The Candrian Empire
28-07-2007, 22:17
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CANDRIAN AEROSPACE TECHNOLOGIES
AGM CC-25H
HYPERSONIC STANDOFF MUNITIONS DELIVERY VEHICLE
'APOLLO'
History
The AGM CC25h Hypersonic Standoff Cruise missile is the premier standoff munition in the Candrian Empire; an intimidating munition designed to operate above Mach 14, engage a land target, and obliterate it. As one of the more advanced weapons in the Candrian arsenal, the AGM CC25 missile is perhaps the best known of any of the weapons implemented by the CAF. And by that, it should be noted that it's probably the only weapon with any real exposure to the international community. Testing began early in the 2010s, and by 2016 the first few missiles were delivered to Candrian service.
Design
The missile is a hypersonic waverider. Considering that, unlike the Ih7 or Bh28, the missile was intended as a single-use weapon, the design team at CAT could take a few liberties. As a result, the framework of the missile is built of lightweight titanium - aluminum alloy to save weight, while worries about dynamic load stress could be discounted. For thermal protection the missile uses a few different tricks - an airspike laser array at the front offsets the shockwave and copper heatpipes cross under the skin and channel heat from the leading edges to the rear of the vehicle. Intended launch platform is the FA-15 Cardinal, traveling at a minimum airspeed of Mach 1.4.
Effectively, the missile is divided into 6 major components; the forward section containing the airspike laser array and solid-state batteries; this airspike system engages on the descent of the aircraft, producing a shockwave forward of the vehicle. This shockwave produces a bufferzone around the delivery vehicle, cushioning it from the intense temperature and shocks of the boundary air. This allows the vehicle to dive from upwards of 40,000 meters to it's target at speeds upwards of Mach 14 without prematurely destroying the vehicle. This technology is being looked at to minimize the shielding of the Ih7 and Bh28, aircraft designed to cruise at Mach 12 and above.
The second section, immediately behind the first, is the payload section. There are several different potential payloads, and for most versions, there is a penetrator-type warhead to make effective use of the high velocity. They will be discussed in further detail in their own dedicated section.
The third section is the electrical power supply - typically a set of electrochemical double-layer supercapacitors - this section provides the aircraft's electricity, in a more compact, efficient, and denser form than any batteries. This section also contains the guidance equipment, explained in detail later.
The fourth section is the upper fuel tank and pumping system. From here fuel is pumped to the heat exchanger to the rear and through the engine nozzle, cooling both. Some fuel is also pumped forward to cool the avionics. differs between modern models of the missile and export/early models.
The fifth section is a cooling grid; in this section, the heat pipes running through the forward sections of the vehicle and the leading edges run through a heat exchanger with the cryogenic hydrogen fuel, producing a current in the heatpipes that cools the leading edges.
The sixth section is the engine and the majority of the fuel tank. The engine sits under the upper five sections and the fuel tank. The fuel tank is designed to carry cryogenic liquid hydrogen.
Powerplant
The primary domestic powerplant for the CC25h missile is a hybrid ramjet/scramjet engine. Articulated shock bodies in the intake function to slow down incoming air by forcing it to go through a shockwave, similar to the function of the plates in a variable geometry intake. These plates can fold flush with the engine floor and ceiling for smoother operation under Scramjet mode without the risk of adverse shockwaves forcing the air out and choking the engine. The engine's exhaust nozzle is an airspike-type, facilitating use at a variety of altitudes. The airspike is cooled by the cryogenic hydrogen fuel, pumped into the engine at several different points; these points are determined by a computerized system designed by JEC taking into account airspeed velocity, altitude, predicted shockwave reflection, among other things, inputting these into a set of three identical boards, two of which interpret the information, feeding to the third, which runs error checking.
To power the missile through the first stage of flight, a rocket booster is attached, running through the engine chamber and towards the missile empennage. The booster is a solid-fuel APC rocket. Upon burnout, the booster is jettisoned and the Ramjet mode overtakes for acceleration, until the Scramjet sustainer mode can operate efficiently.
Guidance
The guidance system is GPS-corrected inertial guidance. Onboard solid-state gyroscopes keep the delivery vehicle stabilized and on the proper flightpath. The GPS correction can be used to update target information, allowing the missile to hit a moving target; this, however, is highly not recommended as high maneuvering could very easily destroy the missile enroute. Such a system could be implemented for an air-to-air warhead to be used against slow-moving targets, increasing the adaptability of this missile.
Warhead
The vehicle is capable of accepting several different payloads; many of which have a penetrator variant associated with them. A conventional penetrator/solid explosive warhead exists, consisting of a 1.49 meter long DU spike hollow for the rear 1/3 of it's length; this cavity is packed with RDX. A pure thermonuclear warhead also exists, similar in size, yield, and operation to the old US W-50 nuclear warhead, with a selectable yield up to 400 kt. A wide variety of warheads exist, however, and customer nations may make their own as long as they fit within the dimensions of the chamber and accept the fitting bolts and safety-arm-payload connections. This chamber is 1.497 meters long, .491 meters wide, and .485 meters high. Four fitting acceptor bolts are found at opposite ends of the length of the chamber, ensuring the payload fits properly within the confines of the missile. .31 meters from the forward section of the chamber are the connection wires, which cover the functions of arming the missile and informing the pilot of the delivery aircraft of the specific payload of the missile. The maximum acceptable weight of the payload is 190 kg.
Role: Hypersonic Standoff Cruise Missle
Design: Waverider Vehicle
Dimensions
Length: 7.325 Meters
Wingspan: 1.887 Meters
Height: .909 Meters
Weight: 2,350 kg
Warhead Weight (maximum): 190 kg
Propulsion:
Primary Stage: Ammonium Perchlorate Composite Propellant Solid Fuel Rocket Motor
Secondary Stage: Cryogenic Hydrogen Dual mode Scramjet/Ramjet Integrated engine
Maximum Speed: Mach 14.24
Altitude: Launch 10.2 km, Maximum 41 km
Range: 1,100 km
Cost: $62,171,000
CANDRIAN AEROSPACE TECHNOLOGIES
AGM CC-25H
HYPERSONIC STANDOFF MUNITIONS DELIVERY VEHICLE
'APOLLO'
History
The AGM CC25h Hypersonic Standoff Cruise missile is the premier standoff munition in the Candrian Empire; an intimidating munition designed to operate above Mach 14, engage a land target, and obliterate it. As one of the more advanced weapons in the Candrian arsenal, the AGM CC25 missile is perhaps the best known of any of the weapons implemented by the CAF. And by that, it should be noted that it's probably the only weapon with any real exposure to the international community. Testing began early in the 2010s, and by 2016 the first few missiles were delivered to Candrian service.
Design
The missile is a hypersonic waverider. Considering that, unlike the Ih7 or Bh28, the missile was intended as a single-use weapon, the design team at CAT could take a few liberties. As a result, the framework of the missile is built of lightweight titanium - aluminum alloy to save weight, while worries about dynamic load stress could be discounted. For thermal protection the missile uses a few different tricks - an airspike laser array at the front offsets the shockwave and copper heatpipes cross under the skin and channel heat from the leading edges to the rear of the vehicle. Intended launch platform is the FA-15 Cardinal, traveling at a minimum airspeed of Mach 1.4.
Effectively, the missile is divided into 6 major components; the forward section containing the airspike laser array and solid-state batteries; this airspike system engages on the descent of the aircraft, producing a shockwave forward of the vehicle. This shockwave produces a bufferzone around the delivery vehicle, cushioning it from the intense temperature and shocks of the boundary air. This allows the vehicle to dive from upwards of 40,000 meters to it's target at speeds upwards of Mach 14 without prematurely destroying the vehicle. This technology is being looked at to minimize the shielding of the Ih7 and Bh28, aircraft designed to cruise at Mach 12 and above.
The second section, immediately behind the first, is the payload section. There are several different potential payloads, and for most versions, there is a penetrator-type warhead to make effective use of the high velocity. They will be discussed in further detail in their own dedicated section.
The third section is the electrical power supply - typically a set of electrochemical double-layer supercapacitors - this section provides the aircraft's electricity, in a more compact, efficient, and denser form than any batteries. This section also contains the guidance equipment, explained in detail later.
The fourth section is the upper fuel tank and pumping system. From here fuel is pumped to the heat exchanger to the rear and through the engine nozzle, cooling both. Some fuel is also pumped forward to cool the avionics. differs between modern models of the missile and export/early models.
The fifth section is a cooling grid; in this section, the heat pipes running through the forward sections of the vehicle and the leading edges run through a heat exchanger with the cryogenic hydrogen fuel, producing a current in the heatpipes that cools the leading edges.
The sixth section is the engine and the majority of the fuel tank. The engine sits under the upper five sections and the fuel tank. The fuel tank is designed to carry cryogenic liquid hydrogen.
Powerplant
The primary domestic powerplant for the CC25h missile is a hybrid ramjet/scramjet engine. Articulated shock bodies in the intake function to slow down incoming air by forcing it to go through a shockwave, similar to the function of the plates in a variable geometry intake. These plates can fold flush with the engine floor and ceiling for smoother operation under Scramjet mode without the risk of adverse shockwaves forcing the air out and choking the engine. The engine's exhaust nozzle is an airspike-type, facilitating use at a variety of altitudes. The airspike is cooled by the cryogenic hydrogen fuel, pumped into the engine at several different points; these points are determined by a computerized system designed by JEC taking into account airspeed velocity, altitude, predicted shockwave reflection, among other things, inputting these into a set of three identical boards, two of which interpret the information, feeding to the third, which runs error checking.
To power the missile through the first stage of flight, a rocket booster is attached, running through the engine chamber and towards the missile empennage. The booster is a solid-fuel APC rocket. Upon burnout, the booster is jettisoned and the Ramjet mode overtakes for acceleration, until the Scramjet sustainer mode can operate efficiently.
Guidance
The guidance system is GPS-corrected inertial guidance. Onboard solid-state gyroscopes keep the delivery vehicle stabilized and on the proper flightpath. The GPS correction can be used to update target information, allowing the missile to hit a moving target; this, however, is highly not recommended as high maneuvering could very easily destroy the missile enroute. Such a system could be implemented for an air-to-air warhead to be used against slow-moving targets, increasing the adaptability of this missile.
Warhead
The vehicle is capable of accepting several different payloads; many of which have a penetrator variant associated with them. A conventional penetrator/solid explosive warhead exists, consisting of a 1.49 meter long DU spike hollow for the rear 1/3 of it's length; this cavity is packed with RDX. A pure thermonuclear warhead also exists, similar in size, yield, and operation to the old US W-50 nuclear warhead, with a selectable yield up to 400 kt. A wide variety of warheads exist, however, and customer nations may make their own as long as they fit within the dimensions of the chamber and accept the fitting bolts and safety-arm-payload connections. This chamber is 1.497 meters long, .491 meters wide, and .485 meters high. Four fitting acceptor bolts are found at opposite ends of the length of the chamber, ensuring the payload fits properly within the confines of the missile. .31 meters from the forward section of the chamber are the connection wires, which cover the functions of arming the missile and informing the pilot of the delivery aircraft of the specific payload of the missile. The maximum acceptable weight of the payload is 190 kg.
Role: Hypersonic Standoff Cruise Missle
Design: Waverider Vehicle
Dimensions
Length: 7.325 Meters
Wingspan: 1.887 Meters
Height: .909 Meters
Weight: 2,350 kg
Warhead Weight (maximum): 190 kg
Propulsion:
Primary Stage: Ammonium Perchlorate Composite Propellant Solid Fuel Rocket Motor
Secondary Stage: Cryogenic Hydrogen Dual mode Scramjet/Ramjet Integrated engine
Maximum Speed: Mach 14.24
Altitude: Launch 10.2 km, Maximum 41 km
Range: 1,100 km
Cost: $62,171,000