All Questions
Tagged with engine-design propulsion
26
questions
7
votes
4
answers
2k
views
What kind of engine does this Isp = 1600 refer to? Is it cubesat-friendly?
These two good answers (one and two) to the question "Is there a maximum Isp for 'exothermic chemical reaction rockets?'" put the limits around 500-550 seconds for the limits of practical ...
- 149k
12
votes
1
answer
11k
views
Rocket Engine Plumbing: Still don't understand the Full Flow Staged Combustion Cycle
I just found this incredible video KSP Doesn't Teach: Rocket Engine Plumbing and ran through it a few times. It's very helpful in the way it outlines the various issues first, and then designs the ...
- 149k
13
votes
4
answers
3k
views
Do rocket engines have shock absorbers?
With a million pounds of thrust and many g of acceleration and a significant fraction of a g of vibration, connecting the engine to the rocket can't be trivial.
At launch the mass is very high and ...
- 149k
11
votes
3
answers
3k
views
What are the phases of ignition (and flameout) of a liquid fuel engine?
As I observed ignition of several rocket engines (Shuttle, AMDE, Lynx Suborbital, Saturn V) they all come through a couple phases - emitting various vapors, unfocused flame, etc, before the proper "...
- 55k
27
votes
8
answers
21k
views
Why aren't linear aerospike engines in common use?
Linear aerospike engines are an old idea that seem so full of promise. Why are they not widely used today by the likes of Boeing, SpaceX, etc.?
- 669
4
votes
1
answer
2k
views
How do you determine what the temperature will be in the combustion chamber of a rocket engine?
I am guessing it is dependent on the fuel and oxidiser and the chamber pressure but is there an equation that would calculate the chamber temperature?
- 357
2
votes
1
answer
385
views
Could a CubeSat be propelled by this low-tech electromagnetic propulsion system?
I have come up with a conceptual idea for a low-tech electromagnetic propulsion system for a CubeSat, and I would like to know if it would create (on a theoretical basis) a net force strong enough to ...
user28781
18
votes
1
answer
3k
views
Why the non-symmetric design of rocket nozzles?
Although I have seen many perfectly symmetric nozzles, I have also seen designs such as this (Virgin Galactic) which is only symmetrical about one axis:
Why is this?
- 303
14
votes
1
answer
3k
views
Are MMH and UDMH interchangeable?
Can Monomethylhydrazine and Unsymmetrical dimethylhydrazine be used one in place of another for the class of the existing orbital maneuver engines (with reduced performance may be)? Such as Shuttle's ...
user54
21
votes
7
answers
13k
views
Can ion thrusters be scaled up?
All ion thrusters are quite small. Having read through the more approachable information about them, as they use physics pretty beyond me, I don't understand what it is about them that makes it ...
- 21.4k
17
votes
1
answer
8k
views
What are the advantages of Ox-rich staged combustion?
In the context of staged combustion, I understand that burning ox-rich creates complications associated with having hot, high pressure, oxidizer. Some engines, notably the RD-170 and RD-180 family run ...
- 720
10
votes
1
answer
1k
views
Why did the MarCO space probes use fire extinguishant as their propellant?
In many news articles, it's mentioned that the MarCO spacecraft, launched with InSight, used fire extinguishant as the propellant for its cold gas thrusters. I originally assumed that this was ...
- 311
4
votes
3
answers
744
views
At what size does a bigger solar sail stop increasing your acceleration?
Is there a point where the larger solar sail would not add more thrust? What is the most thrust a solar sail can produce?
Can a solar sail be added to an ion engine and work better?
- 1
29
votes
8
answers
7k
views
Would a grinding machine be a simple and workable propulsion system for an interplanetary spacecraft?
I am wondering if any space agency has ever considered using a grinding machine as a propulsion system for an interplanetary spacecraft. This system would not be used to lift the spacecraft off of a ...
user28781
16
votes
2
answers
2k
views
How do you confirm ignition in the combustion chamber of a rocket?
Is ignition confirmed using a temperature sensor, pressure sensor or another device?
- 357
16
votes
3
answers
1k
views
Pumped propellant propulsion - is it viable?
A recent article on Slashdot got me thinking.
While the article is about using electric turbopumps for moving fuel from tanks to engines during launch phase and is just a small, incremental ...
- 55k
14
votes
2
answers
19k
views
Efficient types of nozzles used in rockets
Is there any other type of nozzle other than common convergent-divergent nozzle (see picture below) which is used in many rockets?
...
- 18k
13
votes
2
answers
23k
views
Is the concept of the Epstein Drive based on actual theorized scientific research which is considered plausable?
I've always found it interesting when we see real life taking its cues from fictional arts, especially when it comes to Science Fiction technology. There are plenty of examples of classic books, TV ...
- 555
11
votes
1
answer
243
views
When regenerative cooling is used, how is the nonuniform radius of the combustion chamber handled?
As the combustion chamber necks down and flares out, the 1-D cross section past which which fuel must pass as it cools the wall of the chamber will change. If there are lots of tubes, they will bunch ...
- 11k
7
votes
2
answers
708
views
What challenges are there for more, smaller liquid fuel engines instead of one large?
Some questions popped up about difficulties of creating throttleable liquid fuel engines.
I wonder why the obvious alternative isn't more common: multiple engines, from which only some will be lit; ...
- 55k
6
votes
1
answer
698
views
Which is the preferred mode of liquid rocket engine cutoff - fuel lean cutoff or fuel rich cutoff?
When a bi-propellant liquid rocket engine receives a command to shut down,
will the fuel gets cut off first and then the oxidiser - a fuel lean cutoff?
Will the oxidiser gets cut off first and then ...
- 4,469
4
votes
1
answer
540
views
Does LOx stay as liquid when entering combustion chamber?
Given the heat from combustion and increased temperature, would the LOx still be in liquid form after emanating from the injector? Or will it instantly transform into gas?
Are injectors cooled using ...
- 4,469
3
votes
1
answer
197
views
RS-25 Component weight
I need to determine the weight for specific components of the RS-25 Rocket engine. Namely the combustion chamber and nozzle separate from all other engine components?
I must have found hundreds of ...
3
votes
2
answers
1k
views
What are the choice of materials for LOx pumps casing and impellers?
Given the highly corrosive nature of LOx and the extremely low temperature, what materials are usually used for the LOx pumps?
Steel, Copper, and many alloy tend to be flammable in liquid Oxygen ...
- 4,469
3
votes
1
answer
155
views
Rocket engine power vs. Sound
Is there any relationship between the sound emitted from a rocket engine and the amount of thrust it gets at surface temperature and pressure?
- 4,285
2
votes
1
answer
1k
views
Why spray LOx into combustion chamber, if GOx is more effective?
Are there any issues in transforming the liquid oxygen into gaseous oxygen before injecting into the combustion chamber?
Gaseous Oxygen will be readily available for combustion and will mix well with ...
- 4,469