A method of estimating the apogee and perigee error incurred in establishing the orbit of a spin-stabilized vehicle

A theory has been developed which determines the influence of primary errors upon the dispersion of the apogee and perigee altitudes of the orbit of a satellite vehicle. It is seen that the apogee and perigee altitudes are influenced chiefly by the errors in velocity and flight-path angle at burnout of the next-to-last stage, guidance, velocity increment and thrust alinement, and pitching rate at ignition of the last stage. The theory will allow the probability of a satellite vehicle successfully obtaining a given orbit to be determined. A series of charts which greatly reduce the amount of work required in applying the theory are included. The theory has been applied to the Scout missile for a range of injection altitudes and one payload weight which is representative of the capability of this vehicle. One of the major requirements of any future satellite vehicle will be an improved guidance system so that the Scout probably will be the worst case to which the theory will be applied.

Name thesis:degree_name

Master of Science

Level thesis:degree_level

masters

Discipline thesis:degree_discipline

Aeronautical Engineering

Department dc:contributor.department

Aeronautical Engineering

Grantor dc:publisher

Virginia Tech

Year dc:date.issued

1960

Author dc:creator

• Garland, Benjamine J.

Chair dc:contributor.committeechair

• Eades, James B. Jr.

Committee member dc:contributor.committeemember

• Truitt, Robert W.

Statement dc:rights

• In Copyright

Licence dc:rights.uri

• http://rightsstatements.org/vocab/InC/1.0/

Language dc:language.iso

en

Dc Identifier Other

etd-08012012-040052

OAI identifier oai:identifier

oai:vtechworks.lib.vt.edu:10919/44040