to CSA done signing in a process, see it.

Complicated carbon fiber parts for rover and ground
stations, require complicated molds. Design such molds require quite a time to
be properly designed. As a solution for fast mold design was choose 3D printing
technology with material withstand temperature for a 1 stage cure (93C) of
epoxy and mold dissolvable in water. Material is PVA (in long spaghetti form),
and printer is Mendel Prusa. It takes a time (1 month) to build such printer
mostly because printer is in experimental stage, source code in 3 different
languages, technology require precise temperature control, adjustments for
experimental filaments like PVA is mandatory / complicated, extruders is in
experimental stage too. But after questions with software and temperature
control was sorted out, 3D printing allows to simplify mold design. Now it
takes 5-7 times faster to make suitable mold then when mold was made from
alumini plastic. Alumini plastic actually better suited to work in molds – it can
hold second curing temperature (163C) for epoxy, but saving time is more advantageous
in that case. Another advantage is to have 3D printer at hands – this is allow another
time savings – ordering via online alumini molds can not be done faster then
two weeks cycle.

You can see captured screen of a printer printing
first (base) part of the dissolvable mold –

For sure software (ether java or pyton ) require improvements – estimated time to finish print shows
years to finish task, and who knows! – may be software estimation is right ;-)

I would say (to my surprise) it is not bad as I was expected.

Last 3 months it was communication – now I believe we have good antenna (CTO even insists to get patent), for ground station sorted out questions with mold creation – it is combined technology with dissolvable mold and alumini parts (takes a lot of time to make 3D printer working but now it saved a lot of time in design), amplifiers starts to give a promising gain. Temperature stabilization for a craft and satellite – study was done – problems and solutions for electronics temperature control was outlined. Stepper motors modes was also done study – there some promising development with precisions in antenna’s orientation. Everything ready for debugging algorithms on inclination table (simulation moon gravity).

On a business front there is interesting development – we made attempt to push for Canadian microsatellite launcher – our proposals/ ideas was in a form of special letter for Canadian Space Agency. Now we are working on a signing process from supporting business. Nothing is visible now but…

Problems not resolved et – power station, solar panels, With power it is hard – without experiments on an orbit with Cubesat everything is in a fog.

Video – not much - we have may be 15-20 min video for communication tests – raw video – may be next month we can make video with frame (rover/ground station) creation and wheels testing on inclination table.

Hello Serg!

Files with schematics - http://www.adobri.com/misc/stm_bt/RF_GrSt.sch and http://www.adobri.com/misc/stm_bt/RF_GrSt.pcb file with PCB of 2.4 amplifier.

If provider will block files use .zip http://www.adobri.com/misc/stm_bt/RF_GrSt.zip

I use ExpressPCB – not best but not bad – most important for me – I get PCB manufactured on a 3 day after order.

Antenna for ground station - http://www.shapeways.com/model/322767/2-4ghz-antena.html , Antenna for Cube Sat - http://www.shapeways.com/model/322768/small-2-4ghz-antena-for-cubesat.html

Pictures:

Bluetooth - http://www.nordicsemi.com/eng/content/download/2730/34105/file/nRF24L01_Product_Specification_v2_0.pdf

Power amplifier- http://ww1.microchip.com/downloads/en/DeviceDoc/S71291.pdf

Low noise amplifiers - http://cache.freescale.com/files/rf_if/doc/data_sheet/MC13850.pdf

Switches - http://semicon.njr.co.jp/njr/hp/fileDownloadMedia.do?_mediaId=788

Voltage regulators 500ma http://www.analog.com/static/imported-files/Data_Sheets/ADP3335.pdf and http://cds.linear.com/docs/Datasheet/1761sff.pdf 100 ma

All components in database - http://174.6.165.86/dbadobri/Search.aspx

In Australia on two antennas like for ground station with regular wi-fi distance 12km without problem – limit is horizon (or height of antenna mount) – no need for any amplifiers — I think with 20-40mwt for wi-fi distance can be 20-60 km. If to connect Bluetooth that it must work on 1 km. One man claimed that on 4 antennas together (made less fancy made then my – people used cut PVC sewage pipes) he get signal from Mars orbiter.

Schematic which I send in last tests was without regulators 3.3v – for power amplifier and for LNA. I removed them and connect 3.3v from 1amp regulator – regulators works somehow unstable – I think is just some of my mistake with capacitors – I need individual regulators for Bluetooth+PIC and separate supply for a TX and RX

R1 and R2 in power amplifier — I set 2.9V by a separate variable resistor for a voltage reference – conformed value – in original schematic was bug - fixed

С26 — my inserts — otherwise switches does not works – another bug – fixed

С34 — same bug - fixed

L2 — have no idea - in typical application 12nH – but I put 8.2nH

Then I fixed problem in control signals for TX-RX – was stupid bug in tracing.

Then was a bug in soldering on U4 (I believe this is when I baked voltage regulator 3.3 100ma)

Then was bug with sizes — capacitors size 402 (1мм х 0.5мм) and resistors 805 (2мм х 1.25мм), but on PCB I placed all sizes 402 – as a result I have to cut spaces for a bigger resistors and 10uF capacitors.

If two antennas used then stable signal is over open air - 500 -670 m. If one antenna will be behind window glass then distance reduced to 120m. If I put amplifiers, then on 500m over glass packets travels fine. Another sign that power amplifier somehow working – with antennas only (1mwt) behind trees no receptions on 100m – with amplifiers at the same spot perfect reception. Also over air 500m is definitely better reception (LED blinking only on packets used in protocol – period of blinking give rough estimates). But power amplifier should give 36 dB – am I right or not – input 1mwt – 36dB output 1Wt (current also shows 350 ma)? If it is 1Wt – than signal must be really strong – even on another side of downtown with reflection I should see reception? With 1mwt I perfectly get reflection from nearest building – with 1Wt – no reflection – only direct open air.

Run with CubeSat prototype at 3AM aroundVancouveris interesting task – all Boms are curious – usual question – Is that technology can be used to get high? At day time it is funny too – tourists

I also do not understand – first – capacitors on RF-IN RF-OUT? What sizes of traces before and after capacitors should be?

And actually what for that capacitors? – lest assume for decoupling. Then why on power amplifier it is 1.2pF and for LNA it is 2.4pF? – Frequency of a sample application for a same 2.4GHz, or this picoF just what you have today for soldering? Or this pico depend on width and length of a trace?

Does they depend on a height? No seriously – after soldering a lot of buggers on traces – trace like hatchbacks – does it require to clean buggers or make it bigger – to adjust picoF? Then thickness of PCB – how account this?

And what a hack this L1 – bloody inductor! In recommendation it is stated: “Could be removed (really?!) if -7dB(?!) return (!?) loss (??!) is acceptable (?!)” – What loss? Why loss back? — is it -8 is OK and -6 is very bad? What is ACCEPTaBLE? dB of what? And that documentation is really good – in other specs for a different chips – only pins – event horizon for a creativity – try what you like with combinations 16*15*14*… etc.

Now antenna – I soldered it on J3 over capacitor (1.2?.2.4?) – as on a picture – direct connection of a antenna to a capacitor and without capacitor – What will be proper way to soldering /connect with or without?

Then connection to a Bluetooth – today it is a coaxial 25cm (2.4Ghz length of wave) in a future Bluetooth will be on same PCB but now coaxial – question – from a point of connection length/width of a trace to capacitors should be??? 1/6 or 1/32 of wave’s length. Or nature likes different fractions?

Next – “50om /85 mil” or “50om/120mil” or something even more mysterious – “50om RFIN” “50om RFOUT” – Yes I know – it was a man with a last name Ohm – also Ommm is Tibetan song – and what? 120mil * 3 = 360 +15 = 375 = small bottle in liquor store. But how liquor store related to U=I*R?

May be needs additional amplifier? The power amplifier designed to work for wi-fi. And 1mWt is not enough to work?

Also on schematics present noise canceling QHX220IQT7. But I am fighting with difference noise - in a head mostly. I even did not soldered it.

If you understand – you help will be appreciated. My knowledge is limited in RF area - as you know.

Alex.

(a) Ground station – I do not have resources to afford double development, as a result I adopted idea that rover itself will be a ground station.

It is crazy but that is my only option – rover has to be able orient antenna to the earth when it will be on the moon (one of the task rover has to perform).

Ground station will be a stripped from solar panels, batteries, camera stand, wheels will be reinforced (two wheels), power will be delivered by a external cord.

Status is: Design of a two wheel rover ground station: done. Stepper motors control: ready. Gyro system: ready. Antenna 2.4 GHz: ready. Amplifiers for receiver/transmitters: investigation where to buy. Transmitter/receiver 2.4GHz: debugging stage. Software for orbit simulation: ready. Software to control rover/ground station: in pre design stage. Noise cancelation – in pre design stage.

(b) Main communication will be on 2.4GHz, in Canada do no require to get operating license on hopping frequency band, no restriction on antennas, and maximum power for transmitter is 4WT. Otherwise (for different frequency) it will require license and this can get a time – licenses are two type – commercial and armatures. On armatures license in Canada I can not transfer data and receive for that transfer any payments.

2.4Ghz was chosen basically because of that reason – I am in a competition – if I’ll use radio, is it a commercial or amateurs use? Hard to say. To avoid such question better to use “open” band.

Another ground station problem – what to do if satellite on another side of earth and I need to communicate with it – for example to make main engine burn – well - needs backup communication.

Problem: it is -40C to +85C range, and manufacturer asking about air pressure 1atm. What I wont to do – is to place it in a compartment – compartment will be epoxy, I’ll just submerge it into epoxy only connectors needs to be extended.

To minimize noise in British Columbia needs to go some were in wildness – 1-2 hours driving time and big Vancouver noise can be shielded by mountains. Otherwise ground station can be located outside on any field – theoretically I need open 10m x 10m area.

(c) If you need a help to tack you satellite , and transmit/receive data – I need to have yours equipment/antenna (if it is a standard equipment I need to know where to get it), if it will be not a ‘no license’ frequency band – then I need in advance to apply for a license to operate ground station.

In a case of lunar mission planning location on earth for a communication will be Vancouver, Florida, East Brazil, South Africa, Ukraine, Kazakhstan, West Australia, Japan, Hawaii.

(d) Testing – Two tests spec (and form for certification) I get from a CubeSat website.

One is vibration test and another is ourgasing at vacuum and with temperature 60/70 C.

First is to test for launch vehicle frequency profile, on a website is a profile for a Dnepr rocket. To pass this test I am planning to send ready for test CubeSat inside a specified harness to a company (there are a couple around Seattle area) testing everything on vibration tables.

Second test from one point is little bit complicated but from another point it is also simple – place to a vacuum chamber ready CubeSat – reach level of a vacuum – heat till 70C (or 60C) - record pressure during 2 hours, if pressure did not drifted high then specified level (numbers on website and I also attached it to a letter) then test passed.

(e) Temperature requirements. I assumes that temperature will be -40C +125C. I choose epoxy with a range -65C +300C, all electronics -40 +125C, capacitors -40 +85C, stepper motors -40+85C, frame – aluminum, backup communication -40+85C. Parts with ranges less then -40C +125C will be placed inside epoxy compartment – and temperature has to be monitored.

Heating / cooling – no chance to control except by rotating satellite. Reflection - gold layer.

(f) For shielding from a radiation – I think on orbits till 400-500 km radiation will be not a big problem. I choose Microchip products – PIC was tested – some CubeSat team in already did radiation tests – PIC is OK.

To get radiation protection I’ll will use soldering squares under microchip area (only small part of a microchip holds electronic – this part has to be protected) soldering will be lead 40, tin 60 – or may be I’ll put more lead.

On top on chip will be placed temperature conductive epoxy – on top of epoxy will be placed another lead shield, thin layer of gold will be on top of everything.

Question that I am interesting based on (page 481 book by Boris Chertok reference http://history.nasa.gov/SP-4110/vol3.pdf in Russian version it is better to read but anyway):

"During Molniya-1’s third and subsequent spaceflights a rapid degradation of the photovoltaic converters (FEP) was detected.(33) It was the manifestation of a little known effect of irradiation when passing through near-Earth radiation belts. Another factor affecting the performance of the solar arrays was thermal cycling—a temperature differential from plus 120 degrees in the Sun to minus 180 degrees in the shade during each orbit.

In 1966, to reduce degradation and extend the life of the solar arrays, Lidorenko’s institute introduced a silica glass coating to the working surfaces of the photovoltaic cells. We had to give in and increase the mass, but we had some leeway there, thanks to the efforts of Dudnikov’s designers. Additional solar arrays shaped like special pleated curtains were installed, which made them heavier. When needed, the curtains opened and fresh elements that hadn’t been harmed by radiation or thermal cycling were put into operation."

Because I do not have access to good solar cell – I need to presizley know how available to me cell will perform. According Boris Chertok in one month I can loose half of the power on a Lunar mission.

Thanks for information about Sensormetrix. They are out of my reach. I have to developed everything by myself.

Question is (my question) which one will be better performed on a orbit – I am interesting in a particular case – how they will be deteorate under solar wind at least on a low earth orbit.

I do not have such information for those solar panels – looks like I’ll have to place all of them on CubeSat to check performance against charged particles.

Solar panels in my case has to be combined to get 3.5-4 Volts – then I’ll use voltage regulator http://cds.linear.com/docs/Datasheet/1761sff.pdf to get 2.5 volts – I tried different regulators – this one has low switch-off current and require additional tantalum capacitor. It is 100ma output current.

I did not made final choice – second one is better for temperature range, (in a case of second capacitor needs to use 2.7 V voltage regulator same type).

If temperature will be high then 85 – then capacitors still perform, but life-time shrinks.

Capacitors will be inside compartment – it is not a compartment truly speaking – epoxy/carbon shell with another epoxy as a sealant and thermal conductor.

Voltage regulator will be inside compartment – Quiescent current 20mka will help to fight low temperature.

(b) each solar panel split to a groups with 4V - 100ma capacity (I did not find suitable voltage regulator with high current but this is advantage not disadvantage). Grid of voltage regulators connects each group to capacitors.

Control of a grid performs by http://ww1.microchip.com/downloads/en/DeviceDoc/41341E.pdf it monitors voltage on individual group and capacitors and switch-on/off desired regulator to charge capacitors evenly. PIC16f72x can perform that task autonomously with transferring performance results to a central storage unit (backup computer)

3.3V can be 100ma (power for microprocessors), 5V -1 amp pick 1 sec, and for 12/9V needs to have 1.5amp (backup communication) pick 2 sec.

For main communication module 1WT transmission – I do not have requirements yet.

(d) – grid bust-up regulators connects of capacitors from one side and then distributed to a power suckers – (1) backup/main storage/camera unit processor(first power level) (2) all another processors unit (second level of power consumption). (3) orientation system, (4) transmitters/receivers.

Looks like distribution can work be controlled by same power control unit. If it will be not enough pins on PIC16F72x then may be I’ll put another power’s plant control unit – for controlling distribution – but I did not made decision yet.

(e) all capacitors discharged at launch – simple shot cut resistor grid combined with remove-before-flight tag will do CubeSat requirements job. Six CPC1822N (for power plant) will be also shot cut by CubeSat switch. No power until deployment as it specs.

Oct 17, 2011. Ok – this is a deal – lets assumes – (a) power plant on satellite has 6 surface – each 2 of it can be assumed parallel, looking in opposite direction with solar panel attached, that makes 3 groups by 2, each group orthogonal each other; (b) gyro precession is 1 degree per 4 minutes; (c) magnetometer gives readings (absolute) of a magnetic field with precession 2 degree. First step will be to stabilize satellite (eliminate rotation) to a level 0.5 degree per hour. It can be done by monitoring readings from a solar panels and do correction by rotating stepper motors. Then after 4-5 hours when error is less then 0.5 degree (per hour) magnetometer readings will be prerecorded during two orbits. This gives 2x3x75x75x2 ~ less 100K of data. Data analyzed for min and max of derivative and chunks of data with max and min values can be transferred by backup communication (not require orientation of a craft) to earth control center (~10K of data). On the ground center simulation program of a magnetic field on a low earth orbit will match (by brutal computer run) observed readings with approximated Keplers elements. Basically it will try all possible Keplers elements and find best match for observation reading. When Kepler’s found then for a time equal ½ hour before next communication session can be generated magnetic fields readings which craft has to follow for a proper orientation in a time of beginning of the session. When session will starts, gyro with precession 1 degree per 4 minutes (session time) can orient satellite to perform session. Ground station antenna will use the same logic for orientation with assumption that earth rotates 360 per 24 hours, coordinates and direction to a north magnetic pole can be reliably verified. The picture taken by camera fixed to the craft frame using the same method of orientation (30 minutes of prior picture session) can confirm precision of a method. The same technique will be used to orient craft for a main impulse on a way to the moon, in this case max 160 minutes of predicted magnetic field values needs to be downloaded. More complicated procedure on a way to the moon (travel time 7-9 days) for correction impulses – lets assume the orientation of a magnetic field in each point of trajectory will be stable during at least 1 hour. Direction to the of a moon and earth can be preloaded, then using gyro it is possible to orient craft’s camera (fixed to a frame) to estimated direction to centers of the earth and the moon. Picture can be taken and gyro will return craft back to the orientation before picture session with precision 0.25 degree (basically this mean picture has to be taken in a intervals of 1 minutes). Then magnetometer’s readings can be used to stabilized previous (before session) direction. Solar plant will give another vector for orientation to the sun. Two picture can be processed on board to get direction to the center of the earth and the moon. And calculated earth’s direction can be used for communication session. On correction impulse it has to confirm (by picture) direction to the earth, the moon, the orientation of a magnetic field and using gyro (1 min) before impulse to orient the craft. Brake impulse performed the same way.

This require – gyro/magnetometer needs to be able to collect data during 160 minutes. Collected data must be processed on board to find max and min of a derivative. Stepper motors was to able to perform full rotation of a craft during 1 min. Onboard computer must process images of the earth and the moon to find direction to center of the body. On ground station (tra application, additionally) needs to be able to simulate earth magnetic field on low earth orbit (< 350KM). The same application needs to be able to match trajectory with magnetic field’s readings. On ground test for power plant and orientation system needs to include proper rotation elimination. On ground test for magnetometer needs to include harness with rotation of a magnet in some plane. The readings can be used to debug kepler’s elements matching and debugging orientation system stepper motors commands. Full flight tests can be simulated on a ground. GPS on board system will be used for Kepler’s elements verification. May be trajectory calculation app will work in a distributed mode to speed up process. If in 1-1.5 year frame gyro with precision better then 1 degree per hour can be obtained scenario of a flight can be revised.

(b) confirm power plant working and gyro module working for Keplers elements calculation, data transferred (to earth) using backup communication;

(f) conformation of onboard processing center of earth calculation (from captured image);

(g) conformation of onboard processing center of moon calculation, in a failure of this tests imaginary data and gyro readings has to be transferred back to earth for additional processing;

(g) simulation of a main engine firing preparation, this includes upload magnetic fields targeting values, gyro position target values, center of earth targeting values.

Sep 1, 2011. Antenna 2.4Ghz – for ground station helical antenna design and manufacturing – it will be better to print such antenna than make it by hands – 3D printing material suitable is Nylon 12. 3D model: (click on picture to see in SolidWorks eDrawings, req automatically installed plugins):

Also was discussed the same technique for suppress noise on a transmitter – transmitter antenna on satellite oriented to the point on the earth at the same time noise helical antenna looks backward 180 degree. Second (noise) antenna needs to be with receiving pattern covering the same sky area as a ground antenna (this depend on a orbit, otherwise needs mechanical adjustment). Mixing delayed (61.3mm) noise on 2.4Ghz from a particular place on a sky with a transmitting signal, then subtracting same noise on receiver can give ~50+20=70 dB which will be good as it sounds. Complications: it is hard to get precise receiving pattern for noise antennas on transmitter and receiver; such scenario would not work from the Moon.

With active antenna this actually can be done – interesting: does anybody made such experiments?

5 Aug, 2011. Small panic about 526N epoxy – by all parameters it is acceptable (-78C +300C tolerance, flexibility, outgassing, and etc.), but it is not in it http://outgassing.nasa.gov/cgi/sectionb/sectionb_html.sh Material Alphabetical Listing. This (not in list) may be problematic for any composites used in vehicle and craft. Epoxies 517, 556, 568 present in a section B list but it is not suitable.

After contacting manufacturer it was confirmed that 526N actually was tested around 20 years ago for outgassing study and Total Mass Loss at 125C is 0.49 (less then 1%) and Collective Volatile Condensable (at 25C) Materials is (0.00) with curing conditions 2H (93C) and 16H (204C). Epoxy is good, looks like it will be require re run ASTM E-595. Anyway satellite (including vehicle) was to pass vibration tests according launch vehicle profile and thermal-vacuum bakeouts to ensure level of outgassing at minimum vacuum 5x10-4 Torr. Manufacturing of composites was to be documented.

Last one is preferable – needs one conformation ORBCOMM would it be able to communicate with low earth orbit.

July 20, 2011. Main onboard computer and power station. Computer Rabbit with industrial temperature requirements. 3 Microcontrollers to control orientation’s stepper motors, flash memory, 5 high-capacitance capacitors, 3 type of a solar panels with separated method of deployment (flexible one will be extended using springs). All power capability – 1W.

July 19, 2011. Astro- navigation system needs pin hole camera (20 g) and software processing captured image in main onboard computer. Format of a captured image JPEG. Source code for a extracting image available…. In ground tests can be included processing image from available space videos converted to exact format from a camera. Also for matching starts and the Moon it is possible to do series test on a ground and Photoshop mock-up images of a Moon. Full system must be tested on orbit before attempt to fly to the Moon.

July 18, 2011. Communication system 2.4GHz. For a small cube-type satellite it will be impossible to test full helical antenna (562mm) , as a result all test has to be done on shorter one (100mm), this will reduced gain from 17dB to 9dB and increase half power bandwidth from 25 to 60. Analog part of a communication system was not designed yet. Communication protocol is all software related topic, nothing complicated. For communication system needs to build 2 portable ground stations. Station needs orientation platform (using for a amateurs telescopes) for following satellite on a sky. Each station needs to be equipped with 4 helical antenna. Stations will be used later for communication with a probe on path to the moon.

July 17, 2011. Orientation system will include 3 stepper motors. For a test on 1kg total mass it will be require motors with bearing. Suitable weight for each 30 g. And lubrication can be changed to molybdenum. Gyro sensor readings should be compared with targeting XYZ values. Onboard main computer has to be adaptable to different type of motors, (a) different inertia momentum, (b) delays of control to avoid oscillation. Dynamic parameters of a system has to be calculated (not predetermined) using same gyro-sensor. Placement of 3 stepper motors may be not in a center of mass – as a result to support orientation along any of 3 axes, system should calculate parameters by itself. On ground tests for a system can be done only for one axe, and in plane intersect center of mass. In worth case scenario it will require to download new binary for orientation system (effectively for a main onboard computer).

July 16, 2011. GPS any way needs to be developed for correct main impulses direction. Electronics can be done in 2 weeks, and software will be major development. First it will transfer ID29,30 satellites reading using backup communication. Then by formula on a ground calculates Keplers elements and transfer orbit params back using backup system. Weight for a sensor 25 g. For ground tests can be used the same TRA app with 5 GPS satellites Keplers element and simulation of a ID 29,30 data. When formulas finalized and errors estimated the same source code can be inserted into a flight main computer. No backup calculations of Keplers elements in microcontrollers.

July 15, 2011. Check - which systems from a craft can not be tested on a ground but in orbital flight. The critical one

(e) astro-navigation system (calculation direction to the center of Earth, and star matching system).

July 13, 2011. NASA workshop. Talk about active experiments on Apollo sites, no power require for measure distance using laser from the Earth observatory and reflector on a Moon. Seismometers data will be really interesting by science community. Why not to combine all together – small sensor with nanowatt power requirements, radioactive heater of a couple milligrams to heat electronics at lunar night, modulation system on reflector, light weight solar panel (even if after couple years it will might be enough), place everything under surface/dust for thermal protection (or use power harwested from ceramic elements). Same modulation system on reflector can be used for transferring any data from a Moon without big power plant.

July 12, 2011. Fiasco on Team Plan B speech – engineers do not like to talk about “political agenda”, even on a first day of a summit was a lot of talks about how to attract investments, and protection of intellectual property. Common outcome of a first day was – more likely investment to teams will come in a form of “angel’s investments”. Anyway one check box in requirements by Boris Chertok done – Patent System on Software is in a mess, and has to be changed, and this is aside from our project. Never say – “I made the mistake”, but every time explain – “What a interesting problem I faced last week!”

July 11, 2011. NASA, big wind tunnel, metal and composites really nice. It is interesting how was organized tools storage. SOFIA infrared observatory – impressive (Why I am not a scientist?!). Really impressive Team from Barcelona.

July 9, 2011. TSSOP cases not only be light weight (twice as SOIC) but size of PCB needs to be smaller – all electronics will be inserted inside frame (tube) – routes has to avoid side edges, on perimeter of a board has to be placed crush-protecting holes, two rows on each side at least.

July 8, 2011. Soldering passed perfectly. New soldering station works fine (never before use hot air) SOIC cases is ok. TSSOP was actually better then SOIC. For next round (after analog part finished) needs to retrace PCB for TSSOP because of different pins assignment.

July 7, 2011 – PCB arrived – funny conversation with custom – what is it for? What a company doing with it? How and where it can be used? (On a Moon?!). No need to pay duties and taxes on PCB! Actually this can be a major problem for a project – today it is possible to order all rover’s parts from metal shop over internet, each part will cost around 200USD/CDN (total 35 parts * 200 = 7000CDN), if to order 25 rovers it will be just twice expensive. Development process each time needs to make one change, or another and order another modified part. What about delivery?! Delivery costs is not in same proportion as a manufacturing – delivery for some unknown reason is only available from big parcel service company. All other companies do not what to listen to a question – Can you send my carbon fiber supplies by post office or by different delivery company? Results - with a price of a PCB $51 – delivery costs $40. For $150 solar panels – delivery, duties, taxes, multiplication calculations was total $100. And this not all – money not only a problem - time is lost – delivery time of 3 days can be stretched to 2 weeks. Last month parts costs $1200 and delivery was $357 – more then 25%.

June 31, 2011 – PCB was ordered - will be ready after holidays in US and Canada, Parts ordered (it takes a time to check sizes and temperature tolerances for each chip). SOIC case:

U17 - PIC16F88 http://www.microchip.com/wwwproducts/Devices.aspx?dDocName=en010243 Memory and 16LF88 is from -40 + 85C, all another is -55+125

75AC74 (-45+85) http://search.digikey.com/scripts/DkSearch/dksus.dll?Detail&name=296-1064-1-ND or

June 29, 2011 - PCB layout done: adcdac_1.pcb It takes 3 days. Possible to reduce time to 1, needs to accommodate to a tool before using it.

June 26, 2011 – Now attempt to use quartz crystals with 30MHz frequency – Crystal give ether 3 or 6 MHz instead of 30.

June 23, 2011 – Time was spend on investigation – which software to use for creation PCB and schematics. Tried Multisim – schematic was created fast, library not full but similar cases can be used, good but expensive. It gives quick routing, only one problem - it better be used when needs to make a PCB board with all component soldered, different PCB manufactures does not accept Multisim format. PCAD was tried long time ago and it is not preferred schematic tool (may be because I am not an electronic engineer and do not understand benefits of PCAD). Tried another two applications, including free software in Windows and Linux. Best choice is Express PCB. Schematic available: adcdac.sch

June 22, 2011 – No ideas how to solve problem – suddenly after connecting LED to random legs on random chips (for visualizing) receiver became a good boy! Removing one LED creates a noise, inserting to another place removes noise. Place of insertion does not matter. Turned out – power supply instead of regulated 5V gives 5.5 – insertion of a LED suck more current and reduce power to 5V. Ok – forget about 5V – and switch to 3V (which is kind of 3V 3.1, 3.2 - depend of LED, amount of chips, and etc.) everything become perfect – messages flying, units responding, etc.

June 21, 2011 – Porcupine was extended to receiver. Nothing works even previously working transmitter. CY7C199CN require bypass capacitors. Yes - needs to RFM. Each memory chip gives a noise, 0.1mF helped, but communication with microprocessor receiver units (terminal app over serial port used) does not work. Applying bypass capacitors to all chips did not helped. Switching units (the same software in each did not helped) – transmitter working and receiver persistently on strike. Was enabled Master Reset in 16LF88 – reset on Transmitter works, reset on Receiver noisy – garbage on output port without any pattern.

June 19, 2011 – Unfortunately Alex’s skills in digital design is really rudimentary. A lot of time was spend on prototyping. Especially in debugging logic NAND and NOT gates. Good simulation of a digital logic will be beneficiary, but any way - transmitter is ready in a form of a porcupine’s bread board and works.

June 17, 2011 – IUP (Inter Unit Protocol) was re-designed from old code – now each unit has serial output connected to nearest unit’s serial input. I.e. main computer serial output connect to Transmitter’s serial input, then Transmitter’s serial output connected to Receiver’s serial input, and Receiver output connected back to main computer serial input. In passive state bytes from any units travels (looping) over entire net. Integrity of all network can be verified by any units individually. NAND gates can be used to bypass un-functional unit. RST in high state will enable transmit data btw nearest units, and pull-down resistor can be used to skip broken. Both microcontrollers (16LF88) for LDF (Laser Distance Finder) transmitter and receiver designed to be exactly the same (difference in command “wW” and “wV’ – W set W/R high, and V set ports bus into input mode). Source code: STM_LTRX.c, and for and project: STM_LTRX.mcp, STM_LTRX.mcw

1. Transmitter starts with resets W/R = 0, CLCR =0, RST = 0, then set RST=1 sequence “2wcrR2” where

2. Microcontroller (or main computer) will store in transmitter memory wave (data or for laser byte 0xFF coded “on” or 0x00 coded “off” state) to be transmitted CLCR = 1, W/R = 1 then needs to set on bus 8bit data to store in memory and set CLCR will clock-in byte into CY7C199CN

“8” is just a helper command it will store sinus wave in 4096 bytes for debugging Each byte value will stored on a raising CLCR (first byte is not important) At the end of 32K bytes needs to set W/R = 0 CLCR = 1 and back CLCR =0

3. Now transmitter memory ready – oscillator signal with 30MHz will clock-out data from memory to DAC (U6 - HI 3338). For debug it can be 2Mhz from 16LF88 on a pin 12 (RA6) by setting configuration bits, or by disabling clock on RA6 it can be manually set pin 12 on/off. Sequence is (for oscillator, and 2MHz debugging ): “2wcrRVC2”:

“V” – W/R will be in low and data bus on 16LF88 will be set in input mode on RA and RB

“C” – CLCR high and oscillator drives counters. On each rising edge data will be send to DAC and on each failing edge of oscillation DAC fill latched previous byte.

4. Transmitter and receiver uses same oscillator. It is possible to set delay for receiver to start to store DAC data into receiver memory by switch/jumpers U9. Delay can be useful because on long distances 25 km == laser beam travels 50km time delay == 1.(6) E-4 sec, this for a frequency 30MHz require to store digitized samples in 5000 bytes (for laser beam travels from a craft and bounced back from a Moon surface). Error in calculation will be 10-20m. Less data to be processed (by microcontroller) faster (less delay) to measure distance. Ideally instead of jumpers possible to set comparator this will trigger receiver to run by some delay. Roughly 16LF88 running on 8MHz (2Mil or /sec) can process one measure per sec. This give (at speed 2800m/s) 1 ms accuracy of 0.01 to start break engine. At the same time main computer will be able to process 50 measurements per sec. To confirm calculation looks like needs to start measure 8-9 sec before impact by main computer – when first measure will be obtained, needs to switch for a backup microprocessor and compare calculated time. Speed of a craft does bring error in time travel 1.(6)E-4 of a laser beam around 1 m. Speed of a craft can be calculated by two different measurements by calculation difference distances and knowing time btw measurements.

“V” W/R set low and data bus on 16LF88 receiver will be set in input mode on RA and RB

“C” oscillator connected to counters on transmitter data clocked out with 30MHz – delay passed and receiver memory already with measure data

“w” – W/R low on receiver (prev tag was opened communication with receiver)

7. Bus data and control signals RST, CLCR, W/R will be sheared with individual microprocessors (backup) and main computer – this require commands for microprocessor “L” – listen – in this case both units will put all ports RA,RB into “input” mode.

June 3, 2011. During descent, to ignite brake engine at 2800 m/s requires real time distance measurement to Moons’ surface. We think radar or laser can be used. Weight for radar is heavier of the two concepts, around 2-3 kg, which is too large for our small landing vehicle design. Alternative approach is a Laser Distance Finder (LDF). In this case weight will include only two optical lenses, electronic equipment and mounting, significant saving in total mass of a probe. Off-shelf laser range finders can work on maximum distance for a couple kilometres.

Requirements – measure distances from 30 km to 5km, reflection from a lunar dust, 0.5W laser.

Additionally (a) if it possible the same system can be used to transfer data by laser beam and (b) be used to measure distance to reflectors on a moon on early approach stage.

The Craft will be a polygonal aluminum frame mounted on the top of the vehicle frame. Fixing both frames together will be done via pins removable by inflating air-bags system. On the craft’s frame will be mounted 4 fixed impulses engines and a low trust engine. 4 engines will be mounted orthogonal to each other with center axes project via centre of mass of a probe. Firing sequence – fist orbit correction, second orbit correction, main impulse, brake impulse will be each time projected via the centre of mass of the probe.

Hermetically sealed parts of a frame will at the same time tanks for a liquid (ethanol/alcohol) propellant body for a low trust engine. Pumps will be require to precisely adjust probe’s centre mass position.

While in a flight, the probe's orientation will be performed via inertia momentum created by the rotation of three masses. Those masses will be mounted to stepper motors located close for central mass point inside two fixed engines frame. Third stepper motor will be mounted directly to a craft’s frame.

Engines will be carbon fibre cylindrical boxes. Small compartments will be in two of engines to accommodate stepper motors with rotating masses. Graphite nozzle will be mounted inside rear part of each engine.

Same rotation momentum will be used to control thrust vector direction at engines firing.

Location of a low-thrust engine not determine et, but it must be orthogonal to plane of 4 fixed impulse engines.

Requirements for a vehicle’s mass 6 kg on a Moon surface brings requirements for a total mass on a low earth orbit to100kg. That weight puts a craft onto a category of amateur satellites. Amateur satellites usually launched as a second payload for a regular launch. It will be desirable to stay in limits of 100kg, otherwise price for a launch can be high. Here is a reference for a OSCAR type: