Goose CS-110 is a fully unpowered interceptor round, thrown from a ground tube on shop air at 189.2 m/s and flying a ballistic arc on six fixed fins. This page is the round itself: every part, every station and every figure the design closes.
Goose CS-110 is a pneumatically launched, fully unpowered kinetic interceptor. It leaves a ground tube on shop air, flies a ballistic arc, and defeats a small uncrewed aircraft by collision.
The round is a solid steel nose on a moulded glass-filled nylon airframe: 1.600 kg all-up, Ø90.00 mm across the obturator, 463.0 mm long, 6.6 calibres nose to tail. It is indexed into the breech, thrown by air, and from the muzzle onward it is on its own. Nothing on it is powered and nothing on it is armed, because there is nothing to arm.
That is the design position, and it is a short list of absences. The round carries no battery, no motor, no receiver, no servo, no sensor, no indicator and no initiator, and so it carries no wiring of any kind. It carries no warhead, no fuze, no primer, no propellant and no energetic material. Nothing in the fleet transmits by radio and nothing guides on a link, and on this round that doctrine costs nothing to hold: there is nothing aboard for an adversary to reach into. Guidance on this line sets out the three tiers and where each program sits.
What throws the round is ground equipment with its own page — the launch platform holds the accumulator, the breech and the tube. What goes on the front is a subject of its own again, at heads and the nose interface. The loop they run together, cue to reload, is the engagement, and the line sits behind CDNS UAV Platforms. This page is the round.
Powered flight was priced at this mass before it was set aside. At 1.6 kg the number came back near 22 kW, and a round this size cannot carry the battery that feeds it.
Hold a 1.6 kg body at the speed a launch tube already gives it, around 212 m/s, and the sustained shaft power lands near 22 kW. The conclusion in the engineering is flat: the round cannot carry the battery. Small bodies pay a punishing price for speed, and every gram of pack, motor, controller and wiring comes straight out of the part that does the work at the far end.
So the round spends nothing. The accumulator does the work once, in 28.6 ms of barrel time, and hands the round 28.64 kJ at the muzzle. After that the only forces on it are gravity and drag, and the only authority over its attitude is the geometry it was moulded with. The same arithmetic that closed powered flight at 1.6 kg opens it further up the mass scale, in a separate class with its own bore and its own tube: CS-120 carries a motor, a battery and a flight computer at 15 kg, where the sustain figure falls to about 0.78 kW.
Unpowered is not a stripped-down powered round. It is the decision that lets this one be five parts, an adhesive and a steel slug.
Count the round and the answer is five moulded or machined parts and one structural bond. That is the whole bill of material, front to back.
Item 1101 is the nose slug, machined from AISI 4140 in the normalized condition, 41.0 mm deep and presenting a flat Ø70 face. Item 1201 is the forward body shell, 120.0 mm of moulded PA66-GF33 at Ø70.00 mm. Item 1301 is the tail boom, 260.0 mm at Ø32.00 mm. Item 1401 is the fin, moulded six off. Item 1501 is the obturator cup, 12.0 mm thick, the part that takes bore pressure across the full Ø90.00 mm and pushes everything ahead of it up the tube. The sixth line on the bill is a two-part structural epoxy.
Those five lengths are the round: 41.0 and 120.0 and 30.0 and 260.0 and 12.0 make the 463.0 mm overall. The build runs in the same order. The nose is weighed against the one interface baseline every head is built to and set into the forward shell. Shell and boom are bonded across the transition cone. Six fins go into their boom lands in a jig. The obturator cup goes on last. Two acceptance gauges sit at the bench, the fin bond is not accepted until each of the six reads 60° ± 0.5°, and a build card follows each round from OP 10 through OP 120.
The moulds are the product on this line, cut in-house; the reasoning sits on the manufacturing page.
The budget closes on 1.600 kg to within 0.4%. Four of the five lines are the airframe, and together they are less than a quarter of the round.
A round is a mass argument before it is anything else. Every gram in the airframe is a gram not arriving at the target, so the budget is written to push mass forward into the one part that does the work and hold everything behind it to the minimum the structure allows. The forward shell, the boom, the six fins and the obturator cup together come to 368 g. Everything else is nose.
| Item | Part | Material | Mass |
|---|---|---|---|
| 1101 | Nose slug | AISI 4140 normalized | 77.1% of all-up mass |
| 1201 | Body shell, forward | PA66-GF33 | 89 g |
| 1301 | Tail boom | PA66-GF33 | 84 g |
| 1401 | Fin set, six off | PA66-GF33 | 88 g · 14.7 g each |
| 1501 | Obturator cup | PA66-GF33 with a TPU or filled PTFE land | 107 g |
| — | All-up mass | Five parts and a structural bond | 1.600 kg |
The mass budget as the design closes it, with the nose carried as a fraction of all-up mass.
The table carries one reading, and the rest of the round follows from it: the round is 77% nose by mass, the airframe is a carrier, the steel is the effect, and there is no chemistry anywhere in it.
One machined slug of AISI 4140 in the normalized condition, 41.0 mm deep behind a flat Ø70 face, is three quarters of the round and the whole of what it does at the far end.
The nose is not strength-critical. It is a mass item, and it is chosen as one: AISI 4140 normalized, ultimate tensile strength around 655 MPa, density 7,850 kg/m³, to ASTM A29/A331 as the reference the machining works to. Steel is chosen for density in a bore of fixed diameter. Nothing about the nose is asked to be clever; it is asked to be heavy, to be square to the axis, and to sit at the one interface baseline every head on this line is ballasted to.
That last point is what makes the line work as a line rather than as three separate rounds. Because each nose is built to the same interface mass, the round flies identically whichever nose is loaded, the launcher delivers the same 30 bar over the same 3.00 m stroke to any of them, and one magazine can index a kinetic round and a capture round in the same belt. The mechanical detail of that joint — a Ø64.9 spigot register, a Ø70 shoulder and a three-lug bayonet, and not one conductor across it — is set out at heads and the nose interface.
The effect at the target is collision, and collision is all of it. There is no explosive train anywhere in this round, no initiator, no primer and no propellant, and pneumatic launch means there is no propellant on the magazine either. The steel arrives at speed, and the speed came from air.
The moulded shell is 2.50 mm thick. Strength alone would allow 1.19 mm; buckling under the launch stroke demands 2.14 mm, and moulding practice rounds it up from there.
Two failure modes were carried side by side at a safety factor of 2.0, and buckling governs the shell by roughly 1.8× over material strength. That is the ordinary result for a thin moulded tube pushed hard from behind: the wall is not going to be crushed, it is going to fold. Conditioned PA66-GF33 needs 1.19 mm to carry the axial load and 2.14 mm to stay stable under it, so 2.50 mm is selected and the extra goes to a wall thickness a mould tool can hold consistently.
At the critical station the numbers are comfortable in both directions, and it is the buckling margin that decided the wall.
Axial compression. 26.5 MPa applied against a 110 MPa allowable for conditioned PA66-GF33 at 50% RH, giving a margin of safety of +3.16. Material strength is not the constraint on this shell at any station.
Shell buckling. The same 26.5 MPa against a 71.9 MPa critical stress, giving a margin of safety of +1.72. This is the mode the wall thickness is chosen for, and it is why the shell is thicker than a strength calculation on its own would ask for.
The body does not run at bore diameter to the tail. It steps from Ø70 to Ø32 across a 30 mm cone, and the slim boom that follows carries the highest shell stress in the round.
Two requirements pull the aft end in opposite directions. The stability solve wants a long moment arm behind the centre of gravity, and the fins want span: 29.0 mm of exposed semi-span on each of six, reaching from the boom out to the Ø90 bore line. A boom at Ø70 would leave the fins 10 mm of blade. Stepping down to Ø32 gives them the span the stability solve asks for while the transition cone keeps the load path continuous through the diameter change.
The step is paid for in stress. At Ø32 with the same 2.50 mm wall, the boom carries 78.8 MPa against the same 110 MPa allowable, a margin of safety of +0.40. That is the tightest number in the round's structure and it sits, deliberately, in the cheapest and most easily replaced moulding on the bill. The load it is holding is the full peak base force of the launch, applied at the obturator cup behind it and carried forward through the boom into the body and the nose.
| Station | Figure | What sets it |
|---|---|---|
| Bore and obturator OD | Ø90.00 mm | The tube. Bore area 63.617 cm². |
| Main body OD | Ø70.00 mm | The stability solve. |
| Tail boom OD | Ø32.00 mm | The fin span requirement. |
| Shell and boom wall | 2.50 mm | Buckling, rounded to moulding practice. |
| Transition length | 30.0 mm | The Ø70 to Ø32 cone. |
| Overall length | 463.0 mm | 6.6 calibres on the Ø70 reference. |
The principal stations of the round, each one carrying the reason it is that number.
Six is the answer the stability solve gives. Four does not close and eight is over-stable. They are bonded into lands in the boom, and there is no cam, no trim tip and no servo anywhere on the round.
Each fin is a moulded PA66-GF33 blade with a 120.0 mm root chord, a 60.0 mm tip chord at a taper ratio of 0.5, 4.00 mm thickness and 25.0° of leading-edge sweep. Exposed semi-span is 29.0 mm, exactly half the difference between the Ø90 bore and the Ø32 boom, so the fin set reaches the bore line and no further. The six weigh 88 g together, 14.7 g each.
They are bonded, not hinged. Six lands are moulded into the boom, the fins are set into them in a jig, and the bond is checked at 60° ± 0.5° before it is accepted. From that point the round's aerodynamic configuration is frozen in the part. Fin alignment is an acceptance check at the bench and never an active trim in flight, and the round leaves the muzzle with its attitude decided by geometry alone.
The division of labour is clean and it is the reason the round can be this cheap. The launcher aims: it holds the boresight offset, computes the laying solution and drives the mount to a solved azimuth and quadrant elevation. The round flies ballistic. Nothing at the muzzle bends anything, and nothing in flight is asked to.
The gap between them is the static margin, and on this round it is 2.01 calibres — inside the 1.5 to 2.5 band the design works to, with room on both sides.
A heavy nose and a long tail is the oldest stability trick there is, and this round is an unusually pure example of it. Three quarters of the mass sits in the first 41 mm, which puts the centre of gravity 90.0 mm from the nose tip, 1.29 calibres back. The fin set at the far end of a 260 mm boom puts the centre of pressure at 230.4 mm, 3.29 calibres. The difference is 2.01 calibres of static margin.
Too little margin and the round is loose in pitch and yaw off the muzzle. Too much and it weathercocks into the crosswind and throws the laying solution away. Sitting near the middle of the band matters more on an unguided body than on a guided one, because there is no loop downstream to absorb what the airframe gets wrong. Six fins rather than four is part of the same answer: four does not close the solve at this mass distribution, and eight puts the round over-stable at the top of the band.
A fixed accumulator volume expands into a growing barrel volume behind a cup that spans the full bore. The whole event is over in 28.6 ms and puts 28.64 kJ into the round.
The model behind these figures is an isentropic expansion of a fixed accumulator volume into the growing volume behind the round, integrated as a two-state differential system with a valve-opening ramp and constant seal drag, at a ratio of specific heats of 1.40. The obturator cup takes full bore pressure across Ø90.00 mm — 63.617 cm² of area — and pushes the round up the tube ahead of it. Charge pressure is 30.0 bar, which is shop-air class and deliberately so, and the stroke is 3.00 m.
| Quantity | Figure | Note |
|---|---|---|
| Charge pressure | 30.0 bar | Shop-air class. |
| Stroke | 3.00 m | Ø90.00 mm bore, 63.617 cm². |
| Accumulator volume per shot | 15.9 L | After the gas-inertia correction. |
| Muzzle velocity | 189.2 m/s | The exit figure the model closes on. |
| Time in the barrel | 28.6 ms | Valve open to muzzle exit. |
| Muzzle energy | 28.64 kJ | Into a 1.600 kg round. |
| Combined energy efficiency | 85.9% | Accumulator energy into muzzle energy. |
| Muzzle residual pressure | 9.0 bar | Vented at exit; the source of muzzle blast. |
Interior ballistics for the round as the engineering closes them, at 30.0 bar over a 3.00 m stroke.
Two of those lines matter commercially rather than technically. The 15.9 L per shot is what an accumulator has to give back before the next round can go, and recharge, not the tube, is what sets the tempo of a launch line — that argument belongs to the launch platform. And 85.9% combined efficiency is what decides how much compressor a launch line needs standing behind it.
Both figures are the round's, and they are not interchangeable. The mean describes the stroke. The peak arrives in the first fraction of a millimetre and every part on the bill is sized against it.
Peak acceleration is 11,369 m/s², or 1,159 g, at x = 0 and t = 0.14 ms. Mean acceleration over the stroke is 5,966 m/s², or 608 g. The ratio between them is 1.91, and the peak base force is 18,191 N. Structure on this round is sized against the peak at a safety factor of 2.0, because the peak is the load the round actually sees.
The peak cannot be tuned out of the system, and the arithmetic showing why is a single line. Peak base force occurs at x = 0, before the round has moved at all, so the acceleration is simply the pressure difference across the cup times the bore area over the mass: 30 bar less atmospheric, across 63.62 cm², into 1.6 kg. Accumulator volume sets exit velocity; it does not touch the peak. The only levers on launch shock are lower pressure, a smaller bore or a longer stroke, and a softer valve is not one of them.
This is the figure that decides what a nose is allowed to be. A solid steel slug does not care about 1,159 g. A payload does, and the arithmetic of what survives the stroke is the first page of the capture round's design at Encapsulator CS-111. It is also why the heavier class launches so much more gently: CS-120 peaks near 240 g, and live electronics can ride that.
From the muzzle the round is ballistic. The quadrant table below is computed as a point mass at ISA sea level with a drag coefficient of 0.35 on the Ø70 reference, and that assumption travels with the numbers.
Six fins are live from the first metre and the static margin holds the round on its axis, so the trajectory is set entirely at the mount: the launcher solves for azimuth and quadrant elevation, drives to it, and the arc follows. Nothing reaches the round after the muzzle and nothing aboard it corrects anything.
| Quadrant elevation | Range |
|---|---|
| 5° | 525 m |
| 10° | 894 m |
| 15° | 1,165 m |
| 20° | 1,364 m |
| 30° | 1,599 m |
| 45° | 1,636 m |
Range by quadrant elevation, computed as a point mass at ISA sea level with Cd0 = 0.35 taken on the Ø70 reference diameter. Cd0 is a literature value, and the table stands on it.
The round arrives with the energy the tube gave it, less what drag took on the way. Nothing else happens at the target, because there is nothing else aboard for anything else to happen with.
At 10° of quadrant elevation the round is doing 120.6 m/s at impact and carrying 11.7 kJ. At 45°, the long, high arc, it arrives at 99.7 m/s and 8.0 kJ. Both come off the same trajectory model and the same drag assumption.
Set those against the job. Structurally destroying a light composite or polymer airframe is an order-of-magnitude 0.1 to 1 kJ proposition. The round arrives with eight to twelve, and over-match at that scale is not a marginal call: it is one to two orders of magnitude of headroom against the airframes this class of threat is made of. So the engineering attention on this line goes where it belongs. Miss distance is the failure mode, not insufficient energy — and miss distance is a property of the cue, the laying solution and the mount, all of which live on the engagement and the launch platform rather than on the round.
A round that misses is a falling 1.6 kg moulded body with nothing in it: nothing to initiate, and no arming state to have got wrong. What that means for the ground behind the target is set out at safety on the launch line.
A steel, a glass-filled nylon, an elastomer or filled fluoropolymer for the sealing land, and a structural epoxy. The register is four lines long, and that is the point of it.
A short material register is a cheap round, a short supply chain and a forward cell that can make the airframe close to where it is used. Everything below is named as the reference the engineering works to.
| Ref | Where | Material | Properties as taken |
|---|---|---|---|
| M-01 | Nose slug | AISI 4140, normalized | UTS ~655 MPa · density 7,850 kg/m³ · reference ASTM A29/A331 · a mass item, not strength-critical |
| M-02 | Body, boom, fins, cup body | PA66-GF33, 33% glass-filled nylon 6/6 | 110 MPa and 7.0 GPa conditioned at 50% RH · density 1,400 kg/m³ · Poisson 0.35 · references ISO 1874 and UL 94 |
| M-03 | Obturating land | TPU 90A or filled PTFE | The sealing face against the bore |
| M-04 | Bonds | Two-part structural epoxy | Lap shear 20–30 MPa |
The round's material register. Standards are named as the references the engineering applies.
Read the register against the effect and the commercial argument follows from it. One steel slug does the work. One moulded polymer does the carrying, in four shapes off tooling the group owns. One land seals the bore. One adhesive holds it together. There is no initiator to store and no energetic material anywhere in the round or on the magazine that feeds it.
The round suits a buyer who has to hold ground against numbers and wants the exchange to run in their favour. It suits nobody looking for a missile, and it is not built to be mistaken for one.
The useful first conversation is about ground, numbers and authority. The figures above will still be here afterwards.
Bring the sector you have to hold, the ground you can stand a launch platform on, and the magazine depth the threat picture asks of you. Canadian Shield answers with the round, the tube and the interface between them. Enquiries are screened, counsel comes first on any international transfer, and permits are taken per shipment.
The rest of the line reads in order. CDNS UAV Platforms is the whole picture in one page. The launch platform is what throws the round. Heads and the nose interface is what goes on the front and what never crosses the joint. Guidance on this line puts the three tiers side by side. Safety on the launch line is the interlock chain and the exclusion zones. The engagement runs the loop from cue to reload.
All CDNS UAV Platforms designs are patent pending; international transfer is export-controlled and subject to Canadian government permits taken per shipment, and nothing on this page is an offer.
