JPH078833Y2 - Ducted Rocket - Google Patents

Description

[Detailed Description of the Invention] [Industrial field of application] The present invention relates to a ducted rocket with a variable thrust, particularly using a solid sustainer propellant.

[Prior Art] A ducted rocket is also called a ram rocket and is used as an oxidizer after being launched from an aircraft or after being accelerated to a speed at which sufficient ram pressure is obtained using booster propellant, for example, transonic speed. It will continue the Sustainer jet while taking in the outside air. For this reason, the ducted rocket has a gas generator for primary combustion of sustainer propellant to generate fuel gas and a duct for taking in external air, and the fuel gas is mixed with the external air taken in to perform secondary combustion. It has a ram burner.

A configuration of such a ducted rocket will be described with reference to FIG.

The rocket 1 is of the type that is launched from the ground, and is designed to be launched to a high altitude using the booster propellant described above and then to continue the Sustainer jet according to the flight pattern illustrated in FIG. That is, after the time t ₁ elapses after the launch, the propellant is burned down and the booster jet ends, and almost simultaneously, the rocket starts the sustainer jet with the sustainer propellant and is injected into the high altitude orbit Hh, and the cruise speed on this orbit. Fly with. Then, after a lapse of time t ₂ after the launch, this time the locus changes to a low altitude orbit Hl, and if this low altitude is required, it will fly toward the target while correcting the orbit.

Returning to FIG. 5, reference numeral 2 is a steering wing that controls injection into the track, transfer, correction, etc., and is driven by the servo mechanism 3. A ram combustor 5 is provided at the rear of the shell 4 of the rocket 1, and a gas generator 12 is provided at the front thereof.

The ram combustor 5 is a ram combustion chamber 6 formed inside the shell 4.
And a sustainer nozzle 7 attached to the rear end of the combustion chamber,
For example, four ducts 8 arranged around the shell 4 are provided. The rear end of each duct 8 opens into the ram combustion chamber and is directed forward. Initially, as shown by the chain double-dashed line, the opening is closed by the openable port cover 9, the ram combustion chamber 6 is loaded with the booster propellant 10, and the sustainer nozzle 7 is provided with the booster nozzle 11. It is detachably fitted.

The gas generator 12 is loaded with pillars of the main sustainer propellant 13 and auxiliary sustainer propellant 14 on the rear side and the front side, respectively, and these pillars are in close contact with each other to expose only the rear end surface 13a of the main sustainer propellant. I am allowed. And this rear end face 13a
A combustion chamber 16 is formed between the partition wall 15 and the partition wall 15, and an igniter 17 is disposed therein, and a nozzle 18 directed to the inside of the ram combustion chamber 6 is formed in the partition wall 15.

Sustainer propellants 13 and 14 are rubber-based fuels such as polybutadiene as a binder mixed with metallic fuel such as aluminum powder and oxidizer powder such as ammonium perchlorate.The oxidizer causes these fuel components to self-combust. It is mixed to such an extent. Therefore, when the rear end surface 13a is ignited by the igniter 17, the main sustainer propellant 13 and then the auxiliary sustainer propellant 14 are naturally (primarily burned) parallel to the rear end surface, respectively, and heat containing a large amount of unburned fuel. Generates gas (fuel gas). This gas generation amount W (Fig. 4)
Is expressed by W = ρ · r · A [kg / sec] (1). Here, ρ is the propellant density, r is the fuel speed, and A is the combustion area (= area of the rear end face 13a ... Constant). Then, the gas generation amount W ₂ of the secondary sustainer propellant 14 is defined as the main sustainer propellant.
Than the generation amount W ₁ of 13 sets the relationship between both the [rho · r to be large, and the main sustainer propellant 13 from the time t ₁
The relationship between the burn speed and the length of the drug column is set so that it will be burned down exactly during t ₂ .

The control device 19 has a built-in sequencer using a timer or the like, and the servo mechanism 3 based on the pre-program of the rocket.
Steering instruction to igniter 17, ignition instruction to igniter 17, port cover 9
And an instruction to remove the booster nozzle 11 are issued.

Therefore, when the booster propellant 10 is ignited on the launch pad and the rocket 1 is launched, the rocket 1 is accelerated to the transonic speed and reaches a high altitude to burn out the booster propellant. Here, the booster nozzle 11 is disengaged, and immediately after that, when the time t ₁ has elapsed, the port cover 9 is opened and the igniter 17 is operated. As a result, the outside air is pushed into the duct 8 and is taken into the ram combustion chamber 6, and fuel gas is generated from the main sustainer propellant 13, which is injected into the combustion chamber 6 through the nozzle 18 and is taken in as described above. Secondary combustion is performed by mixing with outside air. Around this time, the rocket 1 is thrown into the high altitude orbit Hh, and the high temperature combustion gas due to the secondary combustion is ejected from the sustainer nozzle 7 to efficiently cruise in the lean outside air of the orbit Hh. After that, when time t ₂ elapses and the locus is transferred to the low altitude orbit Hl, the main sustainer propellant 13 is burned down almost at the same time, and the sub-sustainer propellant 14 starts primary combustion this time. As a result, the amount of fuel gas generated is increased and the thrust is increased, so that the rocket continues the sustainer jet while countering the low-altitude aerodynamic drag.

As a means for increasing the fuel gas by the auxiliary sustainer propellant 14, the product of the density ρ and the fuel speed r is set as described above, or in parallel with this, for example, the propellant 14 has an inner hole 14a. In some cases, the combustion area A can be increased by forming the.

[Problems to be solved by the invention]

By the way, the ducted rocket using such a solid sustainer propellant has an advantage that its main structure is extremely simple, but has a drawback that it is difficult to arbitrarily change the flight pattern.

In the conventional case, since the burning time of the main sustainer propellant was set according to the transition time to the low altitude orbit, for example, if it is attempted to accelerate this transition time according to the situation, at this time the sub-sustainer propulsion Since the fuel gas is not increased by the medicine, the rocket stalls with insufficient thrust,
Alternatively, since the amount of increase in the amount of gas generated due to the adjustment of the propellant density, fuel speed, combustion area, etc. is naturally limited, even if the low altitude orbit is corrected to a lower position, the thrust corresponding to this This is because the expansion is not easy and the flight pattern of the rocket cannot be largely separated from the preprogram for these reasons.

Therefore, an object of the present invention is to make it possible to obtain a thrust characteristic corresponding to the flight pattern even if the flight pattern is changed.

[Means for solving problems]

Means of the present invention for solving this problem are thrust control means for issuing thrust augmentation instruction according to the flight pattern set for the ducted rocket, and storing auxiliary fuel source and responding to the thrust augmentation instruction. A fuel supplement means for supplementing the auxiliary fuel to the ram combustor is provided.

[Operation] According to this means, the thrust control means gives an instruction for augmentation when thrust augmentation is required according to the flight pattern.
Even if the flight pattern is changed, the instruction is issued at an appropriate time according to the change. On the other hand, the rocket is equipped with a fuel supplement means in addition to the original gas generator, and this means supplements supplementary fuel to the fuel gas generated by the sustainer propellant in response to the thrust augmentation instruction. Can be performed easily and in a timely manner.

[Embodiment 1] An embodiment of the present invention will be described with reference to FIG.

This ducted rocket 20 is of a type that is launched from the ground as in the case of FIG. 5, in which the shell 21 of the rocket 20 has partition walls 22, 23 and 24 in order from the rear inside thereof. A ram combustor 25 is formed behind 22. This ram combustor has a sustainer nozzle 26 and four ducts 27 in the same manner as the conventional one, and the rear ends of these ducts open toward the front of the ram combustion chamber 28, and the air intake 29 is there. Is formed. Initially these air intakes are blocked by the port cover, and the ram combustor 28 is loaded with the booster propellant and the sustainer nozzle 26
The booster nozzle is detachably attached to the device, but these initial components are omitted in the drawing.

The gas generator 30 is an end-combustion type sustainer propellant 31 loaded with only the rear end face exposed in the section between the partition walls 24 and 23.
And a combustion chamber 32 formed between the rear end surface 31a and the partition wall 23.
An igniter 33 arranged in the combustion chamber, and a gas duct 34 fixed to the central portion of the partition wall 23 and extended to the vicinity of the partition wall 22.
And a main nozzle 35 formed at the rear end of this gas duct and directed to the ram combustion chamber 28. Sustainer propellant 31 is a composite system of excessive fuel content as described above, and is entirely formed of one drug species. Therefore, when the igniter 33 is ignited and the rear end surface 31a of the sustainer propellant 31 is ignited, a fixed amount of fuel gas is always generated from the propellant 31, which passes through the gas duct 34 into the ram combustion chamber 28 from the main nozzle 35. It is ejected and mixed there with the outside air taken in from the duct 27 for secondary combustion. Therefore, the rocket 20 continues the thrusting of the sustainer while maintaining a constant thrust.

The fuel supplementing means of this embodiment is constituted by the auxiliary gas generator 40. The auxiliary gas generator 40 stores an excessive fuel composite auxiliary sustainer propellant 41 as an auxiliary fuel source, and the propellant 41 is formed into a thick-walled tubular shape, and the gas duct 34, the partition wall 23 and the shell It is loaded in the space surrounded by 21, and its rear end face 41a is exposed. Reference numeral 42 is a heat-resistant insulator interposed between the inner surface of the propellant and the gas duct 34. In addition to the shell 21, the heat-resistant insulators are each partition wall.
It is also attached to 22,23,24, but the illustration is omitted to avoid complication. The auxiliary gas generator 40 is also the rear end face mentioned above.
A combustion chamber 43 formed between the partition wall 41a and the partition wall 22, an igniter 44 disposed in the combustion chamber 43 for igniting the rear end surface 41a, and a sub-nozzle 45 formed in the central portion of the partition wall 22. The nozzle 45 surrounds the main nozzle 35 and opens in front of the outside air inlet 29. Therefore, when the rear end surface 41a of the secondary sustainer propellant 41 is ignited, a fuel gas containing a large amount of unburned fuel is generated and ejected from the secondary nozzle 45, which serves as auxiliary fuel in the ram combustion chamber 28.
Is supplemented to. Then, the supplementary amount of the auxiliary fuel, and thus the gas generation amount of the auxiliary sustainer propellant 41, is set based on the formula (1) so that necessary thrust augmentation can be performed in each altitude region of the planned low altitude orbit, Further, the medicine length L of the propellant 41 is set so that the above-mentioned fuel supplement is performed over the entire planned orbit.

Reference numeral 46 is a steering wing, 47 is a servo mechanism for controlling the steering, and reference numerals 48 and 49 are cable tunnels for accommodating cables for transmitting an ignition instruction signal to the igniters 33 and 44, respectively.

On the other hand, a control room is formed on the front side of the partition wall 24 and the control device is installed here.
Install 50. As shown in FIG. 2, the control device 50 includes a sequencer 51 for instructing a series of operations such as removal of the booster nozzle, opening of the port cover, and operation of the gas generator 30 in the same manner as in the conventional case, and the following configuration. Provide. The flight pattern setter 52 sets the flight pattern as shown in FIG. 6 based on its operation program before the launch of the rocket 20. Then, when the ignition instruction signal is sent from the sequencer 51 to the igniter 33 of the gas generator 30, and the rocket 20 starts the sustainer jet with a constant thrust as described above, the flight pattern setter 52 inputs the signal. Further, while inputting an altitude signal from the altitude sensor 53, a steering instruction is given to the steering control unit 54 in order to put the rocket into a set high altitude orbit. The steering control unit 54 guides the rocket to a high altitude orbit while controlling the steering blades 46 via the servo mechanism 47 in accordance with the steering instruction, and then makes a cruise flight along the orbit. Further, the flight pattern setter 52 measures the elapsed time from the time when the ignition instruction signal is input or when the predetermined high altitude is reached, and calculates the cruising distance while inputting the flight speed signal from the speed sensor 55. Then, when this distance reaches a set value, a steering instruction is given to the steering control unit 54 to transfer the rocket to a low altitude orbit. And altitude sensor
When the detected altitude of 53 has dropped to the set value, the operation signal S1 is transmitted to the thrust control unit 56. The thrust control unit 56 of this embodiment is constituted by a switching means interposed in the ignition circuit of the igniter 44 in the auxiliary gas generator 40, and the means is closed when receiving the operation signal S1 and used as a thrust augmentation instruction. The ignition instruction signal S2 is transmitted. Therefore, the igniter 44 ignites in response to the signal S2 and ignites the rear end surface 41a of the auxiliary sustainer propellant 41. Here, the propellant 41 starts primary combustion to generate a fixed amount of auxiliary fuel gas, which is ejected from the auxiliary nozzle 45 and supplemented to the fuel gas from the main nozzle 35. As a result, the thrust is augmented and the rocket ejects while countering the aerodynamic drag in the low altitude orbit. When the steering control unit 54 receives the target position signal S3 from the target search means or the like, the steering control unit 54 also has a function of correcting the instructed trajectory.

[Second Embodiment] A second embodiment of the present invention will be described with reference to FIG.

This ground-launched ducted rocket 60 has bulkheads 62 and 63 in the rear of the hull 61 and in front of it, respectively.
A ram combustor 65 behind the partition wall 62, and also with the partition wall 62.
The gas generators 70 and 63 are respectively constructed between them.

The ram combustor 65 has a ram combustion chamber 66, four ducts 67, an outside air intake 68 and a sustainer nozzle 69 in the same manner as that of the first embodiment, and initially, the port cover, booster propellant, It has a booster nozzle. Gas generator 70
In the same manner as in Example 1, the end face combustion type sustainer propellant 71, the combustion chamber 72, and the igniter 73 are provided.
A nozzle 74 is formed at the center of 62.

The fuel supplementing means of this embodiment is constituted by four fuel injectors 75 housed in the cowling 64 following each duct 67, and each stores, for example, a hydrocarbon liquid fuel 76 as an auxiliary fuel source. That is, each fuel injector 75 is a cylinder 77, a piston 78 fitted therein, a gas cylinder 79 filled with high-pressure gas, and a pulse-responsive normally-closed solenoid valve 80 mounted on the outlet side of the cylinder 77, for example. A spray nozzle 81 that goes from this solenoid valve into the ram combustion chamber 66
Liquid fuel 76 in the cylinder chamber defined by 77 and piston 78
And the high gas pressure of the gas cylinder 79 is applied thereto via the piston 78 to store the fuel 76 in a pressurized state. Therefore, when the solenoid valve 80 is opened, the spray nozzle 81
A mist of liquid fuel 76 is ejected from the liquefied fuel, which is supplied to the ram combustion chamber 66 as auxiliary fuel.

Reference numeral 82 is a steering wing, and 83 is a servo mechanism that controls the steering. The rocket 60 receives a command from a ground fire control unit by an antenna 84 and flies while setting a flight pattern according to this command.

Referring also to FIG. 4, the flight pattern setting unit 86 of the control device 85 comprises a pattern indicator 87, an altitude setting device 88, a distance setting device 89 and a speed setting device 90. Further, the timer 91 presets the booster jetting time to this, and when this time elapses after the firing, the time signal t ₁ is emitted and inputted to the pattern indicator 87. Then, when the rocket is on the launch pad or when the altitude and flight distance of the high altitude orbit are commanded from the shooting control unit during the booster jet, the pattern indicator 87 receives this command from the antenna 84 and stores it. Then, when the time signal t ₁ from the timer 91 is inputted, the corresponding setters 88 and 89 are instructed to set the commanded altitude and flight distance, respectively, and the booster nozzle is detached or the port cover An opening instruction is given, and at the same time as this, an ignition instruction signal is sent to the igniter 73 of the gas generator 70 to ignite the sustainer propellant 71. This causes the rocket to initiate a Sustainer jet. Immediately after this, the altitude setter 88 inputs the actual altitude signal from the altitude sensor 93 to give a difference from the set altitude to the steering control unit 92, and this steering control unit steers the steering wings 82 via the servo mechanism 83. While focusing on the set altitude. This causes the rocket to cruise in the commanded high altitude orbit. In addition, the distance setter 89
Inputs a cruising time signal from a clock 94 and an actual speed signal from a speed sensor 95 to calculate a cruising distance, and outputs a distance signal when this reaches a set distance.

On the other hand, if the altitude and flight speed of the low altitude orbit are commanded by the shooting control unit during this cruise period, the pattern indicator 87 stores these parameters and inputs the above distance signal and at the same time sets the altitude. The controller 88 is instructed to change the setting to a low altitude, and the speed setter 90 is instructed to set the command speed. As a result, the altitude setter 88 transfers the rocket to the commanded low altitude orbit in the same manner as when the altitude setter 88 enters the high altitude orbit. Further, the speed setter 90 inputs the actual speed signal from the speed sensor 95 and calculates the deviation between this and the set speed, and the thrust control unit 96 outputs a pulse signal S5 of a fixed cycle having a pulse width corresponding to this deviation. Output as thrust augmentation instruction. This pulse signal is transmitted to the pulse injector type normally closed solenoid valve of the fuel injector 75.
Enter 80. Therefore, the electromagnetic valve 80 is opened oscillatingly according to the pulse width, so that the liquid fuel 76 stored in the cylinder 77 under pressure is supplied from the spray nozzle 81 to the ram combustion chamber 66.
The fuel gas from the gas generator 70 is supplemented to the fuel gas. As a result, the thrust is augmented and the rocket 60 jets out against the aerodynamic resistance of the low altitude orbit, and this thrust is used as the flight speed so that the commanded speed can be obtained while returning from the speed sensor 95 to the speed setter 90. Control the amount of supplementary fuel.

In this embodiment, since liquid fuel is used as the auxiliary fuel source, it can be supplemented by a required amount at any time, which makes it possible to respond to flight pattern change commands not only at low altitude but also at high altitude orbits. . In this case the fuel injector
By constructing 75 together using an annular cylinder and piston, the annular fuel injector can be housed in the barrel in a manner similar to that of the auxiliary sustainer propellant 41 in FIG. However, there is an advantage that the total length of the rocket can be shortened by separately accommodating in the cowling 64 as in this embodiment, and accordingly, the auxiliary gas generator 40 of the first embodiment is also divided into a plurality of parts to form a cylinder. It may be arranged outside the cylinder.

[Effect of device]

As described above, according to the present invention, since the fuel supplement means is provided in addition to the gas generator loaded with the solid sustainer propellant, when the thrust becomes insufficient depending on the flight trajectory, the means is operated independently. The required thrust can be increased.

Therefore, the present invention can increase the degree of freedom in selecting and changing the flight pattern while taking advantage of the advantages of the ducted rocket mainly using solid propellant.

[Brief description of drawings]

FIG. 1 is a sectional view of the main part of the rocket showing an embodiment of the present invention, FIG. 2 is a block diagram showing the details of the essential parts of FIG. 1, and FIG. 3 is another embodiment of the present invention. Fig. 4 is a sectional view of the main part of the rocket shown in Fig. 4, Fig. 4 is a block diagram showing the details of the main part of Fig. 3, Fig. 5 is a sectional view of the main part illustrating a conventional ducted rocket, and Fig. 6 is a flight pattern. It is a diagram showing an example. 20,60 …… Ducted rocket 25,65 …… Ram burner 27,67 …… Duct 29,68 …… Outside air intake 30,70 …… Gas generator 31,71 …… Sustainer propellant 40,75 …… Fuel supplementing means 41,76 ...... Auxiliary fuel source 50,85 ...... Control device having flight pattern setting means and thrust control means

Claims (1)

[Scope of utility model registration request] 1. A gas generator for primary combustion of a sustainer propellant to generate a fuel gas, and a duct for taking in outside air, which is mixed with the above-mentioned fuel gas into the outside air to carry out secondary combustion. In addition to the ram combustor, the thrust control means for instructing thrust augmentation according to the flight pattern set for the rocket, the auxiliary fuel source are stored, and the auxiliary fuel is burned in the ram in response to the thrust augmentation instruction. Ducted rocket with fuel supplementary means to supplement the vessel.