Missile defense system research and restoration

25/04/2022

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23/04/2022

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23/04/2022

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05/04/2022

Nike Zeus
The Nike Zeus missile has a very interesting history. Two major versions of it are known, with a third version produced for ASAT duties. The same missile was further developed, but was renamed as Spartan as the radars and deployment changed during the 1960s.

Nike Zeus A
Nike Zeus A ready for launchThe Nike Zeus A is aerodynamically very similar to the Nike Hercules, just scaled up. However, the Nike Zeus A was designed for a very different mission - it was designed to perform an interception of ballistic missile RVs at high altitude. Like Nike Hercules, it was a two stage missile but instead of using the Nike Ajax booster, a new booster was used which was the largest single chamber solid rocket motor produced in the US at that time delivering over 450 000lb of thrust.

The Nike Zeus A had a very short life as it only had a small number of launchers before being replaced by the Nike Zeus B. As a result, some sources claim that this was infact a flight test article for the booster and not actually a Nike Zeus missile at all. I find this hard to understand as the 2nd stage is new, or at least the fins have been redesigned (especially when comparing it to a Nike Hercules), indicating some design work had taken place for this missile.

The capability of the missile was constrained by the 200 mile range restriction that was issued by Secretary of Defence Wilson in 28 November 1956. This restriction was rescinded 12 months later once Sputnik 1 had orbited the earth. This then allowed the US Army to then develop the Nike Zeus B which overcame some of the limitations already present and known in the Nike Zeus A.

Launch History
All launches took place at White Sands Missile Range.

Nike Zeus A Launch
# Date Comment
1 26 August 1959 Fist stage only was live. Exploded shortly after launch.
2 14 October 1959 First stage only was live. Successful.
3 16 December 1959 Both stages live. Failed.
4 3 February 1960 Successful.
5 9 March 1960 Full Range test. Successful.
6 25 May 1960 Successful.
Specifications
Length: 13.28m (44ft 3in)
Diameter: 0.91m (3ft)
Span: 3m (9ft 9.6in)
Weight: 5,000kg (11,000lb)
Range: 320km (200 miles)
1st Stage Motor: Thiokol TX-135 450,000lb thrust
2nd Stage Motor: Thiokol
Guidance: Radio command
Warhead: Nuclear, 20kt
Nike Zeus B
Nike Zeus B was a far more capable missile than the A version due to a number of factors. It had a greater range, it was a three stage missile and it was designed to intercept targets outside the atmosphere. The main reason for this missile being developed was due to the dropping of the range restriction that had been imposed during 1956/7. By increasing the range, the missile could defend a much larger area which meant that fewer installations were required which provided some cost savings while still maintaining a defence.

Nike Zeus B Mockup
The first stage was the same as that of Zeus A, but everything after that was new. The second stage had a slightly smaller diameter than the booster, while the third stage was slightly smaller again. The large aerodynamic fins that were so prominent on the Zeus A sustainer were gone, and replaced with small vanes at the top of the missile which provided some control while in the atmosphere. Once the missile had left the atmosphere control was obtained through the 3rd stage motor. Target destruction was obtained through the use of a nuclear warhead. This warhead was tested during 1962 at Christmas Island in the Pacific Ocean.

With the Nike-X ABM system, studies went into an extended range version of the Zeus B, and that missile was called Nike Zeus EX. It was renamed as Spartan when Nike-X was renamed as Sentinel in 1967.

Launch History
Due to the improved performance of the missile, it was no longer possible to test the missile at full range at White Sands. The Naval Test Range at Point Mugu was upgraded with the necessary radars and equipment to allow launches to take place there. However, Pt Mugu also proved unsatisfactory due to range safety restrictions which caused a number of good missiles to being destroyed early in their flights.

Suitable sites were then investigated in the Atlantic Range area, but due to the sensitive nature of the missile firings, using foreign countries for the testing was deemed unacceptable. Attention then shifted to the Pacific, and Kwajalein was chosen. On February 12, 1959 the DoD aproved a test program for Nike Zeus which used Kwajalein as the launch site for the missile.

Nike Zeus B Launch
# Date Comment
1 28 April 1960 Only 1st stage was live. Successful.
Testing of two stage versions completed in summer of 1961.
9 September 1961 First 3 stage flight. Tested from Point Mugu Naval Station.
14 December 1961 Nike Zeus intercepts a Nike Hercules missile at WSMR.
19 July 1962 Intercepted an Atlas D RV. Zeus launched from Kwajalein, Atlas from Vandenberg. Passed within 2km of RV.
22(12?) December 1962 Nike Zeus intercepted an RV (Atlas D from Vandenberg?) and passed within 22 metres.
End 1963 A total of 13 RVs had technically been destroyed. Number of launches is unknown.
Specifications
Length: 14.73m (48ft 4in)
Diameter: 0.91m (3ft)
Span: 2.44m (8ft)
Weight: 10,350kg (22 800lb)
Range: 400km (250 miles)
Ceiling: 280km (174 miles) - altitude obtained during ASAT test
1st Stage Motor: Thiokol TX-135, 450,000lb thrust
2nd Stage Motor: Thiokol TX-238
3rd Stage Motor: Thiokol TX-239
Guidance: Radio command
Warhead: W-50 Thermonuclear, 400kt
Nike Zeus DM-15S
In April/May 1962 Defence Secretary McNamara agreed to a US Army request to reorient the Nike Zeus missile into an anti-satellite program. This program was called Project 505 with a code name of "Mudflap".

To achieve this, a modified Nike Zeus missile was developed designated DM-15S. To allow the high altitude, long rage interception, a number of changes were made to the missile. These changes included a two stage hydraulic pump, a higher performing booster propellant and a longer life battery (5 minutes instead of 2).

A modified DM-15B was tested at White Sands in December 1962 and successfully intercepted a fix point in space at 100 nautical mile altitude. A DM-15S was launched on 15 February 1963 and it intercepted a fix point in space at an altitude of 151 nautical miles. The first attempted interception of a simulated satellite took place on 21 March 1963 at an altitude of 112 nautical miles. The MTR failed to track the missile and the launch was considered a failure. Success was finally achieved on 24 May 1963 against a real target. An Agena D, which had special instruments installed to measure the miss distance, was tracked and intercepted by a DM-15S.

On 27 June 1963 McNamara ordered that a Nike Zeus missile be kept ready at all times at Kwajalein complete with a live nuclear warhead. The US thus had an operational ASAT capability. Although not directly related to the Nike Zeus, the US Air Force had also deployed in the ASAT role Thor IRBMs which were based at Johnston Island. Despite performing the same mission, the two missiles complemented each other. The Nike Zeus was a faster reacting missile, but was limited by its range. The Thor was a slower reacting missile due to its liquid propellants (and during the last part of its life as an ASAT missile, its reaction time was measured in weeks), but Thor had a much greater range. McNamara eventually believed that the two ASATs competed with each other and only one should be deployed. Thus in May 1966, Program 505 was declared redundant and it was directed to shut down thus leaving the Thors to perform the ASAT role.

On a side note, Hurricane Celeste caused extensive damage to the facilities for the Thor ASATs in August 1972 and repairs were made. Once put back on active service, it was found that the damage was more extensive than original thought and in December 1972 the Thors were phased out from operational use.

Launch History
Launch # Date Location Comment
1 17 December 1962 White Sands Success. Intercepted point in space at 100nm altitude.
2 15 February 1963 White Sands Success. Intercepted point in space at 151nm altitude.
3 21 March 1963 Kwajalein Failure. MTR failed to track the missile.
4 19 April 1963 Kwajalein Failure. Beacon loss at 30sec before intercept.
5 24 May 1963 Kwajalein Success. Target was a specially instrumented Agena D.
6 6 January 1964 Kwajalein Success - this was against a simulated satellite at 93 nautical mile range and at an altitude of 79 nautical miles.
7 ?? April 1964 Kwajalein Success - this was to test communications with the missile, exo-atmospheric beam intercept and exit altitude control.
8 ?? June 1965 Kwajalein Success
9 ?? June 1965 Kwajalein Success
10 ?? July 1965 Kwajalein Success
11 ?? July 1965 Kwajalein Failure
12 13 January 1966 Kwajalein Success - this was launched by an operational missile crew.
The Programs: Early Years Nike Zeus Nike-X Sentinel Safeguard

The Hardware: Nike Zeus Nike-EX/Spartan Sprint Radars Computers

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Last Modified: 3-Feb-2012

22/03/2022

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14/03/2022

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13/03/2022

Radar Course Directing Central (RCDC) was the technical name for the Integrated Fire Control (IFC) area of a Nike Missile Site. All command and control of the missile, to include its firing, originated from this area.



Section 1 (C) FUNCTIONAL DESCRIPTION

17 (U). General

The radar course directing central (RCDC) consists of the ground guidance equipment located in the battery control area. The functional relationships of the major subsystems of the RCDC are illustrated in figure 9. Each block represents a functional subsystem of the RCDC except the blocks that are shown with broken lines. The tactical control system relays tactical control data, consisting of information and orders, among all areas of the Improve Nike-Hercules System or the Nike-Hercules ATBM System.

18 (C). Functional Analysis

Note. The function of the RCDC in the Nike-Hercules ATBM System is the same as that of the RCDC in the Improved Nike-Hercules System.

a. In a surface-to-air mission, the high power acquisition radar (HIPAR) (f`ig 9). the auxiliary acquisition radar (AAR) and the low power acquisition radar (LOPAR) transmit pulsed RF energy form continuously rotating. highly directional antenna. An object in the path of the transmitted RF energy reflects a portion of the energy back to the antenna. The acquisition radar system converts the reflected RF energy into video for display on cathode-ray tube indicators. The radar select circuit permits selection of either HIPAR/AAR or LOPAR video for display.

a.1. Anti-jam display (AJD) facilities are provided for both the HIPAR/AAR and the LOPAR systems. In the presence of enemy jamming, the AJD allows the target to remain visible on the cathode-ray tube indicators.

b. An identification friend or foe (IFF) system also is associated with each of the two acquisition radar systems. When IFF identification of an unidentified object is required, the IFF system transmits IFF interrogation pulses to the unidentified object. If the object is a friendly aircraft with IFF equipment, IFF response pulses are transmitted by the aircraft and received by the IFF system. The IFF response pulses are converted into IFF video for display on the cathode-ray tube indicators

09/03/2022

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09/03/2022

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03/03/2022

The radar course directing central (RCDC) consists of the ground guidance equipment located in the battery control area. The functional relationships of the major subsystems of the RCDC are illustrated in figure 9. Each block represents a functional subsystem of the RCDC except the blocks that are shown with broken lines. The tactical control system relays tactical control data, consisting of information and orders, among all areas of the Improve Nike-Hercules System or the Nike-Hercules ATBM System.

18 (C). Functional Analysis

Note. The function of the RCDC in the Nike-Hercules ATBM System is the same as that of the RCDC in the Improved Nike-Hercules System.

a. In a surface-to-air mission, the high power acquisition radar (HIPAR) (f`ig 9). the auxiliary acquisition radar (AAR) and the low power acquisition radar (LOPAR) transmit pulsed RF energy form continuously rotating. highly directional antenna. An object in the path of the transmitted RF energy reflects a portion of the energy back to the antenna. The acquisition radar system converts the reflected RF energy into video for display on cathode-ray tube indicators. The radar select circuit permits selection of either HIPAR/AAR or LOPAR video for display.

a.1. Anti-jam display (AJD) facilities are provided for both the HIPAR/AAR and the LOPAR systems. In the presence of enemy jamming, the AJD allows the target to remain visible on the cathode-ray tube indicators.

b. An identification friend or foe (IFF) system also is associated with each of the two acquisition radar systems. When IFF identification of an unidentified object is required, the IFF system transmits IFF interrogation pulses to the unidentified object. If the object is a friendly aircraft with IFF equipment, IFF response pulses are transmitted by the aircraft and received by the IFF system. The IFF response pulses are converted into IFF video for display on the cathode-ray tube indicators.

c. Tactical control data from an Army Air Defense Command Post (AADCP) is supplied through either the fire unit integration facility (FUIF) or the battery terminal equipment (BTE) to the tactical control system. If the tactical control data received by the tactical control system from the AADCP or IFF indicates that the unidentified object is an enemy aircraft or missile, the object is designated as a target. Designated target position data, derived from the selected acquisition radar display, is supplied to the target tracking radar (TTR) system.

22/02/2022

Credit Hours . . . . . . . . . . . . . . . . . . . . . . . . Two
TEXT
SECTION I. COMPUTER STEERING PHASE.
1. PURPOSE. Computer-controlled flight starts approximately 7.3 seconds after the missile is fired and ends with missile burst. The two track radar systems supply continuous target and missile position informa- tion to the computer. From a comparison of differences between the missile and target information, the computer issues directional commands to the missile. The commands are designed to make the missile intercept the target by following the course that gives the quickest possible intercept. The quantities for solving the fire control problem are target and missile positions and velocities. From these quantities the computer determines the correct missile course and necessary guidance orders to bring the missile to this course. The missile course is correct as long as the target’s course or speed does not change. If the target’s course or speed changes, the required missile course also changes, and the computer issues new steering orders to the missile. During an engagement, the computer operates continuously to keep the missile as close as possible to the latest correct course.
2. BLOCKDIAGRAM ANALYSIS.
a. Closingvelocity solver(fig 1).
(1) General. Five inputs are fed into the
closing velocity solver: radar-to-radar parallax informa- tion, distance to the target from TTR, distance to the missile from MTR, time to intercept as determined by the “time-to-intercept’’ computer, and ballistics fall-in. With these inputs the closing velocity solver determines the rates at which the distance between the target and missile should diminish so that the missile may intercept the target in the predicted time to intercept (T).
(2) Radar-to-radar parallax. The dis- placement of the MTR from the TTR is known as radar-to-radar parallax. This parallax distance must be considered because target distances are measured from the TTR and missile distances are measured from MTR. The radar-to-radar parallax voltage allows the closing velocity solver to compensate for differences in TTR and MTR emplacement. The parallax information is handset into the computer by means of three variable resistors which allow the computer to see the MTR and TTR as if it were at the same location.
(3) Distance to target and missile. Since all distance inputs to the closing velocity solver are in rectangular earth coordinates, the velocity solver can easily determine the remaining distance the missile must travel by subtracting the missile distance and radar-to- radar parallax from the target distance. These distances
MMS 150,7-P1

15/02/2022

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06/02/2022

In a surface-to-air mission, the high power acquisition radar (HIPAR) (f`ig 9). the auxiliary acquisition radar (AAR) and the low power acquisition radar (LOPAR) transmit pulsed RF energy form continuously rotating. highly directional antenna. An object in the path of the transmitted RF energy reflects a portion of the energy back to the antenna. The acquisition radar system converts the reflected RF energy into video for display on cathode-ray tube indicators. The radar select circuit permits selection of either HIPAR/AAR or LOPAR video for display.

04/02/2022

https://www.jber.jb.mil/Services-Resources/Environmental/Nike/Missile/

The official website for the Joint Base Elmendorf-Richardson

01/02/2022

American missilery dates from January 1945 when the Chief of Ordnance authorized Bell Telephone Laboratories Inc. to make a formal study for a complete, workable antiaircraft guided missile capable of combating high-speed and high-flying aircraft. The Nike program--named after the Greek Goddess of Victory- became a reality from this and in time gave America her first family of missiles.
In 1954, the US Army deployed the world’s first operational, guided, surface-to-air missile system. This system, the Nike Ajax, was conceived near the end of World War II and developed during the early years of the Cold War. SAM-A-7 was the designation before 1962; MIM-3, 3A were the designations used after 1962. With an increasing perception of a direct Soviet bomber threat to the American mainland, the Army rushed Nike Ajax into production and deployed the missile system around key urban, military, and industrial locations.

17/01/2022

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09/01/2022

Radars
Nike Zeus Radars
The Nike Zeus system was based on similar concepts to the Nike Ajax and the Nike Hercules systems. The first radar was the Zeus Acquisition Radar (ZAR). One of its many features was the main Luneberg lens receiver aerial which weighed over 1000 tons. Due to its shear size, it was actually built as two individual components, a transmitter and a receiver. The transmitter was triangular in shape, with all three faces transmitting simultaneously as it rotated. Surroung the transmitter, was a 27.5m (90ft) high stainless steel "beam forming" fence. Located outside this fence was the ZAR receiver. This was a 25m (85ft) diameter antenna.

Despite the great size and capability of this radar, it still could not discriminate between an actual RV and a decoy. This job fell to another radar, which was strangely called the Discrimination Radar (DR). This was contained in a dome on a large square building with dual fences around it. This radar was one of the first to have a hybrid mechanical/electronic scanning capability. No one company could produce such monsters and RCA, Sperry and GE all made contributions towards their development.

Once the RV had been detected, the relevant tracking information was then passed to another two radars. The target-track radar (TTR) and the Missile track radars (MTR). These two radars are not as spectacular as the ZAR and DR and were essentially just scaled up versions of the equivalent radars used in the Nike Hercules missile batteries. The TTR was used to track the target on its inbound trajectory, while the MTR was used to follow the path of the Nike Zeus missile. Information from both radars were fed into a computer which determined the best flight path for the Nike Zeus missile to intercept the incoming RV.

27/12/2021

The Nike Missile Air Defense System

The Nike-Ajax was the first ground-based supersonic anti-aircraft missile system to become operational in the United States. The Nike missiles were deployed at sites in a circular pattern around key American industrial and military locations. The first Los Angeles area Nike-Ajax battery was emplaced in the mountains above Malibu in 1954. By 1958, there were 16 Nike-Ajax launch sites guarding the greater Los Angeles area, protecting an area of some 4,000 square miles. The Los Angeles Defense area was manned by several battalions of US Army Regulars and National Guardsman, under the command of the 47th Air Defense Brigade from 1954 to 1969.
Nike missiles were launched from a self-contained launch area. Each site was equipped with two or three launching platforms each with an underground storage magazines, an elevator and four missile erectors. The missiles were stored

Nike Hercules (left) and Nike Ajax at Site LA 88,
Chatsworth 1960s. US Army Photograph

underground on rails and were brought to the surface by an elevator. Once on the surface, they were pushed on rails to an erector and with the proper electrical and hydraulic connections completed, raised to an angle of about 85 degrees for firing.

The Nike missiles employed the "command guidance" system in which the major control equipment was ground-based and not part of the expendable missile. The missiles were guided from a control area located at least 1000 yards from the launch area. It contained the radar equipment for acquiring and tracking the target and missile. Separate radars simultaneously located and tracked both the target and the Nike missile. Data from these radars was fed to the electronic computer which sent "commands" to the missile in flight to guide it to the target.

The newer, more powerful Nike-Hercules missiles replaced the Nike-Ajax during the period 1958-1963. Nike-Hercules had the capability of being armed with a nuclear warhead. The Hercules was completely powered by solid fuels, eliminating the troublesome and dangerous liquid fueling procedure of the Nike-Ajax. Nike-Hercules also brought with it improved acquisition radar systems and an improved command coordinating system. The Nike Hercules were installed into modified Nike-Ajax sites in the Los Angeles area. Only 9 of the original 16 sites were converted to fire the Nike-Hercules missiles.

The Nike Hercules was designed for defense against attack by large formations of bombers. As the perceived threat changed from bomber attack to missile attack, the usefulness of the Nike Hercules diminished. On 4 February 1974, the Army ordered all existing US Nike batteries were inactivated.

Specifications

Nike Ajax

Nike Hercules

Designation MIM-3A MIM-14B
Weight gross 2,259 pounds 10,711 pounds
Length 392 inches 478 inches
Cost (1958) $19,300 $55,200
Warheads 3 High Explosive 1 High Explosive or 1 Nuclear
Range 30.7 miles 96.3 miles
Altitude 60,000 feet 100,000 feet
Speed Mach 2.3 Mach 3.65
Flight time 1 minute 2 minutes

27/12/2021

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24/11/2021

https://warbirdsnews.com/warbird-articles/abandoned-nike-missile-bases-united-states.html

Abandoned Nike Missile Bases of the United States

22/11/2021

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11/11/2021

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01/11/2021

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24/10/2021

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24/10/2021

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12/09/2021