Apparatus and method for simulating rocket-to-ramjet transition in a propulsion system
US5831155A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Dec 2, 1996 |
| Grant date | Nov 3, 1998 |
| Priority date | — |
| Expiry date | Dec 2, 2016 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01M15/14
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
A test facility for realistically simulating selected operating conditions for a multi-mode aircraft propulsion system employs bypass ducting to rapidly introduce heated compressed air to a ramjet engine immediately following rocket booster operation. Heated compressed airflow from a suitable supply is initially utilized to ensure that incidental ducting, control elements, and instrumentation are stabilized in temperature, by bypassing the totality of the heated compressed airflow from a location close to the multi-mode propulsion system out to ambient atmosphere. Upon stable conditions being realized, the rocket thrust component of the propulsion system is actuated and selected physical parameters e.g., pressure, in the multi-mode propulsion system are measured. Upon certain criteria being fulfilled, inlet port covers are opened, allowing heated, compressed air to pass through to the ramjet engine, as well as continuing to bypass a reduced amount of air. A mixture of fuel and a portion of the available heated compressed air is then burned in a ramburner component of the propulsion system. The thrust generated by the propulsion system in its rocket propulsion mode, rocket-to-ramjet…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.