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Questions tagged [rockets]

Questions regarding the boosters or thrusters used to propel man-made objects. For rockets firing opposite the primaries, see [retrorockets]. See wiki for other related tags.

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How has rocket propulsion system designs developed over the years in terms of effectiveness?

I am working on a research project about developing rocket propulsion designs for school work. More specifically, I am researching how rocket propulsion designs have changed over the last century, in ...
Aryan's user avatar
  • 11
1 vote
0 answers
69 views

What is the ratio of air and ethyl alcohol that must be in order to power a rocket engine? [closed]

There is a rocket engine that will run on a fuel pair: air + ethyl alcohol, but what percentage of components should be supplied ...
DYNAMIC AEROSPACE's user avatar
2 votes
3 answers
5k views

Could SpaceX ever make a Heavy version of Starship Super Heavy

As of now, SpaceX is preparing for Starship Flight 4, and once starship is mature enough and achieves Elon Musk's goal, will they make a Heavy version like with Falcon. Even Before Integrated flight ...
Lawn Hollander Lawn's user avatar
5 votes
1 answer
579 views

How do you measure specific impulse Isp of a rocket engine?

Specific impulse (Isp), is one of the two most important parameters used to characterise a rocket engine. The other being thrust (T). For example, the RS-25 Space Shuttle Main Engine (SSME) has a ...
Galerita's user avatar
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3 votes
1 answer
292 views

Feasibility of landing all 3 Cores of the Falcon Heavy on Droneships [duplicate]

All of the Falcon Heavy launches up to now are either expending the Center core and landing the side boosters on land, or expending all of them (some examples: Falcon Heavy test flight, both boosters ...
Lawn Hollander Lawn's user avatar
1 vote
2 answers
180 views

Feasibility of landing Starship's Super Heavy booster on a droneship

Recently, after IFT 3 of Starship Super Heavy, I went to ponder: Can SpaceX land their Super Heavy boosters on Autonomous Spaceport Droneships to get extra performance. Currently, it separates with ...
Lawn Hollander Lawn's user avatar
0 votes
1 answer
84 views

Landing Zones 1 and 2 in Cape Canaveral and yet launching from KSC?

On Google Earth, I saw Cape Canaveral and Kennedy Space Center (KSC) are separate sites. However, I do not understand why SpaceX lands it's boosters on LZ 1 and 2 at Cape Canaveral but launches them ...
Lawn Hollander Lawn's user avatar
0 votes
1 answer
152 views

How much deltaV would it take to launch from the top of mount Everest straight up then circularize at 200km once in space?

I realize there are several similar questions, but i didn't see mention of the amount of deltaV needed beyond saying there is a slight benefit that is more than offset by dozens of social/political/...
Rasip's user avatar
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0 votes
1 answer
50 views

Example using NASA GMAT to model a sounding rocket launch

I'm wondering if anyone has an example GMAT script that describes a sounding rocket launch and return. Not necessarily looking for high fidelity but just something that shows the parameters for a ...
Eric Smith's user avatar
4 votes
1 answer
196 views

Theoretical viability of a liquid rocket engine concept [closed]

[DISCLAIMER: I am an aerospace engineer undergrad and I do NOT want to build this. I wanted to come up with an alternative for the usual hypergolic mix so US military personnel would have one less ...
user avatar
2 votes
1 answer
391 views

What rocket engine is this?

I came across a meme depicting a supposedly oxygen rich, fuel rich, and "engine rich" cycle of rocket engine. However, I'm pretty sure at least one of them is incorrect listing what looks a ...
fyrepenguin's user avatar
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11 votes
2 answers
4k views

Why are nitric acid and hydrogen combinations not used as rocket fuel?

I was recently doing a chemistry assignment about bond energy when I noticed the incredibly low bond energy of nitric acid. Given the high bond energy of a nitrogen triple-bond, this set me wondering ...
Robert Goddard-Wright's user avatar
2 votes
0 answers
39 views

How to calculate the cooling jacket of a liquid propellant engine with an external component? [closed]

When designing a small rocket engine with a thrust of 100 N, questions arose about the cooling of the combustion chamber and the nozzle apparatus. It was decided to ...
DYNAMIC AEROSPACE's user avatar
0 votes
1 answer
171 views

Does Raptor rocket engine of SpaceX include a cracker or fuel conversion system to crack the hydrocarbon fuel into its constituents?

In the Raptor rocket engine, where is the hot turbine exhaust gas transferred, when gaseous fuel arrives from the heat exchanger? Does the Raptor rocket engine include a cracker or fuel conversion ...
Lakshay's user avatar
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1 vote
0 answers
51 views

Combustion chamber pressure calculation [duplicate]

A liquid propellent rocket engine: how is combustion chamber pressure calculated? Is it the different between turbopump outlet pressure and the drop in the injectors (losses aside)? Thanks!
Mariner's user avatar
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4 votes
2 answers
270 views

Engine most likely to be available in the next 80 years to accelerate a craft at 1G for 4 weeks [closed]

I am wondering what type of engine would most likely be available in the next 80 that can constantly accelerate a spacecraft at 1G. Preferably, it could accelerate it for 4 weeks. The engine could be ...
Tom's user avatar
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5 votes
2 answers
437 views

Could Starship lift mass to orbit (both low and geo-stationary) cheaper than a skyhook?

In response to this question which appears to ask only about space elevators and not skyhooks, would Starship's cost per kilogram to LE or Geo-stationary orbits be lower than a skyhook's? I ask only ...
user121330's user avatar
1 vote
0 answers
40 views

What was the mass flow rate of the Titan IIIE stage 1 during the voyager 1 launch

I am doing a project and I cant seem to find an exact value for the mean mass flow rate of the Titan IIIE booster during stage one of the voyager 1 launch?
owinius's user avatar
  • 31
2 votes
1 answer
283 views

Why aren't more companies manufacturing the RS-25 (Space Shuttle Main Engine)?

The RS-25 is a great engine with a terrific ISP. It was used 42 years ago (on April 12th 1981) for the first Space Shuttle flight; therefore, the most of the patents on it must have expired long ago. ...
phil1008's user avatar
  • 5,593
1 vote
1 answer
138 views

Question on improved SSME thrust chamber construction

How do you get the closed out copper liner of the thrust chamber, which is hour glass shaped, into a jacket that is also the exact same shape like shown? I'm gonna guess it was done by diffusion ...
Meatball Princess's user avatar
11 votes
4 answers
6k views

Do the flames from a rocket cast a shadow, and, more generally, does the rocket exhaust cast a shadow?

Also, would there be any difference between shadows cast by the exhaust from a rocket as opposed to the flame from a rocket?
Chuey's user avatar
  • 111
-1 votes
1 answer
124 views

What should be the fuel mass of a hypersonic (Mach 7) rocket using APCP fuel that would deliver a 50 gram payload?

Well, I used this rocket calculator besides asking ChatGPT and BingGPT and both gave me similar answers where the amount of fuel would be around 300 to 4000 grams of APCP fuel. And 30 to 100 grams for ...
Fulano's user avatar
  • 153
2 votes
2 answers
99 views

Space Exploration: Recommendation for Books

I have a master degree in Electrical Engineering specialized in RF. I would like - as a "hobby" in my free time - to get a deeper technical knowledge on what concerns physics in space and ...
Tripola's user avatar
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0 votes
0 answers
60 views

Is the turbopump outlet pressure higher or lower than the combustion chamber pressure? [duplicate]

I always thought turbopump outlet pressure was higher, but when I asked chatGPT, it said the chamber pressure is higher in open cycle rocket engines. Now I am confused because how would that work if ...
Anish Kommireddy's user avatar
0 votes
0 answers
64 views

Misting/Fogging Nozzles as Rocket Injectors

Misting and Fogging Nozzles are nozzles often used in irrigation and cooling. They basically use high pressure to break the liquid into tiny droplets achieving really great atomization. I think these ...
Anish Kommireddy's user avatar
7 votes
2 answers
391 views

How does the power output of the 33 Raptors on SpaceX's Superheavy compare to the power distributed on America's electrical grid?

I recall hearing somewhere that the Space Shuttle's power was similar to that of the US electrical grid at some point in the past - but that might have been a myth. If anyone thinks that they know how ...
phil1008's user avatar
  • 5,593
1 vote
0 answers
108 views

How high will this rocket be, when MECO occurs?

Find the altitude of the rocket at the time of engine cut-off. Rocket Mass = 369208 kg, Rocket Area = 391 m2, Fuel = 170697 L, Fuel density = 21 kg/l, Exhaust Speed = 1338 m/s, Exhaust Area = 164 m2
Praveen Kumar's user avatar
0 votes
2 answers
146 views

Need clarification of units on rocket nozzle equation

I have been working on modeling liquid rocket engines and have read the book How to Design, Build and Test Small Liquid Fuel Rocket Engines, I had a question about the nozzle area and the units ...
chad jensen's user avatar
1 vote
0 answers
84 views

Would SLS Block 1B's payload capacity increase if it used 4 srbs instead of 2?If so,how much?

The SLS block 1b could carry 105 tons into LEO.If it used four boosters instead of 2, how much would its payload capacity to Leo and moon increase?
Shahida Begum's user avatar
3 votes
2 answers
139 views

sending a satellite in the right direction

I suspect that the required accuracy of satellite velocity direction is very high. This is especially the case for low earth orbits. The radius of the earth is 6400 km. The altitude of a low earth ...
S. Kohn's user avatar
  • 203
3 votes
1 answer
623 views

How could the Soviet Energia rocket go to orbit without an upper stage, and how could it have carried payload to the moon?

The Energia rocket could loft a massive 100 tons into orbit. It could also shoot about 32 tons to a trans-lunar injection. It did not have any upper stage. So, could it really go to orbit and even ...
Shahida Begum's user avatar
2 votes
3 answers
207 views

Disposing of Obsolete Satellites by Propelling to the Sun

I'm not scientifically adept, so bear with me. Would it be feasible to retain enough fuel on new satellites/space stations, etc., that we could dispose of them when obsolete by sending them to the ...
user avatar
2 votes
0 answers
43 views

Nozzle contour estimation (Merlin 1D Vacuum)

I would like to run a fluid simulation of the diverging section of a Merlin 1D Vacuum engine. While most relevant parameters (such as expansion ratio, flow rate, and nozzle area) are readily available,...
FTT's user avatar
  • 149
5 votes
2 answers
488 views

Are rockets deliberately throttled back towards the end of the burn to spare crew and airframe g-forces?

Throughout its burn, a rocket gets lighter as propellant is consumed. As a result, acceleration (and g-force) increase. In the shuttle, the SSMEs were throttled back towards the end of the burn ...
Woody's user avatar
  • 22.1k
1 vote
0 answers
105 views

Are smaller rockets easier to land? [closed]

Is it easier to land a smaller rocket compared to bigger rockets?? Since they are lighter
Rocketsss's user avatar
1 vote
0 answers
99 views

Single shaft turbopump vs two turbopumps

What are the pros and cons of using same turbopump for fuel and oxidizer and using 2 different pumps for both?
Rocketsss's user avatar
1 vote
0 answers
118 views

Does an overexpanded nozzle behave like a suction cup?

It is generally said that, to obtain optimal specific impulse, a nozzle should be just the right size that the exhaust pressure is equal to the ambient pressure. Quoting this answer, a relevant ...
Charles Staats's user avatar
0 votes
0 answers
51 views

Methane vs propane as rocket fuel [duplicate]

How would propane compare with methane as rocket fuel? Propane can also be stored as liquid under pressure.
Rocketsss's user avatar
1 vote
1 answer
126 views

Gas generator exhaust for roll control

Can the exhaust from the turbopump of a rocket engine be used for roll control if a rocket only has 1 engine? Did the falcon 1 rocket control roll this way?
Rocketsss's user avatar
0 votes
0 answers
82 views

Dual expander bleed cycle

Would dual expander bleed cycle be a good idea? The lox will pass through the nozzle and drive the lox pump And the fuel will also pass through the nozzle to drive the fuel pump Both will be expander ...
Guest12345's user avatar
3 votes
0 answers
146 views

What are the major tradeoffs for a launch vehicle having either one 400 kN engine or eight 50 kN engines?

Given the problem of choosing to build and launch a small rocket to put a smallsat into orbit with either of these two configurations, what are the major tradeoffs between them? For specific issues ...
Muhammad Ahsan's user avatar
2 votes
0 answers
143 views

What was the exhaust pressure of the Saturn V? [duplicate]

I am trying to write some code to simulate rocket launches, and I am doing a proof of concept using the Apollo 11 as a model, to fill my values. When calculating thrust I am using the equation: F=m⋅Ve+...
owinius's user avatar
  • 31
0 votes
0 answers
45 views

How to calculate the tank boost system for the displacement feed system?

There is a liquid rocket engine running on two components: highly concentrated hydrogen peroxide and kerosene, fuel vapor is ...
Андрей Александров's user avatar
1 vote
0 answers
167 views

How can I determine characteristic length (L*) of a rocket engine combustion chamber if there is little to no data collected on a similar engine? [closed]

I am designing a liquid bi-propellant rocket engine using Nitrous Oxide and Isopropyl Alcohol. I have all the necessary parameters for nozzle design and am at the stage of determining the combustion ...
Frahanco Deressa's user avatar
4 votes
1 answer
277 views

What is the significance of a heat flux value of 1135 W/m^2 when jettisoning the payload fairing? [duplicate]

I have seen that many rockets jettison their payload fairing at an altitude where the aerothermal heatflux is leass than or equal to 1135 W/m^2. What is the reason behind considering this particular ...
Tejaswi's user avatar
  • 41
0 votes
0 answers
90 views

How do you approximately calculate the center of pressure during flight? [duplicate]

I'm working on a simulator for landing the falcon 9 booster rocket. I'm aiming to incorporate aspects like the effects of restorative torque. However, I've been trying to figure out how to determine ...
IsolatedSushi's user avatar
1 vote
0 answers
53 views

Rough values for the staytime or characteristic length of the combustion chamber of an oxygen/methanol rocket engine?

I'd like to have some idea of the staytime or characteristic length of the combustion chamber of an oxygen/methanol rocket engine. Are there sources for this, or a way to estimate it? I've tried, but ...
Kevin's user avatar
  • 11
1 vote
1 answer
2k views

Why was Booster 9's 29 engine static fire ended 2.36 seconds early? [duplicate]

Suggested by Darth Pseudonym in answer to my other similar question. Recently (August 7), Booster 9 conducted a static fire test where it shutdown after only 2.74 of the planned 5 seconds of burn ...
Starship - On Strike's user avatar
3 votes
1 answer
2k views

Why were 4 engines shutdown prematurely during Booster 9's static fire?

Recently (August 7), Booster 9 conducted a static fire test where it only ignited 29 of 33 engines. This is the big static fire, there not another one. I have found that they were shutdown prematurely ...
Starship - On Strike's user avatar
3 votes
1 answer
152 views

What is missing in the conversion of specific impulse from units of seconds to thrust/mass flow rate? [duplicate]

I was trying to get the Specific Impulse of the Saturn V engines, hoping for a value in N/kg/s, as I need to know the mass consumption rate per thrust value. Any and all sources give me the value in ...
confused_aspirant's user avatar

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