To install click the Add extension button. That's it.

The source code for the WIKI 2 extension is being checked by specialists of the Mozilla Foundation, Google, and Apple. You could also do it yourself at any point in time.

4,5
Kelly Slayton
Congratulations on this excellent venture… what a great idea!
Alexander Grigorievskiy
I use WIKI 2 every day and almost forgot how the original Wikipedia looks like.
Live Statistics
English Articles
Improved in 24 Hours
Added in 24 Hours
What we do. Every page goes through several hundred of perfecting techniques; in live mode. Quite the same Wikipedia. Just better.
.
Leo
Newton
Brights
Milds

Pad Abort Test 2

From Wikipedia, the free encyclopedia

Pad Abort Test 2
Apollo LES Pad Abort Test (NASA)
Mission typeAbort test
OperatorNASA
Mission duration1 minute, 52.6 seconds
Distance travelled2.32 kilometers (1.44 mi)
Apogee2.82 kilometers (1.75 mi)
Spacecraft properties
SpacecraftApollo BP-23A
Start of mission
Launch dateJune 29, 1965, 13:00:01 (1965-06-29UTC13:00:01Z) UTC
RocketApollo LES
Launch siteWhite Sands LC-36
End of mission
Landing dateJune 29, 1965, 13:01:54 (1965-06-29UTC13:01:55Z) UTC
Project Apollo
Abort tests
← A-003
A-004 →
 

Pad Abort Test 2 was the follow-on second abort test to Pad Abort Test 1 of the Apollo spacecraft .

YouTube Encyclopedic

  • 1/3
    Views:
    477 030
    166 373
    12 387 409
  • NASA’s Ascent Abort-2 Test of Orion
  • Launch of Orion Spacecraft Ascent Abort-2 Test
  • SpaceX Pad Abort Test

Transcription

Objectives

Apollo Pad Abort Test 2 was the fifth of six uncrewed Apollo missions that flight tested the capability of the launch escape system (LES) to provide for safe recovery of Apollo crews under critical abort conditions. This flight was the second test of the launch escape system with the abort initiated from the launch pad.

The launch escape system included qualified launch escape and pitch motors and was equipped with canards to orient the vehicle aft heat shield forward prior to tower jettison and parachute deployment. A boost protective cover was also provided. The spacecraft was BP-23A, a boilerplate Apollo command module that had been used on mission A-002 and refurbished to more nearly simulate a Block-I-type command module in mass and other characteristics. The Earth landing system was similar to the one used in mission A-003.

Flight

The test flight was conducted on June 29, 1965. The vehicle was lifted from Launch Complex 36 by the launch escape motor at 13:00:01 UTC (06:00:01 MST). The launch escape and pitch control motors ignited simultaneously, placing the test vehicle into the planned initial trajectory. A moderate roll rate developed at lift-off, which was due to the aerodynamic asymmetry of the vehicle configuration; however, the roll rate did not affect the success of the test.

The canard surfaces deployed and turned the vehicle to the desired orientation for drogue parachute deployment. During the turnaround maneuver, the launch escape tower and forward heat shield were jettisoned as planned. The boost protective cover, which was attached to the launch escape system, protected the conical surface of the command module and remained intact through a canard-induced pitch maneuver. At tower jettison, the soft boost protective cover, as expected, collapsed because of differential pressure during removal from the command module. No recontact or interference between the major components was evident during tower jettison and parachute deployment.

Although one of the pilot parachute steel cable risers was kinked, the Earth landing system functioned properly. The drogue parachutes inflated and stabilized the command module for pilot and main parachute deployment, and the rate of descent while on the main parachutes was satisfactory. The maximum altitude achieved was 9,258 feet (2,822 m) above mean sea level, approximately 650 feet (200 m) higher than predicted. The command module landed about 7,600 feet (2,300 m) from the launch site, some 2,000 feet (610 m) farther than planned.

Four glass samples had been mounted on the command module in the general area planned for the rendezvous and crew windows. No soot appeared on the samples, but an oily film was found on the exposed surfaces of three of the four samples. This film, however, was not expected to cause excessive degradation to the horizon scan or ground orientation ability during an abort. The test was highly successful and all planned objectives were fulfilled.

External links

Public Domain This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.

This page was last edited on 9 February 2024, at 07:58
Basis of this page is in Wikipedia. Text is available under the CC BY-SA 3.0 Unported License. Non-text media are available under their specified licenses. Wikipedia® is a registered trademark of the Wikimedia Foundation, Inc. WIKI 2 is an independent company and has no affiliation with Wikimedia Foundation.