Questions tagged [propulsion]

Systems for propelling a spacecraft from one place to another, such as rockets.

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In a gridded-ion thruster, why are the ions accelerated away from the thruster and do not just stay close to the negatively charged grid?

Basically, if the ions are accelerated due to their attraction to a negatively charged gird at the back end of the thruster, why don't the ions just stay by the grid? How are they ejected out of the ...
lewellyn's user avatar
9 votes
2 answers
2k views

Is there any satellite that uses LOX as oxidizer?

With Liquid Oxygen being used as an Oxidizer in Starship and some other rocket engines, I was curious if LOX was also used for propelling satellites as well.
Prayag's user avatar
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Propellant consumption of Starship trip from NRHO to Mars

People, I am trying to estimate the amount of propellant (liquid oxygen+ liquid methane) required by Starship to reach Mars from NRHO (Near-rectilinear halo orbit). Also the propellant consumption ...
Prayag's user avatar
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2 votes
0 answers
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Would (Dual Spool and Concentric Powerhead) FFSC Cycle engine be possible to engineer

I,ve been wondering if it was possible engineer and how we would we work it out DUAL SPOOL FFSCC ENGINE with concentric core and individual concentric turbine inside one another and maybe it could ...
ALPHA X FUTUR COMPANY AEROSPAC's user avatar
3 votes
1 answer
189 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 ...
Slartibartfast's user avatar
3 votes
2 answers
583 views

Fueling the RS-25 Turbo pumps?

Is there any way to know the weight of Fuel / Oxidizer consumed by just the turbo pumps of the RS-25 rocket engine?
Slartibartfast's user avatar
19 votes
3 answers
3k views

How is the Quantum Drive performing on board the BARRY-1 cubesat?

Since 2001 there has been chatter about reactionless “quantum drives” such as the EmDrive developed by Satellite Propulsion Research Ltd. These drives supposedly produce thrust without consuming ...
Woody's user avatar
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Propulsion options for orbital transfers after release from space elevator

In a recent discussion of cost estimates of hypothetical space elevators it was mentioned that a space elevator is (obviously) well suited to bring payloads to a geosynchronous orbit while reaching ...
Peter - Reinstate Monica's user avatar
6 votes
2 answers
833 views

Is it ever normal to vent LOX from spacecraft with active engines? Isn't it a fire hazard?

This is regarding: "SpaceX Chief Executive Elon Musk says a propellant dump caused the destruction of the Starship upper stage" "Musk said the failure was linked to venting liquid ...
TheMatrix Equation-balance's user avatar
1 vote
1 answer
137 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
3 votes
1 answer
174 views

Why does the Vulcan-Centaur upper stage do ullage burns after engine shutdown?

During the livestream of the recent Vulcan-Centaur launch, the animation of the upper stage shows what appear to be extensive ullage burns (at least four minutes, at least three minutes, and at least ...
Mark's user avatar
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Would tidal forces be strong enough to stabilize a configuration where one satellite is being used to tow another satellite?

The scenario that I'm contemplating is one in which there is a first "depleted satellite" that has run out of propellant and a second "rescue satellite" that is designed to rescue ...
phil1008's user avatar
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3 votes
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Why is the value of the Isp of the Rocketdyne J-2 Saturn V engine in my calculation so off?

While calculating the delta V the Saturn V has on its second stage, I wanted to also calculate the Isp of the J2 rockets engines. However, the value difference between my results and the values given ...
The Rocket fan's user avatar
1 vote
0 answers
94 views

What kind of propulsion did/does the Raytheon EKV vehicle use?

Raytheon has developed an Exoatmospheric Kill Vehicle, designed to intercept an ICBM and destroy it through a collision. Here are some related links: Wikipedia page YouTube video about the project, ...
Steve's user avatar
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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
2 votes
1 answer
91 views

Combustion stability for the second stage of Sea Dragon

I was listening to a video about SHLV's (Super Heavy Launch Vehicles), and Sea Dragon's first stage engine was mentioned. In terms of combustions stability, the suggested fix would be large combustion ...
AnarchoEngineer's user avatar
2 votes
1 answer
159 views

How often does a CubeSat leverage its ADCS?

I'm wondering how often an Earth observation-focused CubeSat (6U - 27U) would leverage its onboard Attitude Determination and Control System (ADCS). Would it be employing its ADCS to optimize every ...
spacegr33q's user avatar
9 votes
1 answer
434 views

Has a rocket engine with LOX as the oxidizer ever fired beyond the GEO belt?

Intuitive Machines' Nova-C lunar lander is scheduled to launch in mid-February of this year. Notably, the lander uses liquid methane as fuel and liquid oxygen as the oxidizer, and it will rely on this ...
quinnkenri's user avatar
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2 answers
157 views

Deep space mission propellant

For an interplanetary mission that has a duration of 40 years cam we use hydrogen peroxide monopropellants? Can we use arcjets?
RemyJ's user avatar
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1 answer
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Propellant choices for a Mars landing; tradeoffs between LOX/CH4 and H2O2/RP-1?

What are the tradeoffs between LOX/methane and peroxide/kerosene for a Mars landing mission? In which ways are each better or worse than the other? I think the second one would more attractive for ...
Hartsfield's user avatar
0 votes
0 answers
115 views

How to estimate the fuel required to send 1 kg to lower mars orbit?

Imagine a rocket with a payload of 1 kg. How much liquid fuel would be required to send that 1 kg payload to lower mars orbit. (1 kg is just the payload not the whole dry mass of the rocket) I want ...
Shardul's user avatar
2 votes
1 answer
105 views

How is stage 2 propelling the spacecraft forward? [closed]

A decent response on how the burning process works but how does this glowy burner push the spacecraft
rick's user avatar
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1 answer
341 views

Why wasn't SpaceX heavy rocket tested thoroughly on ground before being sent to space?

I do not know how much testing SpaceX did before launching their heavy rocket but it to blow up 3 mins later and call is a success seems a bit misleading. I understand they gathered data but to what ...
Sam B's user avatar
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2 votes
1 answer
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Closed Loop Space propulsion

While browsing for Space propulsion found this book : https://www.knygos.lt/lt/knygos/closed-loop-space-propulsion-new-faster-approach-2e4zy/ Closed Loop Space Propulsion New Faster Approach : The ...
Stoyan's user avatar
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1 answer
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Is Electromagnetic Propulsion Like Radiation Pressure propulsion?

while browsing for new propulsion methods I found the following interesting: https://en.wikipedia.org/wiki/Radiation_pressure "Radiation pressure (also known as light pressure) is the mechanical ...
Stoyan's user avatar
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2 votes
2 answers
220 views

Do full flow rocket engines still use injectors? If so, how? How exactly are the oxidizer and fuel sent into the combustion chamber?

I'm learning about rocket engines and full flow engines, and I'm a little confused about what goes on in the combustion chamber. It was my understanding that injectors were pretty much necessary to ...
Aferb's user avatar
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3 votes
1 answer
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Propellantless propulsion in gravity field

I have a proposal for a following propellantless maneuver. It is propellantless in sense that no mass is lost from spacecraft. It is not reactionless as spacecraft interacts with planet through ...
Andris Atteka's user avatar
5 votes
3 answers
193 views

What space applications could benefit from batteries with much higher power densities than the common Li-ion type?

This Australian company claims the development of the Graphene Aluminium-Ion Battery that is up to 70 times faster in charging and has up to 3 times more battery life than current Lithium-Ion ...
Cornelis's user avatar
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1 answer
145 views

What would be the most fuel-efficient propulsion solution to accelerate a 100-ton piece of NEO asteroid towards Earth?

We need acceleration to about 300-500 m/s relative to an NEO asteroid - to get to an LEO. What is needed is the lightest package possible, that includes engine, fuel tanks, control module and ...
TheMatrix Equation-balance's user avatar
1 vote
2 answers
780 views

Lorentz force space propulsion

While browsing for Space propulsion, I've found the following article As shown in Figure 2, the conductor I0 gets through the coil L0, and they are fixed together and form a system. a is the main ...
StoyanNikolov's user avatar
-4 votes
2 answers
217 views

Can Nuclear Pulse Propulsion (Project Orion) accelerate a 100,000 ton M-type (metallic) asteroid to a LEO? [closed]

Project Orion: specific impulse in the range of 6,000 seconds. For example – Starship Interplanetary (SpaceX): Max Fuel (after refueling at orbit) - 1,950 ton Fuel left after arriving at NEO asteroid –...
user avatar
4 votes
1 answer
779 views

Advice on ionic thruster

I am a high school student, and this year our school requires us to do this Year-long project, I chose building ionic thrusters as my project's first choice. My question is, which type of ionic ...
yuzhe chong's user avatar
2 votes
1 answer
185 views

Has there ever been a fully-reusable big-dumb-booster design proposed?

I know of fully expendable Big Dumb Boosters, as well as "smart" reuse in systems like NEXUS (all versions) and their contemporaries, what I'm trying to figure out (after hours of sorting ...
AnarchoEngineer's user avatar
2 votes
1 answer
247 views

Main engine gimballing in Saturn V

The first stage of Saturn V has 5 main F-1 engines, but only 4 of the outer engines can gimbal and the engine at the center was fixed (Source : https://youtube.com/clip/...
Prasanna B's user avatar
3 votes
0 answers
133 views

How can I derive Starlink specs looking at the incident of February 2022?

I am trying to calculate and speculate the specifications of Starlink satellites (mainly related to propulsion) based on the accident on the 3rd of February 2022. There are multiple sources that ...
Playstation_waifu's user avatar
5 votes
4 answers
503 views

What is the most promising fusion technology for rocket propulsion?

Given current fusion technology (barely above q=1 as of the 12/12/22), is a fusion plasma torch rocket engine viable? I'm asking in terms of basic science, not engineering, as I know this would ...
AnarchoEngineer's user avatar
0 votes
2 answers
675 views

The costs of a single SLS solid fuel rocket booster

Why didn’t Nasa cluster four solid fuel shuttle boosters around an Atlas V booster. The thrust would be substantially more than that of the SLS, with no fueling problem on the launch pad. It would be ...
James Tosky's user avatar
2 votes
0 answers
77 views

Are there any proposals for propulsive debris deorbiting which address basic requirements for efficiency?

This illustration shows many of the challenges using propulsive deorbiting: https://www.smithsonianmag.com/air-space-magazine/34_aug2017-cleaning-up-space-junk-180963932 The trust line of the tug is ...
Woody's user avatar
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5 votes
1 answer
279 views

Thrust to weight of large solid fuel boosters

I have been looking at examples of large solid fuel rocket boosters or first stages used for space launch, such as P80, the Space Shuttle SRB, the various versions of Graphite-Epoxy-Motor, the solid ...
Ögmundur Eiriksson's user avatar
2 votes
1 answer
84 views

How to find cost data for commercially available spacecraft components?

I'm trying to research how much it should cost to build a small spacecraft, but it's super hard to find good information on the cost of various components. Can anyone suggest any good resources? For ...
ghufran syed's user avatar
1 vote
0 answers
113 views

What are better ways to deliver heat directly to propellant in a Thermal Rocket design for use in launch than UV such as in the Nuclear Lightbulb?

Most advanced, high-power engine concepts that I came across aren’t suited for atmospheric launch, so I got curious about what kinds of engines could launch a very heavy craft from the surface of a ...
PedrohSpaceWolfy's user avatar
0 votes
0 answers
65 views

A hybrid micropropulsion system for CubeSats

I am curious about how much potential would a hybrid (electric & chemical) micropropulsion system have for CubeSats. The chosen propellant is water due to its non toxic nature, cheap cost and high ...
JD_PM's user avatar
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1 vote
3 answers
389 views

Propellant Density Calculation for LOX/Kero

I am trying to make sense of the equation for propellant density calculation, rho=(rw-1)/(rw/bo+1/bf). Sutton, 7th edition, gives this equation (7-2) as: $ \ \ \ \rho_{av} = \frac {\rho_o\rho_f(1+r)} {...
Mrr's user avatar
  • 41
5 votes
2 answers
525 views

Resources for Rocket Propulsion

I am a Mechanical Engineering student who is very much interested in Rocket propulsion. Lately I have been searching for good resources to learn concepts about rocket propulsion. I'd be glad to get ...
Prasanna B's user avatar
1 vote
0 answers
93 views

rocket propulsion elements [closed]

i tried to solve the following problem this rocket engine area is cut off at 50% of the exit area, calculate the new Mach value. data old engine: P1=2068Mpa , chamber temp 2222k , flow mass 1kg/sec ,...
richard p's user avatar
7 votes
1 answer
372 views

In Apollo hardware, why were sump tanks needed?

I'm looking at the Apollo CSM Propulsion Systems. These were bi-propellant hypergolic systems. However, for some reason each type of propellant was divided into a storage and sump tank. For example, ...
DrZ214's user avatar
  • 4,556
5 votes
0 answers
369 views

Do cold gas thrusters fueled by supercritical CO2 have a higher Isp than those fueled by liquid CO2?

The private space company Pixar has developed an autonomous space vehicle (Wall-e) propelled by a cold gas thruster Hand-Held Maneuvering Unit as demonstrated in this press release: From https://...
Woody's user avatar
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1 vote
0 answers
134 views

Is there any major difference between acceleration of solid propelled and liquid propelled rockets during launch

Few days ago, ISRO launched its PSLV-C53, which had solid first stage. (Clip here) Also, the SpaceX's starlink launched on 24th July, 2022, having liquid first stage. (Clip here) Is there any major ...
Priyansu Tank's user avatar
2 votes
1 answer
320 views

Is adiabatic flame temperature the same as nozzle stagnation temperature?

I am trying to understand whether these two concepts are in fact, the same parameter. The way I see it, the adiabatic flame temperature is the highest temperature achieved by stoichiometric combustion ...
MRR's user avatar
  • 21
5 votes
1 answer
206 views

Variant of the Tsiolkovsky rocket equation including engine specific power and efficiency, can anyone help me under stand how this works

First of all this code is not mine I am trying to understand how the equation for m_u works. This comes from a master thesis called Trajectory design for a Titan mission using the Direct Fusion Drive ...
Gwyn Davies's user avatar

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