the missile to intercept the target or come within lethal
range of it.
The flight control consists of the autopilot and the
hydraulic group. These function to provide control
signals and mechanical energy to move the external
control surfaces that guide the missile toward the point
of intercept, and to stabilize the missile in pitch, yaw,
The warhead is located between the target seeker
explosive-loaded, and it contains the fuze, fuze booster
charge, and the safety and arming (S&A) device. It is a
continuous-rod type of warhead. At detonation, the rod
sections expand into a continuous ring. Target kill is
accomplished by collision of the continuous ring with
the target. Detonation is triggered either by a fuze pulse
from the target seeker at the nearest point of intercept or
a fuze pulse from the flight control upon impact with
The DTRM attaches to the aft end of the missile
flight control section. It is equipped with a SAFE/ARM
igniter assembly that is manually locked in either the
SAFE or ARMED position. This switch can only be
repositioned with an arming key. When in the SAFE
position, the arming key cannot be removed. This
switch prevents accidental firing of the motor. It should
immediately before aircraft launch.
The control surfaces consist of four delta-shaped
wing and fin assemblies. The wings and fins are
designed for quick attachment and release without the
use of tools. The wing assemblies attach to the flight
control section, which controls their rotary motion to
produce the desired pitch, yaw, and roll. The tail fin
assemblies attach to fittings on the rear of the rocket
motor and provide stability to the missile.
Another series of the Sparrow III guided missile is
surface-to-air guided missiles. They are used in some
ships in the ship's Basic Point Defense Surface Missile
System (BPDSMS) and Improved Point Defense
Surface Missile System (IPDSMS), respectively. As an
Aviation Ordnanceman, your responsibility for these
missiles is in the area of handling and stowage only.
For further information concerning the Sparrow III
(series) missiles, refer to publication Organizational,
Intermediate, and Depot Maintenance Instruction
Manual with Illustrated Parts Breakdown, NAVAIR
01-265GMAD-9-3 (series) and NAVAIR 11-140-6
Airborne Weapons Assembly Manual.
Harpoon Guided Missile
The Harpoon surface attack guided missile,
AGM-84 series (AGM-84/C/D Tactical) air-launched
missile (fig. 3-7), is an all-weather antiship attack
weapon. The SLAM tactical missile (fig. 3-7),
AGM-84E, is a standoff land attack missile. The
Harpoon can be delivered from the F/A-18, P-3, and
S-3 aircraft. Both missiles are AURs and require no
assembly other than installation of the wing and control
fin assemblies. The missile consists of the guidance
section, warhead section, sustainer section, boattail
section, wings, and control fins. The missile is
approximately 151 inches in length and weighs
approximately 1,144 pounds.
The Harpoon missile has a low-level cruise
trajectory with over-the-horizon range that makes it
less susceptible to radar detection. It uses active
guidance and has counter-countermeasure capability.
The guidance section contains the seeker, radar
altimeter, midcourse guidance unit, and power supply.
A radome on the front of the guidance section provides
the required aerodynamic shield to protect the internal
components of the seeker. During ground handling, a
radome protector cap protects the radome.
The warhead section contains a penetration blast
type of explosive, the guided missile fuze, fuze booster,
and the pressure probe assembly. It also provides
internal routing of the interconnecting cable from the
guidance section to other parts of the missile.
The sustainer section contains the fuel tank and fuel
supply system, missile battery, pyrotechnic relay panel,
and the turbojet engine. Three BSU-4/B missile wings
and one BSU-43/B missile wing are attached to the
sustainer section by quick-attach, clevis-type fittings.
These wings are attached to the missile at the
organizational level. They provide the aerodynamic lift
required sustaining missile flight. They are made of a
framed aluminum honeycomb construction and are
The boattail section contains four control actuators,
nonfolding missile control fins (BSU-44/B) provide
proportional to the input signal received from the
guidance section. The control fins are one-piece
aluminum castings, and are attached to the control fin
actuators by means of an integral torque-limiting,