Lunar Module Circuit Breakers Panel Diagram

Mission J*

Figur«; 2. 1 18 Dfflcent Kleine C'iinlrol Schematic (She^t l ul 2) GUIDANCE, NAVIGATION, AND CONTROL SUBSYSTEM Djal- r*"J_ffbn"'r>' Clu"«« "*" 1 *Prl' '»71 Page J. 1-J7

LMA890 3 LM A PO I j I.O OPERATIONS HANDBOOK SUBSYSTEMS DATA

Figure 2. 1-18. Desrent Engine Control Schematic (Sheet 2 of 2)

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Figure 2. 1-18. Desrent Engine Control Schematic (Sheet 2 of 2)

GUIDANCE, NAVIGATION, AND CONTROL SUBSYSTEM Mission LM Basic Date 1 February 1970 Change Date

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I.MA7UU-3-I.M AKJl.l.O OPERATIONS HANDBOOK SUDSYSTEMS DATA

F11,111«: 2. 1 -1 ü. Abitiil t. nullit' centro] .Sc:h<;mulic (Slicel 1 uf 2) GUIDANCE, NAVIGATION, AND CONTROL SUBSYSTEM LM Basic Datt-_ 1 Ft'bruuri lb70 Chance- Date 15.Juiifc 1970 2.1-39

I.MA7M-3-LM A COLIjO OPKRATIONS il ANniu X)K SUBSYSTEMS DA fA

Figure 2. 1-19. Ascent Engine Control Schematic (Sheet 2 "f 2)

GUIDANCE. NAVIGATION. AND CONTROL .SUBSYSTEM p

Pae:e_2. 1 -40 ___Mission _LM_Basic Date_l February 1970___Change Date 15

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Figure 2. 1-20. GN&CS Power Distribution (Sheet I o( 2)

guidance. navigation, and control subsystem

Mission LM _ Basic Date 1 February 1970 Changp Date_15 June 1970 Page 2.1-41

LMA790-3- l,M APOI.1,0 OPERATIONS HANDBOOK SURSYSTEMS DATA

Fijrurp 2. 1-20. GNJiCS Power Distribution (Sheei 2 «>f 2)

Page_2.1-42

GUIDANCE. NAVIGATION. AND CONTROL SUBSYSTEM Mission LM Basic Date_lX?br_u_a_TY L9?0..__Change Date__15 June 1970

The signal conditioner assembly (SCA) receives its operating power from the PSA. The operating power includes IMU operate and IMU standby +28 volts dc used for B+ voltage in the SCA circuits, and reference voltages consisting of 800-cps and 3, 200-cps 1% feedback voltage from the IMU. Three additional reference voltages (2. 5 volts dc for bias, an 800-cps square wave, and a 3, 200-cps square wave) are generated in the SCA.

The AOT receives 115 volts ac for illumination of the reticle, from the AC BUS A and the AC BUS B: AOT LAMP circuit breakers. The heaters in the AOT receive power from the CDR's d-c bus through the HEATERS: AOT circuit breaker.

All power (ac and dc) required by the ASA is provided by the ASA power supply, which receives 28-volt d-c power from the STAB/CONT: ASA circuit breaker (panel 16). The power supply provides regulated 28 volts dc for current regulators, +12 volts dc to bias amplifiers in the accelerom-eters, +4 volts dc for use in a frequency countdown subassembly and the gyros, -12 volts dc for use in the gyros, -6 volts dc for use as bias for the gyros, and -2 volts dc for use as bias in the frequency countdown subassembly. A-C voltages are provided for the accelerometer gyros and pulse torquing servoassemblies by 28-volt, 800-cps inputs from the ATCA.

The AEA uses two power supplies. One operates in the standby and operates modes. It supplies power to clock countdown circuits and for the three integrating registers of the input-output subassembly. The other power supply operates in the operate mode and supplies power to the remainder of the AEA. These power supplies receive 28-volt d-c power from the STAB/CONT: AEA circuit breaker (panel 16) and 115-volt, 400-cps power from the AC BUS B: AGS circuit breaker (panel 11). They also receive 28-volt, 800-cps power from the ATCA power supply for synchronization. The operate power supply provides -2, +4, +6, +13. 5, +14, -13. 5, and -18 volts dc.

The DEDA operating power consists of +4 and -2 volts dc supplied by the operate power supply of the AEA.

The CDR's and LMP's 28-volt d-c buses and the CDR's 115-volt a-c bus supply power to the CES. The ACA receives 28-volt d-c power from the CDR's bus for two-jet direct control through the I STAB/CONT: ATT DIR CONT circuit breaker. D-C excitation from the ATCA is used by the ACA to I generate pulse commands. Proportional rate commands are generated from a 28-volt, 800-cps signal I from the ATCA. This input signal to the ACA is also used by the TTCA during AGS control, for gener- I ation of throttle commands. During PGNS control, the PSA supplies the excitation voltage for the TTCA. The TTCA receives ±15 volts dc via an S&C control assembly from the ATCA power supply for the generation of translation commands. The STAB/CONT: ATT DIR CONT circuit breaker also provides power for the secondary coils of the TCA's during the direct mode and when the +X TRANSL pushbutton is used. I

The ATCA primary power supply receives 28 volts dc from the LMP's bus through the I

STAB/CONT: ATCA circuit breaker. When the ATCA/ AGS circuit breaker is on and GUID CONT switch is set to AGS and the MODE CONTROL: AGS switch is set to ATT HOLD or AUTO, the thruster drivers | are enabled. When the BAL CPL switch is set to ON, the 28 volts from the circuit breaker enables the four upward-firing thrusters. Power from the circuit breakers is also used to test the RGA, using the GYRO TEST switches (panel 3).

The ATCA primary power supply provides regulated +15, -15, and +4. 3 volts dc for the ATCA and other GN&CS equipment, and +6 and -6 volts dc for the ATCA only. The power supply is synchronized by a 1. 6-kpps signal (square wave) to generate a regulated 28-volt, 800-cps, 1« output and a regulated, isolated, 28-volt, 800-cps, 30 output for RGA gyro spin motor excitation. Single phase is also supplied for AEA signal reference excitation. If the synchronizing pulses are lost, the power supply runs free at 800 cps ±1%. Another ATCA power supply uses the 28-volt d-c input to generate redundant -4.7 volts dc for use within the ATCA, for jet solenoid driver bias. Also, 28-volt, 800-cps | power is supplied to the RR as "backup" power and to the IS and the rate displays as reference.

The STAB/CONT: DECA PWR circuit breaker supplies +28 volts dc to the descent engine control circuit in the DECA. When the descent engine is armed, this input power is routed to the actuator isolation valves of the descent engine. The power supply of the DECA consists of a reference power apply and an auxiliary power supply. The reference supply receives +15 and -15 volts dc from the ■.. 3-volt d-c ATCA power supply. D-C active regulators in the reference supply convert the +15 and -15 volts dc to +6 and -6 volts dc, respectively. The 6-volt outputs of these regulators are very stable; they are used as a source for a voltage divider, which supplies the reference voltages to the comparators.

The auxiliary power supply receives 400-cps power from the CDR's a-c bus through the AC BUS A: DECA GMBL circuit breaker. The power supply rectifies and filters the a-c power to supply +22 and -22 volts dc for the DECA manual throttle circuit and +22 volts dc for the power failure time-delay circuit. During an ATCA power failure, the auxiliary power supply provides +6 volts dc to the descent engine control circuit and enables full thrust of descent engine. In addition, +22- and -22-volt d-c reference voltages are used for a power failure monitor circuit in the DECA. The +15- and -15-volt d-c inputs to the reference power supply are also connected with the +22- and -22-volt d-c inputs, respectively, to supply the manual throttle circuit if the 22-volt d-c supplies fail.

Power from the STAB/CONT: DES ENG CONT circuit breaker enables the engine control circuits in the DECA. This power is interrupted when the ABORT STAGE pushbutton is used or when the ABORT or STOP pushbuttons are used. The STAB/CONT: ENG START OVRD, AELD (2), ABORT STAGE (2) ENG ARM, and DES ENG OVRD circuit breakers are used in conjunction with the relay logic of the DECa and S&C control assemblies to accomplish ascent or descent engine control.

The GASTA receives 115 volts ac from the CDR's a-c bus through the AC BUS A: GASTA circuit breaker and 28 volts dc from the CDR's d-c bus through the FLIGHT DISPLAYS: GASTA circuit breaker. These two inputs energize the computer servo in the GASTA.

2.1. 3. 6. 4 ORDEAL Power Distribution.

The ORDEAL receives 115 volts ac from the CDR's a-c bus through the AC BUS B: ORDEAL circuit breaker and 28 volts dc from the CDR's d-c bus through the FLIGHT DISPLAYS: ORDEAL circuit breaker. The 115-volt a-c power lights the ORDEAL panel and drives the resolvers. The d-c power is used for switching.

2. 1. 3. 6. 5 800-cps Synchronization Loop. (See figure 2. 1-21.)

Because the CES uses 800-cps analog signals as a reference, the various assemblies must be synchronized. In the primary guidance mode, the ACA's and TTCA's receive 28-volt, 800-cps | signals from the PSA of the PGNS. The proportional attitude commands to the LGC are either in phase or 180° out of phase with this 800-cps signal. In the abort guidance mode, the ACA's and TTCA's receive 28-volt, 800-cps signals from the ATCA. The proportional attitude commands fed back to the ATCA are now synchronized with the ATCA power supply. The AGS and RGA receive 28-volt, 800-cps signals from the ATCA; their outputs, returned to the ATCA, are synchronized. The FDAI's also receive the 800-cps synchronization voltage to properly display the RGA signals. In turn, the ATCA itself is synchronized to the clock (1, 600 pps) of the PCMTEA; however, it can run free as its own source should this synchronizing pulse be lost.

2. 1. 4 MAJOR COMPONENT/FUNCTIONAL DESCRIPTION.

2.1. 4.1 Primary Guidance and Navigation Section - Inertia! Subsection.

The ISS comprises the navigation base (NB), IMU, the coupling data unit (CDU), the pulse torque assembly (PTA), the power and servo assembly (PSA), and the signal conditioner assembly (SCA). (See figure 2.1-22.)

ISS operation can be initiated automatically by the LGC, or manually by the astronaut using DSKY entries to command the LGC to select the various operating modes. The ISS status or mode of operation can be displayed on the DSKY, as determined by a computer program. The IMU furnishes the inertial reference; it consists of a stable member with three degrees of freedom, stabilized by three integrating gyros. The stable member must be aligned with respect to the reference coordinate system each

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