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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 595 records · Page 33
All sourcesNASA NTRSDOE OSTI
NASA NTRS1973

Scale model testing of drogues for free drifting buoys

Instrumented model drogue tests were conducted in a ship model towing tank. The purpose of the tests was to observe and measure deployment and drag characteristics of such shapes as parachutes, crossed vanes, and window shades which may be employed in conjunction with free drifting buoys. Both Froude and Reynolds scaling laws were applied while scaling to full scale relative velocities of from 0 to 0.2 knots. A weighted window shade drogue is recommended because of its performance, high drag coefficient, simplicity, and low cost. Detailed theoretical performance curves are presented for parachutes, crossed vanes, and window shade drogues. Theoretical estimates of depth locking accuracy and buoy-induced dynamic loads pertinent to window shade drogues are presented as a design aid. An example of a window shade drogue design is presented.

Vachon, W. A.↗
NASA NTRS1974

Reliability analysis of redundant systems

A method is proposed to compute the transition probability (the probability of partial or total failure) of parallel redundant system. The effect of geometry of the system, the direction of load, and the degree of redundancy on the probability of complete survival of parachute-like system are also studied. The results show that the probability of complete survival of three-member parachute-like system is very sensitive to the variation of horizontal angle of the load. However, it becomes very insignificant as the degree of redundancy increases.

Yeh, H. Y.↗
NASA NTRS1974

Splash evaluation of SRB designs

A technique is developed to optimize the shuttle solid rocket booster (SRB) design for water impact loads. The SRB is dropped by parachute and recovered at sea for reuse. Loads experienced at water impact are design critical. The probability of each water impact load is determined using a Monte Carlo technique and an aerodynamic analysis of the SRB parachute system. Meteorological effects are included and four configurations are evaluated.

Counter, D. N.↗
NASA NTRS1976

Evaluation and operation of Wallops Flight Center Mid-Air Retrieval System on a Skyvan aircraft

A Mid-Air Retrieval System (MARS) for parachute-borne payloads has been evaluated and made operational at Wallops Flight Center. The evaluation indicated that the Skyvan is a near-optimum aerial retrieval platform from the standpoints of safety, reliability and economy. The system is presently capable of retrieving parachute-borne payloads launched by rockets and balloons weighing from 10 to 325 pounds as far as 250 n mi from Wallops. Its payload retrieval capability could be increased to as much as 1000 pounds.

Young, D. C.↗
NASA NTRS1979

Study to determine the aquatic biological effects on the Solid Rocket Booster (SRB)

The surface of the reusable solid rocket boosters (SRB), which are jettisoned from the Shuttle Orbiter to parachute in the sea, are studied for colonization by marine life. Techniques for monitoring the marine microbial fouling of SRB materials are presented. An assessment of the nature and degree of the biofouling expected on the SRB materials in the recovery zone is reported. A determination of the degree and the effects of seasonal variation occurring on microbial fouling in the retrieval zone waters is made. The susceptibility of the SRB parachute recovery system to microbial fouling and biodeterioration is investigated. The development of scanning electron microscopy and epifluorescence microscopic observation techniques for rapid assessment of microbial fouling is discussed.

Colwell, R. R.↗
NASA NTRS1979

Space Shuttle Solid Rocket Booster Decelerator Subsystem Drop Test 3 - Anatomy of a failure

A test failure dramatically points out a design weakness or the limits of the material in the test article. In a low budget test program, with a very limited number of tests, a test failure sparks supreme efforts to investigate, analyze, and/or explain the anomaly and to improve the design such that the failure will not recur. The third air drop of the Space Shuttle Solid Rocket Booster Recovery System experienced such a dramatic failure. On air drop 3, the 54-ft drogue parachute was totally destroyed 0.7 sec after deployment. The parachute failure investigation, based on analysis of drop test data and supporting ground element test results is presented. Drogue design modifications are also discussed.

Runkle, R. E.↗
NASA NTRS1979

Space Shuttle Solid Rocket Booster decelerator subsystem - Air drop test vehicle/B-52 design

The air drop development test program for the Space Shuttle Solid Rocket Booster Recovery System required the design of a large drop test vehicle that would meet all the stringent requirements placed on it by structural loads, safety considerations, flight recovery system interfaces, and sequence. The drop test vehicle had to have the capability to test the drogue and the three main parachutes both separately and in the total flight deployment sequence and still be low-cost to fit in a low-budget development program. The design to test large ribbon parachutes to loads of 300,000 pounds required the detailed investigation and integration of several parameters such as carrier aircraft mechanical interface, drop test vehicle ground transportability, impact point ground penetration, salvageability, drop test vehicle intelligence, flight design hardware interfaces, and packaging fidelity.

Runkle, R. E.↗
NASA NTRS1981

Space shuttle solid rocket booster recovery subsystem

The studies, the development, and the testing program that led to the design and delivery of all flight hardware are described. Special emphasis was placed on the recovery parachutes. The parachutes were designed to deploy in a severe environment and safely lower to Earth an 85 ton rocket motor casing.

Runkle, R. E.↗
NASA NTRS1984

Titan atmospheric probe

Increased scientific interest in the structure and composition of Titan's atmosphere, clouds and surface have led to the study of mission options to the Saturnian system with the main goal of placing a probe into the atmosphere of the satellite. Two probe concepts have been studied by NASA: the first concept, a slightly modified Galileo probe capable of withstanding approximately 50 earth G during atmospheric entry heating and deceleration, would consist of a blunted 53 degree, 136-cm-diameter half-angle cone with a hemispherical afterbody, and a descent module containing scientific instruments and a parachute; the second concept, a system designed to provide in situ atmospheric measurements of Titan's organic haze layer, would consist of a probe using a 165-cm deployable graphite fabric decelerator, a 50-cm-diameter cylindrical descent module containing five instruments and a 2.5 m-diameter parachute and a 50-cm-radius spherical nose cap. Although the modified Galileo probe is feasible, its scientific drawback includes its inability to obtain in situ measurements above approximately 100 km.

Swenson, B. L.↗
NASA NTRS1985

The aerodynamic challenges of SRB recovery

Recovery and reuse of the Space Shuttle solid rocket boosters was baselined to support the primary goal to develop a low cost space transportation system. The recovery system required for the 170,000-lb boosters was for the largest and heaviest object yet to be retrieved from exoatmospheric conditions. State-of-the-art design procedures were ground-ruled and development testing minimized to produce both a reliable and cost effective system. The ability to utilize the inherent drag of the boosters during the initial phase of reentry was a key factor in minimizing the parachute loads, size and weight. A wind tunnel test program was devised to enable the accurate prediction of booster aerodynamic characteristics. Concurrently, wind tunnel, rocket sled and air drop tests were performed to develop and verify the performance of the parachute decelerator subsystem. Aerodynamic problems encountered during the overall recovery system development and the respective solutions are emphasized.

Bacchus, D. L.↗
NASA NTRS1986

Stable Ejection Seat

Drogue chute for ejection seat slows down seat in more stable fashion than conventional parachutes and thus improves chances for survival. Square drogue linked to seat from its corners suppresses tendency of seat to rotate in pitch and yaw. New parachute expected to reduce dynamic forces on ejected person and extend maximum possible ejection altitude by 50 percent. Used at high or low speeds.

Hirsch, R. S.↗
NASA NTRS1988

The possible contamination of Jupiter

The Galileo probe, though at present its future is uncertain, would, if not sterilized, represent a good chance of contaminating Jupiter. Most scientists opposed to sterilizing the probe argue that to order the probe sterilized would be the death of the project, since sterilization would entail a reconstruction of the probe, and there are not enough funds to accomplish this. These scientists, however, are ignoring a relatively simple and inexpensive alternative to the traditional heat sterilization method. The main threat of contamination comes from Galileo's exterior surfaces: the shell of the probe and its parachute. The probe innermost components would not represent a threat since the probe is sealed. In light of the fact that only the exterior of Galileo would have to be sterilized, heat would not have to be used as a method of sterilization. Instead, various gas mixtures could be sprayed entirely over the probe and its parachute, gases which would kill any and all bacteria. This idea is more thoroughly examined.

Garcia, Joe↗
NASA NTRS1989

Preliminary design of the Shuttle-C avionics recovery system

The analysis done in developing a recovery system for the Shuttle-C cargo vehicle is presented. This recovery system is comprised of a reentry capsule which houses the vehicles avionics. The avionics are contained in a single package which is extracted from the capsule by the parachute recovery system. The Shuttle-C will be able to satisfy NASA's design and mission requirements. Included, is an analysis of the structural, thermal protection, and parachute recovery systems. A discussion of the merits of the proposed system is also included.

Brookfield, Morgan↗
NASA NTRS1990

Preliminary Subsystem Designs for the Assured Crew Return Vehicle (ACRV), volumes 1-3

A long term manned facility in space must include provisions for the safety of the crew. The resolution of this need was the design of an Assured Crew Return Vehicle (ACRV). The main focus is on the braking and landing system of the ACRV. This subsystem of the ACRV was divided into three phases. The Phase 1 analysis showed that the use of a tether to aid in the reentry of the ACRV was infeasible due to cost and efficiency. Therefore, a standard rocket would be used for reentry. It was also found that the continental United States was an achievable landing site for the ACRV. The Phase 2 analysis determined the L/D of the vehicle to be 1.8, thus requiring the use of a lifting body for reentry. It was also determined that shuttle tiles would be used for the thermal protection system. In addition, a parachute sequence for further deceleration was included, namely a ringslot drogue chute, a pilot chute, and finally a ringsail main parachute. This sequence was found to be capable of slowing the vehicle to a descent velocity of 9 to 10 m/s, which is the required velocity for aerial recovery. The Phase 3 analysis proved that a Sikorsky CH-53E helicopter is capable of retrieving the ACRV at 5.5 km altitude with minimal g-forces induced on the ACRV and minimal induced moments on the helicopter upon hookup. The helicopter would be modified such that it could stabilize the ACRV close to the bottom of helicopter and carry it to the nearest designated trauma center.

Source record↗
NASA NTRS1991

Selectable-Towline Spin-Chute System

Selectable-towline spin-chute system designed to enable in-flight deployment of single emergency spin-recovery parachute from more than one attachment point on airplane. Eliminates multiple parachutes and multiple deployment systems, reducing weight and cost of emergency system. Minimizes inertial and aerodynamic deviations on airplane, contributing to overall simplification of structure and aerodynamics.

Vairo, Daniel M.↗
NASA NTRS1991

Liquid booster engine reuse - A recovery system

The paper presents the design of a recovery system for a suborbital payload of an Atlas E rocket. This program utilizes off-the-shelf and previously qualified avionics, flotation, and decelerator systems. A brief history of liquid-engine recoveries is presented first, then the system design utilizing two self-contained structurally-identical pods diametrically mounted to the thrust section is outlined. A mortar-deployed drogue and the main parachute are described, and experimental procedures are considered. Data obtained from one tricluster drop employing a cylindrical test vehicle and helicopter is analyzed, and a satisfactory load balance between the parachutes is observed.

Von Eckroth, Wulf↗
NASA NTRS1992

Piloted simulation study of a balloon-assisted deployment of an aircraft at high altitude

A piloted simulation was used to study the feasibility of a balloon assisted deployment of a research aircraft at high altitude. In the simulation study, an unmanned, modified sailplane was carried to 110,000 ft with a high altitude balloon and released in a nose down attitude. A remote pilot controlled the aircraft through a pullout and then executed a zoom climb to a trimmed, 1 g flight condition. A small parachute was used to limit the Mach number during the pullout to avoid adverse transonic effects. The use of small rocket motor was studied for increasing the maximum attainable altitude. Aerodynamic modifications to the basic sailplane included applying supercritical airfoil gloves over the existing wing and tail surfaces. The aerodynamic model of the simulated aircraft was based on low Reynolds number wind tunnel tests and computational techniques, and included large Mach number and Reynolds number effects at high altitude. Parametric variations were performed to study the effects of launch altitude, gross weight, Mach number limit, and parachute size on the maximum attainable stabilized altitude. A test altitude of approx. 95,000 ft was attained, and altitudes in excess of 100,000 ft was attained.

Murray, James↗
NASA NTRS1991

Recovery system termination load reduction through the use of a central load core

A study is presented of the development and testing of a parachute central load core, an adaptive device whose primary function is to minimize parachute stored elastic energy while providing adequate rotational stiffness to prevent shroud line fouling from twisting and sufficient resistive torque for any balloon gondola positioning requirements. Empirical relations are given for the uninhibited drag area growth which are derived in the classical nondimensional form. Attention is given to development considerations and design along with model simulations, small and midscale drop test data, full-scale flight data, and instrumentation applications.

Robbins, ED↗