Patent Application
20200348332
Not applicable.
Not applicable.
Conventional pitot-static elements are configured to measure airspeed and airspeed related parameters by measuring a ram air pressure and a static air pressure with a pitot-static tube. Error can be introduced into the parameters if the pitot-static tube is misaligned with the ram air flow. Pitot-static tubes featuring gimbaled heads can help reduce error due to misalignment, but they have limitations regarding how many degrees the gimbaled heads can pivot. Conventional pitot-static tubes are generally limited to ±25 degrees of misalignment.
In this disclosure, reference may be made to the spatial relationships between various components and to the spatial orientation of various aspects of components as the devices are depicted in the attached drawings. However, as will be recognized by those skilled in the art after a complete reading of this disclosure, the devices, members, apparatuses, etc. described herein may be positioned in any desired orientation. Thus, the use of terms such as “above,” “below,” “upper,” “lower,” or other like terms to describe a spatial relationship between various components or to describe the spatial orientation of aspects of such components should be understood to describe a relative relationship between the components or a spatial orientation of aspects of such components, respectively, as the device described herein may be oriented in any desired direction.
This disclosure describes a multidirectional airspeed detection system configured to measure flight parameters of an aircraft, and the system may be especially useful for a tail-sitting aircraft that pitches over to wing-borne flight. The system has a pitot tube array, which is fixedly mounted to the aircraft, and the array has a plurality of edge ports. Each of a plurality of pressure transducers is in fluid communication with an edge port for measuring air pressure at each edge port. A computer, which may be integrated within the array or carried elsewhere on the aircraft, is configured to receive outputs from the transducers for use in calculating the flight parameters. Additionally or alternatively, data from the array may be communicated to an onboard or remote flight control system (FCS).
Referring specifically to
System 501 further comprises a first transducer 541, a second transducer 543, a third transducer 545, a fourth transducer 547, a fifth transducer 549, a sixth transducer 551, a seventh transducer 553, an eighth transducer 555, a ninth transducer 557, and a tenth transducer 559. Transducers 541, 543, 545, 547, 549, 551, 553, 555, 557, 559 are typically static pressure sensors, however, in some embodiments, they can be dynamic pressure sensors.
Edge ports 505, 507, 509, 511, 513, 515, 517, 519, 521 are each in fluid communication with an associated transducer 541, 543, 545, 547, 549, 551, 553, 557, 559 such that air pressure detected by each transducer 541, 543, 545, 547, 549, 551, 553, 557, 559 increases as airflow increases generally a corresponding arrow 523, 525, 527, 529, 531, 533, 535, 537, 539. Side port 205 is in fluid communication with transducer 559, such that air pressure detected by transducer 559 increases as static air pressure increases generally adjacent disk 201.
Air data computer 503 is electrically coupled to transducers 541, 543, 545, 547, 549, 551, 553, 555, 557, 559 and can use outputs from transducers 541, 543, 545, 547, 549, 551, 553, 555, 557, 559 to determine airspeed, angle of attack, and sideslip throughout a full conversion corridor of tail-sitting aircraft 101. Each transducer 541, 543, 545, 547, 549, 551, 553, 555, 557, 559 is sampled concurrently to determine a magnitude and direction of a wind vector. A flight control computer, processor, or another signal conditioner might be used in place of air data computer 503. For example, an aircraft moving in direction 571 would likely detect a pressure in edge port 511 greater than all other edge ports because airflow along arrow 529 is greater than in other directions, whereas edge port 515 would likely have minimal or no pressure increase. Another example is if an aircraft moves in direction 573, then a pressure in edge port 515 will be greater than all other edge ports because airflow along arrow 533 is greater than in other directions.
For each embodiment, it should be noted that the side port for measuring static pressure can be optional, with static pressure being measured at one or more of the edge ports that are generally perpendicular to or pointed away from the direction of travel of the aircraft. As the aircraft pitches over in conversion to wing-borne flight, the particular edge port or ports used to measure static pressure will change based on the attitude of the aircraft. Alternatively, edge ports may be used when the system is unable to measure pressure at a side port, such as, for example, when a side-port pressure transducer is inoperative.
At least one embodiment is disclosed, and variations, combinations, and/or modifications of the embodiment(s) and/or features of the embodiment(s) made by a person having ordinary skill in the art are within the scope of this disclosure. Alternative embodiments that result from combining, integrating, and/or omitting features of the embodiment(s) are also within the scope of this disclosure. Where numerical ranges or limitations are expressly stated, such express ranges or limitations should be understood to include iterative ranges or limitations of like magnitude falling within the expressly stated ranges or limitations (e.g., from about 1 to about 10 includes, 2, 3, 4, etc.; greater than 0.10 includes 0.11, 0.12, 0.13, etc.). For example, whenever a numerical range with a lower limit, R1, and an upper limit, Ru, is disclosed, any number falling within the range is specifically disclosed. In particular, the following numbers within the range are specifically disclosed: R=R1+k*(Ru−R1), wherein k is a variable ranging from 1 percent to 100 percent with a 1 percent increment, i.e., k is 1 percent, 2 percent, 3 percent, 4 percent, 5 percent, . . . 50 percent, 51 percent, 52 percent, . . . , 95 percent, 96 percent, 95 percent, 98 percent, 99 percent, or 100 percent. Moreover, any numerical range defined by two R numbers as defined in the above is also specifically disclosed. Use of the term “optionally” with respect to any element of a claim means that the element is required, or alternatively, the element is not required, both alternatives being within the scope of the claim. Use of broader terms such as comprises, includes, and having should be understood to provide support for narrower terms such as consisting of, consisting essentially of, and comprised substantially of. Accordingly, the scope of protection is not limited by the description set out above but is defined by the claims that follow, that scope including all equivalents of the subject matter of the claims. Each and every claim is incorporated as further disclosure into the specification and the claims are embodiment(s) of the present invention. Also, the phrases “at least one of A, B, and C” and “A and/or B and/or C” should each be interpreted to include only A, only B, only C, or any combination of A, B, and C.
