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Figure 144.- Close-up of SP flyaway release rods. The relay antenna was folded next to the back of the outboard +X subpanel during the launch phase. Simultaneous with the panel tip release, the relay antenna was unlatched by relieving the force on a spring-loaded control cable. This control cable pulled a clevis pin and allowed the antenna spring strut to deploy the antenna to its required position. The high-gain antenna was constrained in the stow position during launch by a pin puller which...

Info

Magnetic latching relay in response to the command, which modified the VO electrical power configuration. Power to cause the state change of the relay was provided by the 30 V dc bias supplies. The ACS Sun-sensor circuit issued a Sun-gate signal when the array had Sun acquired within its dead band of 5.0 1.5 . This Sun-gate signal was routed to the share mode detector circuit to automatically enable the boosting function. This function enabled with the presence of the Sun-gate signal and...

Hhe

FflXH re lief (r) Press reg ( Filter Manual valve ll- -ll- -ICk valve Q Orifice FBV fuel B P valve H Field joint Solenoid valve OxBV Ox B P valve Position Figure 135.- Schematic diagram of PROPS. flowed from the propellant tanks, through the propellant isolation assemblies, and into the rocket engine combustion chamber. There they mixed and chemically reacted creating gaseous reaction products which were accelerated through the engine and ejected at high velocity. The combustion chamber...

Table Rocket Engine Rated Performance Summary

Thrust chamber physical characteristics Combustion chamber Diameter, cm (in.) 7-G2 (3.0) Characteristic lenyth, cm (in.) 29.5 (11.6) Throat diameter, cm (in.) 3.44 (1.3555) Exit diame ter, cm (in.) 26.7 (lo 5) Contour . . . . Modified 80 be3 1 Throat area, cm' (in2) '3.31 (1.44 31) Exit, area, cm2 (in2) 553.6 (Rf-,.59) Steady-state performance characteristics Specific impulse, N-sec kg (lb-sec lb) 2858 (291.7) Mixture ratio Ox, kq sec (lb sec) 0.282 (0.620R) Fuel , kq sec (lb sec) r,. 1 h7 (0 ....

Data Handling

The data handling configuration depicted in figure 28 shows the functional flow of all on-board data. Data were divided into two groups, VO and VLC each of which is further categorized as follows Engineering data Memory data IR science data VIS data All data generated by VO S S's plus VLC cruise data were routed to the FDS for selection and initial processing. After FDS processing, the data were routed to the MDS and or the DSS. VLC preseparation data at 1000, 2000, 40001, or 16 0001 bps were...

Temperature Control

The VO temperature control design was configured to maintain all parts of the VO within favorable temperature limits for the range of conditions which the VO would experience between launch and an extended stay in Mars orbit. Temperatures were monitored within all VO subsystems. In addition, heaters, SEC's, and the control of these items required more than a temperature-sensing type interface with the PROPS, ARTCS, PWRS, and CCS. The SEC's and temperature control louvers for the bus and...

Irtms I Mawds

Figure 6.- Simplified block diagram of PWRS. Solar panel mode When the VO solar panels were illuminated, raw dc power was supplied by the panels. The VO was considered to be in a solar panel mode when the total VO power load demand was within the output power capability of the panels. Share mode A battery solar panel share mode existed when the fully or partially illuminated solar panel output power was insufficient to support the VO power demand. While in this mode, the solar panel output...

Description Of Major Subsystems

A simplified functional block diagram of the VO is presented in figure 7. The S S's are briefly described as follows in the order given in table 1. Structure subsystem STRUS provided mechanical support and alignment for all flight equipment, passive thermal control, and micrometeoroid protection. In addition, the structure provided means for handling the assembled VO for flight qualification testing, transporting, and mating operations with the VLC and the LV. STRUS included a basic bus...

Introduction

The Viking Project was initiated in 1968 and was climaxed with the launching of two Viking spacecraft in 1975. The first landing on Mars was July 20, 1976, and the second landing was September 3, 1976. Each spacecraft contained an orbiter and a lander. The objective of the Viking Mission was to increase significantly man's knowledge of the planet Mars through orbital observations by the orbiter as well as by direct measurements made by the lander during Martian atmospheric entry, descent, and...

Pwrs Pyros

Open helium pressurant line first time Close helium pressurant line first time Open helium pressurant lino second time Close helium pressurant lino second time Open helium pressurant line third time, when this cmd was issued, there was no way to close the pressurant 1ine again Open squib-actuated B P valve in fuel supply line use only if sol iso valve fails closed Open squib-actuated B P valve in Ox supply lino use only if sol iso valve fails closed Open latching sol valve in Ox supply line if...

Power Capabilities And Requirements

The VO had 2.4-kHz single-phase, 400-Hz three-phase, regulated dc 30 V and 56 V and unregulated dc 25 V to 50 V power sources. Unregulated dc power was also provided for the VLC. Arrays of photovoltaic cells arranged on four double-section, folding solar panels furnished primary power for all Sun-oriented operations. Two identical nickel-cadmium batteries were used as a secondary source of power for off-Sun operations and to share the load when power demand exceeded the solar array capability....