260" SRM - as an ICBM

I can't imagine what it'd take to thump those things upwards.

They would have more general overall utility to humanity than SLBMs that can only kill.
 
publiusr said:
I can't imagine what it'd take to thump those things upwards.

They would have more general overall utility to humanity than SLBMs that can only kill.
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not true.
a. older SLBM's are used as sounding rockets and target launchers.
b. 260" has no utility
 
publiusr said:
I can't imagine what it'd take to thump those things upwards.
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A gas generator that makes roughly the total stack weight in thrust for a fraction of a second, if I understand the basics correctly.

Which sounds terrifying but isn't that bad since you use a superexpansion rocket nozzle to get the temps and pressures down.
 
Scott Kenny said:
A gas generator that makes roughly the total stack weight in thrust for a fraction of a second, if I understand the basics correctly.
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You presumably need to exceed the stack weight, that being how physics works, and provide enough energy to lob the thing out of the silo to whatever height you've deemed safe for main stage ignition. It's presumably similar to an interior ballistics calculation.
 
Yellow Palace said:
You presumably need to exceed the stack weight, that being how physics works, and provide enough energy to lob the thing out of the silo to whatever height you've deemed safe for main stage ignition. It's presumably similar to an interior ballistics calculation.
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That "enough energy to lob the thing clear" part usually comes from further expanding gasses continuing to push.

I'd also assume that it's basically an interior ballistics calculation.

The gas generators for a Trident are about the size of a water heater. So yes, whatever you'd need for a 260" monster rocket would be a lot bigger than that, but mostly in terms of diameter not length. So, more like a hot tub full of solid rocket fuel instead of a water heater.
 
Doable then.

I'd like at least 4 in Florida for asteroid intercept, with warheads that can be swapped out below ground in case of another Oumuamua...a small probe and upper stage.

Asteroid nuke

On solids

Cracks

Targeting

Nosecones

In flight retasking

Space logistics

Debris
 
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The words "Florida" and "below ground" do not belong together. If you want some form of underground basing, do it somewhere where the water table is lower.
 
Grey Havoc said:
It was implied to be a Saturn V derivative but I haven't been able to dig up anything more so far.
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I am wondering if anyone has been able to find any information about the TABAS proposal?

TABAS sounds to grandiose to be a serious 1980s era proposal, it sounds more like something from the 1960s, or like it was something Jerry Pournelle cooked up to frighten a journalist. As far as I am aware this is the only proposal to weaponize the Saturn V and I haven't seen it talked about in any of the Saturn histories.

The only source I've been able to find external to these posts is in Christy Campbell's Airland Battle: 2000, I'm laughable amaturish at research so I haven't had much luck. I am trying to reach out to Christy Campbell to see if he still has his notes (Quite the tall ask) but so far I haven't been able to find any contact info for him.

*Edit: I've reached out to him and I am hoping to hear back
 
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For comparison, there is also the proposed but rejected monoblock configuration of the UR-500:
1747520779028.png
SOURCE: http://www.astronautix.com/m/monoblockur-500.html

Payload: 12,000 kg (26,000 lb). Thrust: 8,119.80 kN (1,825,404 lbf). Gross mass: 543,400 kg (1,197,900 lb). Height: 54.00 m (177.00 ft). Diameter: 6.20 m (20.30 ft). Apogee: 200 km (120 mi).

Stage 1. 1 x UR-500 Monoblok Stage 1M. Gross Mass: 367,360 kg (809,890 lb). Empty Mass: 25,560 kg (56,350 lb). Thrust (vac): 8,989.700 kN (2,020,965 lbf). Isp: 310 sec. Burn time: 115 sec. Isp(sl): 280 sec. Diameter: 6.20 m (20.30 ft). Span: 6.20 m (20.30 ft). Length: 30.00 m (98.00 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: 8D43 + 11D43.

Stage 2. 1 x UR-500 Stage 2. Gross Mass: 137,700 kg (303,500 lb). Empty Mass: 16,000 kg (35,000 lb). Thrust (vac): 3,183.200 kN (715,612 lbf). Isp: 320 sec. Burn time: 119 sec. Diameter: 4.10 m (13.40 ft). Span: 4.10 m (13.40 ft). Length: 10.90 m (35.70 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: RD-0213.

Stage 3. 1 x UR-500 Stage 3. Gross Mass: 23,940 kg (52,770 lb). Empty Mass: 2,180 kg (4,800 lb). Thrust (vac): 613.110 kN (137,833 lbf). Isp: 320 sec. Burn time: 110 sec. Diameter: 4.10 m (13.40 ft). Span: 4.10 m (13.40 ft). Length: 3.70 m (12.10 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-0212.
 
Boldgambit said:
I am wondering if anyone has been able to find any information about the TABAS proposal?

TABAS sounds to grandiose to be a serious 1980s era proposal, it sounds more like something from the 1960s, or like it was something Jerry Pournelle cooked up to frighten a journalist. As far as I am aware this is the only proposal to weaponize the Saturn V and I haven't seen it talked about in any of the Saturn histories.

The only source I've been able to find external to these posts is in Christy Campbell's Airland Battle: 2000, I'm laughable amaturish at research so I haven't had much luck. I am trying to reach out to Christy Campbell to see if he still has his notes (Quite the tall ask) but so far I haven't been able to find any contact info for him.

*Edit: I've reached out to him and I am hoping to hear back
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The only reference I've found about it was in an issue of Military Technology back in the 90s. I'll see if I can dig it up over the holiday weekend next week. And it wasn't much. Said more in passing when describing a different system.
 

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