CN205918517U - Big airborne solid rocket engine aircraft climb assisting unit - Google Patents
Big airborne solid rocket engine aircraft climb assisting unit Download PDFInfo
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- CN205918517U CN205918517U CN201620433529.7U CN201620433529U CN205918517U CN 205918517 U CN205918517 U CN 205918517U CN 201620433529 U CN201620433529 U CN 201620433529U CN 205918517 U CN205918517 U CN 205918517U
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Abstract
The utility model belongs to the technical field of take off, concretely relates to engine aircraft climb assisting unit. Big airborne solid rocket engine aircraft climb assisting unit (201), its technical scheme is: ignition control installs the head in solid rocket engine body (102) with come off separating mechanism (101), and the afterbody in solid rocket engine body (102) is installed in spray tube (103), and some firearm (104) is connected with ignition control and the separating mechanism that comes off (101), aircraft climb assisting unit (201) bilateral symmetry's carry is at the afterbody of big aircraft (202). The utility model discloses can provide short time high thrust helping hand in takeoff phase for big aircraft fast, shorten big aircraft and reach minimum take -off speed to shorten the take off distance.
Description
Technical field
This utility model belongs to takes off technical field and in particular to a kind of engine takeoff booster.
Background technology
Big aircraft, is often referred to large aerospace aircraft, such as military transportation airplane, civilian cargo aircraft etc., is characterized in loading capacity amount
Greatly, take-off weight is big, the distance that takes off of needs, and aircraft engine power output requires big.Generally, total matter of aircraft
Amount (deadweight and load-carrying sum) is bigger, and the distance of taking off of needs is longer, engine power require bigger it is desirable to minimum rapidly
Degree is about big.Some in particular cases, a kind of situation be big aircraft reach maximum fully loaded quality slightly or even exceed maximum fully loaded
Quality.For example in wartime, big aircraft needs to execute emergency transportation mission, is fully loaded with or exceeds nominal load capacity；One kind be and with fly
Machine runway cannot meet the shortest distance of taking off.For example ruined in wartime runway part, big aircraft need urgent transfer this two
In the case of kind, big aircraft just cannot take off or face very big risk.
Content of the invention
The purpose of this utility model is: for solving the deficiencies in the prior art, provides one kind can provide for big aircraft and takes off
The mechanism arrangement of boosting.
The technical solution of the utility model is: big aircraft solid propellant rocket JATO engine, and it includes: solid fire
Arrow engine body, lighter, IGNITION CONTROL and separating mechanism and the jet pipe of coming off；
IGNITION CONTROL is arranged on the head of solid propellant rocket body with the separating mechanism that comes off, and jet pipe is arranged on solid fire
The afterbody of arrow engine body, lighter connects IGNITION CONTROL and the separating mechanism that comes off；
The symmetrical carry of JATO engine is in the afterbody of big aircraft.
Beneficial effect: 1) this utility model quickly can provide short time high thrust power-assisted for big aircraft in takeoff phase,
Shorten big aircraft and reach minimum takeoff speed, thus shortening distance of taking off.
2) this utility model is easy for installation, and using flexible, booster is solid propellant rocket, can store for a long time.
Small volume simultaneously, can be saved in airport or carry at random, flexible and convenient to use.
Brief description
Fig. 1 is structural representation of the present utility model；
Fig. 2 is use schematic diagram of the present utility model.
Specific embodiment
Referring to accompanying drawing 1,2, big aircraft solid propellant rocket JATO engine 201, it includes: solid propellant rocket
Body 102, lighter 104, IGNITION CONTROL and separating mechanism 101 and the jet pipe 103 of coming off；
IGNITION CONTROL is arranged on the head of solid propellant rocket body 102 with the separating mechanism 101 that comes off, and jet pipe 103 is pacified
It is contained in the afterbody of solid propellant rocket body 102, lighter 104 connects IGNITION CONTROL and the separating mechanism 101 that comes off；
During use, according to the difference of required thrust, in some JATO engines 201 of big aircraft 202 afterbody carry, for keeping
Thrust symmetrical it is necessary to the paired carry in left and right, big aircraft 202 every pendant 3 pieces of winged boosters 201 of load shown in Fig. 2,6 pieces altogether.
Big aircraft 202 accelerates initially with self power, when reaching the specified peak power output of aircraft engine, starts
The lighter 104 of winged booster 201 is lighted a fire, and provides extra-push model for big aircraft 202；After big aircraft 202 takes off, booster
201 abandon solid propellant rocket body 102 by IGNITION CONTROL with the separating mechanism 101 that comes off.Due to without tire and ground
The frictional force in face, resistance suffered by big aircraft 202 reduces, and aircraft engine itself thrust just can drive aircraft to continue flight and climb
Rise.Thus reaching increase takeoff thrust, shorten the effect of distance of taking off.
This utility model is not disclosed technology and belongs to general knowledge as well known to those skilled in the art.
Claims (2)
1. with solid propellant rocket JATO engine (201), it includes big aircraft: solid propellant rocket body (102), point
Firearm (104), IGNITION CONTROL and the separating mechanism that comes off (101) and jet pipe (103)；
Described IGNITION CONTROL and the separating mechanism that comes off (101) are arranged on the head of described solid propellant rocket body (102), institute
State the afterbody that jet pipe (103) is arranged on described solid propellant rocket body (102), described lighter (104) connects described point
Fire control system and the separating mechanism that comes off (101)；
It is characterized in that: the afterbody in big aircraft (202) for the symmetrical carry of described JATO engine (201).
2. as claimed in claim 1 big aircraft with solid propellant rocket JATO engine (201) it is characterised in that: described
Big aircraft (202) accelerates initially with self power, when reaching the specified peak power output of aircraft engine, takes off described in startup
Described lighter (104) igniting of booster (201), is that described big aircraft (202) provides extra-push model；When described big aircraft
(202), after taking off, described booster (201) is abandoned described solid-rocket by IGNITION CONTROL with the separating mechanism that comes off (101) and is sent out
Motivation body (102).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620433529.7U CN205918517U (en) | 2016-05-12 | 2016-05-12 | Big airborne solid rocket engine aircraft climb assisting unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620433529.7U CN205918517U (en) | 2016-05-12 | 2016-05-12 | Big airborne solid rocket engine aircraft climb assisting unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205918517U true CN205918517U (en) | 2017-02-01 |
Family
ID=57876150
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620433529.7U Active CN205918517U (en) | 2016-05-12 | 2016-05-12 | Big airborne solid rocket engine aircraft climb assisting unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205918517U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108995832A (en) * | 2018-07-26 | 2018-12-14 | 西安航天动力技术研究所 | A kind of Pneumatic booster formula stage separation mechanism |
| CN109896022A (en) * | 2019-03-28 | 2019-06-18 | 河南机电职业学院 | A kind of light-duty unmanned plane high-pressure pneumatic accelerated take-off device |
| CN110143287A (en) * | 2019-07-04 | 2019-08-20 | 哈工大机器人（岳阳）军民融合研究院 | Booster separation device |
-
2016
- 2016-05-12 CN CN201620433529.7U patent/CN205918517U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108995832A (en) * | 2018-07-26 | 2018-12-14 | 西安航天动力技术研究所 | A kind of Pneumatic booster formula stage separation mechanism |
| CN109896022A (en) * | 2019-03-28 | 2019-06-18 | 河南机电职业学院 | A kind of light-duty unmanned plane high-pressure pneumatic accelerated take-off device |
| CN109896022B (en) * | 2019-03-28 | 2023-12-08 | 河南机电职业学院 | High-pressure pneumatic booster take-off device of light unmanned aerial vehicle |
| CN110143287A (en) * | 2019-07-04 | 2019-08-20 | 哈工大机器人（岳阳）军民融合研究院 | Booster separation device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |