System for reducing thermal barrier of hypersonic aero vehicle

Abstract

A system for reducing thermal barrier of hypersonic aero vehicle is disclosed, wherein the obelisk shaped hypersonic aero vehicle is covered by combined multiple long and narrow plates. Across the plates, roller bearings are placed and spaced in short distance. The air frictions across the roller bearings of the hypersonic aero vehicle consecutively and the coefficient of friction is 0.002. The heat of the air friction is just normal and does not cause the thermal barrier and melting. The system improves the speed and reduces the energy consumption significantly.

The advantages of the system are: 1. reducing the thermal barrier with innovative structure; 2. solving the problem of thermal barrier which is common for conventional hypersonic aero vehicle.

Claims

1. A system for reducing a thermal barrier of a hypersonic aero vehicle, comprising an obelisk shaped hypersonic aero vehicle (a rocket or a supersonic aircraft), combined multiple long and narrow plates which cover the obelisk shaped hypersonic aero vehicle, multiple roller bearings which are arranged across the multiple long and narrow plates and are spaced in a short distance.

2. The system, as recited in claim 1, wherein an included angle of a head of the hypersonic aero vehicle is less than 20?.

3. The system, as recited in claim 1, wherein inside the roller bearings is a hollow tube inside which bearings are embedded on a left, a middle and a right; an axis rod extends across the bearings; two ends of the axis rod are fixed on upper edges of two sides of the long and narrow plates.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0009] FIG. 1 is a perspective view of an outlook of a head in a regular pyramid shape and a body in a cuboid shape of an intercontinental rocket (a cross section is in a rectangular shape);

[0010] FIG. 2 is a side view of a long and narrow plate with roller bearings and a perspective view of streamlines across a surface of the roller bearings;

[0011] FIG. 3 is a top view of the long and narrow plate with roller bearings from right above.

[0012] Element numbers: 1. head of a rocket in a regular pyramid shape; 2. side view of a body of the rocket in a cuboid shape; 3. long and narrow plate; 4. roller bearing; 5. bearing; 6 roller bearing; 7. bottom of the plate; 8. up edge of the plate; 9. streamline across above the roller bearings; 10. airstream suction above from the bottom of the plate; 11. axis rod.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

[0013] Referring to FIG. 1 of the drawings, according to a preferred embodiment of the present invention is illustrated, wherein a head of the rocket is in a regular pyramid shape, an included angle of which is less than 20? . Combined multiple narrow and long plates are covered on a flat a side view of which is a rectangle on a body of the rocket. Multiple roller bearings 4 are arranged across each of the long and narrow plates. Inside the roller bearings 4 is a hollow tube inside which bearings 5 are embedded; wherein an axis rod 11 extends across the bearings; two ends of the axis rod are fixed below the upper edges 8 of two sides of the long and narrow plates. The streamline of the high-speed rotating roller bearing (the coefficient of friction is 0.002) runs across the roller bearings with a flow speed of the layer as an upper part in the typical Karman Vortex Artier picture, which dose not sink below the roller bearing while the air flow of the bottom of the plate is static. The pressure of the air flow of the bottom of the plate is much higher than the high speed air flow on the top. Based on Bemoueeo theorem, the air flow of the bottom of the plate is suctioned and taken away by the air flow on the top and a rough vacuum is formed. The rough vacuum guarantees an undisturbed clockwise rotation of the roller bearings. When the speed of the rocket is higher than Ma 20 the temperature of the surface of the rocket is around 27? C. due to the coefficient of friction of the bearing is 0.002. Sliding friction still exist at the edges of the plate, which accounts for around 3% percent of the whole area. The heat generated by the sliding friction is conducted to the surface of the roller bearing and dispersed to the air according to the thermal conductivity of the metal. The temperature is reduced, the energy consumption is saved and the speed is increased.

[0014] Long distance launch may adopts another invention Propulsion enhancement arrangement for rocket (U.S. Pat. No. 7,814,835B2) which is able to assist the launch speed to reach Ma 40.

[0015] The present invention requires no complex techniques other than firmly fixation with high accuracy. The production cost is low and the techniques required are simple. The production is able to be carried out in medium factories.