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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 55 records · Page 3
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Skylab payload shroud jettison tests

The separation concept of the skylab payload shroud is presented, and its behavior in three full-scale jettison tests in vacuum is described. The shroud petal arresting mechanism is explained, as well as the primary and secondary data acquisition systems. The first two tests demonstrated the need for some structural design modifications although the separation process was satisfactory in each test. The third test, incorporating these design modifications, was satisfactory in all aspects of shroud performance.

Daye, C. J.↗
NASA NTRS1973

Computer simulation of temperatures on the Centaur standard shroud during heated jettison tests

A heating fixture for simulating the heating and environment encountered by the Centaur standard shroud (CSS) during its ascent through the earth's atmosphere is discussed. A computer program was developed to provide a means of determining the overall temperature profile of a free-skin model of the CSS during the heating portion of the heated jettison tests. The program treats the energy contribution of each lamp on the heater to various points on the CSS surface. The analytic model was verified by adapting the computer program to the configuration of the hardware used in a series of Intermediate Scale Tests performed on a 2.4 meters by 2.4 meters section of the CSS corrugated structure. A comparison of some predicted versus experimental results from these tests is presented.

Hemminger, J. A.↗
NASA NTRS1974

Centaur Standard Shroud (CSS) full jettison test dynamic analysis

During the space power facility jettison tests, the non-domed half of the Centaur standard shroud was allowed to completely separate from its hinge connection and was caught in a horizontal catch net. A rigid body dynamic analysis that was performed to predict the half shroud prior to and after net contact is presented. Analytical predictions of the longitudinal and circumferential bending moments imposed on the half shroud by the catch net and the net pressure on the half shroud corrugated skin are also presented.

Kasper, H. J.↗
NASA NTRS1990

Helicopter in-flight stores jettison

A helicopter emergency external-stores jettison system accommodating an experimental simplified mounting system is presented. The system's conceptual approach is described, including store interface, attachment, functional mechanisms, and system initiation. It is novel both in the stores' mounting interface logic and in the modifications to existing technology for the components. Two nonfragmenting 'ridge cut' explosive bolts were mounted in each 600-pound store to interface with a simple plate on the aircraft. Starting designs with proven technology and functional margins were demonstrated by analysis and test through the design and development. Design details of the system's components, from the explosive bolt to the initiation handle, are described.

Bement, Laurence J.↗
NASA NTRS1953

Free fall and evaporation of N-Octane droplets in the atmosphere as applied to the jettisoning of aviation gasoline at altitude

In connection with proposed rapid jettisoning of aviation gasoline at altitude, a theoretical study was made of the free fall and evaporation of N-octane droplets in the atmosphere ; N-octane was selected for study because of the expected similarity of over-all evaporation behavior of N-octane and gasoline. It was concluded that gasoline (or N-octane) droplets larger than 2000 microns in diameter would be unstable ; terminal speeds and Reynolds numbers were obtained for droplets not larger than 2000 microns at altitudes to 11,000 feet. The motion data were used in the calculation of N-octane evaporation rates under various conditions. It was found that a droplet having an original diameter of 2000 microns would fall about 4000 feet from 6000 feet under NACA standard atmosphere conditions before coming virtually to rest. Finally, it was concluded that temperature effects are of paramount importance; at highest air temperatures a 1000-foot ground clearance would probably be adequate to prevent ground contamination, whereas at lowest air temperatures only an atomizing spray arrangement would prevent ground contamination, irrespective of ground clearance.

FIRE HAZARDS↗
NASA NTRS1947

Calculation of Wing Bending Moments and Tail Loads Resulting from the Jettison of Wing Tips During a Symmetrical Pull-Up

A preliminary analytical investigation was made to determine the feasibility of the basic idea of controlled failure points as safety valves for the primary airplane structure. The present analysis considers the possibilities of the breakable wing tip which, in failing as a weak link, would relieve the bending moments on the wing structure. The analysis was carried out by computing the time histories of the wing and stabilizer angle of attack in a 10g pull-up for an XF8F airplane with tips fixed and comparing the results with those for the same maneuver, that is, elevator motion but with tips jettisoned at 8g. The calculations indicate that the increased stability accompanying the loss of the wing tips reduces the bending moment an additional amount above that which would be expected from the initial loss in lift and the inboard shift in load. The vortex shed when the tips are lost may induce a transient load requiring that the tail be made stronger than otherwise.

Boshar, John↗
NASA NTRS2015

Orion Launch Abort System Jettison Motor Performance During Exploration Flight Test 1

This paper presents an overview of the flight test objectives and performance of the Orion Launch Abort System during Exploration Flight Test-1. Exploration Flight Test-1, the first flight test of the Orion spacecraft, was managed and led by the Orion prime contractor, Lockheed Martin, and launched atop a United Launch Alliance Delta IV Heavy rocket. This flight test was a two-orbit, high-apogee, high-energy entry, low-inclination test mission used to validate and test systems critical to crew safety. This test included the first flight test of the Launch Abort System performing Orion nominal flight mission critical objectives. Although the Orion Program has tested a number of the critical systems of the Orion spacecraft on the ground, the launch environment cannot be replicated completely on Earth. Data from this flight will be used to verify the function of the jettison motor to separate the Launch Abort System from the crew module so it can continue on with the mission. Selected Launch Abort System flight test data is presented and discussed in the paper. Through flight test data, Launch Abort System performance trends have been derived that will prove valuable to future flights as well as the manned space program.

McCauley, Rachel J.↗
NASA NTRSDate not supplied

Jettison and Disposal From Near Rectilinear Halo Orbits, Part 2: Applications

Objects deployed from a Near Rectilinear Halo Orbit (NRHO) experience simultaneous gravitational forces from the Moon, the Earth, and the Sun, and post-deployment behavior is complex. The current investigation applies the theories explored in Part 1 of the study to examine the dynamics of objects deployed from the Gateway NRHO to heliocentric space. Examples include jettison of cubesats and logistics modules as well as end-of-life options for the Gateway itself. Recontact risk with the Gateway as each object departs the lunar vicinity is explored, and both the immediate destination and the long-term fate of the deployed objects are assessed.

Diane C. Davis↗