Multidirectional airspeed detection system
A pitot-static array system for a tail-sitting aircraft has a disk with a plurality of edge ports arrayed about an edge of the disk. Each of a plurality of pressure transducers is configured to measure air pressure at one of the edge ports. The edge ports are arrayed about an axis parallel to a pitch axis of the aircraft.
1. A pitot-static array system for a tail-sitting aircraft, the pitot-static array system comprising:
a disk having a plurality of edge ports arrayed about an edge of the disk; and
a plurality of pressure transducers, each transducer configured to measure air pressure at one of the edge ports;
wherein the edge ports are arrayed about an axis parallel to a pitch axis of the aircraft; and
wherein at least one of the edge ports is used as a ram pressure port;
wherein at least one of the edge ports is used as a static pressure port.
2. The system of claim 1 , further comprising:
a processor configured to receive outputs from the transducers;
wherein the processor determines an airspeed of the aircraft from the outputs of the transducers.
3. The system of claim 1 , further comprising:
a processor configured to receive outputs from the transducers;
wherein the processor determines an angle of attack of the aircraft from the outputs of the transducers.
4. The system of claim 1 , further comprising:
a processor configured to receive outputs from the transducers;
wherein the processor determines a sideslip of the aircraft from the outputs of the transducers.
5. The system of claim 1 , wherein the edge ports are arrayed around one-half of the edge of the disk.
6. The system of claim 1 , wherein the edge ports are arrayed around one-quarter of the edge of the disk.
7. The system of claim 1 , wherein the transducers are located inside the disk.
8. The system of claim 1 , wherein the transducers are located external to the disk.
9. The system of claim 1 , further comprising:
a signal conditioner;
wherein the pressure transducers are assembled with the signal conditioner located inside the disk.
10. The system of claim 1 , further comprising:
a spacing element;
wherein the disk is carried by the spacing element for locating the disk a distance from components of the aircraft.
11. A pitot-static array system, comprising:
a disk having;
an array of edge ports aligned on an edge surface of the disk; and
a side port located on a circular surface of the disk; and
a plurality of pressure transducers configured to measure a ram air pressure of each edge port and a static air pressure of the side port;
wherein each port is in fluid communication with one of the pressure transducers.
12. The system of claim 11 , further comprising:
a spacing element;
wherein the disk is carried by the spacing element.
13. The system of claim 11 , further comprising:
a processor configured to receive outputs from the transducers;
wherein the processor determines an airspeed from the outputs of the transducers.
14. The system of claim 11 , wherein the edge ports are arrayed around one-half of the edge surface of the disk.
15. The system of claim 11 , wherein the edge ports are arrayed around one-quarter of the edge surface of the disk.
16. The system of claim 11 , wherein the pressure transducers are located inside the disk.
17. The system of claim 11 , further comprising:
a signal conditioner;
wherein the pressure transducers are assembled with the signal conditioner located inside the disk.
18. A pitot-static array system for an aircraft, the pitot-static array system comprising:
a disk having a plurality of edge ports arrayed about an edge of the disk;
a side port located on a side surface of the disk;
a plurality of pressure transducers, one of the plurality of transducers being configured to measure ram air pressure at each of the edge ports, and one of the plurality of transducers being configured to measure static air pressure at the side port;
wherein the edge ports are arrayed about an axis parallel to a pitch axis of the aircraft, and the side port is oriented as parallel to the pitch axis.
19. The system of claim 18 , further comprising:
a processor configured to receive outputs from the transducers;
wherein the processor determines an airspeed of the aircraft from the outputs of the transducers.
20. The system of claim 18 , further comprising:
a processor configured to receive outputs from the transducers;
wherein the processor determines an angle of attack of the aircraft from the outputs of the transducers.