![]() A minimum of five starts was available for performing these maneuvers. The propulsion system provided the thrust necessary to place the GATV into a selected orbit and to accomplish major orbital changes. Overspeed shutdown electronic-gate and cable assemblyįuel used was unsymmetrical dimethylhydrazine (UDMH) oxidizer used was inhibited red fuming nitric acid (IRFNA).This rocket engine consisted of the following major components: The XLR-8I-BA-13 was a liquid bi-propellant rocket engine with a minimum capability of five starts and a demonstrated capability of fifteen starts under vacuum conditions. At the initial location of the injection point, transferring the Agena to a catch-up orbit for placing the vehicle at the rendezvous point when specified.Circularizing the Agena at the rendezvous radius and proceeding to an inertial location which was a point lying on the line of the apsides of the catch-up orbit.Adjusting the orbits so that they were coplanar and making the radius of one apside of the Agena orbit equal to the rendezvous radius.Once the GATV was in orbit, the PPS provided the thrust necessary for the following maneuvers : A minimum of five main-engine burns were available to complete the mission requirements one burn was required for injection into orbit and four subsequent burns were available to perform orbital plane and phase changes, as required and selected from ground stations or from the spacecraft. The propulsion system was designed to inject the GATV into an orbital path which has an altitude varying between 161 nautical miles (nm) and 87 nm when measured at a latitude of 28. The remaining portion of the nozzle (13.3:1 to 45:1) was a radiation-cooled titanium extension. The nozzle was regeneratively cooled up to the point at which the area ratio was 13.3: I. This thrust chamber assembly performed satisfactorily throughout a gimbaling orientation of plus 5 deg in a square pattern from the associated planes, with a gimbal acceleration of 30 rads/sec/sec. The XLR-81-BA-13 engine thrust chamber was an 80-percent bell-shape with an expansion ratio of 45:1. All associated pyro devices and solid-propellant rockets.Fuel and oxidizer feed and load system, including propellant tanks, vents, and fill quick disconnects.Pyrotechnically operated helium-control valve (POHCV) and associated pressurization plumbing.Model 8247 rocket engine, also known as XLR-81-BA-13, and its controls, mount, gimbals, and titanium nozzle extension.The Gemini-ATV propulsion system consisted of the following: This weight included propellants still remaining in the main tanks and available for Model 8247 engine operation after the Agena achieved orbit. Vehicle weight-on-orbit was approximately 7200 lb. Orbital length of the GATV was approximately 26 feet. The Model 8247 multi-start main engine and the smaller Model 8250 maneuvering and ullage orientation engines were located in this section. The Agena-D forward section housed the main equipment bay, and the mid-body contained the main fuel and oxidizer tanks which supplied propellants through a feed and load system for the main engine. The Agena-D forward and mid-body sections.This section consisted of the auxiliary equipment rack, the McDonnell Aircraft Company-furnished docking-adapter module, and the clamshell nose shroud. The program-peculiar forward auxiliary section.The Gemini-Agena Target Vehicle design was an adaptation of the basic Agena-D vehicle using the alternate Model 8247 rocket engine and additional program-peculiar equipment required for the Gemini mission. ![]() After docking, the Agena had sufficient fuel reserves to boost the Gemini into high earth orbits, to the edge of the Van Allen radiation belts. To provide the Gemini spacecraft with a rendezvous and docking target, Agena D rocket stages were modified with the addition of a docking collar, status panel display, and restart capabilities for the Gemini program. Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9Ī- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- ZĪmerican modification of the Agena-D upper stage for use as a docking target and space tug for Gemini.
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