ROCKET BRAKED BY AIR RECOVERED BY TURBINES AND DECELERATION METHOD FOR RECOVERY OF SAME

Abstract

The present disclosure discloses a rocket braked by air recovered by turbines and a deceleration method for recovery of the same. The rocket includes a first-stage rocket and a second-stage rocket, where the first-stage rocket includes a first-stage rocket fuselage sequentially provided with a movable baffle, an oxidizer chamber, a fuel chamber, a combustion chamber, and an ejection opening from top to bottom; after the first-stage rocket is separated from the second-stage rocket, the movable baffle of the first-stage rocket is opened to generate resistance for deceleration and adjustment on a descending posture; an air inlet in a turbine is exposed at the same time, and the turbine is turned on; and after a flameout of an engine, stored compressed air is downwards ejected from the bottom of the first-stage rocket to generate thrust for deceleration, so as to achieve safe landing of the rocket.

Claims

1. A rocket braked by air recovered by turbines, comprising a first-stage rocket and a second-stage rocket, wherein the first-stage rocket comprises a first-stage rocket fuselage (1) sequentially provided with movable baffles (2), an oxidizer chamber (3), a fuel chamber (4), a combustion chamber (5), and an ejection opening (6) from top to bottom; the movable baffles (2) are movably hinged with an upper end of the first-stage rocket fuselage (1) and are driven to be opened by hydraulic cylinders (7); turbines (8) are arranged in the first-stage rocket fuselage (1) and on internal walls of the movable baffles (2); and compressed air is delivered, by the turbines (8), into the first-stage rocket fuselage (1) for storage and is downwards ejected via the ejection opening (6) when the rocket descends to be close to the ground.

2. The rocket braked by air recovered by turbines according to claim 1, wherein troughs for mounting the turbines (8) are formed in the first-stage rocket fuselage (1) and have upper edges hinged with upper ends of the movable baffles (2); each said hydraulic cylinder (7) has one end hinged with a top of the corresponding trough and the other end hinged with the corresponding movable baffle (2); and the turbines (8) are arranged on the internal walls of the movable baffles (2).

3. The rocket braked by air recovered by turbines according to claim 1, wherein an oxidizer is located below a piston separator (9) in the oxidizer chamber (3), and fuel is located below a piston separator (9) in the fuel chamber (4); the turbines (8) are communicated, via air tubes, with a space above the piston separator (9) in the oxidizer chamber (3) as well as a space above the piston separator (9) in the fuel chamber (4), so as to fulfill storage of the compressed air; and the air tubes are provided with check valves for guiding the compressed air generated during operation of the turbines into the oxidizer chamber and the fuel chamber.

4. The rocket braked by air recovered by turbines according to claim 3, wherein the space storing the compressed air in the oxidizer chamber (3) as well as the space storing the compressed air in the fuel chamber (4) is communicated with the ejection opening (6) via an air outlet tube; valves in the air outlet tubes are controlled to be opened and closed by a sensor in the first-stage rocket fuselage (1); the sensor sends a signal to open the valves when detecting that the rocket is about to reach the ground; and in this way, the compressed air is ejected via the ejection opening (6) to achieve deceleration, thus achieving safe landing of the rocket for recovery.

5. The rocket braked by air recovered by turbines according to claim 1, wherein four turbines (8) and four movable baffles (2) corresponding to the turbines (8) are uniformly arranged outside the first-stage rocket fuselage (1).

6. A deceleration method for recovery of a rocket braked by air recovered by turbines, comprising: separating a first-stage rocket from a second-stage rocket, and then opening a movable baffle (1) of the first-stage rocket to generate resistance for deceleration and adjustment on a descending posture, wherein an air inlet in a turbine (8) is exposed at the same time; turning on the turbine (8); driving an engine by means of residual fuel to achieve the deceleration in an initial stage; and after a flameout of the engine, downwards ejecting stored compressed air from a bottom of the first-stage rocket to generate thrust for deceleration, so as to achieve safe landing of the rocket.

7. The deceleration method for recovery of the rocket braked by air recovered by turbines according to claim 6, particularly comprising: step a, separating the first-stage rocket from the second-stage rocket, and then opening a movable baffle (2) of the first-stage rocket to generate the resistance for the deceleration and the adjustment on the descending posture; step b, turning on the turbine (8) to generate the compressed air and then deliver the compressed air, via an air tube, into a space above a piston separator (9) in an oxidizer chamber (3) as well as a space above a piston separator (9) in a fuel chamber (4); and step c, driving the engine by means of the residual fuel to achieve the deceleration in the initial stage; and after the flameout of the engine, when a sensor detects that the rocket is about to reach the ground, opening a valve between the oxidizer chamber and an ejection opening as well as the fuel chamber and the ejection opening to make the compressed air be downwards ejected via the ejection opening from the bottom of the first-stage rocket, so as to generate the thrust for the deceleration, thus achieving safe landing of the rocket.

Description

BRIEF DESCRIPTION OF DRAWINGS

[0022] FIG. 1 is a sectional front view of a first-stage rocket of the present disclosure;

[0023] FIG. 2 is a schematic diagram showing a separation state of the first-stage rocket and a second-stage rocket of the present disclosure;

[0024] FIG. 3 is a schematic diagram of a turbine set, in an unfolded state, of the present disclosure; and

[0025] FIG. 4 is a schematic diagram of a mounting structure of a turbine of the present disclosure.

[0026] In the figure, 1. first-stage rocket fuselage; 2. movable baffle, 3. oxidizer chamber, 4. fuel chamber, 5. combustion chamber, 6. ejection opening, 7. hydraulic cylinder, 8. turbine, 9. piston separator.

DETAILED DESCRIPTION

[0027] The present disclosure is further described in detail below with reference to the following embodiments.

[0028] As shown in FIG. 1, a rocket braked by air recovered by turbines includes a first-stage rocket and a second-stage rocket, where the first-stage rocket includes a first-stage rocket fuselage 1 sequentially provided with movable baffles 2, an oxidizer chamber 3, a fuel chamber 4, a combustion chamber 5, and an ejection opening 6 from top to bottom; the movable baffles 2 are movably hinged with the upper end of the first-stage rocket fuselage 1 and are driven to be opened by hydraulic cylinders 7; turbines 8 are arranged in the first-stage rocket fuselage 1 and on internal walls of the movable baffles 2, and four turbines 8 and four movable baffles 2 corresponding to the turbines 8 are uniformly arranged outside the first-stage rocket fuselage 1; and compressed air is delivered, by the turbines 8, into the first-stage rocket fuselage 1 for storage and is downwards ejected via the ejection opening 6 when the rocket descends to be close to the ground.

[0029] Particularly, troughs for mounting the turbines 8 are formed in a side wall of the upper end of the first-stage rocket fuselage 1 and have upper edges hinged with upper ends of the movable baffles 2; each hydraulic cylinder 7 has one end hinged with the top of the corresponding trough and the other end hinged with the corresponding movable baffle 2; and the turbines 8 are arranged on the internal walls of the movable baffles 2; and

[0030] An oxidizer is located below a piston separator 9 in the oxidizer chamber 3, and fuel is located below a piston separator 9 in the fuel chamber 4; the turbines 8 are communicated, via air tubes, with a space above the piston separator 9 in the oxidizer chamber 3 as well as a space above the piston separator 9 in the fuel chamber 4, so as to fulfill storage of the compressed air; the air tubes are provided with check valves for guiding the compressed air generated during operation of the turbines into the oxidizer chamber and the fuel chamber; the space storing the compressed air in the oxidizer chamber 3 as well as the space storing the compressed air in the fuel chamber 4 is communicated with the ejection opening 6 via an air outlet tube; valves are arranged in the air outlet tubes respectively between the oxidizer chamber 3 and the ejection opening 6 and between the fuel chamber 4 and the ejection opening 6, and are controlled to be opened and closed by a height sensor in the first-stage rocket fuselage 1; the sensor sends a signal to open the valves when detecting that the rocket is about to reach the ground; and in this way, the compressed air is ejected via the ejection opening 6 to achieve deceleration, thus achieving safe landing of the rocket for recovery.

[0031] A deceleration method for recovery of a rocket braked by air recovered by turbines particularly includes:

[0032] Step a, separate a first-stage rocket from a second-stage rocket, and then opening a movable baffle 2 of the first-stage rocket to generate resistance for deceleration and adjustment on a descending posture;

[0033] Step b, turn on a turbine 8 to generate compressed air and then deliver the compressed air, via an air tube, into a space above a piston separator 9 in an oxidizer chamber 3 as well as a space above a piston separator 9 in a fuel chamber 4; and

[0034] Step c, drive an engine by means of residual fuel to achieve the deceleration in an initial stage; and after a flameout of the engine, when a sensor detects that the rocket is about to reach the ground, open valves respectively between the oxidizer chamber and ejection opening and between the fuel chamber and the ejection opening to make the compressed air be downwards ejected via the ejection opening from the bottom of the first-stage rocket, so as to generate thrust for deceleration, thus achieving safe landing of the rocket.

[0035] According to the present disclosure, the compressed air is obtained by the turbines by means of kinetic energy in a recovery process; in this way, energy recycling as well as reductions of hydrogen consumption and oxygen consumption is achieved; and safe landing is achieved, so that the risk of explosion is lowered fundamentally.