All Questions
Tagged with propulsionthrust
16 questions
6votes
2answers
595views
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 ...
2votes
1answer
354views
Thrust needed for Ion Thruster Lift off from Earth surface
I've been calculating the needed mass flow rate for a hypothetical ion rocket, lifting off from Earth's surface and propelled with a Dual-Stage 4-Grid ion thruster. Data given: mass of the spaceship /...
- 79
3votes
2answers
323views
Can pyroxene and other silicon compounds be used as a theoretical spacecraft fuel?
I have been reading this patent, which led me to this paper. The first uses polysilane, which basically replaces the $\text{C}$ in a $\text{-R-C-R-}$ group, making an $\text{-R-Si-R-}$ group. I also ...
- 213
1vote
0answers
73views
Sources for values for realistic thrust calculation exercise?
I want to use this simplified equation to calculate the thrust of multiple different real engines: $$F = \dot{m} V_e + (p_e - p_0) A_e$$ Source: https://www.grc.nasa.gov/www/k-12/airplane/rockth....
- 11
1vote
1answer
1kviews
Spacecraft propulsion, Thrust, Delta V
For a spacecraft on an interplanetary mission (e.g. Mars), after deciding the propellant ISP value and Delta V required, how do you calculate the thrust required? $$F = \dot{m} V_e + (p_e - p_0) A_e$$ ...
0votes
0answers
228views
Ion Lifter Thrust Calculation Problem
I've recently started building an ion lifter. I tried calculating the thrust the lifter produces but I came to a value that is way to high for such a small lifter. I'm using a 40kV at 1800mA AC ...
5votes
2answers
728views
single thrust vs. multiple thrust
Does using one 5000 pound thrust engine give the same amount of thrust as five 1000 pound thrust engines? I am asking in terms of effectiveness not efficiency. Do the two different configurations ...
1vote
1answer
95views
What is the precision attitude estimation strategy for satellites, under impulsive thrust manoeuvres?
Satellites mostly rely on star trackers and gyros for precision attitude knowledge. Under impulsive thrust manoeuvres, I expect the star trackers to blur and provide no attitude knowledge. What is the ...
- 186
2votes
1answer
1kviews
Under-expanded nozzle at sea level - is it a problem?
I'm designing a solid rocket motor with a fixed pressure in the combustion chamber $p_{cc} = 70~bar$. When it comes to the choice of the right nozzle, I have to consider the proper expansion ratio, in ...
- 23
7votes
8answers
9kviews
Can we thrust a rocket from earth using electric power?
I wanted to know if we can thrust a rocket from earth using electric power? If yes, how and has anyone tried to do that?
- 1,055
20votes
2answers
4kviews
Where does the thrust act in a rocket engine and how is it transferred to rocket structure?
A rocket engine is basically a device that generates a high pressure inside the chamber and the pressure difference creates a force. A nozzle helps in effectively accelerating the flow and increases ...
- 4,499
12votes
1answer
575views
Do the propellants ionize in chemical rockets?
When combustion takes place in a chemical rocket (LOX/LH2), do the gases ionize due to high temperatures? If they do, how do they get around the problem? Ionization is a waste of energy I believe, ...
user12889
0votes
0answers
84views
Does releasing a gas propellant in a vacuum produce thrust? [Martian Spoilers] [duplicate]
I recently watched, The Martian and was wondering about some of the manoeuvres and propulsion in space. My question is, how is this possible? How can escaping an escaping gas (from a pressurised ...
- 117
5votes
3answers
1kviews
Could the Bloodhound Rocket Car be launched into orbit?
The Bloodhound SSC (Supersonic Car) currently being constructed to break the 1000 mph barrier is powered by a Hybrid Rocket (Solid fuel + HTP) and a Rolls-Royce EJ2000 Jet Engine: Considering the ...
- 6,261
6votes
0answers
163views
Relationship between part dimensions and performance of ion electrospray thruster
I got the relationship between power, thrust and specific impulse for an ion electrospray thruster as follows: $$P/T= 1/2 \times g_o \times I_{\mathrm{sp}}$$ Where: $P$ = power required (in Watts), $...
- 377
