Figured out the Bell Labs SPARTAN Envelope (I think) thanks to this line from:

Draft Memorandum From Secretary of Defense McNamara to President Johnson
Washington, December 22, 1966.
SUBJECT: Production and Deployment of the Nike-X

"The extended-range Spartan—a three stage missile with a hot X-ray, [less than 1 line of source text not declassified] capable of intercepting incoming objects at a range of over 400 nautical miles and at altitudes of up to 280 nautical miles. This missile makes use of some of the components of the old Nike-Zeus."
 

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SPRINT used a hot gas generator to produce hydraulic pressure; we know this because of a contract dispute in 1973:


The US government lost its case and Martin Marietta won the incentive fee of $542,700 for flight FLA-30 on 17 March 1969
 
C.) In doing so, you make ZEUS have potential as a Super Hercules with capabilities against air-breathing targets as well; allowing you to stock one missile at existing NIKE sites to do both missions (SAM/ABM).
Worth remembering here that NIKE 2 - before it became ZEUS - envisaged a system capable of SAM and ABM using a different final stage on the missile.
 
I believe DDR&E was using SPRINT capability against the hardest, worst possible threat -- a incoming MARV with 60G or more maneuver capability -- to define the defended zone of the system for their analyses; counting on the extreme classification of the system to cover their tracks.

I believe I have found the design parameters they were using for the original SPRINT design:

MIRV: A Brief History (COVD-1571) Pages 86-88 and 140

Pg 140

Ref 8
P. Mosher and J. Vullo, Penetration Capability of a Maneuvering Re-Entry Vehicle, Research and Advanced Development Division AVCO Corporation, Wilmington, Massachusetts, Document No. RAD-TM, 62-39, (1962) (Title U, Report SRD).

Ref 9
Preliminary Design Study for Maneuvering Re-Entry Vehicles (Maneuvering Re-Entry Vehicle Project—ARS Program), Research and Advanced Development Division AVCO Corporation, Document No. RAD-TM-62-62, (1962) (Title U, Report SRD).

Pg 86-88

NOTE 12: Excerpt from AVCO reports "Preliminary Design Study for Manuvering Re-Entry Vehicles" and "Penetration Capability of a Maneuvering Re-Entry Vehicle" (References 8 and 9.)

The W/C_D_A of this advanced Minuteman vehicle is 2500 lbs/ft² (12,205 kg/m²), and it has the capability of carrying out a 60 g normal acceleration turn. Although this study utilized the advanced Minuteman, a Titan II re-entry vehicle was designed on the Terminal Guidance Project which has the same W/C_D_A and turn capability. This entire investigation could thus apply to a Titan II vehicle.

The particular group of maneuvers considered are low-altitude maneuvers against a hard-point target. If it is assumed that the re-entry vehicle will have decoy coverage upon re-entry, any maneuver by the re-entry vehicle would immediately reveal its identity relative to the nonmaneuvering decoys. It is thus desirable from an offensive point of view to delay the commencement of a maneuver until the re-entry vehicle is below the survival altitude of the decoys. Further, when considering hard-point targets, the decoys must survive to fairly low altitudes to be effective, since commitment of the interceptor can be delayed until the re-entry vehicle reaches as low as 50,000 feet (15.24 km).
Consequently, the maneuvers considered in this investigation began at 50,000 feet (15.24 km) or below.

The terminal maneuvers start when the re-entry vehicle reaches a descent altitude of 50,000 feet (15.24 km) along a nominal ballistic trajectory. The particular ballistic trajectory selected for the study follows a minimum energy path for a range of 6200 nautical miles (11 470 km). However, the terminal maneuver capability is not a strong function of the ballistic range so the results are generally applicable. Figure 2* shows some of the variations in maneuvers attainable. The extended range or lob maneuver was designed to yield a steep impact angle with a range extension of roughly 100 nautical miles (185 km).

It is possible to get a much larger range extension, if desired, by simply delaying the start of the 60 g pulldown. The range decrease or tuck maneuver yields the greatest range shortening and is probably the most difficult to intercept since the time from the 50,000-foot (15.24 km) altitude to impact is the smallest.

Initially, the study is based on consideration only of variations of the tuck maneuver.

These can be seen in figure 3 which shows 60 g pulldown maneuvers from various altitudes along the ballistic trajectory below an altitude of 50,000 feet (15.24 km). Lateral maneuvers are not considered in this portion of the study.

The dates of the papers cited/copied (1962) fit very well with the SPRINT story, which is roughly:

1959-ish: The USAF begins funding studies on hardened site equipment and vulnerability as an outgrowth of USAF Study Requirement 79813, presumably to protect USAF ICBM sites.

Several studies were conducted for USAF's Rome Air Development Center by a number of aerospace companies including Martin Marietta, United Aircraft, Hughes, Raytheon, General Dynamics and Republic Aviation.

Collectively, these efforts were known as HARK (Hardened Re-Entry Kill) and were completed in 1961.

Shortly after HARK was completed, it was taken away from the USAF on the grounds that terminal BMD was an Army responsibility.

Next year, in 1962; the following study contracts were issued:

Army Ordnance Missile Command (Hardsite) -- Douglas, Martin, North American Aviation (1 OCT 1962)

Advanced Research Projects Agency (Hardpoint) -- Douglas, Hughes, Boeing

A year later in 1963, Martin got the SPRINT contract and Boeing the HIBEX contract.

It's important to remember that a lot of "assumptions" were made from 1959-1962 well ahead of actual testing of radars against actual ICBM re-entry vehicles in actual representative flight paths regarding how decoys would work, and how discriminable they would be IRL.
 
Thanks:), my understanding is that the higher the ballistic coefficient is the accurate the RV is.

This is largely correct, but it partially misses some important caveats.

Broadly speaking, the higher the ballistic coefficient (beta), the lower the amount of drag there is on the RV. As a consequence, as the beta increases, the amount of deceleration due to atmospheric drag decreases, which means that higher beta RV designs will spend less time in the atmosphere, will reach the ground faster, and will have higher velocities when they reach the ground (or the target detonation altitude).

This does not directly translate to improved accuracy. Instead, the improvement comes from how the higher velocity leads to a reduced time of transit through the atmosphere. Thanks to those two factors, the effects of high-altitude winds on accuracy are greatly lessened, as the RV has a much shorter window of exposure to them, and is more resistant to being pushed off course by said winds. While they are still a significant source of error, the amount of error they can introduce is significantly lessened relative to older designs with lower beta RVs.

However beta alone is not the be all and end all of accuracy. Improved RV designs with higher betas are usually co-packaged with other accuracy-improving technology, like improved nose tips, improved fuzes, improved radars, etc.

Nose tips are particularly critical, as it is immensely important that the nose tip can withstand the exceptionally high stress environment of high-speed reentry while wearing down as close to perfectly evenly as possible. This is far from a trivial task, and there are extreme challenges that they must be able to handle. Something as simple as raindrops turn into a lethal threat when you're entering the atmosphere at Mach 25, and while the RV will decelerate significantly, raindrops are still incredibly damaging at lower (typically still double digit) Mach numbers. They will quite literally eat holes into the nosetip as if it had bullets fired at it. The greatest threat is asymmetric ablation, which can send a RV far off course.

Improvements in nose tip design alone can eke out dramatic improvements in accuracy even without changing anything else about the design of the RV.

Similarly, fuze and radar design is an area where there was tons of room for further improvement. Much of the accuracy improvement in higher-beta RVs was actually due to improved fuzes and radars. The Mk21 RV uses radars of a totally different design from the previous Mk12 and Mk12A warheads. The Mk5 RB introduced the radar updated path length (RUPL) fuze, more commonly known as the "super fuze". Both the Mk21 and Mk5 introduced a wide variety of major improvements to the design of their fuzes relative to previous generations of RVs/RBs.

In the end, while it's true that all else being equal a RV with a higher beta will outperform a RV with a lower beta on accuracy due to atmospheric reentry errors, this is not the full picture, and it's rare for all else to be equal.

Even more importantly, you can backport improvements in nose tip and fuze technology to older lower beta RV designs to get dramatic improvements in accuracy without increasing the beta.

Just look at the W76, where:
  • The Mk5's RUPL fuze ("super fuze") has already been backported into the W76-1 via the Mk4A RB in order to provide a substantial accuracy improvement.
  • An improved nose tip design (the Shape Stable Nose Tip (SSNT) that was originally developed for the Mk5) is scheduled to be backported to the W76 RBs in a upcoming mod that will create the Mk4B RB (which is basically just a Mk4A RB that has had its nose tip replaced with the new SSNT). The new nose tip will significantly reduce reentry errors, and should therefore result in another substantial increase in accuracy.
These changes are introducing technology that was originally developed for ultra-high-beta RVs via the ABRES program, which resulted in the ABRV, which in turn was developed into the Mk21 RV (beta = 3000) and Mk5 RB (beta = 2500). And yet now this technology is being backported into the Mk4 RB (beta = 1800).

Sure, the Mk4 will never gain the improved resistance to high altitude winds that the Mk5 and Mk21 have, but it will gain enough improvement in accuracy from backporting the fuze and nose tip designs that the difference in beta won't really matter as much anymore. The introduction of the RUPL alone was enough to give the Mk4 a credible hard target counterforce capability despite its much lower yield. The introduction of the SSNT will only further enhance the lethality of the Mk4.

So yes, higher beta designs do tend to have better accuracy, but it's not just from the higher beta. It's from the whole package. If you threw a Mk4's fuze and nose tip into a Mk5, it'd have pretty atrocious accuracy despite the far higher beta. Heck, the Mk21 lacks a RUPL, so even though it has even higher beta than the Mk5, it's at a disadvantage from a fuzing perspective, and therefore it is significantly less accurate than it could be. The Mk21A mod will integrate a new fuze with RUPL capabilities into the Mk21, which promises to substantially increase the accuracy of Mk21 RVs without any increase in beta.
 
I suppose one way to have a nose-tip that is highly resistant to rain-drop damage and ablate evenly would be for one made out of Tungsten or Tungsten-alloy.
 
What about Osmium (The densest element) with a Tungsten (The element with the highest melting point) jacket?
Not sure it'd help. What we want here is a hard and not-brittle nose cap. We don't really need the extra density.
 

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