Near Space Balloon Performance Predictions

Conner, Joseph; Arena, Andrew S.

doi:10.2514/6.2010-37

Cited by 6 publications

(4 citation statements)

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“…When Reynolds numbers are greater than 10 6 , the drag coefficient is stable at the value of about 0.1, while for Reynolds numbers lower than 10 5 the constant drag coefficient of 0.5 can be used. A drag coefficient model for the ascent balloon in a Reynolds number range of 10 5 ∼10 6 is explored by Conner and Arena [19], which can be expressed as follows: 22The basic equations of airship during ascending can be expressed as follows:ḣ…”

Section: Solar Modelmentioning

confidence: 99%

Coordinated Control of Pressure Difference and Rising Velocity for Stratospheric Airship with Thermal Effects

Hong

Huang

Lin

et al. 2015

Mathematical Problems in Engineering

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Ascending control of stratospheric airship is a challenging control problem, especially if both the rising velocity and the pressure difference between the inside and outside of the airship are required to be controlled simultaneously during ascending. In this paper, a coordinated scheme to control pressure difference and rising velocity of stratospheric airship with vector thrust is presented. With the control scheme, the airship maintains the pressure difference by exhausting air with feedback control. At the same time, the supplemental thrust is generated to compensate the buoyancy fluctuation caused by exhausting air so that the airship’s vertical velocity can track a given reference trajectory. Simulations show that the coordinated control scheme ensures that the airship rises to the altitude of 20 km steadily and rapidly while the pressure difference is always in the safe range. Furthermore, the control scheme is robust enough to the thermal disturbance caused by solar radiation and other thermal processes, which is calculated with partial differential equations.

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Section: Solar Modelmentioning

confidence: 99%

Coordinated Control of Pressure Difference and Rising Velocity for Stratospheric Airship with Thermal Effects

Hong

Huang

Lin

et al. 2015

Mathematical Problems in Engineering

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“…And based on the analysis code, a methodology was proposed for the prediction and optimization of the ascent trajectory (Morani et al, 2009;Palumbo et al, 2010). Conner and Arena (2010) discussed the development of a performance predictor for near space balloon systems and the balloon's volume and drag coefficient were established as a function of altitude. Dai et al (2012) investigated the influence of film radiation properties and clouds on balloon thermal behaviors at float condition but the influence on ascending process was not discussed.…”

Section: Introductionmentioning

confidence: 99%

Influences of initial launch conditions on flight performance of high altitude balloon ascending process

Zhang

2015

Advances in Space Research

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“…"Near space" generally refers to 20 km to 100 km airspace from the ground, and it is a new airspace that does not belong to the traditional category of the aerospace nor the space of aviation [1]. Near space travel vehicle lift by a helium balloon is rapidly developing [2], because it can arrive in complex areas such as the stratosphere unreachable by some fixed-wing aircraft. A flight profile of the high-altitude balloon made by New Mexico Institute of Mining and Technology [3] includes 57 minutes of float at 31 km and approximately 30 minutes of decent.…”

Section: Introductionmentioning

confidence: 99%

Design of mission adaptive landing gear for near space travel lander

Huang¹,

Nie²,

Zhang³

et al. 2016

J. vibroeng.

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The ability to perform vertical takeoff and landing reliably and safely is of great concern for a near space travel lander carrying passengers. Oblique and uneven terrains can severely limit the degree of landing safety, so mission adaptive landing gear is designed and analyzed for its function of automatic adjustment before touchdown. The legs of mission adaptive landing gear are composed of shock absorbers and actuating cylinders, which can adjust angles of the main struts relative to the capsule under control, ensuring all feet touch the irregular surface together. Compared with a conventional landing gear, scaled test and dynamic simulation in three typical conditions verify that the new design can reduce the rotation angle and the translational motion of the capsule to less than 3 degrees and 1 meter, respectively. For buffer process, the overall design reduces peak load of the lander by more than 24 %, enhances efficiency of the shock absorber to more than 85 % and optimizes stroke lengths of shock absorbers. While landing on a slope with an angle of less than 31 degrees, mission adaptive landing gear can ensure the capsule's maximum overload less than 5 and the capsule's attitude angle less than 20 degrees, respectively. Landing performance shows that mission adaptive landing gear is robust to uncertain conditions of the landing surface.

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Near Space Balloon Performance Predictions

Cited by 6 publications

References 0 publications

Coordinated Control of Pressure Difference and Rising Velocity for Stratospheric Airship with Thermal Effects

Coordinated Control of Pressure Difference and Rising Velocity for Stratospheric Airship with Thermal Effects

Influences of initial launch conditions on flight performance of high altitude balloon ascending process

Design of mission adaptive landing gear for near space travel lander

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