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Liquid apogee engine

From Wikipedia, the free encyclopedia

A 400 N hypergolic liquid apogee engine, including heat shield and mounting structure, on display at DLR visitors center, Lampoldshausen, Germany. The engine was designed for use on Symphonie satellites. These were the first three-axis stabilised communication satellites in geostationary orbit to use a liquid bipropellant apogee engine for orbit insertion.[1]

A liquid apogee engine (LAE), or apogee engine, refers to a type of chemical rocket engine typically used as the main engine in a spacecraft.

The name apogee engine derives from the type of manoeuvre for which the engine is typically used, i.e. an in-space delta-v change made at the apogee of an elliptical orbit in order to circularise it. For geostationary satellites, this type of orbital manoeuvre is performed to transition from a geostationary transfer orbit and place the satellite on station in a circular geostationary orbit. Despite the name, an apogee engine can be used for a range of other manoeuvres, such as end-of-life deorbit,[1] Earth orbit escape, planetary orbit insertion[2][3] and planetary descent/ascent.[4]

In some parts of the space industry an LAE is also referred to as a liquid apogee motor (LAM), a liquid apogee thruster (LAT) and, depending on the propellant, a dual-mode liquid apogee thruster (DMLAT). Despite the ambiguity with respect to the use of engine and motor in these names, all use liquid propellant. An apogee kick motor (AKM) or apogee boost motor (ABM) such as the Waxwing, however, uses solid propellant.[5][unreliable source?] These solid-propellant versions are not used on new-generation satellites.[5][6]

YouTube Encyclopedic

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  • How To Make Sugar Rockets
  • How To Make "Screw-Lock" Sugar Rockets
  • Thermosiphon
  • Model Rocket Motor - F and G class
  • Mod-01 Lec-04 Velocity Requirements

Transcription

In a previous project I went to the hobby store and picked up some F-class rocket motors, to try launching a rocket, made out of pool noodles. Now these motors are amazing, but the catch is they’re $17 each. So in this project let’s see if we can use powdered sugar and kitty litter, to make a homemade version, that will rocket up over 2,000 feet high, and cost less than $0.50 make. To start this project we’ll need powdered sugar, potassium nitrate, and a cheap bag of kitty litter. We’re also going to need 3/4” PVC tubing and a 3/4” oak dowel. This is schedule 40 PVC, and you can see I’ve cut the tube into sections 5” long, exactly. The dowel is twice as long as that, and you can see if we push it inside the tube, it’s actually a pretty good fit. This will be a ramming rod, and a template as well. And the markings you see on the stick are designed to make the simplest form of an “E45 equivalent” rocket motor. The markings are actually in reverse order to how we’re going to build it, but you’ll see why it needs to be that way in just a minute. Alright, let’s get ready to make the rocket fuel, and to start off we’re going to need a small blender that we’re not afraid to damage. I found this one at a local thrift shop for $5, and the first thing we have to do is measure out 65 grams of potassium nitrate. I typically get mine as a special brand of stump remover, and it’s a pretty fine grain to begin with, but you can see that after blending it up for about 20 seconds, it becomes a fluffy white powder, that looks a lot like powdered sugar. Now speaking of powdered sugar, we’re going to need some of that next. So let’s zero out our scale, and add exactly 35 grams of sugar to the mix. At this point the powder is a pyrotechnic composition that could ignite with too much heat, so instead of mixing this up with the blender, we’re going to have to shake it by hand for about 3 minutes. This should give it enough time to blend completely, and that’s important because we need this white mix to be as intimate as possible. Alright, our rocket fuel is finished, so let’s transfer it to another container to free up the blender, because now it’s time to bring out the kitty litter. This 7 lb bag was only $0.98, and surprisingly, the cheap kind is the best kind, because it doesn’t have any fragrances or dyes added to it. It’s just a big bag full of bentonite clay, which is probably why the stuff is as cheap as dirt. Alright let’s throw a handful of clay into the blender for 10-20 seconds so it grinds into a power. Holding the blender at a bit of an angle helps mix it better, and reduces the load, on the motor as well. Now when it’s time to remove the lid, it’s important to wear a mask, or do it outside. Because you can see the powder is so fine it escapes like a gas, and its not really good to breathe this stuff in. Ok, we’ve got everything we need, so let’s get to work putting it all together. Place one of the PVC casings on a slab of concrete, and drop in a third of a tablespoon of kitty litter. Now let’s make sure we keep the tube firmly on the concrete so the clay doesn’t spill out the bottom, then slide the oak ramming rod inside, and smack the top firmly with a rubber mallet. It’s going to need about 5-10 good whacks, to compact it as tight as we need it. And you can see it will make a nice little clay plug, at the bottom of the tube. Let’s repeat this process 2 more times until the plug is 3/4” thick, which you can see is conveniently indicated by the marking on the stick. If too much clay gets packed in, no worries. You can just twist the dowel around a few times to loosen the top layer, then pour out the extra clay until it lines up perfectly. At this point, we’re ready to add the white mix. This stuff is extremely light and fluffy, so it’s important to push the ram rod down, very slowly. Once it’s compacted by hand though, we can ram it with the mallet, just like we did the clay, until the rammed “white mix” lines up perfectly with the next marking. The last step for this simple motor is a kitty litter end cap. This will be 3/4” thick as well, the same as the one we made before. But here you can see there’s still a little room left in the tube, and you’ll see what that’s for in another project video. Ok our rocket motor is just about finished. The only thing left to do is make the nozzle. For these motors I use a 7/32” drill bit, which happens to be the exact length and width we need to turn this rammed powder tube, into a core burning rocket. Now to gauge the depth on how far in to drill, we can use the markings on the ram rod to measure exactly where the white mix ends, then mark the drill bit at the point where it lines up with the clay. Now it’s really important to drill this out very slowly and carefully because, remember, this is a rocket motor, and you don’t want to set it off by accident. I’m drilling mine out by hand, so it’s easy to control any heat generated, from the friction. When the marking on the bit lines up with the bottom of the casing, the rocket motor is finished and should look something like this. Now to test the power of these motors I went way out into the dessert, miles and miles away from any people, property or anything flammable. When this one lit off I was blown away by what it could do. The motor, just shot up 2,300 feet high. And of course if we’ve got rockets going that high, we’re going to need a way to deploy, some kind of a recovery system. So the next step, is to give our rocket motors a built in time delay, and a parachute ejection charge. The 100 gram batch in this video is enough to make two “E45 equivalent” motors, with about 20 grams of propellent left over. Which is what I mix with baking soda, to slow the burn, and create a 5 second delay. So watch for those modifications in another video. Well now you know how to repurpose some simple household items, into powerful hobby rocket motors, for less than $0.50 each. Just make sure you have the right permits, location, and common sense before you try launching them. Well that’s it for now. If you liked this project, perhaps you’ll like some of my others. Check them out at www.thekingofrandom.com If you are even considering the thought of trying to build one of these, please promise me you’ll do one thing first. Get on google and do a search for local rocket clubs. They don’t cost much, and they’ll have the best idea of how to keep you out of trouble with the FAA, and make sure nobody gets hurt. Having said all that, I hope you felt the same excitement for this project that I did. I’ve spent 4 years playing with different variations of sugar motors to get to this point, so I’m super excited to finally be able to present this to you. Now going forward, you can expect to see a few more rocket related videos, and then we’re getting into metal melting projects, so please make sure you’re subscribed to my channel because I’d really like to see you around for those project videos. I’ll talk to you then.

History

The apogee engine traces its origin to the early 1960s, when companies such as Aerojet, Rocketdyne, Reaction Motors, Bell Aerosystems, TRW Inc. and The Marquardt Company were all participants in developing engines for various satellites and spacecraft.[7]

Derivatives of these original engines are still used today and are continually being evolved[8][9][10] and adapted for new applications.[11]

Layout

A typical liquid apogee engine scheme could be defined[12] as an engine with:

  • pressure-regulated hypergolic liquid bipropellant feed,
  • thermally isolated solenoid or torque motor valves,
  • injector assembly containing (though dependent on the injector) central oxidant gallery and outer fuel gallery,
  • radiative and film-cooled combustion chamber,
  • characteristic velocity limited by thermal capability of combustion chamber material,
  • Thrust coefficient limited by supersonic area ratio of the expansion nozzle.

To protect the spacecraft from the radiant heat of the combustion chamber, these engines are generally installed together with a heat shield.[citation needed]

Propellant

Apogee engines typically use one fuel and one oxidizer. This propellant is usually, but not restricted to,[7] a hypergolic combination such as:

Hypergolic propellant combinations ignite upon contact within the engine combustion chamber and offer very high ignition reliability, as well as the ability for reignition.

In many instances mixed oxides of nitrogen (MON), such as MON-3 (N
2
O
4
with 3 wt% NO), is used as a substitute for pure N
2
O
4
.[13]

The use of N
2
H
4
is under threat in Europe due to REACH regulations. In 2011 the REACH framework legislation added N
2
H
4
to its candidate list of substances of very high concern. This step increases the risk that the use of N
2
H
4
will be prohibited or restricted in the near- to mid-term.[14][15]

Exemptions are being sought to allow N
2
H
4
to be used for space applications, however to mitigate this risk, companies are investigating alternative propellants and engine designs.[16] A change over to these alternative propellants is not straightforward, and issues such as performance, reliability and compatibility (e.g. satellite propulsion system and launch-site infrastructure) require investigation.[15]

Performance

The performance of an apogee engine is usually quoted in terms of vacuum specific impulse and vacuum thrust. However, there are many other details which influence performance:

  • The characteristic velocity is influenced by design details such as propellant combination, propellant feed pressure, propellant temperature, and propellant mixture ratio.
  • The thrust coefficient is influenced primarily by the nozzle supersonic area ratio.

A typical 500 N-class hypergolic liquid apogee engine has a vacuum specific impulse in the region of 320 s,[17][18][19][20] with the practical limit estimated to be near 335 s.[7]

Though marketed to deliver a particular nominal thrust and nominal specific impulse at nominal propellant feed conditions, these engines actually undergo rigorous testing where performance is mapped over a range of operating conditions before being deemed flight-qualified. This means that a flight-qualified production engine can be tuned (within reason) by the manufacturer to meet particular mission requirements, such as higher thrust.[21]

Operation

Most apogee engines are operated in an on–off manner at a fixed thrust level. This is because the valves used only have two positions: open or closed.[22]

The duration for which the engine is on, sometimes referred to as the burn duration, depends both on the manoeuvre and the capability of the engine. Engines are qualified for a certain minimal and maximal single-burn duration.

Engines are also qualified to deliver a maximal cumulative burn duration, sometimes referred to as cumulative propellant throughput. The useful life of an engine at a particular performance level is dictated by the useful life of the materials of construction, primarily those used for the combustion chamber.[12]

Applications

A simplified division can be made between apogee engines used for telecommunications and exploration missions:

  1. Present telecommunication spacecraft platforms tend to benefit more from high specific impulse than high thrust.[23] The less fuel is consumed to get into orbit, the more is available for station keeping when on station. This increase in the remaining propellant can be directly translated to an increase in the service lifetime of the satellite, increasing the financial return on these missions.
  2. Planetary exploration spacecraft, especially the larger ones, tend to benefit more from high thrust than high specific impulse.[24] The quicker a high delta-v manoeuvre can be executed, the higher the efficiency of this manoeuvre, and the less propellant is required. This reduction in the propellant required can be directly translated to an increase in the bus and payload mass (at design stage), enabling better science return on these missions.[12][23]

The actual engine chosen for a mission is dependent on the technical details of the mission. More practical considerations such as cost, lead time and export restrictions (e.g. ITAR) also play a part in the decision.

See also


References

  1. ^ a b "Unified Propulsion System - Background". Airbus Defence and Space. Archived from the original on 2014-09-25. Retrieved 29 January 2015.
  2. ^ Amos, Jonathan (2012-09-04). "Juno Jupiter probe gets British boost". BBC News. Retrieved 29 January 2015.
  3. ^ Domingue, D. L.; Russell, C. T. (19 December 2007). The MESSENGER Mission to Mercury. Springer Science & Business Media. p. 197. ISBN 978-0-387-77214-1.
  4. ^ "Industrial Policy Committee, Robotic Exploration Plan, Programme of Work 2009-2014 and relevant Procurement Plan" (PDF). European Space Agency. Archived from the original (PDF) on 2016-03-03. Retrieved 25 January 2015.
  5. ^ a b Pocha, J. J. (1987). "The Apogee Manoeuvre". Space Technology Library Volume 1. An introduction to mission design for geostationary satellites. Chapter 4: The Apogee Manoeuvre. Springer. pp. 51–66. doi:10.1007/978-94-009-3857-1_4. ISBN 978-94-010-8215-0.
  6. ^ Ley, Wilfred; Wittmann, Klaus; Hallmann, Willi, eds. (2009). Handbook of space technology. John Wiley & Sons, Ltd. pp. 323–324. ISBN 978-0-470-69739-9.
  7. ^ a b c Stechman, Carl; Harper, Steve (2010). "Performance improvements in small earth storable rocket engines - an era of approaching the theoretical". 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference (2010–6884).
  8. ^ "ESA investigates ALM for in-space satellite engines". LayerWise. Archived from the original on 2014-11-29. Retrieved 15 November 2014.
  9. ^ Hyde, Simon (2012). "Combustion chamber design for additive manufacturing". Space Propulsion 2012 Conference, Bordeaux, France.
  10. ^ Hyde, Simon (2012). "A design optimisation study of a generic bi-propellant injector for additive manufacturing". Space Propulsion 2012 Conference, Bordeaux, France.
  11. ^ Werner, Debra (2013-07-15). "Space propulsion - Moog sees higher-thrust liquid propellant engine as right fit for Mars missions". www.spacenews.com. Archived from the original on November 15, 2014. Retrieved 15 November 2014.
  12. ^ a b c Naicker, Lolan; Wall, Ronan; David, Perigo (2014). "An overview of development model testing for the LEROS 4 High Thrust Apogee Engine". Space Propulsion 2014 Conference, Cologne, Germany (2969298).
  13. ^ Wright, A. C. (February 1977). USAF Propellant Handbooks: Nitric Acid / Nitrogen Tetroxide Oxidizers (AFRPL-TR-76-76 ed.). Martin Marietta Corporation. p. 2.3–3.
  14. ^ "Considering hydrazine-free satellite propulsion". ESA. Retrieved 15 November 2014.
  15. ^ a b Valencia-Bel, Ferran (2012). "Replacement of Conventional Spacecraft Propellants with Green Propellants". Space Propulsion 2012 Conference, Bordeaux, France.
  16. ^ "Green propulsion". www.sscspace.com. Archived from the original on 29 November 2014. Retrieved 15 November 2014.
  17. ^ "Apogee/Upper Stage Thrusters". www.moog.com. Archived from the original on 2015-03-02. Retrieved 15 November 2014.
  18. ^ "400 N Bipropellant Apogee Motors". Astrium Space Propulsion. Archived from the original on 2014-04-26. Retrieved 15 November 2014.
  19. ^ "Bipropellant Rocket Engines". www.rocket.com. Retrieved 15 November 2014.
  20. ^ "Satellite Propulsion System". www.ihi.co.jp. Archived from the original on 24 November 2014. Retrieved 15 November 2014.
  21. ^ "LEROS engine propels the Juno spacecraft on its historic voyage to Jupiter". Retrieved 15 November 2014.
  22. ^ Houston, Martin; Smith, Pete; Naicker, Lolan; Perigo, David; Wall, Ronan (2014). "A high flow rate apogee engine solenoid valve for the next generation of ESA planetary missions". Space Propulsion 2014 Conference, Cologne, Germany (2962486).
  23. ^ a b Naicker, Lolan; Baker, Adam; Coxhill, Ian; Hammond, Jeff; Martin, Houston; Perigo, David; Solway, Nick; Wall, Ronan (2012). "Progress towards a 1.1 kN apogee engine for interplanetary propulsion". Space Propulsion 2012, Bordeaux, France (2394092).
  24. ^ Perigo, David (2012). "Large platform satellite propulsion with a focus on exploration applications". Space Propulsion 2012 Conference, San Sebastian, Spain.
This page was last edited on 4 August 2021, at 18:09
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