AVIA 230 Quiz 5

AVIA 230 Quiz 5 Liberty University

AVIA 230 Quiz Designing the System

1. What type of customers are the primary drive to the development of UAS?
2. of sensor packages and increasing reliability in small airframes and subsystems has enabled some mission capabilities, originally only achievable by relatively large and expensive UASs, to be scaled to smaller UASs.
3. This engine type uses internal combustion, an eccentric shaft, and apex seals
4. drag develops from the shearing stresses that dissipate energy in the thin boundary layer above the surfaces of the aircraft.
5. Several engineering standards organizations have taken up the task to develop standards for UAS design and operations. Which choice is one of those organizations?
6. Unmanned aircraft performance is most clearly defined by the ______________ system.
7. Components of parasite drag do not include:
8. is the sum of all forces opposing movement of an aircraft through the viscous medium of the atmosphere.
9. The use of a starter/generator saves considerable _________ (and ______ on the accessory gearbox), while reducing the overall complexity of the accessory drive system.
10. The choice of UAS _______________ is similarly diverse, ranging from turboprop and turbofan gas turbines to two-stroke heavy fuel engines, or HFEs, with electric, Wankel (aka, rotary), and Otto cycle reciprocating engines filling niches between the extremes of the design spectrum.
11. Many people argue that the design process for UAS typically begins with _________ _________ .
12. The ____________ system is typically composed of a microprocessor or computer that runs algorithms designed to control the aircraft over a preplanned flight path,
13. The _________________ should take precedence above all other factors in a ground-up design of a UAS.
14. The _____________ design affords certain advantages over other designs. Its construction is straightforward with few parts, qualities that simplify assembly and manufacture.
15. For current UAS design, the requirements for safe operations in the NAS dictate that design starts with the ____________ system to enable the operator to remain on the control loop as a monitor or in the control loop to carry out manual tasks.
16. The difference between geometric and effective pitch is referred to as _______.
17. Although industry influence of the design (and operation) of UASs is closely bound to the regulatory process, the influence of industry standards may be strong without the undergirding force of the
18. The _________ was a key to enabling aircraft to be reliably controlled without a human pilot on board.
19. At the most basic level, the UA exists only as a platform to carry the _________ necessary to successfully accomplish mission goals.
20. This type of testing does not only put the autopilot and flight computer software through their paces, but may also verify the function of the servos and control services prior to an actual flight.
21. Traditional hydraulic and pneumatic control systems are being replaced by what types of systems to save in weight?
22. The General Dynamics F-16 was the first aircraft intentionally designed to incorporate a slight aerodynamic instability, known as
23. The aircraft platform and all subsystems and components should function _________________ as a system to optimize overall operational capability of the UAS in achieving mission goals.
24. Hardware-in-the-loop testing is done to simulate flight conditions in which location?
25. drag results from the unbalanced pressure distributions across the area of the projected shape presented to the viscous ow and the turbulence it creates.

Other sets

Covers the Learn material from Module 5: Week 5.

1. EMI is a type of _________.
2. High aspect ratio wings are __________ .
3. The difference between geometric and effective pitch is referred to as
4. is the sum of all forces opposing movement of an aircraft through the viscous medium of the atmosphere.
5. Unmanned aircraft performance is most clearly defined by the ______________ system.
6. Traditional hydraulic and pneumatic control systems are being replaced by what types of systems to save in weight?
7. Materials for a manned aircraft airframe are generally selected to provide maximum strength and stiffness with minimum
8. Several engineering standards organizations have taken up the task to develop standards for UAS design and operations. Which choice is one of those organizations?
9. of sensor packages and increasing reliability in small airframes and subsystems has enabled some mission capabilities, originally only achievable by relatively large and expensive UASs, to be scaled to smaller UASs.
10. The ___________________ is the part of the UAS that provides the control interface to the unmanned aircraft (UA) through which the pilot/operator steers the UA or otherwise manages the mission.
11. The design of both manned and unmanned aircraft must achieve some necessary threshold of performance and reliability while minimizing
12. This engine type has a separate intake, compression, power, and exhaust stroke.
13. Increased ___________ translates into reduced payload, range, and endurance.
14. This engine type uses internal combustion, an eccentric shaft, and apex seals
15. The aircraft platform and all subsystems and components should function _________________ as a system to optimize overall operational capability of the UAS in achieving mission goals.
16. The ____________ system is typically composed of a microprocessor or computer that runs algorithms designed to control the aircraft over a preplanned _flight path,
17. The choice of UAS _______________ is similarly diverse, ranging from turboprop and turbofan gas turbines to two-stroke heavy fuel engines, or HFEs, with electric, Wankel (aka, rotary), and Otto cycle reciprocating engines filling niches between the extremes of the design spectrum.
18. UAS performance is most clearly defined by the ________ system, with the greatest capability coming from turbine engines.
19. What primary element explains the growth in UAS designs not derived from manned aircraft, including small sUAS, where habitation of the aircraft is impossible.
20. The use of a starter/generator saves considerable _________ (and ______ on the accessory gearbox), while reducing the overall complexity of the accessory drive system.
21. Many people argue that the design process for UAS typically begins with
22. drag results from the unbalanced pressure distributions across the area of the projected shape presented to the viscous _ow and the turbulence it creates.
23. The most important feature of the control station is the interface that enables the human pilot/ operator to interact with the UAS
24. testing is widely used for the verification of the aircraft control system, sensor/payload integration, and the CS interface.
25. The _________ was a key to enabling aircraft to be reliably controlled without a human pilot on board.

Other set

1. The _________ was a key to enabling aircraft to be reliably controlled without a human pilot on board.
2. The use of a starter/generator saves considerable _________ (and ______ on the accessory gearbox), while reducing the overall complexity of the accessory drive system.
3. This type of testing does not only put the autopilot and light computer software through their paces, but may also verify the function of the servos and control services prior to an actual flight.
4. Increased ___________ translates into reduced payload, range, and endurance.
5. Components of parasite drag do not include:
6. ____________________ of sensor packages and increasing reliability in small airframes and subsystems has enabled some mission capabilities, originally only achievable by relatively large and expensive UASs, to be scaled to smaller UASs.
7. _______________ testing is widely used for the verification of the aircraft control system, sensor/payload integration, and the CS interface.
8. UAS performance is most clearly defined by the ________ system, with the greatest capability coming from turbine engines.
9. The design of both manned and unmanned aircraft must achieve some necessary threshold of performance and reliability while minimizing_______
10. EMI is a type of _________.
11. While UASs have sometimes provided opportunity for _______________ against competing manned aircraft, this is not universally true.
12. Any UAS platform should be chosen or designed according to the rule of
13. Unmanned aircraft performance is most clearly defined by the ______________ system.
14. Larger sUAS may use an internal combustion engine for propulsion and to drive a _________ as the primary source of electrical power.
15. The difference between geometric and effective pitch is referred to as _______.
16. Materials for a manned aircraft airframe are generally selected to provide maximum strength and stiffness with minimum
17. For current UAS design, the requirements for safe operations in the NAS dictate that design starts with the ____________ system to enable the operator to remain on the control loop as a monitor or in the control loop to carry out manual tasks.
18. The ____________ system is typically composed of a microprocessor or computer that runs algorithms designed to control the aircraft over a preplanned flight path,
19. At the most basic level, the UA exists only as a platform to carry the _________ necessary to successfully accomplish mission goals.
20. The design of any given unmanned aircraft system (UAS) will correspond directly to the______________ of the platform.
21. The _________________ should take precedence above all other factors in a ground-up design of a UAS.
22. This engine type uses internal combustion, an eccentric shaft, and apex seals
23. What type of customers are the primary drive to the development of UAS?
24. The aircraft platform and all subsystems and components should function _________________ as a system to optimize overall operational capability of the UAS in achieving mission goals.
25. Although industry influence of the design (and operation) of UASs is closely bound to the regulatory process, the influence of industry standards may be strong without the undergirding force of the