Thor was the United States's first operational ballistic missile. It was deployed with thermonuclear warheads in the U.K between 1959 and 1963. It went on to spawn a string of space launch vehicles. Its decendants fly to this day as the Delta series of rockets.
Development of the Thor was initiated by the US Air Force in 1954
as a Tactical Ballistic Missile. The goal was a missile system that
could deliver a nuclear warhead over a distance of 1150 to 2300 miles
with a CEP of 2 miles. This range
would allow Moscow to be hit from a launch site in the U.K
The initial design studies were headed by Cmdr. Robert Truax
(US. Navy) and Dr. Adolph K. Thiel (Ramo-Wooldridge Corp, formerly
Redstone Arsenal). They refined the specs to an IRBM with:
Initial development as an IRBM
On November 30, 1955 three companies were given one week to bid on the
project: Douglas, Lockheed, and North American Avation.
They were asked to create "a management team that could pull together
existing technology, skills, abilities, and techniques in 'an
unprecedented time.'" On December 27, 1955 Douglas Aircraft
Corporation was awarded the prime contract for the airframe and
integration. The Rocketdyne division of North American Avation
was awarded the engine contract, AC Spark Plug the primary inertial
guidance system, Bell Labs the backup radio guidance system, and
General Electric the nose cone/reentry vehicle.
Douglas further refined the design by choosing bolted tank bulkheads (as opposed to the initially suggested welded ones) and a tapered fuel tank for improved aerodynamics. The engine was developed as a direct descendant of the Atlas [[MA-3 (rocket engine)|MA-3]] booster engine. Changes involved removal of one thrust chamber and a rerouting of the plumbing to allow the engine to fit within the smaller Thor boat-tail. Engine tests where being performed as of March 1956. The first engineering model engine was available in June, followed by the first flight engine in September. Engine development was complicated by serious turbopump problems. Early Thor engines suffered from what was known as "Bearing Walking', whereby the turbopump bearings rotate axially within their housing, causing it to wear out and the bearings to seize.
Thor test launches were to be from LC17 at Cape Canaveral. The
development schedule was so compressed that plans for the [[Atlas
(rocket)|]] bunker were used to allow the completion of the facility in
time. Nevertheless pad LC17-B was just ready for the first test
flight.
The first flight of the Thor IRBM was on 25 January 1957. The first
airframe, number 101 was delivered in October of the previous year.
The vehicle reached a apogee of 6" whereapon contamination destroyed a
LOX supply valve causing the engine to lose thrust. The Thor slid
backwards through the launch ring and exploded on contact with the
thrust deflector. Serious pad damage occurred.
The second Thor flight (102) lasted 35 seconds after an April 1957 launch.
It was ended by a range safety officer who acted on faulty data from a
readout which showed the missile heading inland over florida.
Thor vehicle 103 (May 1957) exploded on the pad during tanking due to
a faulty main fuel valve resulting in tank overpressurization leading
to tank rupture.
Thor vehicle 104 (Aug 1957) broke up after 92 seconds due to a loss of
guidance.
Thor vehicle 105 (20 September 1957), 21 months after the start of
construction, flew 1100 miles downrange. Estimated range without the
extra load of the R&D instrumentation was 1500 miles.
1957 saw five more flights, the longest of which covered 2700 miles.
Thor was deployed to the UK starting in August 1958.
Thor was noted as forming a good basis for a space launch vehicle
early in its development.
The first space launch type of mission Thor was asked to perform was
the testing of the Atlas reentry vehicle. For these three tests a
Thor core stage was topped by a second stage named Able using the
Aerojet AJ-10-40 engine from the Vanguard second stage. The first
such launch, 116, was lost due to turbopump failure of the main
engine. The results of two succeeding attempts are unknown to this
author.
Thor vehicle 127 was a three stage Thor-Able-Star. The Able stage
from the Atlas reentry vehicle tests was upgraded (to become the Able
I) and topped with a third stage consisting of an unguided Altair
X-248 solid rocket motor. The mission was to place the 84lbs Pioneer
spacecraft into lunar orbit where it would take pictures of the lunar
surface with a TV camera. The mission ended prematurely at 77 seconds
after launch due to yet another turbopump failure.
Thor formed the core of the Thor-Agena vehicle used to launch the
United State's first spy satellites as part of the Corona program.
In January of 1959 the newly formed [[National Aeronautics and Space
Administration]] released a report entitled "The National Space
Vehicle Program". This report addressed the nation's space launch needs.
"Our approach up to this time has been much too diverse in that we
fire a few vehicles of a given configuration, most of which have
failed to achieve their missions, and then call on another vehicle to
take the stage. In this situation no one type of vehicle is tested
with sufficient thoroughness and used in enough firiing to achieve a
high degree of reliability"
The report proposed four vehicles to form the core of the US spacefleet:
NASA let the original Delta contract to Douglas in April of 1959 for
12 vehicles of this design:
{| border="1" cellspacing="0"
|-
|1 || 13may60 9:16pm gmt. || Payload: echo 1. pad 17a. Good first stage. second stage attitude control system failure. vehicle destroyed.
|-
|2 || 12aug60. || good flight. echo 1A placed into 1035 mile, 47degree inclination orbit.
|-
|3 || 23nov60. || Tiros 2. good lfight.
|-
|4 || || explorer 10. placed into elliptical 138,000 mile orbit. 78lbs.
|-
|5 || 12july61. || tiros 3.
|-
|6 || 16aug61. || explorer 12 Energentic Perticle Explorers. EPE-1. highly elliptical orbit.
|-
|7 || 8feb62. || tiros 4.
|-
|8 || 7mar62. || OSO-1 (orbiting solar observatory). 345 mile, 33 degree orbit.
|-
|9 || 26apr62. || Ariel 1. Ariel 1 was seriously damaged by Starfish Prime
|-
|10 || 19jun62. || tiros 5
|-
|11 || 10jul62. || Telstar 1. Also damanaged by Starfish Prime.
|-
|12 || 18sep62. || tiros 6
|}
13. EPE2
14. EPE3
15. 13dec62. Relay 1, second nasa communications sat. nasa's first active one.
16. 13feb63. pad 17b. Syncom 1. Thiokol Star 13B solid rocket as apogee kick motor.
20. july63? Syncom 2. Geosyncronous orbit, but inclined 33degrees due to the limited performance of the Delta.
25. 19aug64. Syncom 3. First true Geosyncronous sat.
26. Intelsat 1
First Delta E. 6nov65. launches GEOS 1.
1. 14dec66. biosatellite 1.
2. 7sep67. biosatellite 2
First operational american ballistic missile.
Missile initiated in 1954 as a Tactical Ballistic Missile with range between 1150-2300 miles CEP 2 miles (thus it could reach Moscow from a launch site in the UK).
1955 became IRBM.
Initial IRBM design study headed by Cmdr. Robert Truax (US. Navy) and Dr. Adolph K. Thiel (Ramo-Wooldridge Corp, formerly Redstone Arsenal).
Initial numbers:
XSM-75 -> WS-315A -> Thor.
Tapered fuel tank to improve aerodynamics, bolted tank bulkheads.
MB-3 engine is a direct decendant of the Atlas MA-3. Remove one thrust chamber, rerouted plumbing. Turbopump development problems. Engine tests as of march 56 at Santa Susana Mountains. First example engine in June. First flight engine in Sept 56.
101. First airfram, 101, Oct 56. First launch from LC17-B. Pad B completed just barely before flight. Atlas blockhouse design borrowed. Pad A not complete at first launch. First flight 25 jan 57. Apogee of 6 inches. Contamination destroyed a LOX supply valve to fail, causing engine to lose thrust. Vehicle slid back down onto pad and exploded on thrust deflector below launch table.
102. apr 57. 35 second flight. ended by range safety officer working from a faulty instrament which indicated an inbound flight, not outbound.
103. may 57. Exploded on pad during tanking due to faulty main fuel valve resulting in tank overpressurization leading to tank rupture.
104. aug 57. 92 seconds. broke up due to loss of guidance.
105. 20 sep 57. 21 months after start of construction. flew 1100 miles downrange. Removing weight of R&D instruments, range would be 1500 miles.
Later flights in 57 (10 all total) reached 2700 miles.
Deployed to UK in aug 58.
Atlas reentry system. Thor flew first, so tested atlas reentry vehicle designs.
June 4, 1962?
A nuclear warhead atop a Thor rocket booster falls into the Pacific Ocean when the booster has to be destroyed.?
June 20, 1962 ?
A second Thor rocket booster fails, and the nuclear device falls into the Pacific. ?
9jul62. Starfish Prime Event. Thor missile 195 launches Mk4 renentry vehicle containing W49 thermonuclar warhead to an altitude of 248 miles. Warhead detonates at altitude with yield of 1.45 MT. Dominic-Fishbowl.
{| border="1" cellspacing="0"
|-
!
! Thor !! Thor Able !! Thor Able Star !! Thor Delta !! Thor Agena A (Thor Hustler) !! Thor Agena B !! Thor Altair
|-
! Stage 1
| Thor
116. Thor-Able. Carried Aerojet AJ-10-40 using Vanguard second stage engine (UDMH/inhubited white fuming nitric acid). Called Able. Three vehicles used to test GE advanced Atlas reentry vehicle. 116 lost due to turbopump failure in thor main engine.
"Bearing Walking" - movement of turbopump bearings axially in their mountings.
127. Thor-Able-Star. Three stage, Thor, Able I (upgraded), Altair X-248 solid upperstage. 84lbs Pioneer. Enter lunar orbit, take pictures with Tv camera. Launch 17 aug 58, exploded at 77 sec due to turbopump failure.
jan 59, The National Space Vehicle Program. "Our approach up to this ptime has been much too diverse in that we fire a few vehicles of a given configuration, most of which have failed to achieve their missions, and then call on another vehicle to take the stage. In this situation no one type of vehicle is tested with sufficient thoroughness and used in enough firiing to achieve a high degree of reliability."
Proposed four vehicles:
april 59 nasa and douglas sign contract for development and production of 12 Delta launch vehicles.
Stage 1: Modified thor irbm. MB-3 Block I RP-1/LOX producing 152,000lbf. gas generator also lox/rp-1, exhaust out of pipe next to nozzle. Gimble mounted, two vernier for roll control.
Stage 2: Aerojet AJ-10-118, 7700lbf, UDMH/nitric acid. Pressure fed via helium. Gas jet attitude control system (had been deleted from earier variants of Able).
Aerojet engine cost $4million to build, 4 times initial bid. Very reliable, still flying.
Used Bell Labs BTL-300 radio guidance system.
Stage 3: 'Altair' Spin stabalized by turntable on top of second stage. Spun up to 100rpm by two solid rockets before seperation. Unguided otherwise. ABL X-248 solid rocket motor. 2800lbf for 38 seconds. weighed 500 lbs. Wound fiberglass casing.
Performance: place 650 lbs into leo of 115 to 230 miles or 100lbs to GTO.
11 of 12 flights successful.
$43 million development and launch support cost. $3million over budget.
Goddard spaceflight center orders 14 more deltas during <=62.
Flights:
{| border="1" cellspacing="0"
|-
|1 || 13may60 9:16pm gmt. || Payload: echo 1. pad 17a. Good first stage. second stage attitude control system failure. vehicle destroyed.
|-
|2 || 12aug60. || good flight. echo 1A placed into 1035 mile, 47degree inclination orbit.
|-
|3 || 23nov60. || Tiros 2. good lfight.
|-
|4 || || explorer 10. placed into elliptical 138,000 mile orbit. 78lbs.
|-
|5 || 12july61. || tiros 3.
|-
|6 || 16aug61. || explorer 12 Energentic Perticle Explorers. EPE-1. highly elliptical orbit.
|-
|7 || 8feb62. || tiros 4.
|-
|8 || 7mar62. || OSO-1 (orbiting solar observatory). 345 mile, 33 degree orbit.
|-
|9 || 26apr62. || Ariel 1. Ariel 1 was seriously damaged by Starfish Prime
|-
|10 || 19jun62. || tiros 5
|-
|11 || 10jul62. || Telstar 1. Also damanaged by Starfish Prime.
|-
|12 || 18sep62. || tiros 6
|}
13. EPE2
14. EPE3
15. 13dec62. Relay 1, second nasa communications sat. nasa's first active one.
16. 13feb63. pad 17b. Syncom 1. Thiokol Star 13B solid rocket as apogee kick motor.
20. july63? Syncom 2. Geosyncronous orbit, but inclined 33degrees due to the limited performance of the Delta.
25. 19aug64. Syncom 3. First true Geosyncronous sat.
26. Intelsat 1
First Delta E. 6nov65. launches GEOS 1.
1. 14dec66. biosatellite 1.
2. 7sep67. biosatellite 2
Launch Pad
First Launches
Deployment
Noteworthy Thor IRBM flights
Thor becomes a launch vehicle
Thor and the Corona program
Thor becomes Delta
scientific satellites and lunar probes during '60 and '61". To be replaced by Vega and Centaur when they came on-line. To emphasize
reliability rather than performance by replacing components which have caused problems on Thor-Able flights. Name from radio code word for 'D', as it was the fourth alteration of Thor as a luanch vehcile behind Able, Able-Star and Agena. Variously known as Delta and Thor-Delta.
Eleven of the twelve initial Delta flights were successful. The total project development and launch cost came
to $43 million, $3 million over budget. An order for 14 mour vehicles was let before 1962.Early Delta flights
Delta Evolution
Delta A
Block II MB-3 engine, 170,000lbf vs. 152,000lbf.Delta B
Upgraded AJ10-118D upper stage--3 foot tank stretch, higher energy oxidizer, solid-state guidance system.
Delta program goes from 'interim' to 'operational' status.
200lbs to GTO.Delta C
Third stage Altair replaced with Altair 2--its engine having been developed as the ABL X-258 for the Scout vehicle. 3" longer, 10% heavier, but 65% more total thrust.Thrust Augumented Thor-Agena D
Developed to handle the growing recon sats of the Corona program.
Three Castor solid rocket strapon boosters. 53,000lbf each. Lit on the grouns and jettisoned after burnout.Delta D
Thrust Augumented Delta.
A Delta C with the TAT core+boosters.Delta E
Thrust Augumented Improved Delta.
1965.
100lbf more to GTO than Delta D.
Castor II vs Castor boosters. Same thrust, longer duration.
MB-3 Block III core engine, 2000 lbf more thrust.
AJ10-118E second stage widened from 33 to 55 inches diameter. Double burn time.
Additional helium tanks allow for almost unlimited restarts.
Two available third stages: Altair 2 or FW-4D. The latter caused the delta to be known as a Delta E1.
New payload fairing from agena.Delta G
Two stage delta Es. used for Biosatellite 1 and 2 flights.Delta J
4jul68. Explorer 38.
Used larger Thiokol Star 37D motor as third stage.Long Tank Thor
Tapered fuel tank changed to cylinderical. Both tanks lengthened.
Core stage 14 feet longer. 49,000lbs more propellant.Delta L
FW-4d motor fir third stage.Delta M
Star 37D for stage 3.Delta N
Two stage version.'Super Six'
Deltas with three extra strap ons.
1000lbs to GTO.Thor missile development
Three companies challanged to bid on 30 Nov 55: Douglas, Lockheed, and North American. Given one week to reply. Contractor expected to create "a management team that could pull together existing technology, skills, abilities, and techniques in 'an unprecedented time.'" Douglas awarded contract on 27 Dec 55 for airframe and integration. Rocketdyne div of North American Aviation awarded engine contract, AC Spark Plug inertial guidance, Bell Labs backup radio guidance, GE nose cone/reentry shield.Thor as launch vehicle
MB-1
170,000lbf
| Thor
MB-1
170,000lbf
| Thor
MB-3
172,000lbf
| Thor
MB-3
170,000lbf
| Thor
MB-3
170,000lbf
| Thor
MB-3
170,000lbf
| Thor
MB-3
170,000lbf
|-
!Stage 2
| -
| AJ10-42
| AJ10-104
| AJ10-118
| Agena A
| Agena B
| X-248 (Altair)
|-
!Stage 3
| -
| X-248
| -
| X-248A5
| -
| -
| -
|-
! Notes
| IRBM || SLV, reentry vehicle test || SLV || SLV || SLV || SLV ||
|}Thor-Agena
Developed for Corona program.Thor as NASA vehicle
7 aug 59 Thor-Able III launches Explorer 6 to study Van Allen belts and take pictures with tv camera.Original NASA Delta vehicle
Delta Evolution
Delta A
Block II MB-3 engine, 170,000lbf vs. 152,000lbf.Delta B
Upgraded AJ10-118D upper stage--3 foot tank stretch, higher energy oxidizer, solid-state guidance system.
Delta program goes from 'interim' to 'operational' status.
200lbs to GTO.Delta C
Third stage Altair replaced with Altair 2--its engine having been developed as the ABL X-258 for the Scout vehicle. 3" longer, 10% heavier, but 65% more total thrust.Thrust Augumented Thor-Agena D
Developed to handle the growing recon sats of the Corona program.
Three Castor solid rocket strapon boosters. 53,000lbf each. Lit on the grouns and jettisoned after burnout.Delta D
Thrust Augumented Delta.
A Delta C with the TAT core+boosters.Delta E
Thrust Augumented Improved Delta.
1965.
100lbf more to GTO than Delta D.
Castor II vs Castor boosters. Same thrust, longer duration.
MB-3 Block III core engine, 2000 lbf more thrust.
AJ10-118E second stage widened from 33 to 55 inches diameter. Double burn time.
Additional helium tanks allow for almost unlimited restarts.
Two available third stages: Altair 2 or FW-4D. The latter caused the delta to be known as a Delta E1.
New payload fairing from agena.Delta G
Two stage delta Es. used for Biosatellite 1 and 2 flights.Delta J
4jul68. Explorer 38.
Used larger Thiokol Star 37D motor as third stage.Long Tank Thor
Tapered fuel tank changed to cylinderical. Both tanks lengthened.
Core stage 14 feet longer. 49,000lbs more propellant.Delta L
FW-4d motor fir third stage.Delta M
Star 37D for stage 3.Delta N
Two stage version.'Super Six'
Deltas with three extra strap ons.
1000lbs to GTO.External Link