The unpowered pneumatic interceptor round. An unpowered round with nothing aboard to power, receive or arm, thrown by air at 189.2 m/s and built for magazine depth.
Goose CS-110 is a steel nose on four moulded parts, with nothing aboard to charge, program or arm. The figures below size it; the cards say why a buyer holding ground against numbers would choose it.
The round carries no electrical system and no energetic material. The launcher holds the energy, and from the muzzle onward the round spends none of its own.
With no pack, controller or harness to carry, the mass goes to the nose. Off a 10° quadrant elevation the round arrives at 120.6 m/s carrying 11.7 kJ.
Every moulded part comes off tooling cut in-house, and the nose is plain turned bar. Depth of fire is bought with moulds and throughput rather than with a more complex round.
Both heads mount to one mechanical nose interface, and the launcher delivers the same stroke to either. The choice of effect is made at the breech.
The specification of Goose CS-110 grouped the way an engineer reads it: the round and its mass, geometry, stability, the launch, structure, flight, materials, the launch interface and handling.
The round and its massGeometryStabilityThe launchLaunch shock and structureFlight and effectMaterialsLaunch interface and safety functionsHandling and storage
| Parameter | Value | Basis |
|---|---|---|
| All-up mass | 1.600 kg | design value; the mass the launch and the stability are sized to |
| Construction | A steel nose and four moulded parts | the tail boom and the six fins are bonded with a two-part structural epoxy |
| Electrical system | None | no battery, motor, receiver, servo, sensor, indicator or initiator, and no wiring harness |
| Energetic material | None | no warhead, fuze, primer, propellant or initiator |
| Parameter | Value | Basis |
|---|---|---|
| Bore and obturator diameter | Ø90.00 mm | design value; the one fixed dimension |
| Bore area | 63.617 cm² | calculated, πD²/4 |
| Main body diameter | Ø70.00 mm | calculated; set by the stability solve |
| Tail boom diameter | Ø32.00 mm | calculated; set by the fin span |
| Fins | Six, fixed, equispaced | calculated; four do not close the stability solve and eight are over-stable |
| Moving surfaces | None | no trim mechanism on the round; the launcher aims and the round flies ballistic |
| Parameter | Value | Basis |
|---|---|---|
| Static margin | Inside the 1.5 to 2.5 calibre design band | calculated; subsonic slender-body method at M 0.55 |
| Fin flutter speed | 2,778 m/s | calculated; 14.7 times the muzzle velocity |
| Parameter | Value | Basis |
|---|---|---|
| Charge pressure | 30.0 bar | design launch case, shop-air class |
| Stroke | 3.00 m | design launch case |
| Accumulator volume per shot | 15.9 L | calculated; isentropic expansion with the gas-inertia correction |
| Muzzle velocity | 189.2 m/s | design value; the interior-ballistics model closes on it at 30 bar over 3.00 m |
| Launch energy | 28.64 kJ | calculated, ½mv² at 1.600 kg |
| Combined energy efficiency | 85.9 % | calculated from five named losses against the ideal expansion |
| Largest single loss | Gas inertia, 5.2 % | calculated; the charge air is accelerated with the round |
| Parameter | Value | Basis |
|---|---|---|
| Peak acceleration | 11,369 m/s², 1,159 g | calculated at x = 0, t = 0.14 ms, before the round moves |
| Mean acceleration | 5,966 m/s², 608 g | calculated, v²/2S over the stroke |
| Peak to mean | 1.91 | calculated |
| Peak base force | 18,191 N | calculated; the design load for every part |
| Structural safety factor | 2.0 | design value, on strength and on shell buckling |
| Moulded wall | 2.50 mm | calculated; buckling governs at 2.14 mm against 1.19 mm on strength |
| Fin root, bending | 7.5 MPa against 110 MPa | calculated; margin of safety +13.7 |
| Parameter | Value | Basis |
|---|---|---|
| Guidance | Tier 1, preset | the launcher sets the laying solution; nothing aboard receives |
| Drag coefficient | 0.35 | handbook value for a blunt-nosed finned cylinder, on the Ø70 reference |
| Range at 10° quadrant elevation | 894 m | calculated; point mass, ISA sea level, drag coefficient 0.35 |
| Range at 45° quadrant elevation | 1,636 m | calculated; point mass, ISA sea level, drag coefficient 0.35 |
| Impact at 10° | 120.6 m/s, 11.7 kJ | calculated on the same trajectory basis |
| Impact at 45° | 99.7 m/s, 8.0 kJ | calculated on the same trajectory basis |
| Effect at the target | Collision | the steel nose is the effect; the airframe carries it |
| Parameter | Value | Basis |
|---|---|---|
| Nose | Alloy steel, AISI 4140 class, normalized | a mass item chosen for density; 7,850 kg/m³, handbook value |
| Body, boom, fins and cup | Glass-filled polyamide, PA66-GF33 | 110 MPa and 7.0 GPa conditioned at 50 % RH, handbook values; 1,400 kg/m³ |
| Obturating land | Thermoplastic polyurethane or filled PTFE | the sealing face against the bore |
| Bonds | Two-part structural epoxy | lap shear 20–30 MPa, handbook value |
| Parameter | Value | Basis |
|---|---|---|
| Cue | Bearing, range and height | over a wire from the fire-control interface, or entered by hand |
| Laying solution | Point mass, computed at the launcher | checked against the mount envelope before the mount moves |
| Mount envelope | ±170° azimuth, −3° to +75° elevation | the launch platform's travel; a solution outside it is refused |
| Breech valve | Normally closed, opens in under 5 ms | with no power on the coil the breech is shut |
| Arming | A person turns the arm key for every shot | four permissives in series ahead of the arm relay |
| Partner fire-control cue | A permissive only | it cannot bypass the interlock chain or the arm action |
| Fire path | No automated or remote-only fire path | a human arm action is mandatory for every shot |
| Parameter | Value | Basis |
|---|---|---|
| Stored state | Inert | no propellant, primer or initiator to store |
| Magazine and indexer | No pyrotechnics | the launch energy is compressed air held at the launcher |
| Handling | Dense steel nose | crush and dropped-object precautions apply |
| To the line | Round storage rack | the storage configuration of the launch platform carries rounds to the launcher |
Goose CS-110 is a pneumatically launched, fully unpowered round that defeats a small uncrewed aircraft by collision. It leaves a ground tube on shop air and flies a ballistic arc on six fixed fins.
The round is a solid alloy-steel nose carried on a moulded glass-filled nylon airframe: a Ø70 body shell, a Ø32 tail boom, six fixed fins and an obturator cup that takes full bore pressure. It weighs 1.600 kg. The mass budget works back from that figure: the structure takes what buckling and stability demand, and the rest goes to the nose, where mass does useful work. The airframe is a carrier and the steel is the effect.
The short list of what the round leaves out is the design. It carries no battery, no motor, no receiver, no servo, no sensor, no indicator and no initiator, and so it has no wiring harness. It carries no warhead, no fuze, no primer, no propellant and no energetic material. The launcher holds the energy, lays the shot and throws the round; from the muzzle onward the round is on its own and asks for nothing.
The round, its heads, the launcher and the fire-control boundary are held to one set of top-level requirements, so that a change on one side of an interface can be traced to the other.
| Requirement | How the design meets it |
|---|---|
| Defeat a small uncrewed aircraft by collision or capture | A kinetic head or a capture head on one nose interface |
| Carry no warhead, fuze or energetic material | A design boundary: none is anywhere in the round |
| Operate with no radio and no satellite navigation on the round | Tier 1 preset: the launcher lays the shot and nothing aboard receives |
| Launch from 30 bar shop air | 189.2 m/s at the muzzle from a 3.00 m stroke |
| Fly stably with a static margin of at least 1.5 calibres | The stepped Ø32 boom and six fixed fins, inside the 1.5 to 2.5 calibre design band |
| Survive the launch shock | Every part sized to the 1,159 g peak at a safety factor of 2.0 |
| Accept a partner fire-control cue as a permissive only | The cue cannot bypass the interlock chain or the arm action |
| Be manufacturable on the company's own tooling | Moulds for every moulded part are cut in-house |
A fixed volume of air expands into the growing barrel behind a cup that spans the full Ø90 bore. The round leaves the muzzle carrying 28.64 kJ.
The figures come from an isentropic expansion of the accumulator charge into the barrel behind the round, with the valve opening and the seal drag modelled. The obturator cup takes the full charge across 63.617 cm² of bore and pushes everything ahead of it up the tube.
| Quantity | Figure | Basis |
|---|---|---|
| Charge pressure | 30.0 bar | Design launch case, shop-air class |
| Stroke and bore | 3.00 m, Ø90.00 mm | Design launch case |
| Accumulator volume per shot | 15.9 L | Calculated, with the gas-inertia correction |
| Muzzle velocity | 189.2 m/s | Design value the model closes on |
| Launch energy | 28.64 kJ | Calculated, ½mv² |
| Where the energy goes | Loss | What it is |
|---|---|---|
| Gas inertia | 5.2 % | The charge air is accelerated along with the round |
| Heat transfer from the barrel | −2.0 %, a gain | The expanding gas cools and heat flows back into it |
| Seal friction | 3.4 % | The obturating land against the bore |
| Blow-by past the obturator | 0.5 % | A pressure-energized cup |
| Fin-tip contact with the bore | 0.2 % | Six tips |
| Combined energy efficiency | 85.9 % | Against the ideal expansion |
Gas inertia is the largest term and no seal recovers it: sealing costs about 3.9 points in all, while the air itself costs 5.2. The lever on it is a smaller accumulator at higher pressure for the same stored energy, which puts less air in motion behind the round.
The peak arrives before the round has moved and is set by pressure, bore and mass alone. The mean over the stroke is 608 g; every part is sized to the peak at a safety factor of 2.0.
Peak base force occurs at x = 0, before the round moves, so accumulator volume sets exit velocity and leaves the peak untouched. A 20 ms valve ramp gives the same peak as an instant one. The only levers on launch shock are lower pressure, a smaller bore or a longer stroke.
At the critical station just ahead of the cup the shell carries the whole round at peak acceleration: 18,191 N in axial compression. Buckling governs the wall, not strength, by roughly 1.8 times. Conditioned PA66-GF33 needs 1.19 mm to carry the load and 2.14 mm to stay stable under it, so the moulded wall is 2.50 mm, a section a mould fills evenly. A strength-only sizing would have produced a 1.2 mm wall and a round that folds in the tube.
| Member and mode | Applied | Allowable | Margin of safety |
|---|---|---|---|
| Fin root, bending | 7.5 MPa | 110 MPa | +13.7 |
A body at bore diameter leaves the fins no span and the round tumbles. Stepping the tail down to a Ø32 boom gives six fixed fins the span to hold the round stable, inside the 1.5 to 2.5 calibre design band.
| Layout | Static margin | Result |
|---|---|---|
| Fins flush to a Ø90 body | −0.80 calibres | Tumbles |
| Body reduced to Ø76 | −0.64 calibres | Tumbles |
| Ø70 body on a Ø40 boom | −0.24 calibres | Tumbles |
| Ø70 body on a Ø32 boom | Inside the 1.5 to 2.5 calibre band | Stable |
The step is not free. The cone from Ø70 to Ø32 carries a negative normal-force slope well aft of the centre of gravity, so the fins have to overcome the step as well as the nose. Four fins do not close the solve and eight put the round over-stable; six hold it inside the band, where an unguided body needs to be, because nothing downstream corrects what the airframe gets wrong.
The fins are bonded fixed. A muzzle-set trim mechanism would add a moving part qualified to the launch shock, a mating feature on every round and a fixture on every tube, for a round whose dispersion is set by the launcher's aim. The launcher aims; the round flies ballistic, its attitude decided by its geometry alone.
The trajectory is decided at the mount and nothing reaches the round after the muzzle. The table is a point-mass solution at ISA sea level with a drag coefficient of 0.35, a handbook value, on the Ø70 reference.
| Quadrant elevation | Range | Time of flight | Impact velocity | Impact energy |
|---|---|---|---|---|
| 5° | 525 m | 3.20 s | 144.7 m/s | 16.8 kJ |
| 10° | 894 m | 6.10 s | 120.6 m/s | 11.7 kJ |
| 15° | 1,165 m | 8.77 s | 107.0 m/s | 9.2 kJ |
| 20° | 1,364 m | 11.24 s | 99.7 m/s | 8.0 kJ |
| 30° | 1,599 m | 15.65 s | 95.4 m/s | 7.3 kJ |
| 45° | 1,636 m | 21.14 s | 99.7 m/s | 8.0 kJ |
Structurally destroying a light composite or polymer airframe is an order-of-magnitude 0.1 to 1 kJ proposition, and across the table the round arrives with between 7.3 and 16.8 kJ. Energy is not the constraint on this line. Miss distance is, and miss distance belongs to the cue, the laying solution and the mount rather than to the round.
A round that misses lands with that same impact energy, on the arc the laying solution set, and a high-angle solution and a flat one put it in very different places. The design answers with an exclusion zone over the full muzzle arc and downrange, kept clear while the launcher is armed and firing; the area-clear key must be made before the launcher will arm.
A steel, a glass-filled nylon, a sealing elastomer and a structural epoxy. The register is four lines long, and nothing on it burns.
| Where | Material class | Design basis |
|---|---|---|
| Nose | Alloy steel, AISI 4140 class, normalized | A mass item chosen for density, 7,850 kg/m³ |
| Body shell, tail boom, fins, cup body | Glass-filled polyamide, PA66-GF33 | 110 MPa and 7.0 GPa conditioned at 50 % RH, handbook values |
| Obturating land | Thermoplastic polyurethane or filled PTFE | The sealing face against the bore |
| Bonds | Two-part structural epoxy | Lap shear 20–30 MPa, handbook value |
Conditioned values are used throughout. Glass-filled nylon loses roughly 40 % of its strength and 33 % of its stiffness as it takes up moisture, and the round is sized to the in-service case rather than to the dry part. The nose is a mass item, not a strength item: any dense, tough, non-frangible steel that makes the mass in its envelope serves.
Every moulded part is made in-house, on moulds cut with the company's own five-axis capability, and the nose is plain turned bar well inside existing machine-shop work. Bar stock, polymer pellets, the structural adhesive and the obturator elastomer are bought in. No process in the round is new to the shop.
The round takes no part in its own engagement. The launcher lays it, a named person arms the launcher, and a normally closed valve releases it.
Bearing, range and height reach the launcher over a wire from the customer's fire-control interface, or a person enters them by hand.
The launcher computes a point-mass laying solution, with lead for a moving target, and checks it against the mount's ±170° of azimuth and −3° to +75° of elevation. A solution outside that envelope is refused.
Four permissives in series have to be made before the arm relay energizes, among them an area-clear key that is made only when the full muzzle arc and the ground downrange are clear. A person turns the arm key for every shot. Nothing on the round changes state, because there is nothing aboard to arm.
The normally closed breech valve opens in under 5 ms. With no power on the coil the breech stays shut.
Six fixed fins are live from the first metre. No link, signal or correction reaches the round after the muzzle.
The breech resets and the magazine indexes. The pace of the next shot is set by how fast the compressor restores the working pressure.
Every head mounts to the same nose interface and no electrical conductor crosses it on any head. The launcher delivers the same 30 bar over the same 3.00 m stroke to whichever is loaded.
A solid alloy-steel nose behind a flat Ø70 face, with no cavity, no chemistry and no mechanism. It carries most of the round's mass and the whole of the effect, which is collision.
The same airframe aft of the nose bulkhead, with a capture bay forward of it: a stored energy source, the capture medium, a dispersal head and a mechanical release. It is held to the round's 1.6 kg, bore and magazine pitch so the two index in one magazine, and it has a specification sheet of its own.
Not a third head and not a product of its own. A capture nose collapses mechanically on contact and the collapse itself releases the net or canopy, with no initiator, no electrical path and no proximity sensing.
The lines that hold for this round on every launch platform and for every customer.
The page this sheet specifies, and the sheets beside it in the line.
The page this sheet specifies, with the pictures and the reasoning.
A first conversation needs the airspace to be held, the ground a launch platform can stand on, the sensing already in place and the magazine depth the threat picture asks for. Every enquiry is screened.
Not an offer. Enquiries are screened, international transfer is subject to Canadian export permits taken per shipment, and all designs, systems and technologies shown are patent pending.
