From richnakka@rogers.com Fri Nov 11 15:31:43 2005 Received: from smtp102.rog.mail.re2.yahoo.com (smtp102.rog.mail.re2.yahoo.com [206.190.36.80]) by mail.exrocketry.net (8.12.8/8.12.8) with SMTP id jABNVgJr011820 for ; Fri, 11 Nov 2005 15:31:43 -0800 Received: (qmail 21769 invoked from network); 11 Nov 2005 23:36:44 -0000 DomainKey-Signature: a=rsa-sha1; q=dns; c=nofws; s=s1024; d=rogers.com; h=Received:Message-ID:Date:From:User-Agent:X-Accept-Language:MIME-Version:To:Subject:Content-Type; b=SzO7w/LHhy97MaREjn5MlZJ72ARgPR6Dvg3NQku1hVb3Xh/81wqeMkYD+alWhOoDNPB546mB51hMIyv421WkJM3VdHWycD2KR8BA8Qejyfxo6YBwr+UWzTo4qd5rB+6ngA6CDshr4vIJ9i1Rt85G/mhN1B4eKjq3zV4hV5VWeLQ= ; Received: from unknown (HELO ?24.42.138.7?) (rnakka@rogers.com@24.42.138.7 with plain) by smtp102.rog.mail.re2.yahoo.com with SMTP; 11 Nov 2005 23:36:44 -0000 Message-ID: <43752B0D.9020107@rogers.com> Date: Fri, 11 Nov 2005 18:36:45 -0500 From: Rich Nakka User-Agent: Mozilla/5.0 (Windows; U; Windows NT 5.1; en-US; rv:1.7.2) Gecko/20040804 Netscape/7.2 (ax) X-Accept-Language: en-us, en MIME-Version: 1.0 To: Propellant Development Team Content-Type: multipart/alternative; boundary="------------020306020604060904000902" Subject: [SS-Propellant] Test message to Propellant Development Team X-BeenThere: ss-propellant@exrocketry.net X-Mailman-Version: 2.1.1 Precedence: list List-Id: List-Unsubscribe: , List-Archive: List-Post: List-Help: List-Subscribe: , X-List-Received-Date: Fri, 11 Nov 2005 23:31:43 -0000 This is a multi-part message in MIME format. --------------020306020604060904000902 Content-Type: text/plain; charset=us-ascii; format=flowed Content-Transfer-Encoding: 7bit Gents, Welcome to the SStS Propellant Development Team mailing list. * Please reply to this message to confirm that you are on the list * Shortly, I'll be sending out a message detailing topics of discussion & proposed propellant research in preparation for moving onward with the SStS project....! Richard Nakka --------------020306020604060904000902 Content-Type: text/html; charset=us-ascii Content-Transfer-Encoding: 7bit Gents,
Welcome to the SStS Propellant Development Team mailing list.

* Please reply to this message to confirm that you are on the list *

Shortly, I'll be sending out a message detailing topics of discussion & proposed propellant research in preparation for moving onward with the SStS project....!

Richard Nakka

--------------020306020604060904000902-- From richnakka@rogers.com Sun Nov 13 11:57:24 2005 Received: from smtp101.rog.mail.re2.yahoo.com (smtp101.rog.mail.re2.yahoo.com [206.190.36.79]) by mail.exrocketry.net (8.12.8/8.12.8) with SMTP id jADJvOJr028919 for ; Sun, 13 Nov 2005 11:57:24 -0800 Received: (qmail 26322 invoked from network); 13 Nov 2005 20:02:29 -0000 DomainKey-Signature: a=rsa-sha1; q=dns; c=nofws; s=s1024; d=rogers.com; h=Received:Message-ID:Date:From:User-Agent:X-Accept-Language:MIME-Version:To:CC:Subject:Content-Type; b=ADvzoc5SKEr04EKo5uW7vB0EFvDscYkwTxbQMJx4AaQBvvn8lWbezKJZOxaifFhun/fy6E1gM1l6NCzkr+knz8+GrzVxAt+gMwBxskdPrWK++O7mq6vQv/5LTts4CmPQykw6Ht8flxoxsGKv4r8K+GxiD6gMN+WOkKdGM8u2JIs= ; Received: from unknown (HELO ?24.42.138.7?) (rnakka@rogers.com@24.42.138.7 with plain) by smtp101.rog.mail.re2.yahoo.com with SMTP; 13 Nov 2005 20:02:28 -0000 Message-ID: <43779BD4.2060100@rogers.com> Date: Sun, 13 Nov 2005 15:02:28 -0500 From: Rich Nakka User-Agent: Mozilla/5.0 (Windows; U; Windows NT 5.1; en-US; rv:1.7.2) Gecko/20040804 Netscape/7.2 (ax) X-Accept-Language: en-us, en MIME-Version: 1.0 To: Propellant Development Team Content-Type: multipart/alternative; boundary="------------060201020900060209080606" cc: Antoon Vyverman cc: william colburn Subject: [SS-Propellant] Launch of the Propellant Development phase of SS2S X-BeenThere: ss-propellant@exrocketry.net X-Mailman-Version: 2.1.1 Precedence: list List-Id: List-Unsubscribe: , List-Archive: List-Post: List-Help: List-Subscribe: , X-List-Received-Date: Sun, 13 Nov 2005 19:57:25 -0000 This is a multi-part message in MIME format. --------------060201020900060209080606 Content-Type: text/plain; charset=ISO-8859-1; format=flowed Content-Transfer-Encoding: 8bit Welcome to the SS2S Propellant Development Team (PDT) e-mail discussion group...! <> Team members: <>* Richard Nakka * Randy Dormans * Matthew McFarland * Chris Richards * José Miraglia (please confirm whether or not you received the earlier test message) * Vlad Mateica * Antoon Vyverman (Antoon, have you signed up to the list? I am cc'ing you for now) <> --- What is on our agenda? <> First, the big news is that test firing of the ¼ scale motor (BEM) will be taking place soon, tentatively at the beginning of December. With sorbitol based propellant (KNSB) being used, it can be expected that the motor thrust curve will experience the odd behaviour that has been seen in the past with KNSB motor. That is, the "triangular" thrust curve, rather than the predicted "flat" curve that BATES should provide. <> For those of you not familiar with this phenomenon (which I'll refer to as "flushing" coined by, C.Knight ), I recommend reading the test report of the Kappa-SB motor: http://members.aol.com/kappadx/ksb002.html#Analysis Note that the use of primer coating and pyrogen ignition does not eliminate this behaviour. <>Also check out C.Knight's hypothesized explanation for this phenom: http://www.nakka-rocketry.net/knsbchar.html <> Tony Vyverman has written an excellent article that also hyhpothesises certain causes such as partially-delayed igntion: http://sugarshot.org/downloads/evaluation_of_kno3.pdf <>It is important that we avoid this type of behaviour for the SS2S motor, for two important reasons: 1) We need full thrust off the pad to get the rocket stable quickly to avoid any deviation from the desired flight path. 2) The low average chamber pressure resulting from a "triangular" thrust significantly cuts into the delivered specific impulse, which we cannot afford. The sims for the flight are based on an average 130 sec. Isp. <>Suggestions are needed on how we can modify the KNSB propellant, or the motor design to achieve this goal. <> Miraglia has suggested the use of a sorbitol/sucrose (SB/SU) mixture. This is an interesting option. Although this may not eliminate the flushing problem (see Tony's report) it may nevertheless help, or such a formulation could provide other advantages. For example, sucrose has a greater density, which means more propellant mass for a given motor volume. A 1 or 2 % performance gain might be realized, based on my calcs. <> My own feeling of late is that flushing might be a result of the grain segments being too close together, causing a sort of self-extinquishing. Perhaps we can do static testing to see if greater spacing helps. Also consider instead of flat faces on segments, have end surfaces sloped (shallow cone). A really interesting suggestion put forth by Tony is the use of KNSU on segment ends. This would also boost thrust off the pad, due to KNSU's greater burn rate. Instead of KNSU, perhaps KNSB doped with Iron oxide ? Thoughts? <> Additives such as carbon or iron oxide to act as opacifier can also be considered/tested. <> Erosive burning behaviour of KNSB should be investigated. Perhaps someone can come up with a test proposal. Consider small modifications to the formulation to improve Isp (e.g. 66/34 instead of 65/35)? GUIPEP runs can be done to get an idea if this is worthwhile. Runs can also be done on KN/SB/SU formulations. <>If the propellant formulation is changed in any way, testing will need to be performed to characterize burnrate & c-star, as well as other qualities such as hygroscopicity and safety with regard to overheating during casting. <> Much of the testing can be done using small, scaled down motors. Vlad has volunteered to do some static testing. Randy, could you do some testing as well? I can do propellant characterization tests, such as strand burner. I may also be able to do limited static testing, say, with the A-100M motor. <>The next major SS2S motor test will be the "short-stack" motor. Before this, we need to come up with a means of casting large propellant grains. The short-stack is slated to have 2 segments, each with a mass of about 34 kg (75 lbs), which is identical to the full-size motor. Also, curing the grains under pressure to ensure positive bonding to the casting tube will need to be investigated and testing done. <>So there is no shortage of work for the PDT, and no shortage of ideas that need to be put forth. And please respond to the ss-propellant list, not to me personally, to keep this a group project. Richard Nakka --------------060201020900060209080606 Content-Type: text/html; charset=us-ascii Content-Transfer-Encoding: 7bit Welcome to the SS2S Propellant Development Team (PDT) e-mail discussion group…! <>

Team members:
<>* Richard Nakka
* Randy Dormans
* Matthew McFarland
* Chris Richards
* José Miraglia (please confirm whether or not you received the earlier test message)
* Vlad Mateica
* Antoon Vyverman (Antoon, have you signed up to the list? I am cc’ing you for now) <>
---
What is on our agenda? <>

First, the big news is that test firing of the ¼ scale motor (BEM) will be taking place soon, tentatively at the beginning of December. With sorbitol based propellant (KNSB) being used, it can be expected that the motor thrust curve will experience the odd behaviour that has been seen in the past with KNSB motor. That is, the “triangular” thrust curve, rather than the predicted “flat” curve that BATES should provide. <>

For those of you not familiar with this phenomenon (which I’ll refer to as “flushing” coined by, C.Knight ), I recommend reading the test report of the Kappa-SB motor:
http://members.aol.com/kappadx/ksb002.html#Analysis

Note that the use of primer coating and pyrogen ignition does not eliminate this behaviour.

<>Also check out C.Knight’s hypothesized explanation for this phenom:
http://www.nakka-rocketry.net/knsbchar.html <>

Tony Vyverman has written an excellent article that also hyhpothesises certain causes such as partially-delayed igntion:
http://sugarshot.org/downloads/evaluation_of_kno3.pdf <>It is important that we avoid this type of behaviour for the SS2S motor, for two important reasons:

1) We need full thrust off the pad to get the rocket stable quickly to avoid any deviation from the desired flight path.

2) The low average chamber pressure resulting from a “triangular” thrust significantly cuts into the delivered specific impulse, which we cannot afford. The sims for the flight are based on an average 130 sec. Isp.

<>Suggestions are needed on how we can modify the KNSB propellant, or the motor design to achieve this goal. <>

Miraglia has suggested the use of a sorbitol/sucrose (SB/SU) mixture. This is an interesting option. Although this may not eliminate the flushing problem (see Tony’s report) it may nevertheless help, or such a formulation could provide other advantages. For example, sucrose has a greater density, which means more propellant mass for a given motor volume. A 1 or 2 % performance gain might be realized, based on my calcs. <>

My own feeling of late is that flushing might be a result of the grain segments being too close together, causing a sort of self-extinquishing. Perhaps we can do static testing to see if greater spacing helps. Also consider instead of flat faces on segments, have end surfaces sloped (shallow cone). A really interesting suggestion put forth by Tony is the use of KNSU on segment ends. This would also boost thrust off the pad, due to KNSU’s greater burn rate. Instead of KNSU, perhaps KNSB doped with Iron oxide ? Thoughts? <>

Additives such as carbon or iron oxide to act as opacifier can also be considered/tested. <>

Erosive burning behaviour of KNSB should be investigated. Perhaps someone can come up with a test proposal.

Consider small modifications to the formulation to improve Isp (e.g. 66/34 instead of 65/35)? GUIPEP runs can be done to get an idea if this is worthwhile. Runs can also be done on KN/SB/SU formulations.

<>If the propellant formulation is changed in any way, testing will need to be performed to characterize burnrate & c-star, as well as other qualities such as hygroscopicity and safety with regard to overheating during casting. <>

Much of the testing can be done using small, scaled down motors. Vlad has volunteered to do some static testing. Randy, could you do some testing as well? I can do propellant characterization tests, such as strand burner. I may also be able to do limited static testing, say, with the A-100M motor.

<>The next major SS2S motor test will be the “short-stack” motor. Before this, we need to come up with a means of casting large propellant grains. The short-stack is slated to have 2 segments, each with a mass of about 34 kg (75 lbs), which is identical to the full-size motor. Also, curing the grains under pressure to ensure positive bonding to the casting tube will need to be investigated and testing done. <>So there is no shortage of work for the PDT, and no shortage of ideas that need to be put forth.

And please respond to the ss-propellant list, not to me personally, to keep this a group project.

Richard Nakka

--------------060201020900060209080606-- From richnakka@rogers.com Sun Nov 13 12:48:06 2005 Received: from smtp103.rog.mail.re2.yahoo.com (smtp103.rog.mail.re2.yahoo.com [206.190.36.81]) by mail.exrocketry.net (8.12.8/8.12.8) with SMTP id jADKm6Jr029021 for ; Sun, 13 Nov 2005 12:48:06 -0800 Received: (qmail 64507 invoked from network); 13 Nov 2005 20:53:10 -0000 DomainKey-Signature: a=rsa-sha1; q=dns; c=nofws; s=s1024; d=rogers.com; h=Received:Message-ID:Date:From:User-Agent:X-Accept-Language:MIME-Version:To:CC:Subject:Content-Type; b=jp7IvX6iy7zzSl1CQMCuoEyBhw+/ZXUQBh+70T9t3K/+DkLrjgnjX4hm0xtaxf9Y0jN5+s1F4Ngsb5acQJcmtXF0V0TBsVQiyrsZFg/F4bVM2KyBEnPZBm/YrlLIJpxbJlM2Lt1VopWWz1929pANwQbJ5Nwz6aKraeOUnp06/ho= ; Received: from unknown (HELO ?24.42.138.7?) (rnakka@rogers.com@24.42.138.7 with plain) by smtp103.rog.mail.re2.yahoo.com with SMTP; 13 Nov 2005 20:53:10 -0000 Message-ID: <4377A7B6.3080006@rogers.com> Date: Sun, 13 Nov 2005 15:53:10 -0500 From: Rich Nakka User-Agent: Mozilla/5.0 (Windows; U; Windows NT 5.1; en-US; rv:1.7.2) Gecko/20040804 Netscape/7.2 (ax) X-Accept-Language: en-us, en MIME-Version: 1.0 To: Propellant Development Team , Antoon Vyverman , "miragli@terra.com.br" Content-Type: multipart/mixed; boundary="------------090600000205030505010100" cc: william colburn Subject: [SS-Propellant] sugar densities X-BeenThere: ss-propellant@exrocketry.net X-Mailman-Version: 2.1.1 Precedence: list List-Id: List-Unsubscribe: , List-Archive: List-Post: List-Help: List-Subscribe: , X-List-Received-Date: Sun, 13 Nov 2005 20:48:06 -0000 This is a multi-part message in MIME format. --------------090600000205030505010100 Content-Type: multipart/alternative; boundary="------------000900000906010007000701" --------------000900000906010007000701 Content-Type: text/plain; charset=us-ascii; format=flowed Content-Transfer-Encoding: 7bit Gents, For reference, I've attached a gif that shows the mass densities of the different sugars. Richard --------------000900000906010007000701 Content-Type: text/html; charset=us-ascii Content-Transfer-Encoding: 7bit Gents,

For reference, I've attached a gif that shows the mass densities of the different sugars.

Richard --------------000900000906010007000701-- --------------090600000205030505010100 Content-Type: image/gif; name="sugardensities.gif" Content-Transfer-Encoding: base64 Content-Disposition: inline; filename="sugardensities.gif" R0lGODlh5wBHALMAAAAAhP8AAP9KSv9jY/97c/+MhP+gmP+1rf+9tf/Gvf/Oxv/Wzv/e1v/n 3v/v5///9ywAAAAA5wBHAAAE/vDJSau9OOvNu/9gKI4SYJJoqq5s675wLM90bd94ru987//A oHA4MRmJFoMgEDA0JMxJFPkAYIyn6pFiDXWplW8J/DAEGI9FYAANSN3IrEVc5RbpHTyYrg9O K39/QlZ9fHZ1fRmJcVdFd1+EJXJaYlsdA2toFIFwjHOfjqFXkWOSlZM+lqV1rKxZkKtdsB0K TAEFmg+cexdYkKqtoHKyobODxsRhosmHwRsMBLYKbW+8oGOVzdfMeItA3KvLy8NYIQyYAtTq nhqk4YmzxqJBhq3M4uGl3hxTmFJsVPa5Cwav2Lx8P+rFMxiroT0PmBY8qGVAAoIACB4kCHDA mjJH/tkOHjoR0pXIHb64WFqp8pTLDw3MBBBQccKBJQI6erS3Etgiks5UASNDtCg9o0iTFpWn tKnTVKieSp1KtarVq1izat3KtatXEimT2loj8QGDAAQmRMs1pFA5Sr+ibtjXo6QHui6mmHlS JkACjU0CFvqITRsHvCgJ59kx5WzNBwIEOIgc0NlBb4gRJ27GEtsrV5OEysUQCCBgJn93isQ8 6qGplnU/InOtxeFChKQ7CYqWloyesITk/pbE0CTuGgrFzba9zcMutWiJDgfJdLC+1d9kv32H j2fc0RYCpZOwEbXvwwQNc3aoXkfyT8tpF/8wRc3jyJPHV56b/jhzhJrB/lDSbPHdZpxluUmw l4J+AfYYEdMVNl8vxA3IXg5hPYLPZxp2+JpzthBQ1lm9PbDWfrH09EqGYUTCR2jgfSUjijPW WBVTNubo1FA69ujjj0AGKeSQRBZpZAwstnONkh4owYQTbYTIFzuNmPKdF0/Vw1+VXG5gBhpq ANTYGoK1c89AmgWYXXtLKtZmBoJUs84gCN7BnV1b7qjIMIjU5llcJ12AyQBs6QLHWTpRqcyZ /c3hDqAetoVKPLIkA851tNiCyxshOqCaHVfyRKGfB15a5n+umXrPM9EwMY2h5EVH40jcUYKg gd0odelyqvqHwTkzrRMnnaMy6iaquaq264bs/q0KorCdQNhLSnjeWlyysy77H68QBSARReqA O6swoAZaaaOmHiMaMp2RgyMGMTFBE6dPnoedlZE62ids+R7pLwpq/iswlr4ObHAKPB6s8MIM N+zwwxBHLNh2RY01hcUFeDouvhzDRbC9KgQswrD1BRZHhPtKWPCx0q4gcggk6xbtUSjfyeao 0lH4aIcq8vvhs4DI/Kll2VRb4Tgv1bUdh6U2iyx9M8Pq4NDBMWr0uZg2zUOEBnbn7Lu5jRUl EwWArBJI5Z6E65ubEda10z8nqUHMZsm6cdFp47Y2y+7h/DZtyQZM9wMXJdqyYmg2up58KyPn 97Vw793B4JAFoPHhSdokfvXRzDYuIM4exw3pz7ZCHV4nF5VNZaiht67vQKWTLvHCL88uMNi2 z57ww7707vvvwAcv/PDEF2987QYjHzYTyvtgcfMiRAAAOw== --------------090600000205030505010100-- From d3xt3rjr@yahoo.com Sun Nov 13 13:26:51 2005 Received: from web31901.mail.mud.yahoo.com (web31901.mail.mud.yahoo.com [68.142.207.81]) by mail.exrocketry.net (8.12.8/8.12.8) with SMTP id jADLQoJr029115 for ; Sun, 13 Nov 2005 13:26:50 -0800 Received: (qmail 13289 invoked by uid 60001); 13 Nov 2005 21:31:55 -0000 DomainKey-Signature: a=rsa-sha1; q=dns; c=nofws; s=s1024; d=yahoo.com; h=Message-ID:Received:Date:From:Subject:To:In-Reply-To:MIME-Version:Content-Type:Content-Transfer-Encoding; b=X8f/xygarYb3/mQzwOEZivAzpNmaN3DWYzrpb5xYvfi157PmjF/kcy/InT5bnq48k75guuEq/q0bgDLAAtDxih7fUrIPnoDCRsYcfX4mozrcUzdVzObBJH+xvxEzlN0t/JZJiCIwA+S+WaBvf9CoR3dDUbR58bGKONXtkAZVnoo= ; Message-ID: <20051113213155.13287.qmail@web31901.mail.mud.yahoo.com> Received: from [194.102.145.85] by web31901.mail.mud.yahoo.com via HTTP; Sun, 13 Nov 2005 13:31:55 PST Date: Sun, 13 Nov 2005 13:31:55 -0800 (PST) From: Mateica Vlad Subject: Re: [SS-Propellant] Launch of the Propellant Development phase of SS2S To: SS-Propellant@exrocketry.net In-Reply-To: <43779BD4.2060100@rogers.com> MIME-Version: 1.0 Content-Type: multipart/alternative; boundary="0-794162506-1131917515=:12561" Content-Transfer-Encoding: 8bit X-BeenThere: ss-propellant@exrocketry.net X-Mailman-Version: 2.1.1 Precedence: list List-Id: List-Unsubscribe: , List-Archive: List-Post: List-Help: List-Subscribe: , X-List-Received-Date: Sun, 13 Nov 2005 21:26:51 -0000 --0-794162506-1131917515=:12561 Content-Type: text/plain; charset=iso-8859-1 Content-Transfer-Encoding: 8bit Rich Nakka wrote:Welcome to the SS2S Propellant Development Team (PDT) e-mail discussion group…! <> Team members: <>* Richard Nakka * Randy Dormans * Matthew McFarland * Chris Richards * José Miraglia (please confirm whether or not you received the earlier test message) * Vlad Mateica * Antoon Vyverman (Antoon, have you signed up to the list? I am cc’ing you for now) <> --- What is on our agenda? <> First, the big news is that test firing of the ¼ scale motor (BEM) will be taking place soon, tentatively at the beginning of December. With sorbitol based propellant (KNSB) being used, it can be expected that the motor thrust curve will experience the odd behaviour that has been seen in the past with KNSB motor. That is, the “triangular” thrust curve, rather than the predicted “flat” curve that BATES should provide. <> For those of you not familiar with this phenomenon (which I’ll refer to as “flushing” coined by, C.Knight ), I recommend reading the test report of the Kappa-SB motor: http://members.aol.com/kappadx/ksb002.html#Analysis Note that the use of primer coating and pyrogen ignition does not eliminate this behaviour. <>Also check out C.Knight’s hypothesized explanation for this phenom: http://www.nakka-rocketry.net/knsbchar.html <> Tony Vyverman has written an excellent article that also hyhpothesises certain causes such as partially-delayed igntion: http://sugarshot.org/downloads/evaluation_of_kno3.pdf <>It is important that we avoid this type of behaviour for the SS2S motor, for two important reasons: 1) We need full thrust off the pad to get the rocket stable quickly to avoid any deviation from the desired flight path. 2) The low average chamber pressure resulting from a “triangular” thrust significantly cuts into the delivered specific impulse, which we cannot afford. The sims for the flight are based on an average 130 sec. Isp. <>Suggestions are needed on how we can modify the KNSB propellant, or the motor design to achieve this goal. <> Miraglia has suggested the use of a sorbitol/sucrose (SB/SU) mixture. This is an interesting option. Although this may not eliminate the flushing problem (see Tony’s report) it may nevertheless help, or such a formulation could provide other advantages. For example, sucrose has a greater density, which means more propellant mass for a given motor volume. A 1 or 2 % performance gain might be realized, based on my calcs. <> My own feeling of late is that flushing might be a result of the grain segments being too close together, causing a sort of self-extinquishing. Perhaps we can do static testing to see if greater spacing helps. Also consider instead of flat faces on segments, have end surfaces sloped (shallow cone). A really interesting suggestion put forth by Tony is the use of KNSU on segment ends. This would also boost thrust off the pad, due to KNSU’s greater burn rate. Instead of KNSU, perhaps KNSB doped with Iron oxide ? Thoughts? <> Additives such as carbon or iron oxide to act as opacifier can also be considered/tested. <> Erosive burning behaviour of KNSB should be investigated. Perhaps someone can come up with a test proposal. Consider small modifications to the formulation to improve Isp (e.g. 66/34 instead of 65/35)? GUIPEP runs can be done to get an idea if this is worthwhile. Runs can also be done on KN/SB/SU formulations. <>If the propellant formulation is changed in any way, testing will need to be performed to characterize burnrate & c-star, as well as other qualities such as hygroscopicity and safety with regard to overheating during casting. <> Much of the testing can be done using small, scaled down motors. Vlad has volunteered to do some static testing. Randy, could you do some testing as well? I can do propellant characterization tests, such as strand burner. I may also be able to do limited static testing, say, with the A-100M motor. <>The next major SS2S motor test will be the “short-stack” motor. Before this, we need to come up with a means of casting large propellant grains. The short-stack is slated to have 2 segments, each with a mass of about 34 kg (75 lbs), which is identical to the full-size motor. Also, curing the grains under pressure to ensure positive bonding to the casting tube will need to be investigated and testing done. <>So there is no shortage of work for the PDT, and no shortage of ideas that need to be put forth. And please respond to the ss-propellant list, not to me personally, to keep this a group project. Richard Nakka _______________________________________________ SS-Propellant mailing list SS-Propellant@exrocketry.net http://www.exrocketry.net/mailman/listinfo/ss-propellant Hi! I will make some static testing with the A-100 motor as soon as I will get my test stand operational and put my hands on some sorbitol(I should receive about 800grams). Richard told me that the SB/SU mixture when is moltem it becomes like water witch is a verry good thing. I hope that when the KNO3 is added the mixturewill still be fluyd enough to cast it into the molds. We could make a multiple grain configuration to the bates. We could make the first bates with a star shape grain to have a maximum burning area, and we could make the ends conical. After that we could use the normal round grain. I made some simulation in GUIPEP and have some good results with a combination of 65grams KNO3+ 22,75 grams sugar+12,25grams sorbitol I ended up with impuls of about 164(the highest of all) Vlad Draco Dormiens Nunquam Titillandus --------------------------------- Yahoo! FareChase - Search multiple travel sites in one click. --0-794162506-1131917515=:12561 Content-Type: text/html; charset=iso-8859-1 Content-Transfer-Encoding: 8bit

Rich Nakka <richnakka@rogers.com> wrote:

Welcome to the SS2S Propellant Development Team (PDT) e-mail discussion group…! <>

Team members:
<>* Richard Nakka
* Randy Dormans
* Matthew McFarland
* Chris Richards
* José Miraglia (please confirm whether or not you received the earlier test message)
* Vlad Mateica
* Antoon Vyverman (Antoon, have you signed up to the list? I am cc’ing you for now) <>
---
What is on our agenda? <>

First, the big news is that test firing of the ¼ scale motor (BEM) will be taking place soon, tentatively at the beginning of December. With sorbitol based propellant (KNSB) being used, it can be expected that the motor thrust curve will experience the odd behaviour that has been seen in the past with KNSB motor. That is, the “triangular” thrust curve, rather than the predicted “flat” curve that BATES should provide. <>

For those of you not familiar with this phenomenon (which I’ll refer to as “flushing” coined by, C.Knight ), I recommend reading the test report of the Kappa-SB motor:
http://members.aol.com/kappadx/ksb002.html#Analysis

Note that the use of primer coating and pyrogen ignition does not eliminate this behaviour.
<>Also check out C.Knight’s hypothesized explanation for this phenom:
http://www.nakka-rocketry.net/knsbchar.html <>

Tony Vyverman has written an excellent article that also hyhpothesises certain causes such as partially-delayed igntion:
http://sugarshot.org/downloads/evaluation_of_kno3.pdf <>It is important that we avoid this type of behaviour for the SS2S motor, for two important reasons:
1) We need full thrust off the pad to get the rocket stable quickly to avoid any deviation from the desired flight path.

2) The low average chamber pressure resulting from a “triangular” thrust significantly cuts into the delivered specific impulse, which we cannot afford. The sims for the flight are based on an average 130 sec. Isp.
<>Suggestions are needed on how we can modify the KNSB propellant, or the motor design to achieve this goal. <>

Miraglia has suggested the use of a sorbitol/sucrose (SB/SU) mixture. This is an interesting option. Although this may not eliminate the flushing problem (see Tony’s report) it may nevertheless help, or such a formulation could provide other advantages. For example, sucrose has a greater density, which means more propellant mass for a given motor volume. A 1 or 2 % performance gain might be realized, based on my calcs. <>

My own feeling of late is that flushing might be a result of the grain segments being too close together, causing a sort of self-extinquishing. Perhaps we can do static testing to see if greater spacing helps. Also consider instead of flat faces on segments, have end surfaces sloped (shallow cone). A really interesting suggestion put forth by Tony is the use of KNSU on segment ends. This would also boost thrust off the pad, due to KNSU’s greater burn rate. Instead of KNSU, perhaps KNSB doped with Iron oxide ? Thoughts? <>

Additives such as carbon or iron oxide to act as opacifier can also be considered/tested. <>

Erosive burning behaviour of KNSB should be investigated. Perhaps someone can come up with a test proposal.
Consider small modifications to the formulation to improve Isp (e.g. 66/34 instead of 65/35)? GUIPEP runs can be done to get an idea if this is worthwhile. Runs can also be done on KN/SB/SU formulations.
<>If the propellant formulation is changed in any way, testing will need to be performed to characterize burnrate & c-star, as well as other qualities such as hygroscopicity and safety with regard to overheating during casting. <>

Much of the testing can be done using small, scaled down motors. Vlad has volunteered to do some static testing. Randy, could you do some testing as well? I can do propellant characterization tests, such as strand burner. I may also be able to do limited static testing, say, with the A-100M motor.

<>The next major SS2S motor test will be the “short-stack” motor. Before this, we need to come up with a means of casting large propellant grains. The short-stack is slated to have 2 segments, each with a mass of about 34 kg (75 lbs), which is identical to the full-size motor. Also, curing the grains under pressure to ensure positive bonding to the casting tube will need to be investigated and testing done. <>So there is no shortage of work for the PDT, and no shortage of ideas that need to be put forth.
And please respond to the ss-propellant list, not to me personally, to keep this a group project.

Richard Nakka

_______________________________________________
SS-Propellant mailing list
SS-Propellant@exrocketry.net
http://www.exrocketry.net/mailman/listinfo/ss-propellant

Hi!

I will make some static testing with the A-100 motor as soon as I will get my test stand operational and put my hands on some sorbitol(I should receive about 800grams). Richard told me that the SB/SU mixture when is moltem it becomes like water witch is a verry good thing. I hope that when the KNO3 is added the mixturewill still be fluyd enough to cast it into the molds. We could make a multiple grain configuration to the bates. We could make the first bates with a star shape grain to have a maximum burning area, and we could make the ends conical. After that we could use the normal round grain.

I made some simulation in GUIPEP and have some good results with a combination of 65grams KNO3+ 22,75 grams sugar+12,25grams sorbitol I ended up with impuls of about 164(the highest of all)

Vlad

Draco Dormiens Nunquam Titillandus

Yahoo! FareChase - Search multiple travel sites in one click. --0-794162506-1131917515=:12561-- From dormans@comcast.net Sun Nov 13 14:33:34 2005 Received: from rwcrmhc12.comcast.net (rwcrmhc13.comcast.net [204.127.198.39]) by mail.exrocketry.net (8.12.8/8.12.8) with ESMTP id jADMXXJr029307 for ; Sun, 13 Nov 2005 14:33:33 -0800 Message-Id: <200511132233.jADMXXJr029307@mail.exrocketry.net> Received: from maincomputer (c-66-229-210-125.hsd1.ca.comcast.net[66.229.210.125]) by comcast.net (rwcrmhc13) with SMTP id <200511132238330150037fgje>; Sun, 13 Nov 2005 22:38:34 +0000 From: "dormans" To: Subject: Re: [SS-Propellant] Launch of the Propellant Development phase ofSS2S Date: Sun, 13 Nov 2005 14:38:36 -0800 MIME-Version: 1.0 Content-Type: multipart/mixed; boundary="----=_NextPart_000_000F_01C5E85F.EE3A1C10" X-Mailer: Microsoft Office Outlook, Build 11.0.5510 X-MimeOLE: Produced By Microsoft MimeOLE V6.00.2900.2180 Thread-Index: AcXoovwOIiPnJpKzQJK52CCXKMfahw== X-BeenThere: ss-propellant@exrocketry.net X-Mailman-Version: 2.1.1 Precedence: list List-Id: List-Unsubscribe: , List-Archive: List-Post: List-Help: List-Subscribe: , X-List-Received-Date: Sun, 13 Nov 2005 22:33:34 -0000 This is a multi-part message in MIME format. ------=_NextPart_000_000F_01C5E85F.EE3A1C10 Content-Type: multipart/alternative; boundary="----=_NextPart_001_0010_01C5E85F.EE3A1C10" ------=_NextPart_001_0010_01C5E85F.EE3A1C10 Content-Type: text/plain; charset="us-ascii" Content-Transfer-Encoding: 7bit Hi all, It sounds like we have a lot of work/fun ahead of us. I think that a mix of SB/SU as Miraglia has suggested, or KN/SU applied only to the ends of the grain to as Tony suggests are definitely worth investigation. I used to use a 50/50 mix of SB/SU mainly as a means of reducing the cost of the Sorbitol. I always thought of it as a performing like Dextrose. Unfortunately I wasn't doing a lot of static testing at the time, but in the static testing that I did the SB/SU mix produced a thrust curve that closely matched the predicted. I suspect that a ratio with more Sorbitol and less Sucrose would give similar results. The motor tested in the attached gif was an unrestricted J-class motor; propellant was 60/40 OX/fuel and 50/50 SB/SU and gave a healthy isp of 122. The thrust curve for NEAR's first firing of the Phenix motor was fairly triangular , but the thrust curve from the 2nd firing was much closer to the predicted (not nearly as triangular). Does any one know what the difference was between the two tests? I can't find the report on their site, but I think that I have a printed copy some where. I read that many commercial/military motors use an oxidizer having a mixture of particle sizes (multi-modal mixtures) as opposed to uni-modal mixtures mostly as a means to lower the viscosity thereby making the propellant easier to process. Something I think we should look into to help with the large grains. I would be happy to do some testing also; Peter and I will hopefully, in addition to the BEM, also be firing a 4inch diameter N-class Sorbitol motor soon. Randy Dormans ------=_NextPart_001_0010_01C5E85F.EE3A1C10 Content-Type: text/html; charset="us-ascii" Content-Transfer-Encoding: quoted-printable

Hi all,

It sounds like we have a lot of work/fun ahead of = us. I think that a mix of SB/SU as Miraglia has suggested, or KN/SU applied only to = the ends of the grain to as Tony suggests are definitely worth investigation. = I used to use a 50/50 mix of SB/SU mainly as a means of reducing the cost of = the Sorbitol. I always thought of it as a performing like = Dextrose. Unfortunately I wasn’t doing a lot of static testing at the time, = but in the static testing that I did the SB/SU mix produced a thrust curve that = closely matched the predicted. I suspect that a ratio with more Sorbitol = and less Sucrose would give similar results. The motor tested in the = attached gif was an unrestricted J-class motor; propellant was 60/40 OX/fuel and = 50/50 SB/SU and gave a healthy isp of 122.

The thrust curve for NEAR’s first firing of the Phenix = motor was fairly triangular , but the thrust curve from the 2^nd firing = was much closer to the predicted (not nearly as triangular). Does any = one know what the difference was between the two tests? I can’t = find the report on their site, but I think that I have a printed copy some = where.

I read that many commercial/military motors use an oxidizer = having a mixture of particle sizes (multi-modal mixtures) as opposed to = uni-modal mixtures mostly as a means to lower the viscosity thereby making the = propellant easier to process. Something I think we should look into to help = with the large grains.

I would be happy to do some testing also; Peter and I will = hopefully, in addition to the BEM, also be firing a 4inch diameter N-class Sorbitol = motor soon.

Randy Dormans

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