FIELD
[0001] The present invention relates to apparatus for providing an interface between a missile
and a launch platform.
BACKGROUND
[0002] Missiles can be launched from a launch platform using a variety of methods. For example,
it is known to use launch rails, which may be suspended from an aircraft, to carry
a missile and to constrain its motion on and immediately after launch. Generally rail
launchers can be used on a number of platforms, including land vehicles and static
ground-based platforms. Launch rails are used with missiles having their own propulsion
systems, and these propulsion systems provide the thrust necessary to separate the
missile from the launcher. By way of further example, launch can also be achieved
using ejection release systems, which operate to propel the missile away from the
launch platform, such that it is at a safe distance from the launch platform before
its propulsion system is initiated. As will be understood, specific mechanical interface
features must be provided on both missile and launch platform for any one launch system
to operate.
SUMMARY
[0003] According to an aspect of the present invention, there is provided apparatus for
providing an interface between a missile and a launch platform, the apparatus comprising
one or more rocket motors, and a jettison device operable to jettison the apparatus
from the missile; the apparatus being configured to launch from the launch platform
with the missile and to jettison from the missile after operation of the rocket motors.
[0004] Herein, the term missile is used to refer to any munition that is capable of flight
and equipped so as to be able to be guided during flight towards a target. The term
is used to include both munitions that are equipped with some means of propulsion,
such as a turbojet or rocket motor, and munitions that lack any means of propulsion
themselves, but are capable of sustained glide through the provision of aerodynamic
control surfaces.
[0005] Use of the apparatus provides platforms with access to a wider variety of missiles.
By way of example, certain missiles are designed for drop launch from fast jet aircraft.
However, smaller, lighter platforms such as helicopters often do not have access to
such missiles, using instead effectors such as laser guided rockets which may have
a range, in rough terms, of up to 10 km, if launched from a relatively high altitude.
Use of the apparatus enables the helicopter to carry missiles designed for fast jet
aircraft with minimal adaptation to the missile itself. The rocket motors provide
an initial boost to the missile, after which it can operate as normal. The helicopter
benefits from a longer range effector (a fast jet drop-launched cruise missile, for
example, could have a range greater than 100km, and even in the less optimal low altitude
helicopter launch conditions will achieve a range several orders of magnitude greater
than current helicopter weapons), with a corresponding greater stand-off distance
from any potential target, and also from the ability to launch at a relatively low
altitude, the missile being able to climb during the initial boost phase of its trajectory.
Thus the helicopter benefits from increased survivability.
[0006] The apparatus may further comprise one or more sensors, said one or more sensors
including one or more of: an altimeter, an inertial measurement unit, a satellite
navigation system, a timer, and a tilt sensor.
[0007] The apparatus may further comprise a processor operable to initiate jettison of the
apparatus from the missile; the apparatus being arranged such that, when the apparatus
is mounted to the missile, wherein the processor is in operative communication with
the sensors so as to determine when to jettison the apparatus from the missile. Said
determination may be made in dependence on one or more predetermined conditions, said
one or more predetermined conditions including one or more of: the missile speed;
the missile altitude; time elapsed since launch from the launch platform; and position
of the missile. The apparatus can therefore be jettisoned in dependence the missile
reaching an appropriate point in its trajectory. For example, the apparatus may be
jettisoned at an appropriate position so as to avoid damage when it falls to the ground.
Alternatively it can be jettisoned after a particular location has been passed and
once a particular speed has been attained; or after a certain amount of time has elapsed
since launch from the launch platform, or since initiation of the rocket motors.
[0008] The apparatus may further comprise: a first mechanical interface attachable to the
launch platform; a second mechanical interface attachable to the missile; and an electronic
interface arranged to provide electrical communication between the missile and the
launch platform.
[0009] The launch platform may comprise a rail launcher, and the first mechanical interface
may be configured to be attachable to the rail launcher. The missile may comprise
lug mounts adapted for a drop launch, and the second mechanical interface may be configured
to be attachable to the lug mounts. The apparatus thus enables a missile configured
to be drop launched to be launched from a launch platform equipped with launch rails.
In some cases, such as where the launch platform is a ground platform or naval vessel,
drop launch is not possible, and so the apparatus enables a particular missile to
be launched from a wider variety of platforms. The use of common munition stockpiles
has considerable benefit in terms of reduced development costs, and reduced through
life costs.
[0010] According to a second aspect of the present invention, there is provided a method
of adapting a drop-launch missile such that the drop launch missile can be launched
in combination with the apparatus described above, the method comprising the steps
of:
- i. identifying external components on the missile that are incompatible with the apparatus;
and
- ii. moving said external components to a location that is compatible with the apparatus,
or removing said external components.
[0011] Such modifications enable the missile to be used in conjunction with the apparatus.
[0012] The method may further comprise the step of adapting the missile control surfaces
such that they are suitable for controlling the missile during and immediately after
operation of the rocket motors. Some aerodynamic stability surfaces may for example
need to be removed to enable the missile to be launched from a different launcher
from that for which it is designed.
BRIEF DESCRIPTION OF THE FIGURES
[0013] Embodiments of the invention will now be described by way of example only with reference
to the figures, in which:
Figures 1a to 1c are schematic illustrations of apparatus in accordance with a first
embodiment of the invention, each from a different perspective;
Figure 2 is a schematic illustration of the apparatus mounted to a missile; and
Figure 3 is a schematic illustration of an exemplary flight profile for a missile
launched in combination with the apparatus.
DETAILED DESCRIPTION
[0014] Generally, embodiments described herein relate to apparatus to provide an interface
between a missile and a launch platform, enabling the missile to be launched from
a wider variety of launch platforms without significant adaptations being necessary
to the missile itself, and also providing additional thrust to the missile, for use
in an initial boost phase of its flight. After the initial, boosted phase, the apparatus
can be jettisoned so as to enable the missile to continue its trajectory operating
in its normal flight mode.
[0015] Figures 1a, 1b, and 1c are schematic illustrations of apparatus 100 intended to provide
an interface between a missile and a launch platform. Figure 2 is an illustration
of a missile 200 attached to the apparatus 100. Apparatus 100 is configured to mechanically
connect to a rail launcher attached to an aircraft. A forward hanger 110 and a rear
hanger 120 are provided to slidably engage with a launch rail. An end stop is provided
to hold the apparatus in place during air carriage. A shotgun connector 140 is provided
to electronically connect the apparatus to the launch platform. The shotgun connector
may connect the apparatus both to a power supply from the launch platform, and to
a launch platform databus so that the apparatus can both communicate with the launch
platform and enable communication between the launch platform and the missile. The
hangers 110, 120, end stop and shotgun connector 140 are provided on a first, typically
upper as shown in Figure 1, portion of the apparatus 100.
[0016] Lug mounts 150 for interfacing with a missile are provided on a second portion of
the apparatus opposing the hangers. Typically the lug mounts are provided on a lower
portion of the apparatus 100, as shown in Figure 1c. The lug mounts are configured
to mechanically interface with the missile. The apparatus 100 is provided with a release
mechanism so that, as described in further detail below, the apparatus can be jettisoned
from the missile at an appropriate time. The release mechanism, and mechanical connection
between the apparatus and the missile, will be configured as appropriate for the missile
with which the apparatus is intended to operate. Appropriate release mechanisms are
well-known in the field. A further connector is provided to enable the apparatus to
electronically connect to the missile. The electrical connector is of the tear-off
type. Such connectors are configured to disconnect on launch of the missile, or, in
the case of the present apparatus, on jettison of the apparatus from the missile.
[0017] The apparatus 100 additionally comprises a processor to enable communication between
the missile and the launch platform, via apparatus 100, and to enable the apparatus
100 to communicate with the launch platform and the missile. The apparatus 100 may
be used to interface between a missile and a launch platform other than that for which
the missile is designed. As a result it is possible that the databus standard used
by the missile may be different to the databus standard used by the launch platform.
Conversion between the launch platform and missile databus standards can be performed
by appropriate software included in the processor. It is also possible that the power
supply from the launch platform may not be compatible with the power supply required
by the missile. In some embodiments, therefore, a power supply conversion adapter
and power conditioning systems are also included within the apparatus 100. Those skilled
in the art will appreciate that such conversions, as well as other adaptations necessary
to enable the launch platform stores management system or launcher management system
to communicate with the apparatus and, via the apparatus, the missile, can be achieved
through standard platform integration work.
[0018] Rocket motors 160, 170 are mounted onto the apparatus. As is explained in further
detail below, on launch from the launch platform, the apparatus and missile are launched
in combination, with the apparatus attached to the missile by lug mounts. Rocket motors
160, 170 provide a thrust boost to the missile and apparatus combination on launch
from the launch platform. The rocket motors operate until their fuel is burnt. The
rate at which fuel is burnt during operation of the rocket motor may vary, and a particular
burn profile can be determined on construction of the rocket motor. The rocket motors
are selected to be appropriate for operational use of the apparatus and missile in
dependence on the launch platform. For example, if there is a constraint on the overall
weight that the launch platform is able to carry, smaller rocket motors having a shorter
burn time may be appropriate, so as to reduce the overall weight of the apparatus
and missile. Rocket motor design trade-offs can identify a compromise between the
missile performance desired and the weight constraints of the launcher.
[0019] The apparatus further comprises a jettison device. Suitable devices are well known
in the art and include squib charges, and explosive bolt charges. There is a risk
that jettison of the apparatus may result in damage to the missile if the apparatus
collides with any part of the missile, such as fins at the rear of the missile, immediately
after jettison. This risk is mitigated by design of the apparatus, providing an offset
between the rear end of the apparatus and any fins. In addition the operation of the
jettison device can be modelled to ensure that the apparatus is ejected with a force
sufficient to ensure its subsequent trajectory does not collide with the missile.
The ejection force can be increased for example by increasing the size of the squib
charge. Subsequent to the jettison, the missile continues its flight under the control
of its standard guidance and flight control mechanisms.
[0020] Operation of the rocket motors and jettison device is controlled by the processor
150. The processor includes a timer. The apparatus further comprises an inertial measurement
unit, altimeter and tilt sensor. Operation of these components will now described
in further detail with reference to Figure 3, which schematically illustrates an exemplary
engagement for a missile used in conjunction with the apparatus 100. In the exemplary
engagement illustrated, the apparatus is used to launch a missile designed to be drop-launched
from a fast jet aircraft to be launched instead from a helicopter 302 equipped with
a rail launcher. In addition the use of the apparatus enables the missile to be launched
from a lower altitude than would normally be the case. Use of the apparatus also enables
a larger stand-off distance between the launch point and a target 304. The lower altitude,
and greater stand-off distance lower the risk to the helicopter platform. For example,
the helicopter may stay at a low altitude such that obstacles 306 obscure the helicopter
from the target 304.
[0021] At a first stage, 310, the apparatus and missile are launched from the helicopter.
A signal is communicated to the apparatus from the helicopter to initiate launch and
provide targeting details to the apparatus. The processor communicates necessary information
to the missile processor and initiates the rocket motors 160, 170. Operation of the
rocket motors provides generates thrust to propel the apparatus and missile along
the launch rail away from the helicopter. The attitude of the helicopter can be controlled
at launch such that the launch rail, and therefore the direction of the thrust generated
by the rocket motors, is in an appropriate direction.
[0022] At a second stage 320, the rocket motors continue to propel the apparatus and missile
until the rocket motors burn out. The apparatus and missile continue in combination
until one or more predetermined conditions are met. These conditions can be determined
by an operator prior to the launch. The predetermined conditions may include one or
more of: the time elapsed since launch; the speed attained; the altitude attained;
and the position reached. The predetermined condition may include a condition that
the apparatus is not jettisoned in certain areas so as to avoid any potential damage
being caused by the apparatus falling to the ground. The processor can determine time
elapsed since launch; and communicates with the inertial measurement unit and altimeter
provided in the apparatus to determine speed, altitude, and position.
[0023] Once the predetermined condition is met, at a third stage 330, the apparatus is jettisoned
from the missile. This can be initiated by the processor. In an initial stage of the
jettison process, the missile and apparatus turn over so that the apparatus is facing
towards the ground. The tilt sensor is used to confirm that the apparatus is facing
downwards prior to jettison. The apparatus 100 is then jettisoned by operation of
the jettison device. The apparatus 100 then falls away. In the present example, the
missile is equipped with a turbojet engine and has fold-out wings. After jettison,
the missile operates in its normal manner. The wings fold out, and the missile is
propelled along its trajectory by its turbojet engine. The turbojet engine can be
initiated at an appropriate time to enable the missile to follow its intended trajectory.
It may for example be spinning up prior to jettison of the apparatus so that it is
able to propel the missile at cruise speed when the apparatus is jettisoned, or when
the rocket motors burn out.
[0024] At a fourth stage 340, the missile continues its flight under its standard controls.
Flight can be controlled using on-board navigation systems such as satellite navigation
systems, or inertial navigation systems. At a fifth stage 350, the missile seeker
systems are used for terminal navigation to guide the missile towards its target 304.
Alternatively it can be used in an 'attack on coordinates' mode using navigation systems.
[0025] A number of modifications may be required in order to adapt a missile to be suitable
for use in combination with the apparatus 100 as described above. The modifications
will depend on the type of missile used. Typically a missile body will have a number
of protrusions that could interfere with operation of the apparatus. These protrusions
may interfere with rail launch, or may interfere with operation of the rocket motors
or other parts of the apparatus. Antennae necessary for the operation of the missile,
such as GNSS or datalink antennae, can be moved to a different location on the missile
body at which no interference with operation of the apparatus is caused.
[0026] Certain aerodynamic stability surfaces that are necessary for drop launch missiles
are not necessary for rail-launched missiles. Drop launch missiles can be provided
with a stabilisation fin protruding vertically upwardly (i.e. in the direction of
the launcher) during the drop phase which contribute to improving flight stability
when the missile is dropped from a high altitude aircraft platform. The stabilisation
fin would prevent rail launch, because it would collide with the launch rail during
launch of the missile. However, the flight stabilisation provided by such a fin is
not necessary in a propelled application from a launcher rail, and so it can be removed
to enable the missile to be launched using apparatus 100.
[0027] Missile control surfaces may need to be deployed during the boost phase in order
to provide control for the initial phase of the trajectory. Such deployment may require
some modification of the missile since during this part of the trajectory the missile
will remain attached to the apparatus. Control surfaces such as fins can be provided
with fin lock mechanisms which operate to lock the fins before and immediately after
launch, for safety reasons. These lock mechanisms can be overridden or modified to
enable the missile control surfaces to deploy and control or correct the boost phase
of the trajectory. As will be understood, missile control surfaces designed for a
drop launch missile are not optimised for the high speed attained during the boost
phase of the trajectory followed when launched in combination with the apparatus.
As a result it is expected that the launch platform itself alter its orientation to
ensure that the launch rail is pointing in approximately the right direction for the
missiles initial flight path. In this way the missile control surfaces need only apply
relatively small corrections, rather than needing to effect a change from missile
level flight to a large missile climb angle.
[0028] The missile is also be provided with a mechanical switch to enable it to determine
when the apparatus has been jettisoned. The switch is positioned such that it is depressed
by the apparatus when the apparatus is attached to the missile, and released on jettison
of the apparatus. The apparatus will affect the flight characteristics and performance
of the missile. If jettison is not successfully accomplished for any reason, the missile
will be able to take alternative action when jettison is not confirmed.
[0029] Certain software updates can also be performed. The missile guidance and control
software can be updated to enable control of the boost phase of the missile trajectory.
For example of the dropped missile, an update is provided to the guidance and control
software to enable control of the boost phase of the missile trajectory. A further
software update can be performed to enable communications interfacing to the platform
stores or launcher management system. Alternatively or additionally, the apparatus
processor may perform this interface function, avoiding the need for this software
update.
[0030] Whilst a number of specific embodiments of the invention have been described in the
above, those skilled in the art will appreciate that a number of variations and modifications
to the above-described embodiments will be possible without departing from the scope
of the invention which is defined in the accompanying claims. For example, whilst
it has been described to use the apparatus in combination with an air platform, it
will be appreciated that the apparatus can be used to enable a missile configured
for drop-launch to be rail launched from a ground-based vehicle or static platform,
or from a naval vessel. Moreover it will be appreciated that the apparatus can be
used both with missiles configured for drop launch and for missiles configured for
eject launch.
[0031] It will also be appreciated that other modifications to the apparatus will be possible.
For example, whilst in the above it has been described to use a mechanical switch
located on the missile to confirm jettison of the apparatus from the missile, in alternative
embodiments it may be that the apparatus includes a transmitter operable to send a
continuous signal to the missile. The continuous signal may for example be a series
of pulses. The missile may then determine successful jettison as a consequence of
cessation of the continuous signal. Further alternatively, an interface disconnected
condition could be detected by the missile when the electrical interface interlock
is removed to the apparatus due to its jettison.
1. Apparatus for providing an interface between a missile and a launch platform, the
apparatus comprising one or more rocket motors, and a jettison device operable to
jettison the apparatus from the missile; the apparatus being configured to launch
from the launch platform with the missile and to jettison from the missile after operation
of the rocket motors.
2. Apparatus as claimed in claim 1, further comprising one or more sensors, said one
or more sensors including one or more of: an altimeter, an inertial measurement unit,
a satellite navigation system, a timer, and a tilt sensor.
3. Apparatus as claimed in claim 2, further comprising a processor operable to initiate
jettison of the apparatus from the missile; wherein the processor is in operative
communication with the sensors so as to determine when to jettison the apparatus from
the missile.
4. Apparatus as claimed in claim 3 wherein said determination is made in dependence on
one or more predetermined conditions, said one or more predetermined conditions including
one or more of: the missile speed; the missile altitude; time elapsed since launch
from the launch platform; and position of the missile.
5. Apparatus as claimed in any one of the preceding claims, the apparatus further comprising:
- a first mechanical interface attachable to the launch platform;
- a second mechanical interface attachable to the missile; and
- an electronic interface arranged to provide electrical communication between the
missile and the launch platform.
6. Apparatus as claimed in claim 5, wherein the launch platform comprises a rail launcher,
and the first mechanical interface is configured to be attachable to the rail launcher.
7. Apparatus as claimed in claim 5 or claim 6, wherein the missile comprises lug mounts
adapted for a drop launch, and the second mechanical interface is configured to be
attachable to the lug mounts.
8. A method of adapting a drop-launch missile such that the drop launch missile can be
launched in combination with the apparatus of any one or claims 1 to 7, the method
comprising the steps of:
i. identifying external components on the missile that are incompatible with the apparatus;
and
ii. moving said external components to a location that is compatible with the apparatus,
or removing said external components.
9. The method of claim 8, further comprising the step of adapting the missile control
surfaces such that they are suitable for controlling the missile during and immediately
after operation of the rocket motors.