Editing Surveyor 1 (section)

== Science instruments ==

=== Television ===
[[File:Surveyor-1-foot-pad.jpg|thumb|Image from Surveyor 1 of its footpad in order to study [[soil mechanics]] in preparation for the Apollo crewed landings.]]
The TV camera consisted of a [[vidicon]] tube, a zoom lens operated at either end of its range resulting in 25 millimeter and 100 millimeter focal-lengths, resulting in optical fields of view of 25.3 or 6.43 degrees, a shutter, clear, orange, green and blue optical filters,<ref name=":0">{{Cite book |url=https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19690027073_1969027073.pdf |title=NASA SP-184 - SURVEYOR Program Results |date=1969 |publisher=NASA |pages=109}}</ref> and [[iris (anatomy)|iris]]-system mounted along an axis inclined approximately 16 degrees from the central axis of Surveyor 1. The camera was mounted under a mirror that could be moved in azimuth and elevation. The rotation of the mirror in the azimuth direction, while providing azimuth coverage capability results in an image rotation proportional to the angular azimuth position of the mirror. This is because the image plane and scanning raster of the vidicon are stationary with respect to the mirror azimuth axis. The mirror drive mechanism consisting of stepper motors provided a step size of 2.48° ±0.1° in elevation and 3.0° ±0.1° in azimuth. This calibrated stepping reference allowed the creation of large composite mosaics of the lunar surface and using the data read-back from the iris and focus positioning of the lens permitted some photogrammetric measurements of various lunar features.<ref>Montgomery, Wolf ''The Surveyor lunar landing television system''. IEEE Spectrum, August 1966, p. 55-56</ref> The TV camera's operation was dependent on the receipt of the proper radio commands from the Earth. Frame-by-frame coverage of the lunar surface was obtained over 360 degrees in azimuth and from +40 degrees above the plane normal to the camera's axis to -65 degrees below this plane. Both 600-line and 200-line modes of operation were used. The 200-line mode transmitted over an omnidirectional antenna for the first 14 photos and scanned one frame every 61.8 seconds. The remaining transmissions were of 600-line pictures over a directional antenna, and each frame was scanned every 3.6 seconds. Each 200-line picture required 20 seconds for a complete video transmission and it used a [[bandwidth (signal processing)|radio bandwidth]] of about 1.2 [[kilohertz]].

Each 600 line picture required about one second to be read from the vidicon tube, and they required a [[bandwidth (signal processing)|radio bandwidth]] of about 220 kilohertz. The data transmissions were converted into a standard TV signal for both [[closed-circuit TV]] and [[broadcast TV]]. The television images were displayed on Earth on a slow-scan monitor coated with a long persistency phosphor. The persistency was selected to optimally match the nominal maximum frame rate. One frame of TV identification was received for each incoming TV frame, and it was displayed in real time at a rate compatible with the incoming image. These data were recorded on a video magnetic tape recorder. Over 10,000 pictures were taken by Surveyor 1's TV camera before the lunar sunset of June 14, 1966. Included in these pictures were wide-angle and narrow-angle panoramas, focus ranging surveys, photometric surveys, special area surveys, and celestial photography. Surveyor 1 responded to commands to activate the camera on July 7, and by July 14, 1966, it had returned nearly 1000 more pictures.
<gallery heights="140px" mode="packed">
File:Surveyor 1 shadow lunarsurface.jpg|Surveyor 1's shadow against the lunar surface (upside-down image)
File:Surveyor 1 Fig 7-41a1.jpg|The mare surface
File:Surveyor 1 Fig 7-41a2.jpg|Another view of the mare surface
File:Surveyor 1 Fig 3-36a.jpg|Irregularly shaped crater at the landing site
File:Surveyor 1 Fig 3-56.jpg|Mottled rock about 50&nbsp;cm long near Surveyor 1
</gallery>

=== Strain gauge ===
Strain gauges were mounted on each leg shock absorber to record the peak axial forces at landing impact of the spacecraft. They were designed to accept a force of approximately 800 [[kilogram-force|kgf]] (7.8&nbsp;kN).