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1993-02-05
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"6_2_15_6.TXT" (5887 bytes) was created on 12-10-87
TRANSIENT PRESSURE TEST ARTICLE (TPTA) PROGRAM
TPTA Purpose
As part of the overall redesign program for the Space
Shuttle solid rocket motor (SRM), a series of tests of the
effects of pressure transients and loads encountered by the
redesigned solid rocket motor during ignition is required. The
Transient Pressure Test Article (TPTA) tests to be conducted in
the East Test Area of NASA's Marshall Space Flight Center in
Huntsvile, Ala., will provide data to verify the sealing
capability of the redesigned SRM field and case-to-nozzle
joints.
The test program will consist of 10 separate tests. A
minimum of four tests are planned prior to resumption of Space
Shuttle flights. Additional tests may be conducted prior to the
STS-26 mission to further assess the redesigned joints under
external loads.
Test Article Configuration Description
The TPTA is a short-stack solid rocket motor test article.
It is more than 52 feet (633 inches) in length and 12 feet in
diameter. The motor weighs 548,144 pounds, including 400 pounds
of propellant to simulate the pressure rise for ignition.
The TPTA consists in part of two case segments loaded with
inert propellant connected by two redesigned field joints. The
field joints are of the redesigned capture feature tang and
clevis design with Viton (TM) O-rings. The mating insulation
surfaces at each field joint are bonded with an adhesive, and
include a non-flight type J-shaped seal utilizing motor internal
pressure to increase the sealing action of the bonded surfaces.
The TPTA includes a redesigned factory joint which connects
a stiffener segment loaded with inert propellant to a external
tank attach (ETA) segment.
Flight configuration joint heaters are mounted around the
motor case at the top and bottom dome joint locations. Each
heater contains two independent electrical power circuits
thermostatically controlled to maintain joint temperatures at a
minimum of 75 degrees F.
The motor case-to-nozzle joint will be of the redesigned
configuration with 100 radial bolts added. The 7/8-inch diameter
radial bolts with Viton Stat-O-Seals (TM) are added to minimize
the amount of joint opening during motor pressurization. The
joint also incorporates adhesively bonded insulation surfaces, a
shaped relief slot and an added Viton "wiper" O-ring designed to
keep the adhesive on the insulation surfaces during assembly.
A standard aft skirt is fitted to the motor. For the TPTA
tests the aft skirt is attached to actual launch pad hold-down
posts.
What Happens During the Test
During the TPTA test, pressure is produced by a standard
solid rocket motor igniter and about 400 pounds of propellant to
duplicate the maximum pressure rise of the motor. Maximum
expected pressure is achieved in about six-tenths (0.6) of a
second and the pressure decay to ambient (outside air) conditions
occurs in about 90 seconds.
During the pressure cycle, dynamic strut loads will be
applied to the motor from a specially designed external tank
attach (ETA) load tower. Three connecting load lines will induce
loads which will simulate the three struts that attach the SRM to
the Shuttle's external tank at the base of the motor.
At the same time, the test article is subjected to a million
pound weight attached above the forward segment. This weight
simulates the remainder of the Shuttle elements on the launch
pad. The strut loads are synchronized with the ignition pressure
transient to recreate joint loading conditions that occur after
ignition when the pressure in the motor jumps causing the case to
bulge and rotate.
The TPTA will be fitted with 1500 instruments to measure
strain, deflection, temperature, pressure data and other
conditions.
The first test will be a nominal verification test of the
TPTA configuration (no flaws). In subsequent tests flaws will be
built into the J-seals and/or O-rings.
Upon completion of each test, the test article will be
refurbished in a facility adjacent to the test stand. A huge
crane will destack segments from the test stand and place them in
the refurbishment facility. Each test motor will be taken apart,
inspected, refurbished and new propellant added before being
fired again.
TPTA Test Objectives
The six primary test objectives are:
o Simulate the SRM maximum pressure rise rate.
o Simulate external loading influences on the sealing
capability of the redesigned SRM joint.
o Provide high temperature gas to demonstrate no evidence
of blowby or erosion of O-rings.
o Obtain reliable, repeatable SRM joint deflection data.
o Verify static and dynamic models of the field and
case-to-nozzle joints.
o Demonstrate design solutions for the field and nozzle
joints.
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