Method and apparatus for missile interface testing

• US 5,414,347 A
• Filed: 07/08/1994
• Issued: 05/09/1995
• Est. Priority Date: 07/13/1992
• Status: Expired due to Term

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Milani, David A., Fowler, David L., Carpenter, Dennis G., Crisafulli, Joseph A., Emmert, Gerald T., Van Cleve, David P., Curry, Robert J., Monk, Ronald W.
• Primary Examiner(s): Wieder, Kenneth A.
• Assistant Examiner(s): BOWSER, BARRY
• Application Number:
  US08/272,441
• Time in Patent Office: 305 Days
• Field of Search: 324/750-762, 89/1.56.1.819
• US Class Current: 324/73.1
• CPC Class Codes: F41G 7/006 Guided missiles training or simulation devices
• CPC Class Codes: G06F 30/15 Vehicle, aircraft or watercraft design
• CPC Class Codes: G06F 30/20 Design optimisation, verification or simulation optimisation, verification or simulation of circuit designs G06F30/30

Abstract

An apparatus (10) for testing an operational status of a missile interface system includes a portable control unit (16) having an interface panel (28). The interface panel (28) has a plurality of umbilical ports adapted to receive data from a plurality of missile stations (12) via a corresponding plurality of umbilical cables (18). The interface panel (28) is further includes a coaxial port (40), adapted to receive data from a radar trap (22) via a coaxial cable (20). The apparatus further includes a fixture assembly (116) having a main body portion (120). The main body portion (120) has a channel (122) through which a first end of the umbilical cable (18) is allowed to pass. The fixture assembly (116) is adapted to be releasably mounted to a missile station (12).

Claims

1. An apparatus for testing an aircraft launcher system of the type including a plurality of missile stations and a radar trap for receiving a radio frequency signal, the apparatus comprising:

a portable control unit having an overall size capable of being transported to an aircraft, the control unit including a plurality of data ports;

a plurality of missile umbilical cables, each of the plurality of missile umbilical cables including a first end having a first electrical connector adapted to electrically attach to one of the data ports and a second end having a second electrical connector adapted to electrically attach to one of the plurality of missile stations;

processing means mounted in the control unit for receiving and processing data from the plurality of missile stations including a first signal generated by the aircraft;

simulation means mounted in the control unit for simulating signals that ordinarily would be provided if actual missiles were present at the missile stations in response to the first signal generated by the aircraft;

a radar umbilical cable including a first end having a first electrical connector adapted to electrically attach to one of the data ports and a second end having a second electrical connector adapted to electrically attach to the radar trap; and

means for receiving a post-launch information signal from the radar trap, the means for receiving being mounted in the control unit and coupled to one of the data ports.

2. The apparatus of claim 1, wherein the means for receiving a second signal further comprises means for determining a time of receipt of the second signal.

3. The apparatus of claim 1, further comprising a test cable and means for generating a self test of the apparatus, the means for generating the self test adapted to communicate with the processing means through the test cable.

4. The apparatus of claim 1, wherein the simulation means is adapted to simulate a preselected sequence of missile signals in response to the first signal generated by the aircraft.

5. The apparatus of claim 4, wherein the simulation means is adapted to simulate a preselected sequence of missile signals corresponding to an AMRAAM response sequence.

6. The apparatus of claim 1, further comprising event sensing means for receiving and recording a time of receipt of a plurality of signals generated by the aircraft.

7. An apparatus for testing an aircraft launcher system of the type including a plurality of missile stations, a radar trap for receiving a radio frequency signal, and a missile interface,the apparatus comprising:

a control unit having an overall size capable of being transported to an aircraft, the control unit including an interface panel having a plurality of data ports, and a microcomputer;

a plurality of missile umbilical cables corresponding in number to the plurality of missiles stations, each of the plurality of missile umbilical cables including a first end having a first electrical connector adapted to electrically attach to one of the data ports and a second end having a second electrical connector adapted to electrically attach to one of the plurality of missile stations;

at least two interface modules mounted in the control unit, a first and second interface module being connected to a first and second data port, respectively;

the interface modules each being adapted to simulate signals that would ordinarily be provided if actual missiles were present at the missile stations in response to a first signal generated by the aircraft;

a radar umbilical cable including a first end having a first electrical connector adapted to electrically attach to one of the data ports and a second end having a second electrical connector adapted to electrically attach to the radar trap; and

a data link module mounted in the control unit and coupled to one of the data ports adapted to receive a post-launch information signal from the radar trap.

8. The apparatus of claim 7, wherein the data link module further includes an edge detection circuitry for determining a time of receipt of the second signal.

9. The apparatus of claim 7, wherein the apparatus includes at least four interface modules.

10. The apparatus of claim 9, wherein the interface modules are each adapted to simulate a preselected sequence of missile signals corresponding to an AMRAAM response sequence.

11. The apparatus of claim 7, further comprising an event sense module adapted to receive a plurality of signals from the aircraft and record a time of receipt of each of the plurality of signals from the aircraft.

12. An apparatus for testing an aircraft launcher system of the type including a plurality of missile stations, a radar trap for receiving a radio frequency signal, and a missile interface, the apparatus comprising:

a control unit having an overall size capable of being transported to an aircraft, the control unit including an interface panel having a plurality of data ports, and a microcomputer;

a plurality of missile umbilical cables corresponding in number to the plurality of missiles stations, each of the plurality of missile umbilical cables including a first end having a first electrical connector adapted to electrically attach to one of the data ports and a second end having a second electrical connector adapted to electrically attach to one of the plurality of missile stations;

at least two interface modules mounted in the control unit, a first and second interface module being connected to a first and second data port, respectively, the interface modules each being adapted to simulate signals that would ordinarily be provided if actual missiles were present at the missile stations in response to a first signal generated by the aircraft;

a radar umbilical cable including a first end having a first electrical connector adapted to electrically attach to one of the data ports and a second end having a second electrical connector adapted to electrically attach to the radar trap, said radar umbilical cable being operative to transmit a post-launch signal received by said aircraft to said control unit;

a data link module mounted in the control unit and coupled to one of the data ports adapted to receive a second signal from the radar trap, the data link module including an edge detection circuitry for determining a time of receipt of the second signal; and

an event sense module adapted to receive a plurality of signals from the aircraft and record a time of receipt of each of the plurality of signals from the aircraft.