Operator and organizational maintenance manual, loader transporter M688, mobility kit M234, tripod hoist M38, sling beam M22, Lance Missile System.

"MS 419586."

Organizational, direct support and general support maintenance repair parts and special tools list including depot maintenance repair parts and special tools for propellant draining kit, guided missile, 10293020, 1450-00-140-3490, Lance Field Artillery Missile System.

Includes index.

DS and GS maintenance manual : guided missile surface attack MGM-52C; container, shipping and storage, guided missile main assemblage M599; and containers, shipping and storage, guided missile control surfaces M596 and M597, Lance Field Artillery Missile System.

Includes index.

List of Applicable Publications (LOAP) for Lance Field Artillery Missile System.

"October 1984."

Direct support and general support maintenance repair parts and special tools list including depot maintenance repair parts and special tools for monitor-programmer, missile guidance set, AN/GJM-24, 1430-00-937-0897, Lance field artillery missile system.

"This manual supersedes TM 9-1430-495-34P, 28 June 1983"--P. [i]

Organizational maintenance repair parts and special tools list for monitor-programmer, missile guidance set, AN/GJM-24, 1430-00-937-0897 (Lance Field Artillery Missile System).

Includes index.

Organizational maintenance repair parts and special tools list for guided missile main assemblage M5 1420-01-133-0537 (in container), control surface, guided missile M29 1420-01-013-8036 (in container), M30 1420-01-013-8035 (in container), shipping and storage container guided missile M599 8140-00-152-0068 ...

Includes index.

Organizational, direct support, and general support maintenance repair parts and special tools list including depot maintenance repair parts and special tools for launcher, zero length, guided missile, M192E1 1440-00-805-3012 control box, launching section, guided missile AN/GSA-132, 1440-00-178-8455 AN/GSA-132 A, 1440-00-602-5055 pallet, loading and storage ....

Includes index.

Operator, organizational, DS and GS maintenance manual for test set, guided missile system, AN/TSM-84 and electrical equipment shelter, S-250/G (modified) : (Lance guided missile system).

Includes index.

Organizational maintenance repair parts and special tools list for loader-transporter, guided missile, M688A1 1450-01-133-4439 handling unit, guided missile equipment M39 1450-01-132-7715 hoisting unit, tripod M38 1450-00-937-0893 sling, beam type M22 1450-00-937-0894, Lance Field Artillery Missile System.

Includes index.

Direct support and general support maintenance repair parts and special tools list including depot maintenance repair parts and special tools for loader-transporter, guided missile, M688A1, 1450-01-133-4439, handling unit, guided missile equipment, M39, 1450-01-132-7715, hoisting unit, tripod, M38, 1450-00-937-0893, sling, beam type, M22, 1450-00-937-0894, Lance Field Artillery Missile System.

Includes index.

Operator and organizational maintenance manual : azimuth laying set, 1430-01-095-5962, Lance Field Artillery Missile System.

Includes index.

Organizational, direct support and general support maintenance repair parts and special tools list including depot maintenance repair parts and special tools for azimuth laying set, 1430-01-095-5962, Lance Field Artillery Missile System.

Includes index.

Investigation of Missile-Shaped Body with Forward-Facing Cavity at Mach 8

A blunt-nosed hypersonic missile mounted with a forward-facing cavity is a good alternative to reduce the stagnation heating rates. The effects of a forward-racing cavity on heat transfer and aerodynamic coefficients are addressed in this paper. Tests were carried out in hypersonic shock tunnel HST2, at a hypersonic Mach number of 8 using a 41 deg apex-angle blunt cone. The aerodynamic forces on the test model with and without a forward-facing cavity at various angles of attack are measured by using an internally mountable accelerometer force balance system. Heat flux measurements have been carried out on the test model with and without a forward-facing cavity of the entire surface at zero degree angle of attack with platinum sensors. A numerical simulation was also carried out using the computational fluid dynamics code (CFX-Ansys 5.7). An important result of this study is that the smaller cavity diameter has the highest lift-to-drag ratio, whereas the medium cavity has the highest heat flux reduction. Theshock structure around the test model has also been visualized using the Schlieren flow visualization technique. The visualized shock structure and the measured aerodynamic forces on the missile-shaped body with cavity configurations agree well with the axisymmetric numerical simulations.

Experimental investigation of heat transfer reduction using forward facing cavity for missile shaped bodies flying at hypersonic speed

Forward facing circular nose cavity of 6 mm diameter in the nose portion of a generic missile shaped bodies is proposed to reduce the stagnation zone heat transfer. About 25% reduction in stagnation zone heat transfer is measured using platinum thin film sensors at Mach 8 in the IISc hypersonic shock tunnel. The presence of nose cavity does not alter the fundamental aerodynamic coefficients of the slender body. The experimental results along with the numerically predicted results is also discussed in this paper.