| THE ORBIT OF ARIEL 2 (1964-15A) - THE FIRST TWELVE MONTHS. |
DEC 1965 |
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| Authors:
R. H. Gooding; ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)
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 | The definitive orbit for Ariel 2 (1964-15A) is computed, from Minitrack observations, for a period of twelve months from the launch of the satellite. The orbit is described by a model with eight orbital parameters and these parameters are listed at every twenty-fifth nodal passage. The angular observations are accurate to about 1 minute and, as a result, the average computed standard deviations of the eight fitted orbital parameters are ... |
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| LONG-TERM EVOLUTION OF MEDIUM-DISTANCE ORBITS. |
DEC 1965 |
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| Authors:
G. E. Cook; Diana W. Scott; ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)
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| A method is developed for predicting the long-term development of orbits having moderate to large eccentricities (0.33 < e < 0.9) and semi major axes up to 10 Earth radii. For many orbits of this type the lifetime depends entirely on the interaction of the luni-solar perturbations with the effects of the Earth's gravitational potential. Lifetime estimates are given for 8 satellites. (Author) |
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| DESCRIPTION AND APPLICATION OF A COMPUTER PROGRAM FOR AREA INSPECTION BY SATELLITE, |
DEC 1965 |
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| Authors:
L. N. Rowell; R. Mobley; RAND CORP SANTA MONICA CALIF
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| A digital-computer program for predicting the motion of satellites over long periods of time and in the presence of major perturbations. The program, called the Area Inspection Program (AIP), is designed to compute accurately and inexpensively the position of a satellite relative to several ground stations at once. It is written in FORTRAN IV for the IBM 7044 computer and consists of only one program, with no utility routines except ... |
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| INVESTIGATION OF THE ACQUISITION PROBLEM IN SATELLITE ATTITUDE CONTROL. |
DEC 1965 |
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| Authors:
A. E. SABROFF; R. L. Farrenkopf; A. M. Frewand ; M. H. Gran; TRW SPACE TECHNOLOGY LABS REDONDO BEACH CALIF
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| The acquisition function of a spacecraft attitude control system consists of properly orienting the vehicle with respect to specified reference directions starting from large initial attitude and rate errors. The resulting control system design problem was examined by establishing suitable mathematical representations, comparing competing control concepts, developing a practical optimization approach, and evaluating a new technique for applying Lyapunov stability theory to the acquisition problem. (Author) |
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| ADVANTAGES OF A 4-AXIS TRACKING MOUNT FOR THE PHOTOELECTRIC PHOTOMETRY OF SPACE VEHICLES |
DEC 1965 |
50 pages |
| Authors:
Kenneth E. Kissell; AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OH
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 | Arguments are presented for the necessity of using a four-axis telescope (Quad-R-Axial) mount for the photoelectric photometry of satellites if small field apertures and hence low sky background signals are to be achieved. Since the signal to noise ratio of the target/background is proportional to the square of the diameter of accepted field, any reduction of guiding errors which will allow smaller field apertures will then allow the photometry of ... |
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| A CLOSED-FORM SOLUTION TO LIFTING REENTRY. |
DEC 1965 |
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| Authors:
Roland N. Bell; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO
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| This report derives closed-form expressions for predicting the longitudinal and lateral range attainable by lifting reentry vehicles. The resultant equations sensitively and accurately define the influence of L/D ratio, bank angle and entry velocity variations over a spectrum of values. To illustrate the usefulness of the method, the derived expressions were used to conduct a parametric reentry study covering a range of L/D ratios from 0.5 to 4.0, bank angles ... |
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| SOVIET SPACE EXPLORATION AS VIEWED BY EAST GERMAN SPECIALISTS, |
15 NOV 1965 |
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| Authors:
Gerhard Erleman; AEROSPACE TECHNOLOGY DIV LIBRARY OF CONGRESS WASHINGTON D C
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| The report deals with Soviet space exploration during the last five years (1960-1964) as viewed by East German specialists. It is based on open literature available at the Aerospace Technology Division of the Library of Congress. The materials have been discussed chronologically in eight sections according to subject. Some East German sources discussed include interesting information not found in Soviet publications. The possible application of parallel connection of launch-vehicle stages ... |
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| INVESTIGATION OF CONTROL SURFACE INSTABILITIES OF LIFTING BODY CONFIGURATIONS. |
NOV 1965 |
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| Authors:
Robert L. Goldman; MARTIN CO BALTIMORE MD
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| Based on aircraft experience, the possibility of the occurrence of unanticipated aeroelastic instabilities of advanced orbital and superorbital lifting body configurations is an appropriate consideration for the vehicle designer. Although oscillatory motions may involve any one of a number of aeroelastic mechanisms, most of them can be categorized as either self-sustained, driven by flow disturbances, or a combination of both forms. In the present investigation, such mechanisms are studied both ... |
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| PROGRAM SUPPORT REQUEST MOL - HSQ, |
NOV 1965 |
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| Authors:
W. Pilgrim; MARTIN CO DENVER CO
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| AERODYNAMIC NOISE TESTS ON X-20 SCALE MODELS. VOLUME 2. SUMMARY AND ANALYSIS REPORT |
NOV 1965 |
67 pages |
| Authors:
David R. Wiley; Michael G. Seidl; BOEING AEROSPACE CO SEATTLE WA
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| Summaries of fluctuating pressure data presented in Volume I for 1/ 15th-scale X-20 models are made and discussed. Particular emphasis is given to the high over-all rms pressures measured aft of convex corners during transonic test conditions. Additional information relating to these pressures is presented in the form of pressure histories, peak-amplitude distributions, and power spectral densities. Fluctuating-pressure data and space correlation measurements for three closely spaced microphones are presented, ... |
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| AERODYNAMIC NOISE TESTS ON X-20 SCALE MODELS. VOLUME I. DATA REPORT. |
NOV 1965 |
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| Authors:
Michael G. Seidl ; David R. Wiley; BOEING CO SEATTLE WASH AEROSPACE GROUP
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| Aerodynamic noise data are reported for tests conducted on a 1/15-scale X-20 model in the 2 transonic and supersonic wind tunnels, and on a 1/15-scale X-20/624A model in another transonic tunnel. Measurements are reported for 16 microphone positions on the model in the transonic and supersonic tunnel tests, and 18 positions for the other transonic tunnel tests. The total Mach range spanned during the tests was 0.5 to 3.5. Angle ... |
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| PERTURBATIONS OF NEAR-CIRCULAR ORBITS BY THE EARTH'S GRAVITATIONAL POTENTIAL. |
NOV 1965 |
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| Authors:
G. E. Cook; ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)
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| The behaviour of near-circular orbits in the Earth's gravitational potential is discussed in detail. The major axis rotates at a non-uniform rate or oscillates about a position of equilibrium depending on the initial conditions. (Author) |
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| RADIATION EFFECTS IN THE STAGNATION REGION BOUNDARY LAYER. |
NOV 1965 |
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| Authors:
Joseph Shwartz; MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
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| The radiation coupled boundary layer of an emitting and absorbing gas at the stagnation region of a blunt body is considered. Solutions are obtained for a wide range of optical thicknesses and radiation intensities, including the radiative effects of the adjoining shock layer. The solutions indicate the decrease in temperatures, their gradients, and the related conductive heat transfer to the wall as well as the net radiant energy contribution. The ... |
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| DIRECT DETERMINATION OF SATELLITE COORDINATE PERTURBATIONS BY THE VON ZEIPEL METHOD. |
NOV 1965 |
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| Authors:
Juris Vagners; STANFORD UNIV CALIF DEPT OF AERONAUTICS AND ASTRONAUTICS
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| By utilizing the canonical variables (R, G, H, r, u, h) of Hill, the in-plane variations in a satellite's coordinates are obtained in a simple manner from the conventional generating functions of the von Zeipel procedure. The generating functions are extended and convenient expressions are found for the radius, radial velocity and the central angle, taking into account the first-order periodic influences of any harmonic in the expansion for the ... |
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| RADIANT HEATING SIMULATION, |
NOV 1965 |
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| Authors:
T. K. Pugmire; R. W. Liebermann; AVCO CORP WILMINGTON MASS RESEARCH AND DEVELOPMENT DIV
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| A review is presented of the radiation energy transfer rates characteristic of the environments for advanced entry missions, and of the techniques suitable for simulating these heat transfer rates in the laboratory. The most promising techniques for laboratory simulation of advanced radiation environments appear to be those associated with the continuous arc discharge. Radiation fluxes which are characteristic of advanced manned reentry environments, can be obtained by direct exposure of ... |
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| FILTERING ASPECTS OF ORBIT DETERMINATION. |
OCT 1965 |
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| Authors:
R. J. Mercer; AEROSPACE CORP EL SEGUNDO CA EL SEGUNDO TECHNICAL OPERATIONS
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| An exciting prospect for modern filtering theory lies in the field of orbital navigation, but as of today the most impressive results in orbit determination have been obtained by classical methods of parameter estimation. Some current experience and problems are described and their implications for modern filtering theory are discussed. Two techniques, found effective in the classical process, are presented in the context of recursive estimation. Four illustrative plots are ... |
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| THE ORBIT OF TIROS 7 (1963-24A) FEBRUARY 13-23, 1965. |
OCT 1965 |
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| Authors:
Diana W. Scott; ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)
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| The orbit of Tiros 7 has been determined from Minitrack observations for part of February 1965, using the RAE orbit improvement programme. A table of orbital parameters is given for 7 nodes spaced at 25-node intervals. The orbital elements are compared with those given by the NASA orbit of the satellite. (Author) |
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| TURN OF THE ORBIT'S PLANE OF ARTIFICIAL EARTH SATELLITE, |
OCT 1965 |
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| Authors:
Yu. M. Kopnin; AERONAUTICAL CHART AND INFORMATION CENTER ST LOUIS MO LINGUISTIC SECTION
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| ON THE PREDICTION OF SATELLITE ORBIT DECAY AND IMPACT, |
OCT 1965 |
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| Authors:
Carl Gazley Jr.; L. N. Rowell; G. F. Schilling; RAND CORP SANTA MONICA CALIF
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| Presentation of problems associated with predicting satellite orbit decay plus a description of several computer programs for computing long-term orbit decay, model atmospheres, and final decay and re-entry. Computation of long-term orbit decay using the RAND Satellite Lifetime Program is illustrated for Explorer 9, and the orbit-decay data from the satellite are used to derive a current model atmosphere different from any standard atmospheres and permitting, in subsequent decay computations, ... |
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| A REVIEW OF RESEARCH PERFORMED AT THE POLYTECHNIC INSTITUTE OF BROOKLYN, AEROSPACE INSTITUTE. |
OCT 1965 |
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| Authors:
Martin H. Bloom; Robert J. Cresci; POLYTECHNIC INST OF BROOKLYN N Y DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS
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| An experimental and theoretical program connected with fluid mechanical and dynamical problems emanating from hypersonic flight is reported. Major emphasis was on the viscous free mixing of homogeneous streams, and the boundary layer flows including effects of deparation, mass injection or suction, unsteady flows, surface discontinuities, and vorticity. Reacting flows, space mechanics, and magnetohydrodynamic effects were also considered. The research is summarized and a bibliography of 33 reports and published ... |
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| RE-ENTRY COMMUNICATIONS STUDIES UTILIZING SEEDING TECHNIQUES. |
OCT 1965 |
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| Authors:
John H. Mullen; Brooks M. Sharp; Ralph A. Murphy; MCDONNELL AIRCRAFT CORP ST LOUIS MO RESEARCH DIV
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| The object of this research was to determine the effects of chemical seedants on the electron concentration of an rf generated air plasma. 'Hot' and 'cold' uncontaminated air plasmas were generated by means of a 25 kW 1 Mc rf generator. A maximum electron density of 2 x 10 to the 12th power electrons/cc was obtained at a pressure of 0.37 torr and air flow of 7.5 x 0.00001 lb/sec. ... |
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| An Investigation of a Deforming Energy-Absorption System for Space- Vehicle Landings |
OCT 65 |
38 pages |
| Authors:
Robert W. Warner; Robert M. Sorenson; Arthur J. Kaskey; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER
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| A deforming system for protecting a space vehicle during a landing impact is described and experimentally evaluated. The impact energy is absorbed mostly by the cutting of plastic foam pads, but partially by the buckling of their tubular support structure. Expandable foam is chosen because of its advantages in packaging and in reducing penetration of the landing surface. The foam and its supporting structure are utilized in such a way ... |
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| RESEARCH ON ELECTROMAGNETICS FOR PROJECT DEFENDER. |
30 SEP 1965 |
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| Authors:
Ernst Weber; POLYTECHNIC INST OF BROOKLYN N Y MICROWAVE RESEARCH INST
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| Progress is reported on a fairly large number of projects dealing generally with electromagnetic phenomena in plasmas and plasma-like media, such as the properties of antennas, excitation of electromagnetic waves in plasmas, coupling of acoustic and electromagnetic waves, propagation through time-varying random media, electron densities in shock waves, basic kinetic theory of ionized media, instabilities in plasmas, and properties of laboratory type plasmas. A smaller group of projects deals with ... |
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| INVESTIGATION OF 'PREDICTOR' DISPLAYS FOR ORBITAL RENDEZVOUS, PROGRAM SUMMARY. |
SEP 1965 |
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| Authors:
William K. McCoy Jr.; George G. Frost; RITCHIE INC DAYTON OHIO
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| A series of studies on the development of predictor display techniques for orbital rendezvous is summarized. The purpose of this program was to evaluate alternative predictive display techniques for orbital rendezvous. After an analog simulation of the rendezvous problem was mechanized and a display format developed, two studies were conducted investigating operator efficiency at control of rendezvous utilizing the side looking display format and predictor display techniques. Also, two display ... |
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| RADIATING FLOWS AROUND RE-ENTRY BODIES, |
SEP 1965 |
|
| Authors:
Robert M. Nerem; OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS DEPT OF AERONAUTICAL AND ASTRONAUTICAL ENGINEERING
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| Topics include: radiative transfer in a flowing gas, radiation from high temperature shock heated gases, the blunt body flow of a radiating gas, hypersonic slender body theory with radiation. |
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| THE APPLICATION OF FLOQUET THEORY TO THE COMPUTATION OF SMALL ORBITAL PERTURBATIONS OVER LONG TIME INTERVALS USING THE TSCHAUNERHEMPEL EQUATIONS, |
AUG 1965 |
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| Authors:
Benjamin O. Lange; Robert G. Smith; STANFORD UNIV CALIF DEPT OF AERONAUTICS AND ASTRONAUTICS
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| This paper deals with a method of calculating the deviation of the path of an orbiting body from a nominal or reference trajectory. The form in which the solution is cast was motivated by a particular perturbation problem. Stanford University is developing a 'drag-free', or 'dragmakeup', scientific satellite which is designed to follow a purely gravitational orbit. The satellite consists actually of two satellites: an inner sphere or proof mass, ... |
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| SOME PERIODIC TRAJECTORIES IN CISLUNAR SPACE VERY RESTRICTED FOUR BODY APPROXIMATION. |
AUG 1965 |
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| Authors:
Raymond Earl Siferd; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
|
| The possibility of existence of periodic or nearly periodic trajectories in cislunar space is investigated. In cislunar space, the motion is determined by the gravitational fields of the earth, moon, and sun. The problem is studied using the very restricted four body approximation. It is assumed that the earth and moon revolve in circular paths about their barycenter and the barycenter of the earth and moon moves in a circle ... |
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| AN INVESTIGATION OF THE EFFECT OF LAUNCH SITE LOCATION AND VARIATION OF LAUNCH PARAMETERS ON LUNAR-EARTH TRAJECTORIES. |
AUG 1965 |
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| Authors:
Paul Stuart Skartvedt; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
|
| Lunar-earth trajectories are examined to determine the sensitivities of earth re-entry angle and velocity to changes in both static and dynamic lunar launch parameters. These trajectories are classified as free return single pass trajectories with no guidance or delta capability considered. The equations of motion for the trajectories are derived from the restricted problem of three bodies in a rotating coordinate system. The earth and moon are considered to rotate ... |
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| ORBIT DETERMINATION AND ANALYSIS BY THE MINIMUM VARIANCE METHOD. |
AUG 1965 |
|
| Authors:
Karlis Minka; MARTIN CO BALTIMORE MD
|
| The aspects of accurate determination of Earth satellite orbits by the Minimum Variance Method are presented. In addition, techniques for the determination of the associated physical constants, such as the coefficients in the Earth's gravitational potential, exospheric temperature, etc., are developed. A method for determination of the state transition matrix is presented. Also included are a review of the time systems employed in satellite orbit determination and a short discussion ... |
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| MINIMUM-FUEL TRANSFERS BETWEEN COAXIAL ELLIPSES, BOTH COPLANAR AND NONCOPLANAR. |
AUG 1965 |
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| Authors:
C. Byron Winn; STANFORD UNIV CALIF DEPT OF AERONAUTICS AND ASTRONAUTICS
|
| This report presents the solutions for the minimum fuel transfers between coaxial ellipses, both coplanar and noncoplanar. These problems are unusual in that the optimal solutions can be obtained analytically. This report merely presents some of the results that have been obtained; the derivations and proofs have been omitted. (Author) |
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| ORBITAL DOCKING SIMULATORS, |
31 JUL 1965 |
|
| Authors:
Robert J. Conlon; BATTELLE MEMORIAL INST COLUMBUS OH
|
| This report is a review of recently available information concerning orbital docking simulators and their use. The survey was limited primarily to docking simulators that have been used since 1960, but includes descriptions of several simulators that are currently being installed and are not yet operational. This study covered docking simulators that were designed and used as research tools as opposed to those used primarily as training devices. Trips were ... |
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| THE EFFECT OF TRANSFER INJECTION ERRORS UPON THE ACCURACY OF HIGH CIRCULAR ORBITS |
JUL 1965 |
68 pages |
| Authors:
Keith Smith; ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)
|
| First-order relationships between the position and velocity errors at start and end of a Hohmann transfer are derived in a two-dimensional analysis. The results are then used to evaluate the effects of uncorrected first injection errors upon the mean radius and eccentricity of the final (nominally circular) orbit, assuming perfect application of the final impulsive velocity. Finally the mean radius and eccentricity errors are expressed in terms of post-orbital velocities ... |
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| SPIN DECAY OF A CLASS OF SATELLITES CAUSED BY SOLAR RADIATION, |
JUL 1965 |
|
| Authors:
B. Etkin; P. C. Hughes; TORONTO UNIV (ONTARIO) INST FOR AEROSPACE STUDIES
|
| A study is presented of the interaction with the solar radiation field of a spinning satellite having long flexible rods. The dynamics of thermal bending of the rods is analyzed, including the effect of vehicle rotation, and the shape, amplitude and phase are calculated. The radiation pressure on the periodically bent rods produces a net average despin torque that depends critically on the phase lag of the thermal bending. The ... |
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| POSITION OF MCMURDO SOUND, ANTARCTICA TRACKING STATION AS DETERMINED BY ARTIFICIAL EARTH SATELLITES. |
JUL 1965 |
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| Authors:
F. T. Heuring; JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
|
| During the Antarctic summer (1964-1965) a doppler tracking station, under cognizance of the United States Antarctic Research Program, National Science Foundation, was installed at McMurdo Sound, Antarctica with equipment furnished by the U. S. Navy. Initial station coordinates were acquired by taking an average value from various sources. Since there are no known triangulation or Hiran ties from Antarctica to any existing datum in the world, it was expected that ... |
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| PRESSURE MEASUREMENTS AT MACH 8 ON AN AERODYNAMICALLY CONTROLLABLE WINGED REENTRY CONFIGURATION. PART OF AN INVESTIGATION OF HYPERSONIC FLOW SEPARATION AND CONTROL CHARACTERISTICS |
JUN 1965 |
485 pages |
| Authors:
Lawrence Meckler; GRUMMAN AIRCRAFT ENGINEERING CORP BETHPAGE NY RESEARCH DEPT
|
| Pressure data were obtained at Mach 8 for a winged reentry configuration having aerodynamic controls. The basic model consisted of a clipped delta wing with an overslung cone-cylinder body. The main controls tested were partial span trailing edge flaps. Data were also obtained on the effect of tip fins, hemisphere-cylinder body and a trailing edge spoiler. The data were obtained over an angle of attack range of -50 deg. to ... |
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| INVESTIGATION OF THE EFFECT OF PLUG TRANSLATION ON THE THRUST VECTOR OF A MACH 3 PLUG NOZZLE |
JUN 1965 |
|
| Authors:
Richard K. Ellingson; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING
|
| An experimental investigation was made of a convergent plug exhaust nozzle to determine if effective thrust vectoring could be achieved through the use of a translating plug which travels in plane motion across a base region of slightly increased diameter. The objective was to determine if effective thrust vectoring could be obtained at higher pressure ratios than 6.2. Results showed that when operating at pressure ratios below the design value ... |
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| MINIMUM FUEL ANALYSIS OF A LUNAR SOFT LANDING MISSION USING FEEDBACK CONTROL. |
JUN 1965 |
|
| Authors:
John R. Hoffman; MICHIGAN UNIV ANN ARBOR
|
| The problem of making a soft landing on the moon's surface with a vehicle using conventional chemical rocket engines with restart capability was studied in this paper. In particular, a minimum fuel control scheme utilizing readily computed controls has been sought and found. By studying the problem from a constant gravity viewpoint, it was found that by running several extremal trajectories backwards from the moon's surface, some very interesting similarities ... |
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| DESIGN ESTIMATES OF STRESSES AND DEFORMATIONS IN MELTING PLATES. |
JUN 1965 |
|
| Authors:
Edward Friedman; Bruno A. Boley; COLUMBIA UNIV NEW YORK DEPT OF CIVIL ENGINEERING AND ENGINEERING MECHANICS
|
| In order to provide calculation procedures and design estimates to determine the mechanical behavior of ablating plates subject to atmospheric re-entry heating, the analysis of a melting elastic-perfectly plastic circular plate based on certain physically reasonable idealizations is considered. The plate, exposed on one face to a heat input which varies in time as a square pulse and insulated at the other face and at the edges, is acted upon ... |
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| BI-ELLIPTIC TRANSFER WITH PLANE CHANGE. |
MAY 1965 |
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| Authors:
H. L. Roth; AEROSPACE CORP EL SEGUNDO CA EL SEGUNDO TECHNICAL OPERATIONS
|
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| A PEGASUS COMPUTER PROGRAMME FOR THE ASSESSMENT OF THE ACCURACY OF SATELLITE ORBIT DETERMINATION |
APR 1965 |
31 pages |
| Authors:
R. H. Gooding; ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)
|
| A computer programme is described by means of which one may estimate the potential accuracy of the elements of a given satellite orbit, if determined from observational data of specified type and assumed accuracy. An application of the programme is made to an orbit of six hours period determined from radar observations at a single station. |
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| ORBIT PREDICTION. |
APR 1965 |
|
| Authors:
G. Gebel; JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
|
| The present method of predicting an orbit for the immediate future is described. A mathematical model of the expected along-track errors is proposed and studied to determine how modification of parameters affects orbit prediction. (Author) |
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| AN ANALYTICAL METHOD OF DETERMINING SATELLITE LOCATION FOR ELLIPTIC ORBITS. |
01 FEB 1965 |
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| Authors:
D. E. MUIR; CENTER FOR NAVAL ANALYSES ALEXANDRIA VA OPERATIONS EVALUATION GROUP
|
| A solution to the problem of determining the location of the ground track of a satellite traveling in an elliptic orbit is given. The approach assumes a satellite of negligible mass moving about a homogeneous earth without atmosphere. Perturbing effects caused by earth oblateness are accounted for. Three steps are required for the solution: (1) the initial ortibal elements are derived from burnout conditions; (2) the location of the longitude ... |
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| LOITER TIME FOR GEMINI B RECOVERY OPPORTUNITIES. |
18 JAN 1965 |
|
| Authors:
R. G. Stern; AEROSPACE CORP EL SEGUNDO CALIF TECHNICAL OPERATIONS
|
| The return of the Gemini B from the Manned Orbital Laboratory (MOL) to a recovery area is evaluated in terms of loiter time. Loiter time is the time required to attain an orbital position from which de-orbit may be performed which subsequently results in return to a recovery area. Maximum loiter time is of interest since an emergency may force the evacuation of the MOL at any arbitrary time. This ... |
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| A STUDY OF TIME-OPTIMAL RENDEZVOUS IN THREE DIMENSIONS (VOL. I). |
JAN 1965 |
|
| Authors:
Bernard H. PAIEWONSKY; Peter J. Woodrow; AERONAUTICAL RESEARCH ASSOCIATES OF PRINCETON INC N J
|
| The results of a study of time optimal rendezvous in three dimensions with bounds on the rocket thrust and the available propellant are described. The equations of motion are linearized and Neustadt's method is used to solve the two-point boundary value problem in the seven-dimensional state space. Three convergence acceleration schemes are studied. Examples of terminal rendezvous paths are presented and discussed in terms of the magnitudes of the bounds ... |
|
| A STUDY OF TIME-OPTIMAL INTERCEPT IN TWO DIMENSIONS (VOL 2) |
JAN 1965 |
69 pages |
| Authors:
Bernard H. Paiewonsky; Peter J. Woodrow; AERONAUTICAL RESEARCH ASSOCIATES OF PRINCETON INC NJ
|
| A planar time-optimal formulation is used to study the terminal phase of interception above the atmosphere in a uniform gravitational field. The dependence on initial conditions of the optimal steering angle is examined for initial relative velocities ranging from 5,000 ft/sec to 50,000 ft/sec and initial distances up to 500,000 ft. Results are presented in graphical form for two typical rockets showing: (1) the range dependence of terminal error sensitivities ... |
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| STATIC STABILITY CHARACTERISTICS OF A WINGED BODY WITH VARIOUS INLET CONFIGURATIONS AT MACH NUMBERS OF 2, 5, 8, AND 10 |
DEC 1964 |
|
| Authors:
R. H. Burt; M. E. Hillsamer; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
|
| An experimental investigation has been conducted at Mach numbers of 2, 5, 8, and 10 to determine the static stability characteristics of a winged body configuration with various sizes and shapes of inlets attached. Selected results of the longitudinal stability and drag characteristics are presented for each configuration at the various mach numbers. The effect of inlet position along the model on the aerodynamic characteristics of two inlet configurations is ... |
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| AN INVESTIGATION OF CREW ESCAPE FROM VEHICLES PERFORMING AT SUPERORBITAL RE-ENTRY VELOCITIES |
NOV 1964 |
|
| Authors:
J. E. Hofferberth; NORTH AMERICAN AVIATION INC COLUMBUS OH
|
| Detailed results are presented from an investigation to determine the technical feasibility of providing crew escape capability for space vehicles during reentry at supercircular velocity. The general requirements for reentry corridor compatibility are discussed, and the NASA M-II and M-I configurations are selected for the Parent and Escape Vehicles, respectively. Detailed flight mechanics analyses are conducted; a guidance concept, which commands a rate of change of lift coefficient as a ... |
|
| HIGH TEMPERATURE INVESTIGATION OF VARIOUS CREW ESCAPE CONCEPTS FOR THE REENTRY FLIGHT REGIME |
NOV 1964 |
|
| Authors:
C. J. Cohan; G. Campbell; W. Herman; W. Nugent; J. Heathman; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGOCA
|
| This report presents the results of an analysis of escape system separation techniques from a maximum heating re-entry trajectory. Four escape capsule concepts applicable to a lifting type flight vehicle were considered. These are (1) a separable-noise ballistic body; (2) a separablenose lifting body; (3) a pod capsule; (4) a turnaround capsule. The objective of the study was to determine the applicability of these capsules and various thermal protection schemes ... |
|
| FLUTTER MODEL TESTS OF ADVANCED WING CONFIGURATIONS AT INITIAL ANGLES OF ATTACK |
OCT 1964 |
|
| Authors:
D. A. Brown; NORTH AMERICAN AVIATION INC COLUMBUS OH
|
| This report describes an experimental and analytical program conducted to determine the transonic and supersonic flutter boundary of a highly swept, low aspect ratio lifting surface typical of re-entry vehicle configurations. Several semi-rigid flutter models were constructed and tested at Mach numbers from .4 to 1.2 and also at Mach numbers from 2.0 to 5.0. The effects on flutter speed of initial angle of attack, un-coupled frequency ratio, model thickness ... |
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| COMPARISON OF SATELLITE GROUND TRACK CALCULATIONS BY RAND AND AFIT, |
SEP 1964 |
|
| Authors:
Peter Bielkowicz; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
|
| The results of the study of the ground track of a 24 hour satellite obtained in the AFIT Research Project 64-21 are reviewed to compare both methods in the present study the same orbital parameters, as in the Rand report are used and results plotted for two cases omega = 0 and omega = 90 degrees, yielding quite different curves. (Author) |
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Spacecraft Trajectories and Reentry
