Solar spectrum research. Launched at 1720 local time. Reached 134.5 km.
A bidders' briefing for the Little Joe launch vehicle was held. As earlier mentioned, this launch vehicle was to be used in the development phase of the manned satellite project. The Little Joe launch vehicle was 48 feet in height, weighed (at maximum) 41,330 pounds, was 6.66 feet in diameter, consisted of four Pollux and four Recruit clustered, solid-fuel rockets, could develop a thrust of 250,000 pounds, and could lift a maximum payload of 3,942 pounds. References: 483 .
After a meeting with officials concerned with the missile and space program, President Dwight D. Eisenhower announced that he intended to transfer to NASA control the Army Ballistic Missile Agency's Development Operations Division personnel and facilities. The transfer, subject to congressional approval, would include the Saturn development program. References: 16 .
The first full range tactical prototype, was fired from AMR at 2220 hours EST. All missions assigned to the flight was successfully accomplished. The missile covered a prescribed range of 1,600.448 nm, with the nose cone impacting 0.9 nm short and 0.6 nm to the right. This was the fourth Chrysler-assembled missile to be flight tested. References: 439 .
The Technical Assessment Panels presented to the Evaluation Board their findings on the contractors' proposals for feasibility studies of an advanced manned spacecraft. On October 24, the Evaluation Board findings and recommendations were presented to the STG Director. References: 16 .
A staff meeting of STG's Flight Systems Division was held to fix additional design constraints for the in- house design study of the Apollo spacecraft.
Fundamental decisions were made as a result of this and a previous meeting on September 20. Additional Details: Design constraints for in-house study of the Apollo spacecraft. References: 16 .
Samuel C. Phillips, Apollo Program Director, notified the Center directors and Apollo program managers in Houston, Huntsville, and Cape Kennedy that OMSF's launch schedule for Apollo-Saturn IB flights had been revised, based on delivery of CSMs 009 and 011:
MSC announced that the bubble-type helmet, designed by Crew Systems Division (CSD) engineers Robert L. Jones and James O'Kane, had been adopted for use in the Apollo extravehicular mobility unit. The new helmet was smaller and lighter than earlier types; extensive studies by CSD had demonstrated its superior comfort, visibility, and don/doff characteristics. References: 16 .
MSC Deputy Director George M. Low advised NASA Hq of Houston's planning schedule for follow-up procurement of Apollo spacecraft for the AAP. Based upon the most recent delivery schedules for the last several command and service modules and lunar excursion modules for Apollo, contract award for those vehicles was scheduled for July and August 1966. In accordance with a 14 July directive from Headquarters, MSC was preparing a procurement plan for the extended CSM and the LEM derivatives covering both the final definition and development and operational phases of AAP. Approval of this plan by Headquarters, Low stated, was anticipated for mid-December, while award of contracts for the program definition phase was set for late January 1966. The contract award date for actual development of the extended CSM was slated for October 1966, while that for the LEM derivatives was postponed until mid- 1967 (in line with revised funding directives from Washington).
The ARD was an 80 percent scale model of the Apollo Command Module, and a technology test for a possible International Space Station Crew Rescue Vehicle. Equipment included a TDRS satellite communications system; a GPS navigation system; 7 DASA 40 kgf hydrazine attitude control thrusters; a 2.8 m diameter heat shield; three 23 metre diameter parachutes, and a SARSAT recovery beacon. The ARD separated from the Ariane EPS upper stage at 12 minutes 2 seconds after launch. ARD and the EPC stage manoeuvred into a 1 km x 830 km orbit, guaranteeing re-entry at the end of the first orbit. The spacecraft splashed down in the Pacific at 3.69 degrees N, 153.35 degrees W, and was successfully recovered by the French Navy.
Maqsat 3 was an instrumentation package used to monitor performance of the Ariane 5 booster. At T+12:43 the Speltra adapter cover separated revealing Maqsat-3. At T+15:14 the EPS stage Aestus engine ignited and burned until T+31:00. At this point on a normal mission the satellite would separate from the EPS, but to avoid creating space debris Maqsat remained attached to the EPS. The EPS/Maqsat-3 was placed in a 1027 km x 35863 km x 7.0 degree geostationary transfer orbit.