make one complete revolution and the period for our orbit is 6038.7878 seconds which is about 1 hour and 40 minutes. The velocity needed to reach our orbit is measured in the change of velocity also know as ΔV. Table 4.3.2.2 breaks down the budget for the 5 kg case of Project Bellerophon. ΔV 4.3.2.2 Breakdown ΔV Variable Value Percent of ΔVtotal 9354 m/s -- ΔVtotal 4 m/s 0.043 ΔVdrag 2034 m/s 21.745 ΔVgravity assist 411 m/s -4.394 ΔVEarth 7727 m/s 82.606 ΔVleo The is a combination of all the other which are: ΔVtotal ΔVs ΔVdrag, ΔVgravity, ΔVEarth assist, refers to the velocity needed to overcome the drag which we will ΔVleo. ΔVdrag experience. This value seems incredibly low, and it should be that way because we are launching from a balloon at an altitude of 30 km. Since we are launching from so high in the atmosphere the air density is relatively low and does not cause much resistance to the launch vehicle. is the velocity needed to overcome gravity drag. assist refers to the velocity ΔVgravity ΔVEarth the Earth’s spin is helping the launch vehicle reach orbit. This is the only which is helping ΔV us, the other are velocities we need to overcome. is the velocity needed to achieve ΔVs ΔVleo our orbit. Figure 4.3.2.1 shows the entire orbit mentioned above. Full orbit of 5kg payload. Fig 4.3.2.1: (Kyle Donahue) In order to obtain any orbit a steering law is needed to put the rocket on the correct path. We created and used a linear-tangent steering law for each stage. There are many other types of steering laws besides linear-tangent. Other types of steering laws include linear with any of the
make one complete revolution and the period for our orbit is 6038.7878 seconds which is about 1 hour and 40 minutes. The velocity needed to reach our orbit is measured in the change of velocity also know as ΔV. Table 4.3.2.2 breaks down the ΔV budget for the 5 kg case of Project Bellerophon. 4.3.2.2 ΔV Breakdown Variable Value Percent of ΔVtotal ΔVtotal 9354 m/s -- ΔVdrag 4 m/s 0.043 ΔVgravity 2034 m/s 21.745 ΔVEarth assist 411 m/s -4.394 ΔVleo 7727 m/s 82.606 The ΔVtotal is a combination of all the other ΔVs which are: ΔVdrag, ΔVgravity, ΔVEarth assist, ΔVleo. ΔVdrag refers to the velocity needed to overcome the drag which we will experience. This value seems incredibly low, and it should be that way because we are launching from a balloon at an altitude of 30 km. Since we are launching from so high in the atmosphere the air density is relatively low and does not cause much resistance to the launch vehicle. ΔVgravity is the velocity needed to overcome gravity drag. ΔVEarth assist refers to the velocity the Earth’s spin is helping the launch vehicle reach orbit. This is the only ΔV which is helping us, the other ΔVs are velocities we need to overcome. ΔVleo is the velocity needed to achieve our orbit. Figure 4.3.2.1 shows the entire orbit mentioned above. Fig 4.3.2.1: Full orbit of 5kg payload. (Kyle Donahue) In order to obtain any orbit a steering law is needed to put the rocket on the correct path. We created and used a linear-tangent steering law for each stage. There are many other types of steering laws besides linear-tangent. Other types of steering laws include linear with any of the
Report_Section_2.docx