Spacecraft with universal test port
A universal test port is connected to the different functional sub-systems of a spacecraft, allowing the sub-systems to be tested from a single location of an assembled spacecraft. The universal test port is mounted on an external surface of the spacecraft and configured to connect to the different functional sub-systems (such as power, propulsion, and command and data handling, for example) of the assembled spacecraft, allowing for the streamlining of testing operations by electrical ground system equipment during assembly, integration, and test (AIT) operations and reducing the risk of collateral damage to spacecraft hardware during testing in AIT.
1. A spacecraft, comprising:
a plurality of electrical systems, including power control circuitry, command circuitry, and mission communication circuitry;
a test port positioned on an external surface of the spacecraft, the test port comprising a plurality of mechanical interfaces for connecting to and receiving electronic test signals from a plurality of external test equipment systems to perform tests on the plurality of electrical systems; and
a plurality of internal cables connecting the test port and plurality of electrical systems to transfer the electronic test signals received from the external test equipment systems at the test port to the plurality of electrical systems.
2. The spacecraft of claim 1 , further comprising:
one or more test sensors connected to the test port, and not connected to the plurality of electrical systems, the test sensors configured to exchange electronic test signals with one or more of the plurality of external test equipment systems through the test port.
3. The spacecraft of claim 2 , wherein the test sensors include one or more accelerometers, test heaters, or thermocouples.
4. The spacecraft of claim 1 , further comprising:
a payload connected to the test port by the internal cables to exchange electronic test signals with one or more of the plurality of external test equipment systems to perform tests on the payload.
5. The spacecraft of claim 4 , wherein:
the spacecraft is a communication satellite,
the payload includes a plurality of radio frequency (RF) channels, and
the electronic test signals include test signals for the RF channels.
6. The spacecraft of claim 5 , wherein the payload includes a plurality of antennae and the external test equipment systems include a plurality of antenna covering structures configured to receive RF signals transmitted from the antennae.
7. The spacecraft of claim 4 , wherein:
the spacecraft is an optical imaging satellite,
the payload includes one or more imaging systems, and
the electronic test signals include test signals for control systems of the one or more imaging systems.
8. The spacecraft of claim 1 , wherein:
the test port and the internal cables are further configured to transfer software from the external test equipment systems to the command circuitry.
9. The spacecraft of claim 1 , wherein:
the test port and the internal cables are further configured to transfer encryption keys from the external test equipment systems to the mission communication circuitry.
10. The spacecraft of claim 1 , wherein the electronic test signals include signals for testing a solar array of the power control circuitry.
11. The spacecraft of claim 1 , wherein the electronic test signals include signals for testing a battery of the power control circuitry.
12. The spacecraft of claim 1 , wherein the plurality of electrical systems further includes electrical component of an attitude control sub-system and a gimbal control sub-system.
13. The spacecraft of claim 1 , wherein the plurality of electrical systems further includes electrical component of a propulsion control sub-system.
14. The spacecraft of claim 1 , further comprising:
an internal communication network over which the plurality of electrical systems are connected, wherein the internal communication network is distinct from the internal cables.
15. A method, comprising:
installing a plurality of functional sub-systems connected over an internal communication network into a spacecraft;
running a plurality of internal test cables from the plurality of functional sub-systems to a region of an exterior surface of the spacecraft, the internal test cables being distinct from the internal communication network and connected to the plurality of functional sub-systems to transfer electronic test signals received from external test equipment systems to the plurality of functional sub-systems to perform tests on the plurality of functional sub-systems; and
connecting the internal test cables to a test port located at the region of the exterior surface, the test port comprising a plurality of mechanical interfaces for connecting to and receiving the electronic test signals from the external test equipment and supplying the electronic test signals to the internal test cables.
16. The method of claim 15 , further comprising:
installing one or more test sensors into the spacecraft; and
connecting the one or more test sensors to the test port, but not the internal communication network, the one or more test sensors configured to exchange electronic test signals with one or more of the plurality of the external test equipment systems through the test port.
17. The method of claim 15 , further comprising:
subsequent to connecting the internal test cables to the test port, connecting one or more of the plurality of the external test equipment systems to the test port and performing a sequence of tests by exchanging electronic test signals over the test port.
18. The method of claim 15 , wherein the plurality of functional sub-systems includes a command sub-system and the method further comprises:
subsequent to connecting the internal test cables to the test port, connecting one or more of the plurality of the external test equipment systems to the test port and transferring software over the test port from the external test equipment systems to the command sub-system.
19. The method of claim 15 , wherein the plurality of functional sub-systems includes a mission communication sub-system and the method further comprises:
subsequent to connecting the internal test cables to the test port, connecting one or more of the plurality of the external test equipment systems to the test port and transferring encryption keys over the test port from the external test equipment systems to the mission communication sub-system.
20. A spacecraft, comprising:
a plurality of functional sub-systems;
an internal communication network connecting the plurality of functional sub-systems;
one or more test sensors not connected to the internal communication network;
a test port positioned on an external surface of the spacecraft, the test port comprising a plurality of mechanical interfaces for connecting to and receiving electronic test signals from a plurality of external test equipment systems to perform tests on the plurality of functional sub-systems; and
a plurality of internal test cables connecting the test port to the plurality of functional sub-systems and to the test sensors, the internal test cables being distinct from the internal communication network and connected to transfer the electronic test signals received from the external test equipment systems at the test port to the plurality of functional sub-systems and to the test sensors.