Longitudinal aerodynamic characteristics of the Viking lander capsule at Mach 6
Longitudinal aerodynamic characteristics of Viking lander spacecraft at hypersonic speed
Emery, J. C.↗
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Experience applicable to the Viking lander from a study of related space flight projects
Related space mission data for baseline evaluation of Viking Lander design and operation
Butterfield, A. J.↗
Transonic aerodynamic characteristics of the Viking entry and Lander configurations
Wind tunnel tests to determine aerodynamic characteristics of Viking spacecraft entry and lander configurations at transonic speed
Mc Ghee, R. J.↗
Mars lander deorbit trajectory analysis
Mars lander deorbit trajectory sensitivity analysis for fixed flight path and communications angles at atmospheric entry, comparing with Monte Carlo simulation
Euler, E. A.↗
A technique for lifting entry and terminal phase system optimization for the 1975 Mars Viking lander
Lifting entry and terminal phase system optimization for 1975 Mars Viking lander, considering graphical tradeoff approach including design parameter and atmosphere model variations
French, C. E.↗
The Viking Lander Power System
Viking Lander power system design, discussing functional requirements by mission and science objectives and reliability features
Farley, K.↗
Manned Mars lander launch-to-rendezvous analysis for a 1981 Venus-swingby mission
A description is given of the return of a manned Mars lander by a launch from the surface of Mars to some intermediate orbit, with subsequent maneuvers to rendezvous with a primary spacecraft (called the orbiter) in a Mars parking orbit. The type of Mars mission used to demonstrate the analytical technique includes a Venus swingby on the Mars-to-Earth portion of the trajectory in order to reduce the total mission velocity requirement. The total velocity requirement for the mission considered (if inplane launches are assumed) is approximately 17,500 ft/sec.
Faust, N. L.↗
Flow field measurements around a Mars lander model using hot film anemometers under simulated Mars surface conditions
Results are presented from a wind-tunnel investigation of the flow field around a 0.45-scale model of a Mars lander. The tests were conducted in air at values of Reynolds number equivalent to those anticipated on Mars. The effects of Reynolds number equivalent to those anticipated on Mars. The effects of Reynolds number, model orientation with respect to the airstream, and the position of a dish-type antenna on the flow field were determined. An appendix is included which describes the calibration and operational characteristics of hot-film anemometers under simulated Mars surface conditions.
Greene, G. C.↗
Formulation of image quality prediction criteria for the Viking lander camera
Image quality criteria are defined and mathematically formulated for the prediction computer program which is to be developed for the Viking lander imaging experiment. The general objective of broad-band (black and white) imagery to resolve small spatial details and slopes is formulated as the detectability of a right-circular cone with surface properties of the surrounding terrain. The general objective of narrow-band (color and near-infrared) imagery to observe spectral characteristics if formulated as the minimum detectable albedo variation. The general goal to encompass, but not exceed, the range of the scene radiance distribution within single, commandable, camera dynamic range setting is also considered.
Huck, F. O.↗
Viking Lander antenna deployment mechanism
One of the mechanisms that is included in the configuration of the Viking Mars Lander is an antenna dish deployment mechanism which utilizes a mechanical escapement device for controlling deployment. The criteria require that the mechanism be capable of deploying the antenna under a wide range of aiding and retarding winds after landing on Mars but must limit the acceleration during deployment and latching of the antenna. Adding to the complexity of the design are the requirements for very accurate alignment after erection and heat sterilization prior to launch. This mechanism has been designed, fabricated and successfully tested to qualification test levels for usage on the Viking mission.
Hopper, K. H.↗
Study of a quasi-microscope design for planetary landers
The Viking Lander fascimile camera, in its present form, provides for a minimum object distance of 1.9 meters, at which distance its resolution of 0.0007 radian provides an object resolution of 1.33 millimeters. It was deemed desirable, especially for follow-on Viking missions, to provide means for examing Martian terrain at resolutions considerably higher than that now provided. This led to the concept of quasi-microscope, an attachment to be used in conjunction with the fascimile camera to convert it to a low power microscope. The results are reported of an investigation to consider alternate optical configurations for the quasi-microscope and to develop optical designs for the selected system or systems. Initial requirements included consideration of object resolutions in the range of 2 to 50 micrometers, an available field of view of the order of 500 pixels, and no significant modifications to the fascimile camera.
Giat, O.↗
Experimental validation of a landing-dynamics computer program for legged spacecraft landers
Validation of a landing-dynamics computer program has been accomplished by comparing analytical data with data from a limited experimental program. Agreement obtained established the subject landing-dynamics computer program as a reliable design tool for legged spacecraft landers.
Mcgehee, J. R.↗
Optical analysis of a compound quasi-microscope for planetary landers
A quasi-microscope concept, consisting of facsimile camera augmented with an auxiliary lens as a magnifier, was introduced and analyzed. The performance achievable with this concept was primarily limited by a trade-off between resolution and object field; this approach leads to a limiting resolution of 20 microns when used with the Viking lander camera (which has an angular resolution of 0.04 deg). An optical system is analyzed which includes a field lens between camera and auxiliary lens to overcome this limitation. It is found that this system, referred to as a compound quasi-microscope, can provide improved resolution (to about 2 microns ) and a larger object field. However, this improvement is at the expense of increased complexity, special camera design requirements, and tighter tolerances on the distances between optical components.
Wall, S. D.↗
The facsimile camera - Its potential as a planetary lander imaging system
The facsimile camera is an optical-mechanical scanning device which is an attractive candidate for planetary lander imaging systems and has been selected for the Viking/Mars mission because of its light weight, small size, and low power requirement. Other advantages are that it can provide good radiometric and photogrammetric accuracy because the complete field of view is scanned with a single photodetector located on or near the optical axis of the objective lens. In addition, this device has the potential capability of multispectral imaging and spectrometric measurements.
Huck, F. O.↗
Cost effectiveness as applied to the Viking Lander systems-level thermal development test program
The economic aspects of thermal testing at the systems-level as applied to the Viking Lander Capsule thermal development program are reviewed. The unique mission profile and pioneering scientific goals of Viking imposed novel requirements on testing, including the development of a simulation technique for the Martian thermal environment. The selected approach included modifications of an existing conventional thermal vacuum facility, and improved test-operational techniques that are applicable to the simulation of the other mission phases as well, thereby contributing significantly to the cost effectiveness of the overall thermal test program.
Buna, T.↗
Viking Mars lander 1975 dynamic test model/orbiter developmental test model forced vibration test
The Viking Mars Lander 1975 dynamic test model and orbiter developmental test model were subjected to forced vibration sine tests. Flight acceptance (FA) and type approval (TA) test levels were applied to the spacecraft structure in a longitudinal test configuration using a 133,440-N (30,000-lb) force shaker. Testing in the two lateral axes (X, Y) was performed at lower levels using four 667-N (150-lb) force shakers. Forced vibration qualification (TA) test levels were successfully imposed on the spacecraft at frequencies down to 10 Hz. Measured responses showed the same character as analytical predictions, and correlation was reasonably good. Because of control system test tolerances, orbiter primary structure generally did not reach the design load limits attained in earlier static testing. A post-test examination of critical orbiter structure disclosed no apparent damage to the structure as a result of the test environment.
Fortenberry, J.↗
Viking lander design and systems integration
Malfunction protection requires redundancy planning and mechanization in Viking lander design and systems integration in order to maximize the chance of getting the data back through the Orbiter. Various subsystems are discussed that protect the downlink to man on the ground in the framework of systems integration and insure the basic objectives of Viking: to land on a planet and to acquire data from its surface.
Goodlette, J.↗
Verification of a landing dynamics computer program using Viking Lander data
An investigation was conducted to verify the accuracy of the Landing Dynamics Computer Program (LDCP) used to simulate the landing event of the Viking Lander (VL) on to the Martian surface. This verification was achieved by comparing the analytical data with results from a test program involving a dynamically scaled model of a VL configuration. A secondary objective of this study was to evaluate the sensitivity of the VL to initial rates and orientations, configuration modifications, and footpad friction.
Muraca, R. J.↗