Patent Application
20050030006
The present invention relates generally to a test method and apparatus and, more particularly, to a test method and apparatus for testing the electrical power system of an aircraft using existing unmodified test equipment not otherwise capable of properly testing and certifying the aircraft for store launching operations for the particular store type.
Modern aircraft, such as an F-15E aircraft manufactured by the assignee of the present invention, and the P-3, the S-3 and the F-16 aircraft manufactured by Lockheed Aeronautical Systems Company, are adapted to carry stores. These stores can, for example, include missiles, such as the Joint Direct Attack Munition (JDAM), the Walleye missile, the Standoff Land Attack missile (SLAM), the SLAM-ER missile, the Harpoon missile, and the Maverick missile. A missile is generally mounted to the wing of a host aircraft, typically via disconnectable pylons, such that the aircraft can carry the missile to the vicinity of the target destination prior to its deployment.
Prior to uploading the store to the aircraft pylon, the aircraft and its provisioning for the store must be tested and certified to be within the specifications for acceptable store launching operation. To perform these preinstallation certification tests, ground support test equipment are deployed with the aircraft for the purpose of testing the aircraft via the Pylon Store Interface Cable Connector. For example the ground support test set for the P-3 aircraft includes the AWM 96 Test Set which has the capability of testing the electrical performance of every circuit in the aircraft-to-store interface cable. This includes testing for proper voltage, frequency, power, timing, and wiring impedance. Discrete signal conductors are tested to insure adequate voltage magnitude and timing. Communication signals are tested for bi-directional transmission and proper protocol. Additional tests verify the ability of the aircraft to provide safety logic and assure that weapon launch and abort functions are operating correctly.
To certify the readiness of the aircraft for weapon store upload and interconnections, the ground test equipment must be precertified as operational. This is assured through proper design and configuration control as well as periodic testing of the ground support equipment itself. Once certified, the ground support equipment can only be changed using costly formal change programs involving lengthy schedule time.
Aircraft, such as the P-3, for example, can be equipped to carry additional weapons, not included in the stores inventory, by adding functions in cable modules and in the umbilical cable wiring between the weapon store and the aircraft pylon connector. Adding functions to the aircraft wiring and weapon umbilical cable allows the aircraft and its existing weapon system to remain unchanged while expanding the weapon store inventory to include additional store types. An example of this is the addition of the SLAM-ER weapon to the P-3 aircraft equipped with the Harpoon weapon system. The SLAM-ER weapon requires special power characteristics and timing not included in the Harpoon weapon system. To achieve the SLAM-ER power compatibility with the P-3 aircraft and its Harpoon weapon system, a special umbilical cable that includes power-switching relays may be added between the aircraft pylon connector and the SLAM-ER weapon store. This cable allows the existing Harpoon weapon system control panel switch functions in the P-3 aircraft to use the Harpoon power sources and logic functions to initiate the power sequences required by MIL-STD 1760 for the SLAM-ER missile launch cycle. However, prior to uploading a SLAM-ER weapon onto the aircraft pylon, the aircraft and its Harpoon weapon system with the SLAM-ER weapon umbilical cable must be certified for the SLAM-ER weapon store.
The test equipment used to certify the P-3 aircraft and Harpoon Weapon system for MIL-STD 1760 SLAM-ER Weapon launching is the AWM 96 Ground Support Test Set. This test set connects directly to the aircraft-to-missile umbilical connector and either certifies the aircraft and its weapon control system to be within specifications for launching a weapon, or rejects the aircraft as non-serviceable. The AWM 96 Test Set includes tests of the source voltages and source impedances required for the MIL-STD 1760 weapon, but the “Go/No-Go” limits are inadequate for the SLAM-ER. That is, the AWM 96 Test Set could certify the aircraft and SLAM-ER weapon system as in specification or a “Go” condition with insufficient source voltage and/or too high of source impedance to successfully launch a SLAM-ER weapon store. For example, the SLAM-ER weapon requires the aircraft to supply DC # 2 open circuit voltage of 26.5 volts and a source impedance of 0.75 ohms, whereas the existing AWM 96 Test Set accepts open circuit voltage of 22 volts and 1.0 ohm source impedance as an acceptable or “Go” test result. The lower voltage and higher impedance allowed by the test set measurement would not assure adequate power delivered to the weapon loads, and therefore would erroneously certify the aircraft for SLAM-ER weapon upload.
The method and apparatus of this invention utilizes an electrical circuit test adapter connected in the wiring between the aircraft-to-missile umbilical cable and the test set used to certify the aircraft and its weapon store to provide translation of source voltage and source impedance such that the test set provides reliable test results without expensive and time consuming modifications to the test set. In accordance with a preferred embodiment of the invention, the method and apparatus of this invention utilizes an electrical circuit test adapter connected in the wiring between the P-3 aircraft-to-missile umbilical cable and AWM 96 Test Set, and provide a translation of the source voltage and source impedance of the aircraft such that the acceptable limit values of the SLAM-ER weapon specifications correspond to the MIL-STD 1760 weapon preset “Go/No-Go” limits of the AWM 96 Test Set. In this preferred embodiment, inserting the apparatus of the present invention between the aircraft-to-store umbilical cable and the AWM 96 Test Set assures that the aircraft's open circuit source voltage is greater than 26.5 volts and source impedance is lower than 0.75 ohms if the test results in the “Go” condition. Similarly, the method and apparatus of the present invention provides for translation of the DC #1 voltage and source impedance such that the AWM 96 “Go” test result certifies both the DC #1 and DC #2 power sources for the SLAM-ER weapon. Therefore, in accordance with a preferred embodiment of the present invention, the method and apparatus of this invention provide for certification of the P3-C aircraft and weapon system as serviceable for SLAM-ER weapon application, using the existing AWM 96 Test Set without the expensive cost and lengthy delays required for test set modification.
Moreover, the AWM 96 Test Set includes preset power sequencing required for the MIL-STD 1760 weapon that is inadequate for the SLAM-ER certification test. The method and apparatus of this invention includes switches in the 3 phase AC power circuit, the DC #1 and DC #2 power circuits, and the release and separation circuits. These switches allow complete launch cycle sequence testing by manually controlling sequencing of power, in conjunction with manual control of the AWM 96 Test Block, to satisfy the SLAM-ER power time line test requirements and the sequencing of release consent and weapon store separation to exercise and satisfy SLAM-ER launch logic.
Thus, the apparatus and method of the present invention utilize a test adaptor for testing the electrical power system of the aircraft, having a weapon store umbilical cable, utilizing a test set to determine whether electrical parameters of the aircraft satisfy predetermined standards for store launching operations. An electrical circuit of the adaptor translates electrical parameters to be tested of the aircraft, such that detection of the translated parameters by the test set provides reliable certification for store weapon launching operations.
Further features and advantages of the present invention, as well as the structure and operation of various embodiments of the present invention, are described in detail below with reference to the accompanying drawings.
The accompanying drawings, which are incorporated in and form a part of the specification, illustrate the embodiments of the present invention and together with the description, serve to explain the principles of the invention. In the drawings:
With reference to the drawings there is shown in
The umbilical cable 14 may be an umbilical cable module connected to the aircraft pylon 16 to enhance the capability of the aircraft to launch additional store types while allowing the aircraft and its existing weapon system to remain unchanged. For example, the P-3 aircraft originally equipped for a Harpoon weapon system may be modified by the addition of the umbilical cable adapter 14 to expand the aircraft's capability to launch a SLAM-ER weapon system. Once installed, the umbilical cable 14 becomes part of the aircraft and weapon store pylon 16. While the umbilical cable 14 may be of a type to enhance the capability of a P-3 aircraft to launch additional store types, such as the SLAM-ER missile, it is to be understood that the umbilical cable 14 need not be specific to any particular aircraft or any particular store type.
The test adapter 12 of the present invention functions as a translation module for translating electrical power parameters, to be tested by the test set 18, of the aircraft such that detection of the translated parameters by the test set provides reliable certification for store weapon launching operations, even though the test set, without the test adapter 12, cannot reliably certify the readiness of the aircraft for store launching operations for the particular store type. For example, in accordance with a preferred embodiment, the test set 18 may be an AWM 96 Test Set for certifying the readiness of a P-3 aircraft for store launching operations of a MIL-STD 1760 missile. If the P-3 aircraft is modified to provide launch capability for a SLAM-ER missile, the test set 18 without the adapter of the present invention cannot provide reliable certification. This is because the electrical power parameters that must be certified in accordance with MIL-STD 1760 must satisfy different standards for the SLAM-ER missile than for a typical MIL-STD 1760 missile. More specifically, the open circuit source voltage parameter for the aircraft electrical power system for the MIL-STD 1760 missile must be at least 22 volts, while for the SLAM-ER missile it must be at least 26.5 volts. The source impedance for the electrical power system for the MIL-STD 1760 missile must be no greater than 1 ohm, while for the SLAM-ER missile it must be no greater than 0.75 ohms. Thus, use of the AWM 96 Test Set designed to certify the MIL-STD 1760 missile for launching operations could, without the test adapter 12, erroneously certify the aircraft for SLAM-ER missile operations upon detecting an open circuit source voltage of less than 26.5 volts and/or a source impedance of greater than 0.75 ohms. Thus, the test adapter 12 translates the electrical power parameters to be tested by the test set 18, of the aircraft such that detection of the translated parameters by the test set provides reliable certification of the aircraft for store launching operations.
In addition to testing for proper aircraft source voltage and source impedance, the test adapter of the present invention also provides for launch cycle sequence testing. While the AWM 96 Test Set could test for the preset power sequencing for the MIL-STD 1760 weapon, it was inadequate for testing preset power sequencing for the SLAM-ER weapon. The test adapter of the present invention allows for complete launch cycle sequence testing of the SLAM-ER missile without modification of the AWM 96 Test Set. With reference to
Thus, there has been described a method and apparatus for testing the electrical power system of an aircraft using existing unmodified test equipment not otherwise capable of properly testing and certifying the aircraft for store launching operations for the particular store type.
While the present invention has been described by reference to specific embodiments and specific uses, it should be understood that other configurations and arrangements could be constructed, and different uses could be made, without departing from the scope of the invention as set forth in the following claims.
