Integral data acquisition capacity

• US 6,598,828 B2
• Filed: 03/05/2001
• Issued: 07/29/2003
• Est. Priority Date: 03/05/2001
• Status: Expired due to Fees

• Current Assignee: the united states of america as represented by the secretary of the navy
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Clark, Keith E., Donohue, Patrick, Oah, Sue, Fiebick, Wayne A.
• Primary Examiner(s): Gregory, Bernarr E.
• Application Number:
  US09/801,126
• Publication Number:
  US 20030071165A1
• Time in Patent Office: 876 Days
• Field of Search: 244/3--, 244/117.R, 244/118.1, 342/25, 342/52-58, 342/61, 342/62, 342/63, 342/64, 342/65, 342/70, 342/71, 342/72, 342/175, 342/190, 342/191, 342/195, 342/196, 342/197, 89/18, 89/11, 89/11.1, 340/945, 340/946, 340/971, 324/500, 324/503, 324/512, 324/513-536, 324/555, 324/556, 731/67, 738/653, 738/659, 738/661
• US Class Current: 244/118.1
• CPC Class Codes: F41G 7/007 Preparatory measures taken before the launching of the guided missiles

Abstract

Provided is a modified configuration that permits operation of instrumentation onboard platforms that may experience severe environmental conditions. The instrumentation permits autonomous acquisition of performance data. Acquired data may be recorded for later playback as well as provided to the platform'"'"'s operator in real time in multiple formats, such as warning lights, digital displays, video, or audio. An application would be for sensor systems used on an automobile to record performance data, providing a warning when routine maintenance is due or a catastrophic failure is imminent. A specific application uses a flight-certified missile launcher pod on an F/A-18 aircraft, as incorporated in the aircraft'"'"'s wingtip and modified to hold instrumentation conforming, at least in part, to the launcher pod'"'"'s internal dimensions. This arrangement enables autonomous onboard display and recording of data from the captive carry testing of an AIM-9X missile and follow-on designs that may be based on the AIM-9X.

Claims

1. A method for configuring an instrumentation package to fit within a missile attached'"'"'to an aircraft to test said missile during a simulated test flight of said missile comprising the steps of:

(a) removing a closed cycle cooling system from an interior of said missile;

(b) measuring available space within the interior of said missile after removing said close cycle cooling system from the interior of said missile;

(c) designing electronic modules for said instrumentation package to fit within said available space in the interior of said missile;

(d) fabricating said electronic modules;

(e) packaging said electronic modules to withstand environmental stress applied to said instrumentation package during the simulated test flight of said missile, and to fit within said available space in the interior of said missile, said instrumentation package including;

(i) a digital recorder having a flash RAM memory, the flash RAM memory of said digital recorder recording flight data received by said digital recorder for a time period of approximately one hour;

(ii) a multiplex data bus connected to said digital recorder;

(iii) a digital to analog converter connected to said multiplex data bus;

(iv) a plurality of sensors attached to said missile, said plurality of sensors being connected to said multiplex data bus, said plurality of sensors generating digital signals representative of said flight data;

(v) said digital to analog converter converting said digital signals to an analog format providing analog signals representative of said flight data; and

(vi) said multiplex data bus transferring said digital signals from said digital recorder to said digital to analog converter for conversion to said analog format by said digital to analog converter; and

(f) mounting said electronic modules within said available space in the interior of said missile.

2. The method of claim 1 wherein said aircraft having said missile attached thereto is controlled by an operator on board said aircraft.

3. The method of claim 1 wherein said instrumentation package when mounted within said missile eliminates a requirement for additional flight testing of said missile.

4. The method of claim 1 further comprising the step of downloading said analog signals representing said flight data to a porfitable data acquisition system having a monitor for viewing by an operator of said aircraft.

5. The method of claim 1 wherein said instrumentation package includes a battery connected to the electronic modules of said instrumentation package to supply DC power to the electronic modules of said instrumentation package.

6. The method of claim 1 wherein said closed cycle cooling system comprises a bottle of pressurized nitrogen.

7. The method of claim 1 wherein said aircraft comprises an F/A-18 aircraft.

8. The method of claim 1 wherein said missile comprises an AIM-9X missile.