
SRM.XLS SRM is an MS EXCEL spreadsheet that takes userinputted motor and grain geometry data and computes Kn over the duration of the motor burn, generates a pressuretime curve, a thrusttime curve, as well as performance parameters such as total impulse and delivered specific impulse. Motor performance data is also summarized for easy input into a trajectory simulation software, such as SOAR. Although primarily intended for designing motors using KNDextrose or KNSorbitol propellant, other propellants may be specified with user inputted propellant properties. Solely for cylindrical grain configurations, such as BATES. Written by R.A. Nakka. SRM_2023 is a newly released version that fixes an incorrect isentropic exponent value and introduces two additional propellants, KNFR (potassium nitrate/fructose) and KNPSB (potassium nitrate/potassium perchorate/sorbitol). SRM_2023.ZIP 803 kbytes Zipped EXCEL 2000 spreadsheet Freeware SRM TIP SHEET Rev.20201221 178 kbytes PDF document SRM_2023_chs.ZIP 761 kbytes Zipped EXCEL 2000 spreadsheet Chinese language version of SRM_2023, translated by Yang Yifan. Freeware SRM_2014_RU.ZIP 1.604 Mbytes Zipped EXCEL 2000 spreadsheet Russian language version of SRM_2014, translated by Vadim Zaharchenko. Freeware SRM_2014_BG.RAR 485 kbytes Zipped EXCEL 2000 spreadsheet Bulgarian language version of SRM_2014, translated by George Andonov. Freeware SRM 1.3.ZIP Version: 1.3 536 kbytes Zipped EXCEL 2000 spreadsheet Freeware Mar.23/23 SRM_RU.ZIP Russian Language Version 1.08 Mbytes Zipped EXCEL 97/2000 SRMCASTELLANO.ZIP Spanish Language Version, translated by Guillermo O. Descalzo 550 kbytes Zipped EXCEL SRM_2014_Po Portuguese Language Version, translated by Phoenix Rocket Tech Team of University of Caxias do Sul (UCS) 930 kbytes EXCEL XLSM file SRM_2014.1_fr .xlsm French Language Version of SRM_2014 893 kbytesTranslated by Jérôme Fouque. METEOR A freetouse online application, METEOR is a convenient, validated tool for designing rocket motors. Includes some useful additional features not currently implemented in SRM.XLS METEOR: DESIGN YOUR SOLID ROCKET MOTOR Written by Jordan Content and Jérôme Bise of Lyon, France.
CASING.XLS This is an MS EXCEL spreadsheet that is used to determine the Design Pressure and Burst Pressure of a solid rocket motor casing. Also determines the elastic deformation of the casing under pressure (important for casebonding consideration). Strength and mechanical properties are supplied for many casing materials such as steels, aluminum alloys, PVC, etc. Written by Richard Nakka. CASING.XLS Version 1.03 61kbytes EXCEL 5.0 spreadsheet Freeware CASING_BG.XLS 70kbytes EXCEL spreadsheet Bulgarian language version of CASING translated by George Andonov. CASING_FR.XLS 74kbytes EXCEL spreadsheet French language version of CASING translated by Jérôme Fouque IGNITER.XLS This is an MS EXCEL spreadsheet that may be used to estimate the chamber pressure that occurs in a rocket motor due to combustion of a pyrotechnic igniter. Use of a properly sized pyro igniter is important for efficient rocket motor design. The motor should reach full operating pressure rapidly without wasting propellant (and thereby reducing Isp). As well, it is important to avoid overpressurization. Although tailored for black powder igniters, this spreadsheet may be used for other pyrotechnic mixtures, as well. The latest version of this spreadsheet (v1.1) also computes parachute ejection charge force. Written by Richard Nakka. IGNITER.XLS Version 1.1 74kbytes EXCEL 2000 spreadsheet Freeware IGNITER_BG.XLS 47kbytes EXCEL spreadsheet Bulgarian language version of IGNITER translated by George Andonov. Freeware IGNITER_FR.XLSX 68kbytes EXCEL spreadsheet French language version of IGNITER translated by Jérôme Fouque. CONVERT Windows software that converts units for Force, Pressure, Density, Area, Distance, Volume and several other measures. Very convenient and simple to use, highly recommended. Written by Joshua F. Madison. www.joshmadison.com/soft , or download it here: CONVERT.ZIP Version 4.08 168 kbytes Zipped file Freeware EzImpulse This Excel spreadsheet is meant to serve as a design aid for amateur/experimental/model rockets. A simple, easy to use spreadsheet that determines the total impulse of a motor that is required to achieve an altitude goal. Metric units. Written by Richard Nakka.
EzImpulse_v1.01.xlsm Version 1.01 40kbytes Excel macroenabled spreadsheet Freeware Screencapture of EzImpulse showing INPUT DATA and RESULTS EzImpulse_v1.0_fr.xlsm 39kbytes EXCEL spreadsheet French language version of EzImpulse translated by Jérôme Fouque EzRocket This Excel spreadsheet is intended as an easytouse design aid for hobby rocketry. Unlike most rocket simulation programs, which predict peak altitude for a given rocket and motor combination, this progam instead considers peak altitude as a design goal. Based on this goal, the program computes what size motor is required to reach this peak altitude. Both English and Metric units. Written by Richard Nakka. EzRocket.xls Version Beta 92kbytes EXCEL 97 spreadsheet Freeware EzRocket_BG.RAR 24 kbytes Zipped EXCEL 2000 spreadsheet Bulgarian language version of EzRocket, translated by George Andonov. Freeware EzRocket_fr.xlsx 31 kbytes EXCEL spreadsheet French language version of EzRocket, translated by Jérôme Fouque. EzAlt An easy to use Excel spreadsheet that predicts the peak altitude, maximum velocity, burnout altitude, acceleration and time to peak altitude of an amateur rocket. Intended primarily as a rocket design aid due to its simplicity of use and ease with which variables (such as rocket mass, motor output, drag coefficient, etc.) can be modified, and the effects of such studied. Both English and Metric units. Written by Richard Nakka. EzAlt_1.3.xls Version 1.2 195kbytes EXCEL 97 spreadsheet Freeware EzAlt_BG.RAR 24 kbytes Zipped EXCEL 2000 spreadsheet Bulgarian language version of EzAlt, translated by George Andonov. EzAlt_RU.XLS 92 kbytes EXCEL 2000 spreadsheet Russian language version of EzAlt, translated by Vadim Zaharchenko. EzAlt_1.3_FR.XLSX 46 kbytes EXCEL spreadsheet French language version of EzAlt, translated by Jérôme Fouque. SOAR This program predicts the flight performance of a rocket. It calculates parameters such as altitude, velocity, acceleration, drag force, dynamic pressure, Mach number, and is capable of handling singlestage, multistage and clustered rockets. Meant to be accurate, the program utilizes efficient professional subroutines for numerical differentiation and integration. Also meant to be versatile and user friendly, it can handle supersonic rockets with a flight ceiling to 100,000 feet. as easily as low altitude model rockets with commercial engines. Runs under DOS only. Written by Richard Nakka & B.W. Nakka. SOAR.ZIP 187 k DOS Freeware Data files of Model Rocket Engines, for use with SOAR program. MROCKENG.ZIP 15 k Data files of the KappaDX & KappaSB Rocket Motor, for use with SOAR program. KAPPA.ZIP 2 k Data files of the B200 & C400 Rocket Motors, for use with SOAR program. ENGINE1.ZIP 1 k WHOOSH This program may be of interest to the slightly less adventurous amateur rocketeer  it predicts the performance of a "soda bottle" rocket (aka "water rocket"). A water bottle rocket, by the way, is a rocket made from a plastic soda bottle (eg 2 litre) filled with a mixture of water and compressed air (surprising performance!). Program calculates parameters such as thrust, jet velocity, and pressure, all as a function of time, as well as total impulse and specific impulse. May be used together with SOAR to predicts the flight performance. Source code (FORTRAN) is available upon request. WHOOSH.ZIP 37k MSWORD 6.0 documentation DOS Freeware ROCCAD & Coefficient of Drag and Centre of Pressure Estimation This program predicts the altitude a rocket may fly given the performance parameters of the motor and the physical characteristics of the rocket. The program also determines the optimum weight of a rocket to achieve maximum altitude. Additionally, the program can estimate the coefficient of drag (Cd) and the centre of pressure (Cp) of a rocket, based on the rocket's geometry. Includes performance parameters for the PVC "G", "H", & "I" rocket motors. Runs under DOS only. Written by: Charles D. Knight. ROCCAD.ZIP 169 k DOS Freeware AEROLAB Aerolab is a very useful and easy to use package that estimates Drag, Lift and Center of Pressure for rockets flying at velocities up to Mach 8. It also estimates the rockets Center of Gravity and Moments of Inertia and performs stability analysis within the entire velocity range. Runs under 32 bit Windows. Written by Hans Olaf Toft. AeroLab_2015.zip MS Windows For free distribution 1000 kb BARROWMAN.XLS This Excel spreadsheet allows the user to quickly and easily compute a rocket's Center of Pressure (C.P.) using the wellknown Barrowman method. Written by Richard Nakka. BARROWMAN.XLS Version 1.04 57kbytes EXCEL spreadsheet Freeware Barrowman.xlsx screenshot Altimeter Correction to Account for Launch Site Temperature Commerical rocket altimeters use a Standard Atmosphere algorithm to calculate the peak altitude a rocket achieves in flight. The drawback to this method of calculating altitude is the Standard Atmosphere assumption that the ground level temperature at the launch site is 15^{O} Celsius (59^{O} F.). If the actual launch site temperature is significantly higher or lower, the reported peak altitude can be in error by an appreciable amount. This Excel spreadsheet makes a correction to account for the launch site temperature to provide a truer peak altitude. For more information, visit Altimeter Correction to Account for Launch Site Temperature . Written by Richard Nakka. Barometric_altitude_correction.xlsx (U.S.units)Barometric_altitude_correction_m.xlsx (Metric units) Version 1.0 150kbytes EXCEL spreadsheet Freeware OPENROCKET OpenRocket is a free, fully featured model rocket simulator that allows you to design and simulate your rockets before actually building and flying them. The main features include: •Sixdegreeoffreedom flight simulation •Automatic design optimization •Realtime simulated altitude, velocity and acceleration display •Staging and clustering support •Crossplatform (Javabased) OpenRocket is an Open Source project licensed under the GNU GPL. This means that the software is free to use for whatever purposes, and the source code is also available for studying and extending. Originally written by Sampo Niskanen. openMotor is an opensource internal ballistics simulator for rocket motor experimenters. The software estimates a rocket motor's chamber pressure and thrust based on propellant properties, grain geometry, and nozzle specifications. openMotor is an Open Source project licensed under the GNU GPL. This means that the software is free to use for whatever purposes, and the source code is also available for studying and extending. Originally written by Andrew Reilley. RASAero II RASAero is a combined aerodynamic analysis and flight simulation software package for model rockets, high power rockets, amateur rockets and sounding rockets. I found RASAero to be refreshingly easy to learn how to use. Menus are intuitive and the software provides a nice visual representation of the rocket being designed and good graphics showing the results of flight simulation. Simulation takes into account parameters such as launch angle, wind and parachute deployment, and as such provides results for both vertical and horizontal distance flown by a rocket. Other simulation results include mach number, angle of attack, Cd and Cl, drag force, CG and CP locations, stability margin, flight path angle and rocket attitude, over the full duration of the simulated flight. Results of simulation can be exported to Excel, which is a particularly useful feature. RASAero software is free. Written by Charles E. Rogers and David Cooper. GUIPEP This program provides a user friendly interface to run the PROPEP propellant evaluation program. PROPEP is a program that determines the chemical equilibrium composition for the combustion of a solid or liquid rocket propellant. Additionally, it determines rocket performance parameters such as Isp and C*, and nozzle design parameters. GUIPEPis a musthave program for the rocketry propellant experimentalist. Runs under Windows. Written by Arthur J. Lekstutis, GUIPEP is available for download at Arthur's web site, which also has a link to PROPEP. GUIPEP and PROPEP MS Windows For free distribution
ProPep 3 by Dave Cooper, 2012 MS Windows 7/10 For free distribution
Expanded data file (pepcoded.daf) for the PROPEP program. Includes entries for Dextrose, Sorbitol, Mannitol, Xylitol, Charcoals, Asphalt, Paraffin and others. Solid Rocket Motor Theory  GUIPEP BURNRATESIMPLE This is an MS Excel application that estimates the burn rate coefficients (a,n) of a rocket propellant based on static test chamber pressure measurements. Requires the pressure vs time data from a pair of static test firings, as well as basic propellant properties. This method is intended to provide a simple means of deriving the fundamental burn rate parameters essential for the design of rocket motors utilizing the given propellant. For a full description of the method, visit my Simplified Method to Estimate Burn Rate Parameters web page. Written by Richard Nakka. BURNRATESIMPLE.XLSX 463 kbyte MS Excel 2019 For free distribution THERMCAS A thermal analysis package that determines the temperature distribution through the thickness of a motor casing wall that results from convective heating due to propellant combustion and resulting gas flow. The package consists of DOS executable file which outputs a table of results which may be copied into a companion EXCEL spreadsheet for plotting. In addition, the spreadsheet contains thermal and material properties required as input data, as well as a calculator for determining the required heat transfer convection coefficient. Runs under DOS only. Written by Richard Nakka. THERMCAS.ZIP 112k DOS Freeware Version 1.01 PARAPAT.XLS This MS EXCEL spreadsheet may be used to create a flat pattern for a parachute gore. A gore is an individual panel that, when stitched together with adjacent gores, forms the canopy of a parachute. The user inputs the basic parachute diameter, as well as the number of gores desired (minimum of 4). The spreadsheet creates a table of coordinates as well as a plot of a single gore. When assembled, the parachute canopy is semiellipsoidal in shape (a "flattened" hemisphere). This form of canopy is more efficient than a hemispherical canopy, in that less material is required to provide equal drag. Written by Richard Nakka. PARAPAT_V1.1.XLS Version 1.1 (June 2016) 75kbytes EXCEL 97spreadsheet Freeware PARAPAT_V1.1_BG.XLS 49kbytes EXCEL spreadsheet Bulgarian language version of PARAPAT_V1.1 translated by George Andonov. Freeware PARAPAT_v1.1_fr.XLSX 42kbytes EXCEL spreadsheet French language version of PARAPAT_V1.1 translated by Jérôme Fouque. Parachute Gore DXF Generator This is a handy, easytouse application that generates a parachute gore pattern in DXF file format. DXF is an opensource 2D drawing format. This allows a fullscale gore pattern to be printed using a standard CAD printer. This application plots gore pattern for both elliptical and toroidal parachutes. User can choose number of gores that make up the chute, and can choose either centimetres or inches.
Download from Google Drive 50 Megabytes EXE (executable) file Freeware Parachute Gore DXF Generator screenshot Chutemaker This useful webbased application generates gore/panel cutting patterns for hemispherical (ellipsoidal) and toroidal parachutes. Easy to use, simply enter parachute parameters such as diameter, spill hole size, number of panels...then click "Generate Pattern". User can select output as PDF or SVG (Scalable Vector Graphics).
Website:
https://chutemaker.lfence.de
Written by Thomas Schmid Free to use LOADCELL.XLS A relatively simpletomake beamtype loadcell may be designed by use of this Excel spreadsheet. The user specifies the dimensions of the loadcell body (basically, a rectangular block of metal) and the size of hole to be drilled through the body, in order to achieve the desired load capacity. The only other materials required are one or two strain gages, and suitable adhesive for mounting such. Written by Richard Nakka. LOADCELL.XLS Version 1.10 210 kbytes EXCEL spreadsheet Freeware LoadCell_fr.xlsx 47kbytes EXCEL spreadsheet French language version of LOADCELL translated by Jérôme Fouque. NOZLBORE.XLS The most time consuming step of machining a rocket nozzle is the process of boring out the conical convergent and divergent passages. In particular, the divergent passage, which has a greater bore depth and more shallow angle. This step may be eased significantly by first drilling out these passages using a series of incrementally larger drill bits. The required drill bit sizes range from the throat diameter to the entrance (or exit) diameter of the nozzle. This operation results in a "stepped" profile which may then be bored to the final smooth profile with a standard boring bar tool. This spreadsheet is intended to aid this drilling operation by supplying the required drill depth for each drill bit size. Written by Richard Nakka. NOZLBORE.XLS Version 1.11 375kbytes EXCEL 2000 spreadsheet Freeware NOZLBORE_BG.RAR 308kbytes EXCEL spreadsheet Bulgarian language version of NOZLBORE, translated by George Andonov. Nozlbore_fr.xlsx 311kbytes EXCEL spreadsheet French language version of NOZLBORE, translated by Jérôme Fouque. Stepdrilled divergent passage of A100M nozzle. A boring tool is then used to finish the contour. PFCBURN.XLS This spreadsheet computes the Kn (burningarea to throatarea ratio) for a Pseudofinocyl propellant grain. A Pseudofinocyl grain configuration consists of a cylindrical grain with a circular bore, from which a number of fins extend radially (similar to a stargrain). Five independant geometric variables allow for great freedom in tailoring of the Kn profile. Such a grain may be fabricated by casting with a suitable mandrel, or by drilling the core, then cutting the fin slots. Written by Richard Nakka. PFCBURN.XLS Version Beta1 165kbytes EXCEL 2000 spreadsheet Freeware PFCBURN.RAR 72 kbytes Zipped EXCEL spreadsheet Bulgarian language version of PFCBURN, translated by George Andonov. Freeware PFCBURN_fr.xlsm> 176 kbytes EXCEL spreadsheet French language version of PFCBURN, translated by Jérôme Fouque. Pseudofinocyl grain crosssection. Example Kn chart. Delaney/Nakka Ejection Charge Calculator Simple to use Windows calculator that computes the mass of Black Powder needed to produce a specified pressure within a rocket parachute compartment. The resulting force tending to eject the nosecone or to separate the rocket sections is also computed. Software written by J.Delaney Help written by Richard Nakka EjectionChargeCalculator.zip Version 1.3 1.4Mbytes MS Windows Freeware GRAINDENSITY.XLS This Excel spreadsheet computes the actual mass density of a sugarpropellant grain based on user input values of grain geometry and mass. This is compared to the ideal mass density by computing the ratio of the two densities. This provides the experimentalist with a "densitometric quality" assessment of a propellant grain. A good quality grain, one with minimal porosity and few voids or other flaws, will have a ratio close to one. A porous grain or a grain with hidden voids, for example, will be marked by a significantly lower density ratio. The usefulness of such a check is apparent when one considers that propellant burn rate and Kn profile can be strongly affected by such grain deficiencies. In extreme cases, a CATO could result from a grain with degraded densitometric quality. Written by Richard Nakka. GRAINDENSITY.XLS Version 1.00 40kbytes EXCEL 2000 spreadsheet Freeware GRAINDENSITY_BG.RAR 13kbytes Zipped EXCEL spreadsheet Bulgarian language version of GRAINDENSITY, translated by George Andonov. Freeware GRAINDENSITY_fr.xlsx 33kbytes EXCEL spreadsheet French language version of GRAINDENSITY, translated by Jérôme Fouque ORING_2.4.XLS The use of orings is an ideal means to pressure seal a rocket nozzle or bulkhead. Orings are inexpensive, simple to incorporate, and are highly reliable. However, it is important to choose the correct size oring for a given application, and to have the correct size gland (groove) into which the oring is seated. This Excel spreadsheet selects the appropriate sized oring based on user input values of casing and nozzle diameters, based on ARP 1232 specifications. Updated for 010, 100, 200 & 300 series (1/16", 3/32", 1/8" & 3/16") orings . Written by Richard Nakka. ORING_2.4.XLS Version 2.4 872kbytes EXCEL spreadsheet Freeware ORING_2.3_fr.xlsx 33kbytes EXCEL spreadsheet French language version of ORING, translated by Jérôme Fouque. PDFCreator An extremely useful "opensource" (GNU GPL) software for reliably converting documents to Acrobat PDF format. Excellent for publishing articles for online format or for emailing. Can be used with any document software (examples: MS Word, MS Excel, Paint Shop Pro, etc.). Easy to use  instead of printing to a device, you simply print to PDF Creator. PDFCreator Version 0.9.3 