Airframes, closed around the mission.

The airframe starts with the mission profile and the constraints that can disqualify a layout. Payload, operating envelope, launch and recovery concept, propulsion installation and balance all occupy the same geometry. Configuration selection is recorded as a trade against the brief.

Orion-T1 is the public example. The concept uses a single-engine shoulder-wing arrangement with a blended chin inlet, a hollow area-scheduled S-duct and an aft-mounted engine. Air-launch and parachute recovery are part of the configuration. The published length is 5,100 mm, and the maximum section is 550 × 580 mm superelliptic.

The release geometry is one boolean-fused closed solid. That gives the concept one external volume for mass-property work and one installation model for clearance checks. Detailed structure, manufacturing definition and physical inspection evidence require later work.

The T1 mass budget names its basis by category. The skin-model structure is 204.8 kg, the engine is 165.2 kg, the declared systems budget is 171.0 kg and usable fuel is 155.5 kg. The published total closes at 696.5 kg, with an empty mass of 541.0 kg.

Balance is carried as a result in the release. The center of gravity is 2,497 mm (49.0% length) and the static margin is 0.130 MAC. The trim record reports 49.1° against 12.2° at CLmax. Those figures let a reviewer see where the concept closes and which assumptions later design stages must replace with hardware data.

A component budget exposes where mass risk sits. A declared systems allowance is different from geometry-derived structure, and the release labels that difference. If payload, fuel or equipment changes, the mass and balance solution must be reopened against the same model.

The engine face is located at x = 2,900 mm and the nozzle exit at x = 4,280 mm. The engine-bay record reports 15.55 mm radial, verified clearance. These values tie the propulsion installation to the airframe model before the flight-dynamics screen begins.

The scripted simulation set contains 6 cards: trim, launch separation, maximum level speed, climb, sustained turn, and fuel and thrust anchors. Each card states its condition and expectation beside the measured simulation result. The set checks whether the generated aircraft and engine deck behave consistently inside the declared model.

That screen can expose a concept that misses trim, separation behavior, a speed condition or engine-deck correlation. The receipt evaluates behavior inside the declared 6-DoF model. Structural life, control-system hardware behavior and manufacturing conformity require later-stage evidence.