O

Total weight of vehicle at lift-off and at ignition of succeeding powered phases less payload. First stage loaded weight does not include 3964 lbs. start and ground leases. Lo* stage weights do not include propellent weight expended without impulse credit during first stage. , > . Second stage propellant weight includes bb lbs. of start propellent. 134 lbs. of lox is bled through the 2nd stage gas turbines during Stage I fxight-. Verniers are ignited rior to Stage I burnout and consume 132...

Atlasagena B

ATLAS SM68D AGEKA B TRAJECTORY AND PAYLOAD DATA The trajectory data presented is based on nominal inputs. The payload data, however, is minimum guaranteed obtained by taking the root-sum-square of the degradations in the booster and algebraically adding the root-sum-square of the degradations in the Agena to obtain the -3 fftotal degradation. In practice this means that there is a quantity of nominally unused propellant contingency in both the booster and the Agena to compensate for trajectory...

C

Characteristics of Delta Guidance System The Delta utilizes a flight controller mounted in the first stage guidance section for control of the vehicle during first stage powered flight. Three xate gyros mounted on the first stage are used in conjunction with the flight controller. At the end of the first 90 seconds of powered flight, the modified 300 BTL radio guidance system, located in the second stage vehicle modifies the first stage flight control programmer signals. The BTL system...

Guidance System Descriptionfor Than B

Spark Plug inertial guidance system weighing 238 lbs. The inertial measurement unit is made up of a gyro stabilized platform, integrating accelerometers and associated electronics. It is housed in a package 19 in diameter by 27 long. Hie computer contains the circuitry and storage required to solve the guidance equations and process gimbal and accelerometer outputs into steering commands. Die digital computer is housed in a package 20 x 22 x 12. Both pieces of equipment...

Titan Eagena B Modi

Dxts vehicle has been studied by Lockheed Aircraft Company. Though not currently under development, performance estimates are presented. The Titan ascent trajectory used is similar to that of the Atlas until first stage separation. However, after ignition of the second stage, the trajectory consists of a phase of constant attitude rate in lnertlal space rather than a consta attitude path in local space. This continues throughout the remainder of the boost and Agena phase of powered flight,...

Centaur Guidance System

The Centaur guidance system is all inertial consisting primarily of a four-gimbal all attitude inertial platform and a general purpose serial digital computer with a magnetic drum memory. Ths fi Lrboms uld amp ncG pro r amp ni is written onto the dnun iDsiDory from a punched paper tape along with a pre-flight calibration and alignment program for trimming and aligning the platform prior to launch. For the 2k hr. equatorial orbit mission the Centaur guidance system performs the following...