NASA/Wallops
Astrobee D
Flight Plan
(Flights 23.012 UU and 23.013 UU )

for

WALLOPS PROJECT: T1-9876 & T1-9877

ASTROBEE D 23.012 UU & 23.013 UU

PRIMARY LAUNCH TIME: 1541Z & 1841Z, JUNE 7, 1979

ALTERNATE LAUNCH TIME: 1600Z & 1900Z, JUNE 8, 1979

WALLOPS JOB ORDER: 001-9638

BADGE NO: 24

FUNCTION	NAME
TEST DIRECTOR	William L. Lord
RANGE SAFETY OFFICER	F. Ronald Sawyer
WALLOPS MISSION MANAGER	Robert J. Frostrom, Jr.
PAD SUPERVISOR	Paul White
PROJECT SCIENTIST	Dr. J. J. Horvath
PAYLOAD MANAGER	Jay Brown
RECOVERY DIRECTOR	Robert T. Long

SUBMITTED	REVIEWED
Robert J. Frostrom, Jr. Mission Manager	Ronald Sawyer Head, Ground & Flight Safety Officer
APPROVED	REVIEWED
Signature Not Legible Head, Project Management Section	William F. Lord Head, Project Operations Section
R. J. Duffy Director of Operations	Signature Not Legible Head, Aeronautical Prgorams Branch

Name	Organization	Function
Dr. J. J. Horvath	University of Michigan	Project Scientist
Mr. John Caldwell	University of Michigan	Electrical Systems Engineer
Mr. Lyle Slider	University of Michigan	Mechanical Systems Eng.

Objectives

The specific objective of this research efffort will be to obtain vertical profiles of nitric oxide concentrations throughout the middle and upper stratosphere in conjunction with the nitric oxide measurements obtained by the Statospheric and Mesospheric Sounder (SAMS) experiement aboard the Nimbus-7 satellite.

Description

A parachute-deployed sensor will be launched on an Astrobee D. The sensor will be ejected at or near apogee and will make the measurement of nitric oxide on the descent portion of the flight. Two launches will be attempted approximately three hours apart. One launch is in conjunction with the Nimbus-7 satellite overpass, the other to study the repeatibility of the sensors.

3. Launch Criteria

Launch operations, recovery and performance evaluations must be satisfactory for Astrobee D 23.013 UU before Astrobee D 23.013 UU will be launched. Launch of Astrobee D 23.013 UU should occur within +/- 30 minutes of the satellite overpass. In addition, payload requirements dictate that the day of either launch be a day of no precipitation and minimum off-shore winds.

4. Vehicle Description

The Astrobee D is a radial burning, dual thrust, solid propellant motor, 15.2 cm in diameter and 279.0 cm long. There is approximately a 4 to 1 boost to sustain ratio, with a motor burn total duration of 18 seconds. The vehicle is stabilized by four magnesium fins, approximately 813 square centimeters in area. The payload is housed in an ogive section 96.5 cm long.

The following table indicates the nominal dimensions and weights of the various components:

Dimensions	Centimeters	Inches
Astrobee D Body Diameter	15.24	6.00
Payload Body Diameter	15.24	6.00
Astrobee D Fin Span	60.96	24.00

Weights	Kilograms	Pounds
Astrobee D Motor	87.317	192.500
Parachute Cannister	6.407	14.125
Instruments & Nose Cone	10.688	23.563
Ballast	1.049	2.312
Motor at Burnout	21.755	47.960
Suspended Parachute Wght	8.477	18.688

a. Rocket Motor

The propellant used in the Astrobee D is hydroxyl terminated polybutadiene which achieves a high initial thrust for reduction of wind effects, as well as sustained burning time.

Thermal effects on the magnesium fins are minimized by attachment of a small stainless steel cuff to the leading edges and spraying the fin panels with a 0.0254 cm coating of an ablative material. The fin attachments are integral with the nozzle and provide for adjustment of the fin assembly for selective roll rates.

The forward launch lug is spring loaded and designed to separate from the rocket subsequent to its release from the lancher. The aft lug remains fixed to the aerodynamic fairing in the nozzle are.

b. Igniter, Separation Device and Paylod Ordnance

(1) Astrobee D Igniter

The Astrobee D igniter is a simple bridgewire pellet type consisting of loosey packed boron potassium nitrate (BPN) ignition granules as a booster for the main BPN pellets. The charge is enclosed in a plastic chamber and is initiated by a Hercules MK 2 Mod-0 squib with the following specifications:

(2) Separation Device

The Astrobee D uses a self-contained Raymond Engineering inertia timer set at "T" +143 seconds to initiate a gas generator through a capacitor discharge ignition system.

Hazard Classilifications

Separately, the Astrobee D motor, the igniter, and the separation devices are classified by the Department of Transportation as Class B propellant Explosives and have an Explosives Hazard Classification of Class 4, Quantity-Distance. These items are classified by the Department of Defense as Class 2B Explosives.

5. Payload Description

The Chemiluminescent Nitric Oxide Detector is a rocket launched parachute decelerated instrument which senses nitric oxide in the altitude region of approximately 50-30 km. The payload is enclosed within an asbestos phenolic nose cone with a 5:1 ogive forebody. The ogive portion of the nose cone will be ejected in flight at "T" + 143 seconds.

The operation of chemiluminescent nitric oxide detector is based upon the detection of light emitted from electroinically excited NO2 molecules which are formed in the reaction of nitric oxide with ozone. The essential elements of the sensor consists of a floro reaction volume, an ozone supply source, a sample input flow tube, a photodetector and a liquid nitrogen cooled absorption pump. Ambient NO enters the sample flow tube along with other ambient constituents and moves into the reaction volume. Here it combines with a calibrated flow of ozone in a mixture with oxyen. The light emitted upon the subsequent de-excitation of NO2 is detected by a photomultiplier. Continuous flow of the reactant gases through the reaction volume is maintained by the LN2 absorption pump. The ozone generated background signal, unique in devices of this kind, is periodically evaluated by substituting for the sample flow a bias gas, N2, which when injected at the sample input flow tube entrance acts like a "gas piston" to prevent ambient NO molecules from entering the chamber while keeping the chamger flow conditions unchanged.

An 8 channel, PCM/FM/FM 500 milliwat telemetry transmitter, operates at a frequency of 1680 MHz.

The following table indicates the nominal dimensions and weights of the various components:

Weights	Kilograms	Pounds
Payload (after assembly)	18.399	40.563
Payload (after ejection)	9.588	21.138
Payload suspended weight	8.477	18.688

Both vehicles will be launched from the South AML launcher, North Rail, loacated in Launch Area No. 2 Based on a Q.E. of 84 degrees, the following performance is expected:

Event	Time (sec)	Altitude (km)	Horizontal Range (km)	Velocity (m/s)
Launch	0.00	0.00	0.00	0.00
Burnout	18.00	11.60	1.71	1240.17
Apogee	127.00	70.00	19.20	157.88
Ejection	143.00	69.80	20.21	216.70
Motor Impact	256.90	- - -	38.40	357.20
Payload Impact	4500.00	- - -	- - -	- - -

The following special gases are requied:

a. LN2
b. O2
c. N2
d. CO2

SECTION B:

RANGE INSTRUMENT SUPPORT

1. Radar digital magnetic tapes, as well as plotboard data of this launch will be required. All data will be 0.1 pps down to 30 km.

Wallops radars 3, 5 and 6 will be required to provide support, as radar track is essential to the success of the experiment. One radar will be required to vector the recovery aircraft to the recovery area.

At approximately T+ 143 seconds, the payload will eject and descend on a parachute. Tracking of the payload/parachute is required.



VI. Project Personnel and Responsibility

B. Scientific Objective and Experiment

Objectives

The specific objectives of this research effort will be to obtain vertical profiles of the nitric oxide concentrations throughout the middle and upper stratosphere in conjuction with the nitric oxide measurements obtained by the Stratospheric and Mesospheric (SAMS) experiment aboard the Nimbus-G satellite.

Experiment

Chemiluminescent nitric oxide detector


C. Launch Criteria

Launch of Astrobee D 23.011 UU (NASA-A) should occur within +/- 30 min. of the satellite overpass. In addition, payload requirements dictate that the day of launch be a day of no precipitation.

D. Vehicle Description

General Description

The Astrobee D is a radial burning, dual thrust, solid propellant motor, 15.2 cm in diameter and 279.0 cm long. There is approximatelly a 4 to 1 boost to sustain ratio, with a motor burn total duration of 18 seconds. The vehicle is stabilized by four magnesium fins, approximately 813 square centimeters in area. The payload is housed in an ogive section 96.5 cm long.


Detailed Description

Motor

The propellant used in the Astrobee D is hydroxyl terminated polybutadiene which achieves a high initial thrust for reduction of wind effects, as well as sustained burning time.

Thermal effects on the magnesium fins are minimized by attachment of a small stainless steel cuff to the leading edges and spraying the fin panels with a 0.0254 cm coating of an ablative material. The fin attachments are integral with the nozzle and provide for adjustment of the fin assembly for selective roll rates.

The forward launch lug is spring loaded and designed to separate from the rocket subsequent to its release from the launcher. The aft lug remains fixed to the aerodynamic fairing in the nozzle area.

Igniter

The Astrobee D igniter is a simple bridgewire pellet type consiting of loosely packed boron potassium nitratre (BPN) ignition granules as a booster for the main BPN pellets. The charge is enclosed in a plastic chamber and is initiated by a Hercules MK 2 Mod-O squib with the following specifications:

Minimum Delay

Separation Device

The Astrobee D uses a self-contained Raymond Engineering inertia time set at "T" +143 seconds to initiate a gas generator through a capacitor discharge ignition system.

Hazard Classifications

Separately, the Astrobee D motor, the igniter, and the separation device are classified by the Department of Transportation as Class B Propellant Explosives and have an Explosive Classification of Class 4, Quantity-Distance. These items are classified by the Department of Defense as Class 2B Explosives.


E. Payload Description

The Chemiluminescent Nitric Oxide Detector is a rocket launched parachute decelerated instrument which senses nitric oxide in the altitude region of approximately 50-30 km. The payload is enclosed within an asbestos phenolic nose cone with a 5:1 ogive forebody. The ogive portion of the nose cone will be ejected in flight at "T" +143 seconds.

The operation of the chemiluminescent nitric oxide detector is based upon the detection of light emitted from electronically excited NO2 molecules which are formed in the reaction of nitric oxide with ozone. The essential elements of the sensor consists of a floro reaction volume, an ozone supply source, a sample input flow tube, a photodetector and a liquid nitrogen cooled absorption pump. Ambient NO enters the sample flow tube along with the other ambient constituents and moves into the reaction volume. Here it combines with a calibrated flow of ozone in a mixture with oxygen. The light emitted upon the subsequent de-excitation of NO2 is detected by photomultiplier. Continuous flow of the reactant gases through the reaction volume is maintained by the LN2 absorption pump. The ozone generated background signal unique in devices of this kind is periodically evaluated by substituting for the sample flow a bias gas, N2, which when injected at the sample input flow tube entrance acts like a "gas piston" to present ambient NO molecules from entering the chamber while keeping the chamber flow conditions unchanged.

An 8 channel, PCM/FM/FM 500 milliwat telemetry transmitter, operates at a frequency of 1680 MHz.

The following table indicates the nominal dimensions and weights of the various components

Dimensions	Centimeters	Inches
Payload Length	17.03	43.250
Chute Cannister Length	9.19	23.345
Total Length (assembled)	26.22	66.595

Weights	Kilograms	Pounds
Payload (after assembly)	20.45	45.00
Payload (after ejection)	8.51	18.72
Suspended Chute Weight	7.38	16.24

F. Nominal flight Data

The Vehicle will be lanched from the RAG launcher (launcher #2). Based on a Q.E. of 84 degrees, the following performance is expected:

G. Special Requirements

The following special gases are requied:

a. LN2
b. O2
c. N2

H. Radar Instrumentation Requirement

Digital magnetic tapes, as well as plotboard data of this launch will be required. All data rates will be 1 pps down to 30 km.

Wallops mobile radars will be required to provide support, as radar track is essential to the success of the experiment. One radar will be required to vector the recovery aircraft to the recovery area.

At approximately "T" +143 seconds, the payload will eject and descend on a parachute.


I. Ground Station Telemetry

1. Telemetry

Wallops Mobile Telemetry is requested to provide telemetry coverage of the Astrobee D payload.

The transmitter operating frequency is 1680 MHz FM/PCM at 1/2 watt output. The T/M receiver information is listed in the folowing charts.

The following PCM information applies to Astobee D 23.011 UU: