Variation in the release time of a solar panel under qualification temperature ranges. A burn wire release mechanism for a spacecraft or other system having two masses initially held together by a pretensioned loop, with a spring configured to push the masses apart. How strong/stiff does the monofilament line need to be? The burn wire release mechanism has 400 firings in component and system level testing … The release status data obtained by the MCU indicated that all the solar panels were released within 2.5 s from the initiation of burn wire triggering, and the time gap between the released panels was at the maximum of 0.43 s. The test results indicated that the proposed mechanism guarantees the synchronous release of multiple solar panels. The multiple functions implemented by applying the pogo pin are advantageous for the proposed mechanism with respect to the simplicity of the system. An increase in the power generation of a CubeSat can increase its potential because data collection, data transmission, and data processing are dependent on the power capacity. The feasibility of the mechanism was evaluated by functional tests under various test conditions, such as different input voltages, different numbers of tightening nylon wires, and various temperature ranges. The electrical pads, which are terminals connected with the resistor, are located on the rear side of the burn resistor PCB. In addition, it can establish a temporal electrical connection and it also acts as a status switch to confirm the solar panel deployment status. [13] proposed a novel deployable solar panel mechanism using spring-loaded pogo pins. A pin? This is tied to the base under load.

CubeSats are revolutionary to the space industry and are transforming space exploration which enables the next generation of scientists and engineers to complete all phases of space missions. Is a kraft tube enough to take them up. When heated the burn wire would cut through the cable due to pre-compressed spring. S2659457) was supported by the Business for Cooperative R&D between Industry, Academy, and Research Institute funded by the Korean Small and Medium Business Technology Administration in 2018. In addition, the time gap between the released panels was only 0.42 s. These observations indicate that the mechanism functioned well even after the launch vibration and TV tests. This area allows to accommodate additional hardware such as a payload or other appendages. The idea is you would compress the nose and body together and secure the line (somehow…). Therefore, in this study, the MCU combined with the current sensing amplifiers were added to the primary PCB to utilize the function of the pogo pins as the deployment status switches for the solar panels. Park, S. H. Kim, H. Kim, and H. U. Oh, “Experimental investigation on the feasibility of using spring-loaded pogo pin as a holding and release mechanism for CubeSat’s deployable solar panels,”, K. Nakaya, K. Konoue, H. Sawada et al., “Tokyo Tech Cubesat: CUTE-I—design & development of flight model and future plan,” in. The mechanism should function well under the given qualification temperature range, to assure its functionality in the on-orbit thermal environment. This significantly increases the output power of the solar cells. Configurations of primary PCB: (a) mechanical configuration and (b) electrical configuration. A. Vilan, F. A. Agelet et al., “Xatcobeo: small mechanisms for CubeSat satellites—antenna and solar array deployment,” in, H. U. Oh, M. S. Jo, K. M. Lee, and D. J. Kim, “Spaceborne tilt mirror mechanism and application of shape memory alloy actuator to implement fail-safe function in emergency mode,”, H. Yano, T. Kubota, H. Miyamoto et al., “Touchdown of the Hayabusa spacecraft at the Muses Sea on Itokawa,”, A. Thurn, S. Huynh, S. Koss et al., “A nichrome burn wire release mechanism for CubeSats,” in, H. U. Oh and M. J. Lee, “Development of a non-explosive segmented nut-type holding and release mechanism for cube satellite applications,”, T. Y. Fundamentally you need to store some energy to later use to separate the rocket. The functionality of the mechanism was verified through the release function tests in ambient conditions, according to the number of repetitive activations, multiple nylon wire windings, and qualification temperature ranges. Figure 8 shows the variation in the release time of the solar panels under the qualification temperature ranges. When the solar panel is in the stowed position, the stroke of the spring-loaded pin should be within the nominal range, to ensure a reliable contact between the pogo pins and electrical pads on the burn resistor PCB. The primary PCB is mainly composed of an MCU, current sensing amplifiers (INA301), and a temperature sensor. The release function tests conducted after the completion of the launch vibration and TV tests showed the nominal function of the mechanism. However, in order to employ a pogo pin-based HRM in a real-time CubeSat mission, the mechanism should be qualified under severe launch and on-orbit thermal vacuum (TV) environments. In addition, the MCU with a current sensing amplifier applied to the mechanism well detected the release status of each solar panel in accordance with the temporary electrical connection implemented by the pogo pins. The maximum relative dynamic displacement at the center of the dummy panel, estimated from the vibration test results, was 1.68 mm. The panels were successfully released within 2.86 s, although there were differences of 13% and 66% with those measured before and after the vibration test, respectively. Representative LLSS test results before and after each vibration test.

The simple, reliable, and inexpensive HRM often contributes to significant cost reductions to a CubeSat program and aids in the success of space missions. 2019, Article ID 2580865, 13 pages, 2019. https://doi.org/10.1155/2019/2580865, 1Space Technology Synthesis Laboratory, Department of Aerospace Engineering, Chosun University, Gwangju, Republic of Korea, 2Soletop Co. Ltd., 409 Expo-ro, Yuseong-gu, Daejeon, Republic of Korea, 3Agency for Defense Development, Yuseong-gu, Daejeon, Republic of Korea. Enlarged configuration of pogo pin mechanism: (a) partially stowed and (b) fully stowed.

How to “safe” the device against accidental firing? pulling out the parachute with it. In addition, the proposed mechanism guarantees the loading capability along the in-plane and out-of-plane directions of solar panels, the synchronous release of multiple panels, and a handling simplicity that differentiates it from the conventional mechanism.

In addition, it still guaranteed a synchronous release of the multiple solar panels because the time gap between the released panels was only 0.83 s. These results indicate that the proposed mechanism also functions well with the application of multiple nylon wire windings. The basic functional test results confirm that the spring-loaded pogo pin constitutes an attractive function for a holding and release mechanism because it works as an electrical interface to provide power to the burn resistor, which is mounted on the burn resistor PCB of the solar panels. Moreover, payloads and data transmission capabilities are also limited if the power generation is insufficient. In the previous version of the pogo pin HRM [13], the function to detect the deployment status of the solar panels was not applied, as its main objective was to validate the feasibility of the mechanism. The temperature reference point (TRP) was located at the center surface of the dummy panel.

These results indicate that the mechanism assures sufficient repeatability for use in CubeSat applications. Release function test setup: (a) before and (b) after deployment of solar panels. In commercial satellites and aerospace engineering, pyrotechnic devices have been used in the HRMs. TV test setup after the release function test of the mechanism. One in the Nose (red) and one in the body tube. The result indicates that the resistors exhibited the resistance variation of less than 0.7% throughout the test phases. Review articles are excluded from this waiver policy.

To enhance the capability of a CubeSat, deployable solar panels are required, which would increase the surface area of a CubeSat for the installation of solar cells and would help orient the panels to face perpendicular to the sun for effective power generation. Sign up here as a reviewer to help fast-track new submissions. The two notched guide pins mounted on the solar panel are combined with the U-shaped displacement limiter, when the solar panel is fully stowed. Thurn et al. This morning we bench tested the burn-wire release system for our benthic lander project.

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