Conical top cover pull type recycling sub-orbital carrier rocket

A launch vehicle and sub-orbital technology, applied in the field of aerospace rockets, can solve the problems of difficulty in recovery, uncontrollable landing point, failure to achieve recovery, etc., and achieve the effect of reducing construction costs, reducing the number of configurations, and reducing supporting costs

Inactive Publication Date: 2022-07-12
精易兴航(北京)科技创新有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It is conceivable that the landing point of the parachute method is uncontrollable, recovery is still difficult, and the required offshore platforms also require high costs
[0005] At present, domestic launch vehicles have not achieved engineering recovery, and the launch cost of the rocket is higher than that of SpaceX.

Method used

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  • Conical top cover pull type recycling sub-orbital carrier rocket
  • Conical top cover pull type recycling sub-orbital carrier rocket
  • Conical top cover pull type recycling sub-orbital carrier rocket

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0058] Example 1: Two fixed "non-swing tube" recovery power engine solutions:

[0059]Two recovery power engines 661 are fixedly installed on the outer side of the shell section 612 of the cone-top cover 61. The thrust of the recovery power engines 661 is preferably 10t. The recovery power engine 661 and its engine nozzle 662 do not swing, providing rocket boost, recovery power and attitude control thrust; the rocket separation force is symmetrically installed on the outer edge of the bottom of the first-stage rocket body 1. Push rocket provided. Its working mechanism: (1) Recover power attitude control function: set the engine with an angle of 30° to the rocket body and control the rocket pitch attitude by adjusting the thrust of the two engines (by installing a simple "pneumatic attitude control system" to control the rocket yaw and roll attitude). (2) Recovery power thrust function: During the ascent of the rocket, the recovery power engine 661 starts to provide forward t...

Embodiment 2

[0060] Example 2: Two "circumferential pendulum" recovery power engines scheme:

[0061] Two unidirectional swing (circumferential) recovery power engines 661 are installed on the outer side of the shell section 612 of the conical top cover 61. The thrust of the recovery power engines 661 is preferably 10t. Recovery power and attitude control thrust; rocket separation force is provided by two reverse thrust rockets symmetrically installed on the outer edge of the bottom of the first-stage rocket body 1. Among them, "circumferential" is relative to the overall columnar launch vehicle, which refers to, please refer to Figure 2B , the engine nozzle 662 can rotate in the direction perpendicular to the plane of the drawing with the swing mechanism 663 as the axis. Its working mechanism: (1) Recovery power attitude control function: the recovery power engine yaw in the same direction to control the pitch attitude, and the opposite direction yaw to control the roll attitude; set th...

Embodiment 3

[0062] Example 3: Two "radial pendulum" recovery power engines scheme:

[0063] Two unidirectional swing (radial) recovery power engines 661 are installed outside the shell section 612 of the cone dome 61. The recovery power engines 661 preferably have a thrust of 10t to provide rocket boost, recovery power and attitude control thrust. Among them, "radial" is relative to the overall cylindrical launch vehicle, which refers to, please refer to Figure 2B and Figure 2C , the engine nozzle 662 can be rotated in the drawing plane with the oscillating mechanism 663 as the axis, for example, from Figure 2B Turn to Figure 2C The state is inclined upward. Its working mechanism: (1) The recovery power attitude control function: the recovery power engine 661 yaw in the same direction to control the pitch attitude, and the recovery power engine 661, which is at an angle of 30° to the arrow body, can also control the pitch attitude by adjusting the thrust (attitude control system). ...

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Abstract

The invention discloses a cone top cover pull type recovery sub-orbital carrier rocket, which belongs to the technical field of spaceflight rockets, and comprises a primary rocket body, a cone top cover arranged at the upper end of the primary rocket body, and a recovery power device, a load is accommodated in the cone top cover; the power recovery device at least comprises a power recovery engine and a power recovery cover arranged on the outer side of the power recovery engine, an engine jet pipe is arranged on the power recovery engine, and the orientation of the engine jet pipe is fixedly arranged or can be adjusted to be downward or outward obliquely downward; the two recovery power devices are symmetrically arranged on the outer side face of the upper portion of the first-stage rocket body or the outer side face of the cone top cover on the two sides. According to the cone top cover pull type recovery suborbital carrier rocket, the technical problems that in the prior art, a landing point is uncontrollable and recovery is difficult are solved, the test environment of ground launching, flight and suborbital flight can be provided, and an environment test in a real state and test services of the environment test can be provided for research and development of aerospace products.

Description

technical field [0001] The invention belongs to the technical field of aerospace rockets, and in particular relates to a cone-top cover pull-type recovery suborbital carrier rocket. Background technique [0002] With the continuous development of the aerospace field at home and abroad, how to reduce the cost of space launch has gradually become one of the main challenges faced by the entire aerospace industry. The development of commercial aerospace has put forward higher requirements for low-cost launch and low-cost rockets, especially for some The low-altitude and high-speed flight test launch, and the recovery and reuse of the carrier and its payload are important measures to reduce costs. Since the middle of the last century, the world's aerospace powers have continued to carry out research and experiments on reusable space transportation systems. [0003] The general two-stage launch vehicle and its separation state during flight are as follows: 1A to 1D shown. The r...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64B64G1/62B64G1/40
CPCB64G1/645B64G1/62B64G1/40
Inventor 隋国发
Owner 精易兴航(北京)科技创新有限公司
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