Rocket engine three-view PD-3S manned rocket front propeller and manufacturing process thereof

Abstract

The invention relates to the technical field of manned rockets, in particular to a front propeller of a rocket engine three-view PD-3S manned rocket and a manufacturing process of the front propeller. The front propeller is designed and installed at the head of the manned rocket, so that the position, posture, speed and accelerated speed of the rocket in the flying process can be sensed, accumulated errors of an inertial navigation system are corrected, and the precision of the manned rocket is improved. By arranging the power generation device, the energy loss is reduced, mechanical support is provided, the dynamic stability of the rocket is improved, and the orbit operation capability of the manned rocket is guaranteed, so that the power generation device is suitable for popularization and application. The technical problems that an existing manned rocket can generate a passive rotation phenomenon under the action of natural force such as airflow and gravitational force, and spinning generally does not greatly influence the flight of the rocket but can influence the flight stability of the rocket are solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of manned rockets, in particular to a rocket engine three-view PD-3S manned rocket front propeller and a manufacturing process thereof. BACKGROUND

[0002] The exploration of the universe by mankind and the strategic needs of various countries have promoted the rapid development of aerospace vehicles. With the continuous development of science and technology, manned rocket technology has made great breakthroughs. At present, manned rockets are usually used to transport astronauts to planetary orbits so that astronauts can reach space.

[0003] During the space flight of the manned rocket, the scene is different, and the force is different. In the gravitational field, the gravity generated by the earth on the rocket is continuous, and the gravity is the reason for the change or work done. The gravity is different from the elastic force, friction and electric field force. The gravity is power. Due to the action of natural forces such as air flow and gravity, the rocket will produce a passive rotation phenomenon. Self-rotation usually does not have too much impact on the flight of the rocket, but it has an impact on the stability of the rocket flight.

[0004] The installation of the front propeller at the head of the manned rocket can perceive the position, attitude, speed and acceleration of the rocket during flight, correct the accumulated error of the inertial navigation system, eliminate the adverse effects of passive rotation, and ensure the stability and accuracy of the rocket. SUMMARY

[0005] The purpose of the present application is to provide a rocket engine three-view PD-3S manned rocket front propeller and a manufacturing process thereof, which solves the technical problem that the existing manned rocket will produce a passive rotation phenomenon due to the action of natural forces such as air flow and gravity. Self-rotation usually does not have too much impact on the flight of the rocket, but it has an impact on the stability of the rocket flight.

[0006] To achieve the above-mentioned purpose, the present application provides a rocket engine three-view PD-3S manned rocket front propeller, which comprises a stabilizer wing surface, and further comprises an inertial measurement device, a navigation system, a power generation device and a damper. The inertial measurement device is used to measure the angular velocity and acceleration of the manned rocket and to calculate the state of the manned rocket. The navigation system is connected with the inertial measurement device and is used to stabilize the signal received in the navigation process. The power generation device is connected with the navigation system and is used to convert the wind resistance kinetic energy generated by the rotation of the propeller during the flight of the rocket into electric energy to power the navigation system. At the same time, the power generation device provides equivalent kinetic energy to the rocket to offset the gravitational resistance of the rocket during flight. The damper is connected with the navigation system and is used to change the speed and direction of the stabilizer wing surface.

[0007] The number of the stabilizing wings is four, and the four stabilizing wings adopt a double spiral structure, two installation angles deflect in the same direction, and the other two installation angles deflect in the opposite direction.

[0008] The navigation system comprises a navigation receiver and a navigation antenna, and one navigation antenna is arranged on each stabilizing wing.

[0009] The power generation device comprises a generator and a power generation damping control slip ring, and the generator and the power generation damping control slip ring are used in cooperation.

[0010] The rocket engine three-view PD-3S manned rocket front propeller further comprises a protective cover, and the protective cover is used for exposing or closing the manned rocket front propeller.

[0011] The rocket engine three-view PD-3S manned rocket front propeller further comprises a geomagnetic module and a self-destruction device, the geomagnetic module is connected with the navigation system and is used for enhancing the anti-magnetic interference performance of the manned rocket, and the self-destruction device is connected with the inertial measurement device and the navigation system respectively and is used for starting the self-explosion of the manned rocket.

[0012] The application further provides a manufacturing process of the rocket engine three-view PD-3S manned rocket front propeller.

[0013] Titanium alloy composite materials or carbon fiber composite materials with high strength and light material are processed into composite plates.

[0014] The composite plates are cut into blade-shaped blanks, and the obtained four blanks are heated.

[0015] After being heated to a certain temperature, the four blanks are processed in a double spiral structure, two installation angles deflect in the same direction, and the other two installation angles deflect in the opposite direction.

[0016] A silicon nitride coating is sprayed on the surface of the processed blank to obtain the required stabilizing wing.

[0017] A navigation antenna is additionally arranged on each stabilizing wing, the navigation antenna is connected with a navigation receiver, and the navigation receiver is installed in a shell.

[0018] An inertial measurement device, a generator, a power generation damping control slip ring, a damper, a geomagnetic module and a self-destruction device are all installed in the shell.

[0019] The protective cover is used to cover the shell and the stabilizing wing, and the manufacturing of the manned rocket front propeller is completed.

[0020] The rocket engine three-view PD-3S manned rocket front propeller and manufacturing process of the present application, the present application can perceive the position, attitude, speed and acceleration of the rocket during flight by designing and installing the front propeller at the head of the manned rocket, correct the accumulated error of the inertial navigation system, eliminate the adverse effects of passive rotation, ensure the stability and precision of the rocket, by setting the power generation device, thereby reducing energy loss, providing mechanical support, improving the dynamic stability of the rocket, and ensuring the orbit operation capability of the manned rocket, therefore, the technical problem of the existing manned rocket being passively rotated due to the action of air flow, gravity and other natural forces is solved, and the self-rotation usually does not have too much influence on the flight of the rocket, but has influence on the stability of the rocket flight. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or prior art description will be briefly introduced as follows.

[0022] Figure 1 is the control principle diagram of the rocket engine three-view PD-3S manned rocket front propeller of the first embodiment of the present application.

[0023] Figure 2 is the flow step diagram of the manufacturing process of the rocket engine three-view PD-3S manned rocket front propeller of the second embodiment of the present application.

[0024] In the figure: 101-stabilizer surface, 102-inertial measurement device, 103-navigation system, 104-power generation device, 105-damper, 106-geomagnetic module, 107-self-destruction device, 108-navigation receiver, 109-navigation antenna, 110-generator, 111-generating damper control slip ring. DETAILED DESCRIPTION

[0025] The embodiments of the present application will be described in detail below, examples of the embodiments are shown in the drawings, the embodiments described below by referring to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation of the present application.

[0026] First embodiment:

[0027] Please refer to Figure 1 , wherein Figure 1This is a control principle diagram of the front propeller of the three-view Yao PD-3S manned rocket, according to the first embodiment of the present invention. The present invention provides a front propeller of the three-view Yao PD-3S manned rocket, including a stabilizing fin 101, an inertial measurement device 102, a navigation system 103, a power generation device 104, a damper 105, a protective cover, a geomagnetic module 106, and a self-destruct device 107. The navigation system 103 includes a navigation receiver 108 and a navigation antenna 109. The power generation device 104 includes a generator 110 and a generator damping control slip ring 111.

[0028] In this embodiment, the present invention, by designing and installing a front propeller at the nose of the manned rocket, can sense the position, attitude, speed, and acceleration of the rocket during flight, correct the accumulated errors of the inertial navigation system, eliminate the adverse effects of passive rotation, and ensure the stability and accuracy of the rocket. By setting the power generation device 104, energy loss is reduced, mechanical support is provided, the dynamic stability of the rocket is improved, and the orbital operation capability of the manned rocket is guaranteed. Therefore, it solves the technical problem that existing manned rockets will experience passive rotation due to the influence of natural forces such as airflow and gravity. While spin usually does not have a significant impact on the rocket's flight, it does affect the stability of the rocket's flight.

[0029] The inertial measurement unit 102 is used to measure the angular velocity and acceleration of the manned rocket and calculate its state. The navigation system 103 is connected to the inertial measurement unit 102 and is used to stably receive signals during navigation. The power generation unit 104 is connected to the navigation system 103 and is used to convert the wind resistance kinetic energy generated by the propeller rotation during rocket flight into electrical energy to power the navigation system 103 and provide equivalent kinetic energy to the rocket to counteract the gravitational drag during flight. The damper 105 is connected to the navigation system 103 and is used to change the rotational speed and direction of the stabilizing surface 101.

[0030] Secondly, there are four stabilizing surfaces 101. The four stabilizing surfaces 101 adopt a double-rotation structure, with two mounting angles deflecting in the same direction and the other two mounting angles deflecting in opposite directions. The stabilizing surfaces 101 are made of high-strength, lightweight titanium alloy or carbon fiber composite materials, and a silicon nitride coating is sprayed on the surface of the stabilizing surfaces 101.

[0031] Furthermore, each of the stabilizing surfaces 101 is equipped with a navigation antenna 109. The navigation receiver 108 and the navigation antenna 109 work together. The navigation system 103 uses a three-view geocentric coordinate system and adjusts the rocket's flight direction by adjusting the engine's jet direction through the Diya algorithm.

[0032] Meanwhile, the generator 110 and the power generation damping control slip ring 111 are used in cooperation.

[0033] In addition, the protective cover is used to expose or cover the manned rocket pre-positioned propeller, so that the manned rocket pre-positioned propeller can be covered in the protective cover when the rocket is not started, so that the manned rocket pre-positioned propeller can be protected, and the manned rocket pre-positioned propeller is exposed from the protective cover when the rocket is started, so as not to affect the normal work of the manned rocket pre-positioned propeller.

[0034] Finally, the geomagnetic module 106 is connected with the navigation system 103, and is used to enhance the anti-magnetic interference performance of the manned rocket; the self-destruction device 107 is connected with the inertial measurement device 102 and the navigation system 103 respectively, and is used to start the manned rocket explosion.

[0035] When the rocket engine three-view PD-3S manned rocket pre-positioned propeller is used, the pre-positioned propeller is designed and installed at the head of the manned rocket, so that the position, attitude, speed and acceleration of the rocket during flight can be perceived, the accumulated error of the inertial navigation system can be corrected, the adverse effects of passive rotation can be eliminated, the stability and precision of the rocket can be ensured, and the pre-positioned propeller is actually a set of components, which is composed of stabilizing wings 101, inertial measurement devices 102, navigation systems 103, power generation devices 104, dampers 105, protective covers, geomagnetic modules 106 and self-destruction devices 107.

[0036] By setting the propeller at the pre-positioned position of the rocket, the protective cover outside the propeller is ejected when the rocket is started, and the propeller is exposed so that the propeller can work normally.

[0037] During the flight of the rocket, the stabilizing wings 101 of the propeller will rotate, and are mechanically connected to the power generation damping control slip ring 111, at this time, the power generation damping control slip ring 111 is used in cooperation with the generator 110, the kinetic energy generated during the rotation of the stabilizing wings 101 is converted into electric energy, the navigation system 103 is powered, and at the same time, the rocket is provided with equivalent kinetic energy to offset the gravitational resistance of the rocket during flight, so that the energy-saving effect can be achieved.

[0038] The propeller takes into account the principle of aerodynamics during design, four stabilizing wings 101 adopt double-rotation structure, two installation angles are deflected in the same direction, and the other two installation angles are deflected in the opposite direction, the resistance is increased or decreased through the damper 105, so as to change the rotating speed and direction of the stabilizing wings 101, control the rotation of the stabilizing wings 101 to a specific position, and then control the attitude of the manned rocket and adjust the flight trajectory of the manned rocket at any time.

[0039] The propeller is internally provided with the navigation receiver 108, and one navigation antenna 109 is mounted on the surface of each stabilizing wing surface 101, the navigation receiver 108 is used in cooperation with the navigation antenna 109, so that the navigation signal can be stably received, and then the received navigation signal is decoded and analyzed, so that the rocket can be positioned and navigated.

[0040] The propeller is internally provided with the geomagnetic module 106 and the self-destruction device 107, the geomagnetic module 106 is arranged, so that the anti-magnetic interference performance of the manned rocket is enhanced, and the self-destruction device 107 is arranged, so that the self-destruction can be started in special cases.

[0041] The navigation system 103 in the propeller uses a three-view solar earth moon three-coordinate system, adjusts the navigation direction of the manned rocket by adjusting the jet direction of the engine through the Dijkstra algorithm, so that the navigation accuracy of the manned rocket is improved.

[0042] The stabilizing wing surface 101 of the propeller is made of high-strength, light-weight titanium alloy or carbon fiber composite material, and a silicon nitride coating is ion sprayed on the surface of the stabilizing wing surface 101, so that the front propeller of the manned rocket can withstand high and low temperatures and stably work in a high temperature difference environment.

[0043] In summary, the front propeller is designed and installed at the head of the manned rocket, so that the position, attitude, speed and acceleration of the rocket during flight can be perceived, the accumulated error of the inertial navigation system can be corrected, the adverse effects of passive rotation can be eliminated, the stability and accuracy of the rocket can be ensured, the power generation device 104 is arranged, so that energy loss is reduced, mechanical support is provided, dynamic stability of the rocket is improved, and orbit operation ability of the manned rocket is ensured, so that the technical problem that the existing manned rocket is affected by air flow, gravity and other natural forces, and passive rotation occurs is solved.

[0044] Second embodiment:

[0045] On the basis of the first embodiment, please refer to Figure 2 , Figure 2 is a process flow step diagram of the rocket engine three-view PD-3S manned rocket front propeller of the second embodiment of the present application, and the present application further provides a manufacturing process of the rocket engine three-view PD-3S manned rocket front propeller, which comprises the following steps:

[0046] S101, the high-strength, light-weight titanium alloy composite material or carbon fiber composite material is processed into a composite plate;

[0047] S102. Cut the composite board into leaf-shaped blanks and heat the four blanks obtained.

[0048] S103. After heating to a certain temperature, the four blanks are processed in a double-spinning structure, with two mounting angles deflected in the same direction and the other two mounting angles deflected in opposite directions.

[0049] S104. Spray a silicon nitride coating onto the surface of the processed blank to obtain the desired stabilizing airfoil 101;

[0050] S105. A navigation antenna 109 is machined on each of the stabilizing surfaces 101, the navigation antenna 109 is connected to the navigation receiver 108, and the navigation receiver 108 is installed in the housing;

[0051] S106. The inertial measurement unit 102, generator 110, generator damping control slip ring 111, damper 105, geomagnetic module 106 and self-destruct device 107 are all installed in the housing.

[0052] S107. Use a protective cover to cover the shell and the stabilizing fin 101 to complete the manufacturing of the manned rocket's front propeller.

[0053] When using the manufacturing process of the three-view Yao PD-3S manned rocket propeller of this embodiment, high-strength, lightweight titanium alloy composite material or carbon fiber composite material is processed into a composite plate. The composite plate is then cut into blade-shaped blanks, and the resulting four blanks are heated. After reaching a certain temperature, the four blanks are processed in a double-spin structure, with two mounting angles deflected in the same direction and the other two mounting angles deflected in opposite directions. After processing, a silicon nitride coating is ion-sprayed onto the surface of the blanks to obtain the desired stabilizing airfoil 101. Then, on each... A navigation antenna 109 is installed on the stabilizing surface 101, and the navigation antenna 109 is connected to the navigation receiver 108. The navigation receiver 108 is installed inside the housing of the front propeller. The inertial measurement device 102, the generator 110, the generator damping control slip ring 111, the damper 105, the geomagnetic module 106, and the self-destruct device 107 are all installed inside the housing of the front propeller. The protective cover is used to cover the housing and the stabilizing surface 101, thereby completing the manufacturing of the manned rocket's front propeller.

[0054] The above-disclosed embodiments are merely one or more preferred embodiments of this application and should not be construed as limiting the scope of this application. Those skilled in the art can understand that all or part of the processes for implementing the above embodiments and equivalent changes made in accordance with the claims of this application still fall within the scope of this application.

Claims

1. A rocket engine three-view PD-3S manned rocket front propeller comprising stabilizer wings, characterized in that, it further comprises an inertial measurement device for measuring the angular velocity and acceleration of the manned rocket and calculating the state of the manned rocket, a navigation system connected with the inertial measurement device for stabilizing the signals received in the navigation process, a power generation device connected with the navigation system for converting the wind resistance kinetic energy generated by the rotation of the propeller during the flight of the rocket into electrical energy to power the navigation system and at the same time provide equivalent kinetic energy to the rocket to offset the gravitational resistance of the rocket during flight, and a damper connected with the navigation system for changing the speed and direction of the stabilizer wings.

2. The rocket engine three-view PD-3S manned rocket front propeller according to claim 1, characterized in that, the number of stabilizer wings is four, and the four stabilizer wings adopt a double-rotation structure, with two installation angles deflecting in the same direction and the other two installation angles deflecting in the opposite direction.

3. The rocket engine three-view PD-3S manned rocket front propeller according to claim 2, characterized in that, the navigation system comprises a navigation receiver and a navigation antenna, and one navigation antenna is installed on each stabilizer wing, and the navigation receiver and the navigation antenna are used in cooperation.

4. The rocket engine three-view PD-3S manned rocket front propeller according to claim 1, characterized in that, the power generation device comprises a generator and a power generation damping control slip ring, and the generator and the power generation damping control slip ring are used in cooperation.

5. The rocket engine three-view PD-3S manned rocket front propeller according to claim 1, characterized in that, the rocket engine three-view PD-3S manned rocket front propeller further comprises a protective cover for exposing or enclosing the manned rocket front propeller.

6. The rocket engine three-view PD-3S manned rocket front propeller according to claim 1, characterized in that, the rocket engine three-view PD-3S manned rocket front propeller further comprises a geomagnetic module connected with the navigation system for enhancing the anti-magnetic interference performance of the manned rocket, and a self-destruction device connected with the inertial measurement device and the navigation system respectively for starting the self-destruction of the manned rocket.

7. A manufacturing process of a rocket engine three-view PD-3S manned rocket front propeller, applied to the rocket engine three-view PD-3S manned rocket front propeller in any one of claims 1 to 6, characterized in that, The steps include: processing titanium alloy composite materials or carbon fiber composite materials with high strength and light weight into composite plates; cutting the composite plates into blade-shaped blanks and heating the obtained four blanks; after heating to a certain temperature, processing the four blanks according to a double-rotation structure, with two installation angles deflecting in the same direction and the other two installation angles deflecting in the opposite direction; spraying a silicon nitride coating on the surface of the processed blanks to obtain the required stabilizer wings; installing a navigation antenna on each stabilizer wing, connecting the navigation antenna with a navigation receiver, and installing the navigation receiver in a housing; The inertial measurement device, the generator, the power generation damping control slip ring, the damper, the geomagnetic module and the self-destruction device are all installed in the shell; The shell and the stabilizer surface are covered with a protective cover, and the manufacturing of the manned rocket front propeller is completed.

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